JP7741774B2 - Combined Power System - Google Patents

Description

The present invention relates to a hybrid power system that integrates a rotating electrical machine system and an internal combustion engine.

A rotating electric machine comprises a rotor with a rotating shaft and a stator positioned on the outer periphery of the rotor. Recently, it has been proposed to combine a rotating electric machine with a gas turbine engine to create a hybrid power system. In this case, the rotating shaft of the rotating electric machine and the output shaft of the gas turbine engine are connected on the same axis. Therefore, the rotating shaft and output shaft rotate integrally.

A permanent magnet is held on the rotating shaft. When the rotating shaft rotates integrally with the output shaft, an alternating magnetic field is formed by the permanent magnet and the electromagnetic coil in the stator. As a result, an induced current is generated in the electromagnetic coil. In other words, in this case, the rotating electric machine functions as a generator.

When induced currents continue to occur in a rotating electric machine, the machine heats up. As a result, the temperature of the permanent magnets rises. As the temperature of the permanent magnets approaches the Curie temperature, the magnetic force of the permanent magnets decreases. To avoid this, rotating electric machines are sometimes cooled. For example, in the technology described in Patent Document 1, compressed air obtained by a turbocharger is cooled in an aftercooler (heat exchanger). The cooled compressed air is supplied to the rotor through a duct installed in the stator of the rotating electric machine (high-speed rotating machine). This cools the stator and rotor.

Patent Document 2 describes forming a cooling jacket (water-cooled jacket) around the outer periphery of the stator. In this case, the cooling water supplied to the cooling jacket removes heat from the rotating electrical machine.

Japanese Patent Application Laid-Open No. 2007-159277 JP 2012-39816 A

Gas turbine engines generate compressed air. One possible solution is to send this compressed air to a rotating electrical machine and use it to cool the machine. However, the compressed air generated by gas turbine engines is relatively hot. For this reason, there is concern that using this compressed air may not provide sufficient cooling for the rotating electrical machine.

The present invention aims to solve the above-mentioned problems.

According to one embodiment of the present invention, a compound power system is provided, which includes a rotating electric machine system having a rotating electric machine housing that rotatably supports the rotating shaft of the rotating electric machine, and a gas turbine engine having an output shaft that rotates integrally with the rotating shaft and that is provided at one end of the rotating electric machine housing. The compound power system includes a compressor wheel that is provided on the output shaft and compresses outside air to obtain compressed air, a shroud case that surrounds the compressor wheel, an engine housing that houses the compressor wheel and the shroud case, a terminal casing that is provided on the outer wall of the rotating electric machine housing and that houses an electrical terminal unit for transmitting and receiving power between the rotating electric machine and an external device, and a terminal casing formed by the gas turbine engine and the terminal casing on the outer wall of the rotating electric machine housing. and a heat exchanger disposed in a recess formed in the shroud case for lowering the temperature of the compressed air. The rotating electric machine has a storage chamber that houses the rotating electric machine housing. The shroud case is formed with an air bleed port for extracting the compressed air to the outside of the shroud case. The engine housing is formed with an air bleed passage through which the compressed air that has flowed into the air bleed port flows. The rotating electric machine housing is formed with a cooling jacket that surrounds the rotating electric machine from the outer periphery. The heat exchanger has a shell and an air inlet passage that is provided inside the shell and communicates with the storage chamber of the rotating electric machine housing. A cooling medium that has circulated through the cooling jacket is supplied to the inside of the shell. The storage chamber of the rotating electric machine housing is downstream of the heat exchanger in the flow direction of the compressed air.

In this invention, compressed air generated by a gas turbine engine passes through a heat exchanger and flows into the storage chamber of the rotating electrical machine housing. In the heat exchanger, heat from the compressed air is absorbed by the cooling medium, thereby lowering the temperature of the compressed air. The compressed air, whose temperature has been lowered in this way, flows into the storage chamber. Therefore, the rotating electrical machine housed in the storage chamber is efficiently cooled.

For these reasons, the temperature of the permanent magnets that make up the rotating electric machine is prevented from reaching the Curie temperature. This prevents the magnetic force of the permanent magnets from decreasing. As a result, a predetermined magnetic force is generated in the alternating magnetic field formed between the permanent magnets and the electromagnetic coil. This allows the rotor to maintain high-speed rotation.

In this way, according to the present invention, the rotating electrical machine can be cooled using compressed air generated by the gas turbine engine. Therefore, there is no need to supply cooling air for cooling the rotating electrical machine to the storage chamber separately from the compressed air. This allows for a simplified configuration of the combined power system while still cooling the rotating electrical machine. Moreover, even with this configuration, the rotor can be rotated at high speed.

FIG. 1 is a schematic overall perspective view of a combined power system according to an embodiment of the present invention. FIG. 2 is a schematic perspective view of the entire rotating electrical machine system that constitutes the compound power system. FIG. 3 is a schematic cross-sectional side view of the rotating electrical machine system. FIG. 4 is an enlarged view of the main part of FIG. FIG. 5 is an enlarged view of a main part of FIG. 3 at a different location from that of FIG. FIG. 6 is a schematic diagram showing the configuration of a current converter provided in a housing of a rotating electrical machine. FIG. 7 is a schematic perspective view of a second sub-housing that constitutes the rotary electric machine housing and an inner housing in the engine housing. FIG. 8 is a schematic cross-sectional side view of the rotating electrical machine system in a phase different from that of FIG. FIG. 9 is a schematic system diagram showing compressed air flow paths and lubricating oil flow paths in a rotating electrical machine system. FIG. 10 is a schematic cross-sectional side view of a gas turbine engine that constitutes a combined power system. FIG. 11 is an enlarged view of the main part of FIG.

In the following, "left," "right," "bottom," and "top" refer to the left, right, bottom, and top directions, respectively, in Figures 3 to 5, 10, and 11. However, these directions are merely used for convenience to simplify the explanation and make it easier to understand. In other words, the directions described in the specification are not necessarily the directions when the combined power system is actually used.

Figure 1 is a schematic overall perspective view of a combined power system 400 according to this embodiment. The combined power system 400 comprises a rotating electric machine system 10 and a gas turbine engine 200. An axis passing through the center of the diameter of the rotating electric machine system 10 and extending along the longitudinal direction (axial direction) coincides with an axis passing through the center of the diameter of the gas turbine engine 200 and extending along the longitudinal direction (axial direction). In other words, the rotating electric machine system 10 and the gas turbine engine 200 are arranged side by side on the same axis.

Hereinafter, the left axial end of each of the rotating electric machine system 10 and the gas turbine engine 200 may be referred to as the first end. Similarly, the right axial end of each of the rotating electric machine system 10 and the gas turbine engine 200 may be referred to as the second end. That is, in the rotating electric machine system 10, the left end away from the gas turbine engine 200 is the first end. In the rotating electric machine system 10, the right end close to the gas turbine engine 200 is the second end. Also, in the gas turbine engine 200, the left end close to the rotating electric machine system 10 is the first end. In the gas turbine engine 200, the right end away from the rotating electric machine system 10 is the second end. According to this definition, in the illustrated example, the gas turbine engine 200 is disposed at the second end of the rotating electric machine system 10. The rotating electric machine system 10 is disposed at the first end of the gas turbine engine 200.

The combined power system 400 is used as a propulsion power source in, for example, an aerial vehicle, a ship, or an automobile. Specific examples of suitable aerial vehicles include drones and multicopters. When mounted on an aerial vehicle, the combined power system 400 serves as a power drive source that rotates, for example, a propeller or ducted fan. When mounted on a ship, the combined power system 400 serves as a rotational force generator for a screw. When mounted on an automobile, the combined power system 400 serves as a power drive source that rotates a motor.

The combined power system 400 can also be used as an auxiliary power source in aircraft, ships, buildings, etc. In addition, the combined power system 400 can also be used as a gas turbine power generation facility.

As described below, the gas turbine engine 200 is an internal combustion engine. The gas turbine engine 200 is also a gas supply device that supplies compressed air (gas).

First, the rotating electric machine system 10 will be described. Figure 2 is a schematic overall perspective view of the rotating electric machine system 10. Figure 3 is a schematic side cross-sectional view of the rotating electric machine system 10. This rotating electric machine system 10 includes a rotating electric machine 12 (e.g., a generator) and a rotating electric machine housing 14 that houses the rotating electric machine 12.

The rotating electrical machine housing 14 has a main housing 16, a first sub-housing 18, and a second sub-housing 20. The main housing 16 is generally cylindrical, with both its first and second ends open. The first sub-housing 18 is connected to the first end (left open end) of the main housing 16. The second sub-housing 20 is connected to the second end (right open end) of the main housing 16. As a result, the first and second ends of the main housing 16 are closed.

The main housing 16 has thick side walls extending in the left-right direction. A hollow interior is formed in the main housing 16. This hollow interior is a storage chamber 22. Most of the rotating electric machine 12 is housed in the storage chamber 22.

A cooling jacket 24 is spirally formed inside the side wall of the main housing 16. A cooling medium flows through the cooling jacket 24. A specific example of the cooling medium is cooling water. In this case, the cooling jacket 24 is a water jacket.

A first casing 26 and a second casing 28 are provided on the outer surface (outer wall) of the side wall of the main housing 16 near the edge of the first end. The first casing 26 and the second casing 28 are part of the main housing 16. In other words, the first casing 26 and the second casing 28 are provided integrally with the main housing 16. As described below, the first casing 26 is a terminal casing. The second casing 28 is a meter casing.

The first casing 26 has a first internal space 29. The second casing 28 has a second internal space (not shown). The first internal space 29 and the second internal space are connected via an interconnecting hole (not shown). The first internal space 29 is also connected to the storage chamber 22.

A holding member that holds a rotational parameter detector is connected to the first sub-housing 18. In this embodiment, a resolver 132 is used as an example of the rotational parameter detector. Therefore, hereafter, the detector holding member will be referred to as the "resolver holder 30." As described below, a cap cover 32 is connected to the resolver holder 30 via screws.

The rotating electric machine 12 comprises a rotor 34 and a stator 36 that surrounds the outer periphery of the rotor 34.

The rotor 34 includes a rotating shaft 40. The rotating shaft 40 has an inner shaft 42 and a hollow cylindrical outer shaft 44. Both ends of the outer shaft 44 are open. That is, the outer shaft 44 has a left open end 441 (see Figure 4) and a right open end 442 (see Figure 5). The inner shaft 42 is removably inserted into the outer shaft 44.

The inner shaft 42 is longer than the outer shaft 44. The inner shaft 42 has a cylindrical portion 421, a left end 422 (see FIG. 4), and a right end 423 (see FIG. 5). The left end 422 connects to the left of the cylindrical portion 421. Therefore, the left end 422 is the end (first end) of the inner shaft 42 that is away from the gas turbine engine 200. The right end 423 connects to the right of the cylindrical portion 421. Therefore, the right end 423 is the end (second end) of the inner shaft 42 that is closest to the gas turbine engine 200. The diameter of the cylindrical portion 421 is smaller than the left end 422 and the right end 423. The diameter of the right end 423 is also smaller than the left end 422.

A portion of the left end 422 is exposed from the left open end 441 of the outer shaft 44. The portion exposed from the left open end 441 is the protruding tip 46, which will be described later. In the illustrated example, the right end 423 of the inner shaft 42 and the right open end 442 of the outer shaft 44 are flush with each other. However, the right end 423 may be positioned slightly closer to the second end than the right open end 442.

As shown in detail in Figure 4, the left end 422 of the inner shaft 42 is provided with a first external thread portion 48, a flange portion 50, a stopper portion 52, and a second external thread portion 54, in this order, toward the right. The outer diameters of the first external thread portion 48, the flange portion 50, the stopper portion 52, and the second external thread portion 54 increase in this order. The outer diameter of the second external thread portion 54 is larger than the inner diameter of the outer shaft 44. Therefore, the right end of the second external thread portion 54 is blocked by the edge of the left open end 441 of the outer shaft 44. Therefore, the portion of the inner shaft 42 to the left of the second external thread portion 54 cannot be inserted into the outer shaft 44.

A resolver rotor 56 is attached to the flange 50. A small cap nut 58 is screwed onto the first externally threaded portion 48. The right end of the resolver rotor 56 is positioned by the stopper portion 52. The left end of the resolver rotor 56 is pressed by the small cap nut 58. As a result, the resolver rotor 56 is positioned and fixed to the flange 50.

A large cap nut 60 is threaded onto the second external thread portion 54. The right end of the large cap nut 60 covers the outer peripheral wall of the left open end 441 of the outer shaft 44. This restrains the left end 422 of the inner shaft 42 to the left open end 441 of the outer shaft 44. Both the first external thread portion 48 and the second external thread portion 54 are reverse-threaded. Therefore, the small cap nut 58 and the large cap nut 60 are rotated counterclockwise when threaded. After threading, it is preferable to deform part of the threads of the small cap nut 58 and the large cap nut 60. This prevents the small cap nut 58 and the large cap nut 60 from loosening.

As shown in FIG. 5, a connecting hole 62 is formed in the right end 423, which is the second end of the inner shaft 42. The connecting hole 62 extends toward the left end 422, which is the first end. A female thread 64 is formed in the inner peripheral wall of the connecting hole 62. The left end of the output shaft 204 is inserted into the connecting hole 62. The left end of the output shaft 204 is connected to the inner shaft 42 by threading into the female thread 64. The output shaft 204 holds a compressor wheel 222 and a turbine wheel 224 (see FIG. 10).

A first internal spline 66 is formed on the outer peripheral wall of the right open end 442 of the outer shaft 44. The first internal spline 66 extends along the axial direction (left-right direction) of the rotating electrical machine system 10.

As shown in Figure 3, the outer diameter of the outer shaft 44 is greatest at approximately the middle portion in the longitudinal direction. Multiple permanent magnets 72 are held in this large-diameter middle portion via magnet holders 70. Adjacent permanent magnets 72 have opposite polarities facing outward. As the rotating shaft 40 rotates, the permanent magnets 72 move around the circumference of a predetermined imaginary circle centered on the center of rotation of the rotating shaft 40.

The left end (first end) of the rotating shaft 40 is rotatably supported in the first sub-housing 18 via a first bearing 74. As shown in FIG. 3, the first bearing 74 is inserted between the outer shaft 44 and the first sub-housing 18. Specifically, the first sub-housing 18 has a cylindrical protrusion 76 that protrudes toward the main housing 16. A first insertion hole 78 is formed in the cylindrical protrusion 76. A first bearing holder 80 that holds the first bearing 74 is inserted into the first insertion hole 78. Thus, the first bearing 74 is positioned in the first insertion hole 78.

The first insertion hole 78 extends in the left-right direction. The left end of the first insertion hole 78 is farther from the output shaft 204 than the right end of the first insertion hole 78. Hereinafter, the left end of the first insertion hole 78 will also be referred to as the "first distal end 781." On the other hand, the right end of the first insertion hole 78 is closer to the output shaft 204 than the left end of the first insertion hole 78 (first distal end 781). Hereinafter, the right end of the first insertion hole 78 will also be referred to as the "first proximal end 782."

A first outer stopper 81 located at the first distal end 781 and a first inner stopper 82 located at the first proximal end 782 are attached to the small-diameter left end of the outer shaft 44. The first bearing 74 is sandwiched between the first outer stopper 81 and the first inner stopper 82. This clamping positioning fixes the first bearing 74. A clearance is formed between the first outer stopper 81 and the cylindrical protrusion 76.

The tip of the left end of the rotating shaft 40 passes through the inner hole of the first bearing 74 and then through the first insertion hole 78. The tip of the left end of the rotating shaft 40 is further exposed outside the cylindrical protrusion 76 (hollow recess 118). Hereinafter, the portion of the rotating shaft 40 that protrudes from the left end of the first bearing 74 will be referred to as the "protruding tip 46." The protruding tip 46 includes the first externally threaded portion 48, flange portion 50, stopper portion 52, and second externally threaded portion 54 of the left end 422 of the inner shaft 42 (see Figure 4).

The right end (second end) of the rotating shaft 40 is rotatably supported in the second sub-housing 20 via a second bearing 84. As shown in Figure 5, the second bearing 84 is inserted between the outer shaft 44 and the second sub-housing 20, which has a generally circular disk shape.

The second sub-housing 20 is connected to the main housing 16 via bolts (not shown). The center of the second sub-housing 20 is a thick-walled cylindrical portion. A second insertion hole 86 is formed in this cylindrical portion. The second insertion hole 86 extends in the left-right direction. The left end of the second insertion hole 86 is farther from the output shaft 204 than the right end of the second insertion hole 86. Hereinafter, the left end of the second insertion hole 86 will also be referred to as the "second distal end 861." On the other hand, the right end of the second insertion hole 86 is closer to the output shaft 204 than the left end of the second insertion hole 86 (second distal end 861). Hereinafter, the right end of the second insertion hole 86 will also be referred to as the "second proximal end 862."

A second bearing holder 88 holding a second bearing 84 is inserted into the second insertion hole 86. Thus, the second bearing 84 is positioned in the second insertion hole 86. The second bearing 84 is clamped between a second inner stopper 90 located at the second distal end 861 and a second outer stopper 92 located at the second proximal end 862. Based on this clamping, the second bearing 84 is positioned and fixed.

Furthermore, at the second distal end 861, a clearance is formed between the second inner stopper 90 and the second bearing holder 88. This clearance is the third sub-branch path 941.

As shown in FIG. 2 , a flow straightening member 96 is connected to the end face of the second sub-housing 20 facing the gas turbine engine 200. The flow straightening member 96 has a bottom portion 98, a reduced diameter portion 100, and a top portion 102. The bottom portion 98 facing the second sub-housing 20 is a large-diameter, thin-walled cylindrical plate. The top portion 102 facing the gas turbine engine 200 is a small-diameter, relatively long cylindrical plate. The reduced diameter portion 100 between the bottom portion 98 and the top portion 102 has a gradually decreasing diameter. Therefore, the flow straightening member 96 has a mountain-shaped or bottomless cup-shaped body. The outer surface of the reduced diameter portion 100 is a smooth surface with low surface roughness.

An inlet 104 is formed on the end surface of the bottom portion 98 facing the second sub-housing 20. The reduced diameter portion 100 is hollow. That is, a relay chamber 106 is formed inside the reduced diameter portion 100. The inlet 104 is an input port for compressed air into the relay chamber 106.

A through hole 108 is formed in the top portion 102 along the left-right direction. The diameter (opening diameter) of the through hole 108 is larger than the outer diameter of the portion of the second outer stopper 92 that extends along the rotating shaft 40. Therefore, the portion of the second outer stopper 92 that has entered the through hole 108 and its outer peripheral wall are spaced apart from the inner wall of the through hole 108. In other words, a clearance is formed between the outer peripheral wall of the second outer stopper 92 and the inner wall of the through hole 108. This clearance is the fourth sub-branch path 942. The relay chamber 106 becomes wider as it approaches the through hole 108 and the fourth sub-branch path 942.

The diameter (opening diameter) of the insertion hole 108 is larger than the outer diameter of the relatively small-diameter left end (small-diameter cylindrical portion 242) of the compressor wheel 222. Therefore, the small-diameter cylindrical portion 242 that enters the insertion hole 108 also moves away from the inner wall of the insertion hole 108. In other words, a clearance is formed between the outer peripheral wall of the small-diameter cylindrical portion 242 and the inner wall of the insertion hole 108. This clearance is the outlet passage 943.

As shown in FIG. 3, the first insertion hole 78 and the third sub-branch passage 941 communicate with the storage chamber 22. Therefore, the first bearing 74 and the second bearing 84 are exposed to the storage chamber 22.

The stator 36, together with the rotor 34, constitutes the rotating electric machine 12. The stator 36 has an electromagnetic coil 110 and multiple insulating substrates 112. The electromagnetic coils 110 include three types of coils: a U-phase coil, a V-phase coil, and a W-phase coil, which are wound around the insulating substrates 112. When the rotating electric machine 12 is a generator, the rotating electric machine 12 is a so-called three-phase power supply. The multiple insulating substrates 112 are arranged in a circular ring shape. This arrangement forms an inner hole in the stator 36.

The stator 36 is stored in the storage chamber 22. Here, the second sub-housing 20 serves as a stator holder. That is, an annular recess 114 is formed in the second sub-housing 20. The insulating substrate 112 included in the stator 36 engages with this annular recess 114. This engagement positions and fixes the stator 36. Furthermore, the cylindrical protrusion 76 enters the left opening of the inner hole of the stator 36.

The inner wall of the storage chamber 22 and the electromagnetic coil 110 are spaced slightly apart from each other. This space electrically insulates the main housing 16 and the electromagnetic coil 110.

A clearance is formed between the outer wall of the cylindrical protrusion 76 and the insulating substrate 112. A clearance is also formed between the outer wall of the permanent magnet 72 and the inner wall of the electromagnetic coil 110. As described below, compressed air, which is a gas, flows through these clearances. In other words, these clearances are part of the compressed air flow path.

As shown in FIG. 4, the first sub-housing 18 has an annular protrusion 116 that protrudes in an annular shape. Inside the annular protrusion 116 is a hollow recess 118. The protruding tip 46, which is part of the left end 422 of the inner shaft 42, extends into the hollow recess 118.

A resolver holder 30 is mounted on the annular protrusion 116. The resolver holder 30 has a flange-shaped stopper 120 that protrudes radially outward. The flange-shaped stopper 120 has a diameter larger than the inner diameter of the annular protrusion 116. Therefore, the flange-shaped stopper 120 abuts against the annular protrusion 116. This abutment positions the resolver holder 30. In this state, the resolver holder 30 is connected to the first sub-housing 18, for example, via a mounting bolt (not shown).

In the resolver holder 30, a small cylindrical portion 122 is provided to the left of the flange-shaped stopper 120. Furthermore, a large cylindrical portion 124 is provided to the right of the flange-shaped stopper 120. The large cylindrical portion 124 has a larger diameter than the small cylindrical portion 122. A retaining hole 126 is formed in the resolver holder 30. Most of the resolver stator 130 is fitted into the retaining hole 126. This fit holds the resolver stator 130 in the resolver holder 30.

When the large cylindrical portion 124 enters the hollow recess 118 and the flange-shaped stopper 120 abuts against the annular protrusion 116, the resolver rotor 56 is positioned in the inner hole of the resolver stator 130. The resolver stator 130 and the resolver rotor 56 form the resolver 132. The resolver 132 is a rotation parameter detector. In this embodiment, the resolver 132 detects the rotation angle of the inner shaft 42. As described above, the resolver rotor 56 is held by the flange 50 on the left end 422 of the inner shaft 42.

An engagement hole 134 is formed in the flange-shaped stopper 120. A transmitting connector 136 engages with the engagement hole 134. The resolver stator 130 and the transmitting connector 136 are electrically connected via a signal line 138. The receiving connector of a receiver (not shown) is inserted into the transmitting connector 136. The resolver 132 and the receiver are electrically connected via the transmitting connector 136 and the receiving connector. The receiver receives the signal emitted by the resolver 132.

The small cylindrical portion 122 has multiple tab portions 140 (omitted in Figure 1). One tab portion 140 is shown in Figure 3. Furthermore, a cap cover 32 is placed over the small cylindrical portion 122. The cap cover 32 closes the left opening of the small cylindrical portion 122 and shields the left end portion 422 of the inner shaft 42. The cap cover 32 is connected to the tab portions 140 via a connecting bolt 142.

As described above, the first casing 26 and the second casing 28 are integrally provided on the side wall near the left end of the main housing 16. The first casing 26 houses the U-phase terminal 1441, the V-phase terminal 1442, and the W-phase terminal 1443. The U-phase terminal 1441 is electrically connected to the U-phase coil of the electromagnetic coil 110. The V-phase terminal 1442 is electrically connected to the V-phase coil of the electromagnetic coil 110. The W-phase terminal 1443 is electrically connected to the W-phase coil of the electromagnetic coil 110. The U-phase terminal 1441, the V-phase terminal 1442, and the W-phase terminal 1443 are electrical terminals to which external devices (external loads or external power sources) are electrically connected. Power generated by the rotating electric machine 12 is supplied to the external devices. An example of an external load is a motor (not shown). Another example of an external device is the battery 146 shown in FIG. 6.

The second casing 28 is adjacent to the first casing 26. The second casing 28 houses a thermistor 148, which is a temperature measuring device. Although not specifically shown, the measurement terminal of the thermistor 148 is pulled out from the second casing 28 and then connected to the electromagnetic coil 110. A harness 149 connected to the thermistor 148 is pulled out from the second casing 28 to the outside.

As shown in Figures 1 and 2, a current converter 150 is provided on the outer peripheral wall of the main housing 16. The current converter 150 is closer to the gas turbine engine 200 than the first casing 26. As shown in Figure 6, the current converter 150 has a conversion circuit 152, a capacitor 154, and a control circuit 156. The conversion circuit 152, capacitor 154, and control circuit 156 are housed in an equipment case 158. The equipment case 158 is disposed, for example, on the outer peripheral wall of the main housing 16 at a location that does not interfere with the first hollow tube portion 1601, the second hollow tube portion 1602, and the third hollow tube portion 1603 (see Figure 1).

The hollow interiors of the first hollow tube portion 1601, the second hollow tube portion 1602, and the third hollow tube portion 1603 are compressed air flow passages through which compressed air flows. That is, in this embodiment, three compressed air flow passages are formed in the rotating electrical machine housing 14. The first hollow tube portion 1601 and the third hollow tube portion 1603 are formed as hollow bulges that bulge from the outer peripheral wall of the main housing 16.

The conversion circuit 152 includes a power module 161. The conversion circuit 152 converts the AC current generated in the electromagnetic coil 110 into DC current. At this time, the capacitor 154 temporarily stores the DC current converted by the conversion circuit 152 as an electric charge. The conversion circuit 152 also has the function of converting DC current sent from the battery 146 into AC current. In this case, the capacitor 154 temporarily stores the DC current sent from the battery 146 to the electromagnetic coil 110 as an electric charge.

The control circuit 156 controls the current density of the DC current flowing from the capacitor 154 to the battery 146, or the DC current flowing in the opposite direction. The DC current from the battery 146 is supplied to a motor (neither shown), for example, via an AC-DC converter.

As shown in Figures 1 to 3, a heat exchanger 310 is installed on the outer peripheral wall of the main housing 16. The heat exchanger 310 is located on the outer peripheral wall of the main housing 16, between the gas turbine engine 200 and the first casing 26. A recess is formed in the main housing 16 by the second sub-housing 20 and the first casing 26. The heat exchanger 310 is disposed in this recess. The heat exchanger 310 is contained within the recess and does not protrude beyond the first casing 26 and the second sub-housing 20. In other words, the heat exchanger 310 is not exposed from the recess. This prevents the combined power system 400 from becoming larger due to the inclusion of the heat exchanger 310.

Heat exchanger 310 has a shell 312. The hollow interior (not shown) of shell 312 is an inner chamber. A tube 314 is housed in the inner chamber. The inner hole of tube 314 serves as an air supply passage. Although not specifically shown, tube 314 is bent into a serpentine shape.

The second hollow tube portion 1602 has one end 160a connected to the tube 314 at the second end of the heat exchanger 310. The one end 160a extends from the second sub-housing 20 toward the heat exchanger 310. The second hollow tube portion 1602 has the other end 160b connected to the tube 314 at the first end of the heat exchanger 310. The other end 160b extends from the heat exchanger 310 toward the first casing 26. The hollow interior of the other end 160b is in communication with the first internal space 29 of the first casing 26.

The interior of the shell 312 is connected to the cooling jacket 24 via the communication path 171 shown in Figure 3. Therefore, the cooling medium that has circulated through the cooling jacket 24 passes through the communication path 171 and then flows into the interior of the shell 312. In the interior, the cooling medium comes into contact with the tubes 314. An exhaust pipe 172 is provided on the side of the shell 312. The cooling medium is discharged to the outside of the shell 312 via the exhaust pipe 172.

One end 160a and the other end 160b of the second hollow tube portion 1602 are tube members that extend along the outer peripheral wall of the main housing 16. One end 160a and the other end 160b (tube members) may abut against the outer peripheral wall of the main housing 16 or may be separated from it. Alternatively, one end 160a and the other end 160b are hollow bulging portions that bulge from the outer peripheral wall of the main housing 16.

The first hollow pipe portion 1601, the second hollow pipe portion 1602, and the third hollow pipe portion 1603 are spaced apart from one another at a predetermined interval (predetermined phase difference) along the circumferential direction of the outer wall of the main housing 16. The first hollow pipe portion 1601 and the third hollow pipe portion 1603 are located in positions that do not interfere with the heat exchanger 310. The first hollow pipe portion 1601 and the third hollow pipe portion 1603 are not located within the recess formed by the first casing 26 and the second sub-housing 20.

The rotating electrical machine system 10 configured as described above is provided with a compressed air flow path (first supply path) and a lubricating oil flow path (second supply path). First, the compressed air flow path will be described.

As shown in FIG. 7 , the second sub-housing 20 has an annular collecting passage 162 formed as an annular recess on its end surface facing the gas turbine engine 200. As described below, part of the compressed air generated by the gas turbine engine 200 flows through the collecting passage 162. Three upstream communication holes 164 are formed in the bottom wall of the collecting passage 162 (annular recess). The upstream communication holes 164 are input ports for compressed air.

Air relay paths 166 are provided inside the second sub-housing 20. The air relay paths 166 extend radially along the diameter of the second sub-housing 20. The air relay paths 166 communicate with the collecting flow path 162 on the outer diameter side via the upstream communication holes 164. In addition, three first downstream communication holes 1681-1683 are formed on the end face of the second sub-housing 20 facing the rotating electric machine 12. The first downstream communication holes 1681-1683 are first output ports of the air relay paths 166. The collecting flow path 162 and the air relay paths 166 form a distribution path.

Three second downstream communication holes 1701-1703 are formed on the end face of the second sub-housing 20 facing the gas turbine engine 200. The second downstream communication holes 1701-1703 are second output ports of the air relay path 166. The second downstream communication holes 1701-1703 are located radially inward of the first downstream communication holes 1681-1683. Therefore, the compressed air that flows through the air relay path 166 is divided into compressed air that enters the first downstream communication holes 1681-1683 (relay communication paths) and compressed air that enters the second downstream communication holes 1701-1703.

As shown in FIG. 2, a first hollow tube section 1601, a second hollow tube section 1602, and a third hollow tube section 1603 are provided on the outer surface of the side wall of the main housing 16. The first downstream communication holes 1681-1683 individually open toward the first hollow tube section 1601-third hollow tube section 1603, respectively. As can be seen from this, the air relay path 166 connects the collecting flow path 162 with the hollow interiors of the first hollow tube section 1601-third hollow tube section 1603. As shown in FIG. 3, the first hollow tube section 1601-third hollow tube section 1603 are located diametrically outward of the cooling jacket 24 formed inside the side wall of the main housing 16.

The first hollow tube section 1601 to the third hollow tube section 1603 extend along the axial direction of the main housing 16. The hollow interior of the first hollow tube section 1601 is connected to the second internal space of the second casing 28. As described above, the second hollow tube section 1602 extends from the second end facing the gas turbine engine 200 toward the first casing 26 (or the first end). Along its way, the second hollow tube section 1602 passes through the interior of the shell 312. The hollow interiors of the second hollow tube section 1602 and the third hollow tube section 1603 are connected to the first internal space 29 of the first casing 26.

As described below, compressed air that flows through the hollow interior of first hollow tube section 1601 forms an air curtain in the second internal space of second casing 28. Curtain air that flows through the hollow interiors of second hollow tube section 1602 and third hollow tube section 1603 flows into first internal space 29 of first casing 26. As can be seen from this, in the flow direction of compressed air, first casing 26 and second casing 28 are downstream of first hollow tube section 1601 to third hollow tube section 1603.

As described above, the first internal space 29 of the first casing 26 and the second internal space of the second casing 28 are connected via an interconnecting hole. Furthermore, the first internal space 29 of the first casing 26 is connected to the storage chamber 22. Therefore, compressed air that flows through the first hollow tube section 1601 to the third hollow tube section 1603 flows into the storage chamber 22 via the first internal space 29 of the first casing 26.

In this embodiment, an example is shown in which first hollow tube section 1601 to third hollow tube section 1603 are provided, but the number of hollow tube sections is determined appropriately depending on the flow rate or flow speed required for the curtain air formed from compressed air. In other words, the number of hollow tube sections is not limited to three. Similarly, the cross-sectional area of the hollow tube sections is also determined appropriately depending on the flow rate or flow speed required for the curtain air.

The compressed air that flows into the storage chamber 22 is then divided into compressed air heading toward the first insertion hole 78 and compressed air heading toward the second insertion hole 86. Specifically, some of the compressed air flows through the clearance between the first sub-housing 18 and the rotor 34 toward the first insertion hole 78. In this way, the clearance between the first sub-housing 18 and the rotor 34 is the first branch path L. Meanwhile, the remaining portion of the compressed air flows mainly through the clearance between the outer wall of the permanent magnet 72 and the inner wall of the electromagnetic coil 110 toward the second insertion hole 86. In this way, the clearance between the outer wall of the permanent magnet 72 and the inner wall of the electromagnetic coil 110 is the second branch path M.

The compressed air that reaches the first branch path L forms an air curtain that seals in the lubricating oil supplied to the first bearing 74. Furthermore, the compressed air that reaches the third sub-branch path 941 (the second distal end 861 of the second insertion hole 86) from the second branch path M forms an air curtain that seals in the lubricating oil supplied to the second bearing 84. In this way, the compressed air that flows into the storage chamber 22 functions as curtain air.

As shown in FIG. 5, three inlets 104 are formed in the bottom portion 98 of the flow straightening member 96. FIG. 5 shows only one of these. One inlet 104 is connected to the second downstream communication hole 1701 (not shown). Another inlet 104 is connected to the second downstream communication hole 1702 (shown). Another inlet 104 is connected to the second downstream communication hole 1703 (not shown). Therefore, compressed air output from the second downstream communication holes 1701-1703 enters the relay chamber 106 of the reduced diameter portion 100 of the flow straightening member 96 via the inlets 104.

The relay chamber 106 is connected to the insertion hole 108 formed in the top portion 102. The width of the relay chamber 106 increases as it approaches the insertion hole 108 and the fourth sub-branch path 942. As a result, the pressure of the curtain air decreases as the compressed air flows through the relay chamber 106.

The outlet of the relay chamber 106 faces the small-diameter cylindrical portion 242 of the compressor wheel 222. Therefore, the compressed air that enters the relay chamber 106 comes into contact with the small-diameter cylindrical portion 242 of the compressor wheel 222. The compressed air is then divided into compressed air that flows toward the fourth sub-branch path 942 and compressed air that flows toward the outlet path 943. As a result, the pressure of the compressed air that flows along the fourth sub-branch path 942 toward the second proximal end 862 of the second insertion hole 86 decreases.

The compressed air that reaches the second proximal end 862 of the second insertion hole 86 from the fourth sub-branch passage 942 forms an air curtain that seals the lubricating oil supplied to the second bearing 84. Furthermore, the compressed air that flows into the outlet passage 943 is directed toward the inside of the first end (open end) of the shroud case 220. This compressed air is then sucked back into the compressor wheel 222.

An exhaust path 173 (first exhaust path) is formed in the main housing 16. Compressed air that reaches the first branch path L and the second branch path M is exhausted to the outside of the main housing 16 via the exhaust path 173.

Next, the lubricating oil flow path (second supply path) will be described. Figure 8 is a schematic side cross-sectional view of the rotating electrical machine system 10. Note that Figure 8 shows a phase different from that shown in Figure 3.

An input passage 174 for supplying lubricating oil is formed in the side wall of the main housing 16. The input passage 174 is formed at a position closer to the first end than the axial center of the main housing 16. The input passage 174 extends along the diameter of the main housing 16 and communicates with the main oil passage 176. The main oil passage 176 is formed on the outer periphery of the cooling jacket 24 and extends along the axial direction of the main housing 16. The main oil passage 176 branches at the point where it communicates with the input passage 174 into a third branch passage N leading to the first sub-housing 18 and a fourth branch passage R leading to the second sub-housing 20.

A first inlet hole 178 is formed in the first sub-housing 18 at a location facing the third branch passage N. Furthermore, a first auxiliary oil passage 180 is formed inside the first sub-housing 18, extending radially inward of the first sub-housing 18. The first auxiliary oil passage 180 bends in two places before reaching the first bearing holder 80.

A first oil supply hole 182 communicating with the first auxiliary oil passage 180 is formed in the first bearing holder 80. The outlet of the first oil supply hole 182 is formed at the first distal end 781 of the first insertion hole 78. Therefore, lubricating oil flowing from the main oil passage 176 into the first auxiliary oil passage 180 flows from the first oil supply hole 182 to the first distal end 781 of the first insertion hole 78 and comes into contact with the first bearing 74.

As shown in FIG. 3, a first drain path 184 (one of the second discharge paths) is formed in the first sub-housing 18. The first drain path 184 drains lubricating oil from the hollow recess 118 formed by the annular protrusion 116 of the first sub-housing 18 and the resolver holder 30.

Three third branch passages N, three first inlet holes 178, three first auxiliary oil passages 180, and three first oil supply holes 182 are formed. Similarly, three fourth branch passages R are formed. Figure 8 shows one third branch passage N, one first inlet hole 178, one first auxiliary oil passage 180, one first oil supply hole 182, and one fourth branch passage R.

As shown in FIG. 7 , three oil receiving holes 186 open on the end face of the second sub-housing 20 facing the rotating electrical machine system 10. The oil receiving holes 186 are located radially outward of the first downstream communication holes 1681-1683. The oil receiving holes 186 are inlets for lubricating oil.

Three second auxiliary oil passages 188 are provided inside the second sub-housing 20 as oil supply passages. The second auxiliary oil passages 188 extend radially along the diameter of the second sub-housing 20. However, the second auxiliary oil passages 188 are formed in a different phase from the phase of the air relay passage 166. In addition, three oil outflow holes 190 are formed in the end face of the second sub-housing 20 facing the gas turbine engine 200. Hollow pin portions 193 of an oil distributor 192 are fitted into the oil outflow holes 190.

A first guide passage 1941 and a second guide passage 1942 are formed inside the oil distributor 192. The lubricating oil that passes through the second auxiliary oil passage 188 is separated into lubricating oil that flows through the first guide passage 1941 and lubricating oil that flows through the second guide passage 1942. The outlet of the first guide passage 1941 is located at the second proximal end 862 of the second insertion hole 86. Therefore, the lubricating oil that flows out of the first guide passage 1941 comes into contact with the second bearing 84 from the second proximal end 862.

The second guide path 1942 branches off midway from the first guide path 1941. The outlet of the second guide path 1942 is connected to the second oil supply hole 195 formed in the second bearing holder 88. Therefore, the lubricating oil that passes through the second guide path 1942 flows out from the second oil supply hole 195 and comes into contact with the second bearing 84.

As shown in FIG. 7, the second sub-housing 20 has two drain ports 197 and two second drain paths 196 (separate second discharge paths). As shown in FIG. 8, the space formed by the flow straightening member 96 and the second outer stopper 92 is connected to the second drain path 196 via the drain ports 197. Therefore, lubricating oil that enters the space is discharged from the second drain path 196 via the drain ports 197.

As shown in FIG. 9 , the first drain path 184 is connected to the gas-liquid separation device 302 (one of the recovery devices/oil supply devices) via a first relay pipe 3001. The second drain path 196 is connected to the gas-liquid separation device 302 via a second relay pipe 3002. The exhaust path 173 is connected to the gas-liquid separation device 302 via a third relay pipe 3003. In other words, the compressed air and lubricating oil supplied to the interior of the rotating electrical machine housing 14 are recovered in the gas-liquid separation device 302. The gas-liquid separation device 302 is provided with a circulation supply line 304 (circulation path) and a discharge line 306 (discharge path). The circulation supply line 304 is provided with a circulation pump 308, which is one of the oil supply devices.

As will be described later, the lubricating oil flowing out of the first drain path 184 and the second drain path 196 contains compressed air. In other words, the lubricating oil flowing into the gas-liquid separator 302 is a gas-liquid mixture. In the gas-liquid separator 302, the gas-liquid mixture is separated into lubricating oil and air. The lubricating oil is discharged from the gas-liquid separator 302 by the circulation pump 308 and resupplied to the input path 174 via the circulation supply line 304. Meanwhile, the air is released into the atmosphere via the discharge line 306.

Next, the gas turbine engine 200 will be described. As shown in FIG. 10 , the gas turbine engine 200 includes an engine housing 202 and an output shaft 204 that rotates within the engine housing 202. The engine housing 202 includes an inner housing 2021 and an outer housing 2022. The inner housing 2021 is connected to the second sub-housing 20 of the rotating electrical machine system 10. The outer housing 2022 is connected to the inner housing 2021. The outer housing 2022 is the housing body.

As shown in Figures 1 and 7, the inner housing 2021 has a first annular portion 206, a second annular portion 208, and a plurality of legs 210. The first annular portion 206 is connected to the second sub-housing 20. The diameter of the second annular portion 208 is larger than the diameter of the first annular portion 206. The legs 210 connect the first annular portion 206 and the second annular portion 208. In the illustrated example, the number of legs 210 is six. However, the number of legs 210 is determined depending on the connection strength required between the gas turbine engine 200 and the rotating electrical system 10. In other words, the number of legs 210 is not limited to six as shown in the illustrated example.

A cylindrical cover portion 212 protrudes from the central opening of the second annular portion 208 toward the rotating electrical machine system 10. The right ends of the legs 210 are connected to both cylindrical cover portions 212. An air intake space 214 is formed between the legs 210.

As shown in Figures 7 and 10, bleed passages 216 are individually formed inside the six leg portions 210. The inlets of the bleed passages 216 are individually formed in the leg portions 210 at the connection points with the cylindrical cover portion 212. The outlets of the bleed passages 216 are individually formed in the end faces of the first annular portion 206 facing the second sub-housing 20. All of the outlets of the bleed passages 216 are located on the circumference of an imaginary circle. Therefore, all of the outlets of the bleed passages 216 overlap with the collecting passage 162, which is formed in an annular shape. In other words, all of the multiple bleed passages 216 are connected to the collecting passage 162. In this way, compressed air from the multiple bleed passages 216 flows into and collects in the collecting passage 162.

An air vent hole 217 is formed in the leg portion 210. The air vent hole 217 extends linearly from the inner wall to the outer wall of the cylindrical cover portion 212. The air vent hole 217 can also extend from the inner wall of the cylindrical cover portion 212 to the outer wall of the leg portion 210. There may be one or more air vent holes 217. Furthermore, it is not necessary to form an air vent hole 217.

As shown in Figure 10, an annular engagement recess 218 is formed on the right end surface of the second annular portion 208. The engagement recess 218 positions and fixes the shroud case 220 and the diffuser 226 (described below).

As shown in FIG. 10, the gas turbine engine 200 further includes a shroud case 220, a compressor wheel 222, a turbine wheel 224, a diffuser 226, a combustor 228, and a nozzle 230.

The shroud case 220 is hollow and larger than the airflow straightening member 96. The small-diameter left end of the shroud case 220 faces the airflow straightening member 96. The large-diameter right end of the shroud case 220 is inserted into the cylindrical cover portion 212 of the inner housing 2021. The shroud case 220 gradually reduces in diameter from the right end to the left end, but the tip of the left end is curved so as to expand radially outward.

The left end of the shroud case 220 is exposed to the intake space 214. The top 102 of the flow straightening member 96 extends into the interior of the left end of the shroud case 220. An annular blocking flange portion 232 is provided on the curved side peripheral wall of the shroud case 220. The outer edge of the blocking flange portion 232 abuts against the inner walls of the cylindrical cover portion 212 and the leg portion 210.

An air bleed port 234 is formed in the side wall of the shroud case 220 between the blocking flange portion 232 and the first engaging protrusion 238. The air bleed port 234 extends from the inner surface to the outer surface of the side wall of the shroud case 220. The air bleed port 234 is the entrance to the chamber 236 through which compressed air enters the chamber 236.

The chamber 236 is located between the bleed port 234 and the bleed passage 216. That is, the chamber 236 connects the bleed port 234 and the bleed passage 216. The chamber 236 is also open to the atmosphere via the air vent hole 217.

A first engagement protrusion 238 protrudes from the right end of the shroud case 220 toward the second annular portion 208. The first engagement protrusion 238 engages with the engagement recess 218 of the second annular portion 208. This engagement, together with the outer edge of the blocking flange portion 232 abutting against the inner walls of the cylindrical cover portion 212 and the leg portion 210, positions and fixes the shroud case 220 to the inner housing 2021. At the same time, a chamber 236 is formed, surrounded by the leg portion 210, the cylindrical cover portion 212, the second annular portion 208, the blocking flange portion 232 of the shroud case 220, the side peripheral wall, and the first engagement protrusion 238. The chamber 236 forms a ring shape surrounding the shroud case 220.

The compressor wheel 222 and turbine wheel 224 can rotate integrally with the rotating shaft 40 and the output shaft 204. Specifically, as shown in detail in Figure 5, the compressor wheel 222 has a small-diameter cylindrical portion 242 at its left end. This small-diameter cylindrical portion 242 enters the insertion hole 108 formed in the flow straightening member 96. A first external spline 239 is formed on the inner wall of the small-diameter cylindrical portion 242. This first external spline 239 meshes with the first internal spline 66 formed on the right open end 442 of the outer shaft 44.

The right open end 442 of the outer shaft 44 is press-fit into the hollow interior of the small diameter cylindrical portion 242. As a result, the inner peripheral wall of the left opening of the small diameter cylindrical portion 242 presses the outer peripheral wall of the right open end 442 of the outer shaft 44 radially inward. The compressor wheel 222 is connected to the outer shaft 44 (rotating shaft 40) by the above-mentioned meshing and press-fitting.

A through hole 240 extending in the left-right direction is formed at the diametric center of the compressor wheel 222. A second external spline 246 is engraved on the inner wall of the left end of this through hole 240. Furthermore, the diameter of the through hole 240 at the point where it connects to the hollow interior of the small-diameter cylindrical portion 242 is slightly smaller than other points. For this reason, an inner flange portion 248 is provided on the compressor wheel 222 near the opening of the through hole 240 on the small-diameter cylindrical portion 242 side. The diameter of the through hole 240 is smallest at the location where the inner flange portion 248 is provided.

The output shaft 204 attached to the turbine wheel 224 is inserted into the through-hole 240. The left end of the output shaft 204 extends to approximately the same position as the left end of the small-diameter cylindrical portion 242 of the compressor wheel 222. As described above, the outer peripheral wall of the right open end 442 of the outer shaft 44 is inserted into the hollow interior of the small-diameter cylindrical portion 242. Therefore, the left end of the output shaft 204 protruding from the through-hole 240 enters the connecting hole 62 of the rotating shaft 40. A male thread 252 is formed on the left end of the output shaft 204. The male thread 252 is threaded into the female thread 64 formed on the inner wall of the connecting hole 62. This threading connects the rotating shaft 40 and the output shaft 204.

A second internal spline 254 is formed near the left end of the output shaft 204. The second internal spline 254 meshes with a second external spline 246 formed on the inner circumferential wall of the through-hole 240. The left end of the output shaft 204 is press-fit into the inner flange portion 248.

As shown in FIG. 10, a ring member 256 is interposed between the compressor wheel 222 and the turbine wheel 224. The ring member 256 is made of a heat-resistant metal material such as a nickel-based alloy.

As shown in FIG. 11 , the ring member 256 has a fitting hole 258 extending from the compressor wheel 222 to the turbine wheel 224. Furthermore, the outer peripheral wall of the ring member 256 has a plurality of (e.g., three) labyrinth-forming protrusions 264 formed thereon. The labyrinth-forming protrusions 264 protrude radially outward from the ring member 256 and extend circumferentially along the outer peripheral wall. As described below, the labyrinth-forming protrusions 264 prevent burned fuel (exhaust gas) generated in the combustor 228 from flowing back into the compressor wheel 222.

An annular protrusion 268 protrudes from the right end surface of the compressor wheel 222 facing the turbine wheel 224. When the left end surface of the ring member 256 seats on the right end surface of the compressor wheel 222, the annular protrusion 268 fits into the fitting hole 258. Meanwhile, the output shaft 204 extends from the left end surface of the turbine wheel 224 facing the compressor wheel 222. A fitting protrusion 270 that surrounds the output shaft 204 protrudes from the left end surface. When the right end surface of the ring member 256 seats on the left end surface of the turbine wheel 224, the top surface of the fitting protrusion 270 fits into the fitting hole 258. As a result, portions of the compressor wheel 222 and the turbine wheel 224 are fitted into the fitting hole 258. In this state, the ring member 256 is sandwiched between the compressor wheel 222 and the turbine wheel 224.

The labyrinth-forming protrusion 264 is surrounded by an intermediate plate 266 within the hollow interior of the outer housing 2022 (see Figure 10). The labyrinth-forming protrusion 264 is inserted into a hole 272 formed in the intermediate plate 266. A labyrinth flow path is formed by the inner wall of the hole 272 and the labyrinth-forming protrusion 264 abutting against this inner wall. Compressed air generated by the compressor wheel 222 reaches the labyrinth-forming protrusion 264 via the back surface of the compressor wheel 222. Meanwhile, combustion gas from the turbine wheel 224 reaches the labyrinth-forming protrusion 264. Because the pressure of the compressed air is higher than the pressure of the combustion gas, the combustion gas is prevented from passing through the labyrinth-forming protrusion 264 and flowing into the space surrounding the compressor wheel 222.

As shown in FIG. 10 , within the hollow interior of the outer housing 2022, portions of the shroud case 220 and compressor wheel 222, as well as the intermediate plate 266, are surrounded by the diffuser 226. A second engagement protrusion 273 is formed on the left end of the diffuser 226. The second engagement protrusion 273, together with the first engagement protrusion 238 of the shroud case 220, engages with the engagement recess 218. This engagement positions and fixes the diffuser 226 to the inner housing 2021.

In the hollow interior of the outer housing 2022, the turbine wheel 224 is surrounded by a nozzle 230, which is in turn surrounded by a combustor 228. An annular combustion air flow passage 274 is formed between the combustor 228 and the outer housing 2022. The combustion air flow passage 274 is a passage through which combustion air flows. A fuel supply nozzle 275 is positioned and fixed to the right end face of the outer housing 2022. The fuel supply nozzle 275 supplies fuel to the combustor 228.

The combustor 228 is formed with a relay hole 276 that connects the combustion air flow passage 274 with the interior of the combustor 228. As described below, combustion air compressed by the compressor wheel 222 passes through the diffuser 226, the combustion air flow passage 274, and the relay hole 276 and reaches the interior of the combustor 228. The combustor 228 also has micropores (not shown). The air discharged from the micropores forms an air curtain that cools the interior of the combustor 228.

The nozzle 230 has a section that surrounds the largest diameter portion of the turbine wheel 224. This section has a delivery hole (not shown) formed in it for supplying combusted fuel together with combustion air to the turbine wheel 224. Hereinafter, combusted fuel will also be referred to as "burned fuel." "Burned fuel" is synonymous with "combustion gas" or "exhaust gas after combustion."

An exhaust port 280 opens at the right end of the outer housing 2022 and the nozzle 230. After passing through the discharge holes and entering the nozzle 230, the burned fuel is blown out of the outer housing 2022 through the exhaust port 280 by the rotating turbine wheel 224. Although not specifically shown, the exhaust port 280 is provided with an exhaust pipe for discharging the burned fuel.

The combined power system 400 according to this embodiment is basically configured as described above. Next, the effects of the combined power system 400 will be explained.

First, DC current is supplied from the battery 146. The conversion circuit 152 of the current converter 150 shown in Figures 2 and 6 converts this DC current into AC current. The AC current is supplied to the electromagnetic coils 110 (U-phase coil, V-phase coil, and W-phase coil) via the U-phase terminal 1441, V-phase terminal 1442, and W-phase terminal 1443. When AC current flows through the electromagnetic coils 110, an alternating magnetic field is generated in the stator 36. As a result, attractive and repulsive forces act alternately between the electromagnetic coil 110 and the permanent magnets 72 of the rotor 34. As a result, the rotating shaft 40 begins to rotate. Alternatively, the rotating shaft 40 may be rotated by a known starter (not shown).

As shown in FIG. 5 , a first internal spline 66 is formed on the outer peripheral wall of the right open end 442 of the outer shaft 44, and a first external spline 239 is formed on the inner wall of the small-diameter cylindrical portion 242 of the compressor wheel 222. The first internal spline 66 and the first external spline 239 mesh with each other. Furthermore, a second internal spline 254 is formed on the output shaft 204, and a second external spline 246 is formed on the inner wall of the through hole 240 of the compressor wheel 222. The second internal spline 254 and the second external spline 246 mesh with each other. Therefore, the rotational torque of the rotating shaft 40 is quickly transmitted to the output shaft 204 via the compressor wheel 222.

In other words, when the rotating shaft 40 starts to rotate, the output shaft 204 also starts to rotate integrally with the rotating shaft 40. Accordingly, the compressor wheel 222 and turbine wheel 224 supported on the output shaft 204 rotate integrally with the output shaft 204. As described above, by meshing the first internal spline 66 with the first external spline 239 and meshing the second internal spline 254 with the second external spline 246, the rotational torque of the rotating shaft 40 can be sufficiently transmitted to the output shaft 204.

Furthermore, the right end of the rotating shaft 40 is press-fitted into the hollow interior of the small-diameter cylindrical portion 242 of the compressor wheel 222. Furthermore, the left end of the output shaft 204 is press-fitted into the inner flange portion 248 of the compressor wheel 222. Therefore, the axis of the rotating shaft 40 and the axis of the output shaft 204 are precisely aligned. This sufficiently prevents the output shaft 204 from rotating eccentrically or vibrating.

In addition, as shown in FIG. 11, a ring member 256 is interposed between the compressor wheel 222 and the turbine wheel 224. An annular protrusion 268 on the right end surface of the compressor wheel 222 and a mating protrusion 270 on the left end surface of the turbine wheel 224 are fitted into a fitting hole 258 of the ring member 256. This fit also contributes to suppressing eccentric rotation (vibration) of the output shaft 204. Therefore, there is no need to provide a mechanism to suppress vibration. There is also no need to increase the diameter of the output shaft 204. This allows the combined power system 400 to be made more compact.

Furthermore, a frictional force is generated between the right end face of the compressor wheel 222 and the left end face of the ring member 256. A frictional force is also generated between the right end face of the ring member 256 and the left end face of the turbine wheel 224. This frictional force causes the compressor wheel 222, ring member 256, and turbine wheel 224 to adhere to one another. This prevents the wheels 222, 224 from rotating out of alignment.

Furthermore, when assembling the combined power system 400, the above-described fitting allows the compressor wheel 222 and turbine wheel 224 to be aligned (centered) with respect to the output shaft 204. In this manner, it is preferable to provide a ring member 256 between the two wheels 222, 224, and to individually fit portions of the two wheels 222, 224 into the fitting holes 258 of the ring member 256. This makes it easier to center the compressor wheel 222 and turbine wheel 224 with respect to the output shaft 204.

As a result of the above rotation, as shown in FIG. 10, air is drawn into the shroud case 220 through the intake space 214 between the legs 210 of the inner housing 2021. Here, the rectifying member 96 is located at the diametric center of the inner housing 2021. As described above, the rectifying member 96 has a mountain-shaped configuration that narrows in diameter as it approaches the shroud case 220. Furthermore, the surface of the narrowing diameter portion 100 is smooth. Therefore, the suctioned air is rectified by the rectifying member 96 so that it flows toward the shroud case 220. Because the right end of the rectifying member 96 enters the left end opening of the shroud case 220, air is efficiently guided into the shroud case 220. Thus, by giving the rectifying member 96 the above-described shape and having the top portion 102 enter the shroud case 220, air can be efficiently collected by the shroud case 220.

The air drawn into the shroud case 220 flows between the compressor wheel 222 and the shroud case 220. Because the space between the compressor wheel 222 and the shroud case 220 is sufficiently narrow compared to the left opening of the shroud case 220, the air is compressed during this flow. In other words, compressed air is generated.

An air bleed port 234 is formed in the shroud case 220. As a result, some of the compressed air flows from the air bleed port 234 into the chamber 236. In other words, the compressed air is diverted. The chamber 236 is annular and has a volume larger than the volume of the air bleed port 234. As a result, the compressed air that flows into the chamber 236 is temporarily stored in the chamber 236.

Since multiple bleed passages 216 are formed, compressed air is distributed from chamber 236 to each bleed passage 216. In this case, the pressure of the distributed curtain air may differ. However, in this embodiment, the compressed air (curtain air) that passes through bleed port 234 flows into a single annular chamber 236. This makes the pressure of the curtain air within chamber 236 uniform. In other words, the pressure of the curtain air is made uniform. In this way, chamber 236 is a pressure adjustment chamber that adjusts the pressure of the curtain air to a substantially constant level.

As mentioned above, the curtain air flowing in from the bleed port 234 is part of the compressed air and is under high pressure. Here, because the volume of the chamber 236 is larger than the volume of the bleed port 234, the curtain air diffuses as it flows into the chamber 236. This reduces the pressure of the curtain air. As can be seen from this, the chamber 236 also serves as a buffer chamber that reduces the pressure of the compressed air.

In addition to the bleed passage 216, the inner housing 2021 is also formed with an air vent hole 217. Excess compressed air is released outside the gas turbine engine 200 (to the atmosphere) through the air vent hole 217. This prevents the curtain air pressure in the chamber 236 from rising excessively. In other words, the air vent hole 217 makes it easy to adjust the pressure in the chamber 236.

In the chamber 236, the inlets of the bleed passages 216 formed individually in each of the six legs 210 open. Therefore, the curtain air in the chamber 236 then flows individually through the six bleed passages 216, thereby traveling toward the second sub-housing 20. As described above, the pressure of the curtain air at this point is approximately constant.

As shown in Figure 7, the outlets of the six bleed passages 216 all overlap the collecting passage 162. Therefore, the curtain air that has flowed through the six bleed passages 216 flows into the collecting passage 162, where it collects and then diffuses in a circular pattern along the collecting passage 162. In this process, the pressure of the curtain air is further equalized.

The curtain air then flows from the collecting flow path 162 into three upstream communication holes 164, and then flows separately along three air relay paths 166. A portion of the curtain air is then discharged from the first downstream communication holes 1681-1683. The remainder of the curtain air is discharged from the second downstream communication holes 1701-1703. Hereinafter, the curtain air discharged from the first downstream communication holes 1681-1683 will be referred to as "first diverted air." The curtain air discharged from the second downstream communication holes 1701-1703 will be referred to as "second diverted air."

The path of the first diverted air will now be explained. The first downstream communication hole 1681 is connected to the hollow interior of the first hollow pipe section 1601. The first downstream communication hole 1682 is connected to the hollow interior of one end 160a of the second hollow pipe section 1602. The first downstream communication hole 1683 is connected to the hollow interior of the third hollow pipe section 1603. Therefore, the first diverted air flows through the hollow interiors of the first hollow pipe section 1601 to the third hollow pipe section 1603 shown in FIG. 1 etc., and flows from the second end to the first end of the rotating electric machine housing 14.

The first hollow pipe portion 1601 and the third hollow pipe portion 1603 are located on the outer periphery of the cooling jacket 24. A cooling medium has been flowing through the cooling jacket 24 in advance. Therefore, as the first diverted air flows along the first hollow pipe portion 1601 and the third hollow pipe portion 1603, the heat of the first diverted air is sufficiently conducted to the cooling medium. This causes the first diverted air to have a relatively low temperature. In other words, in this embodiment, the cooling jacket 24, which cools the rotating electric machine 12, the current converter 150, etc., can lower the temperature of the first diverted air.

One end 160a and the other end 160b of the second hollow tube portion 1602 are adjacent to the cooling jacket 24. Therefore, the heat of the first diverted air flowing through one end 160a and the other end 160b is transferred to the cooling medium flowing through the cooling jacket 24, as described above.

In addition, as shown in Figures 3 and 9, one end 160a and the other end 160b are connected to tubes 314 (see Figure 3) that constitute the heat exchanger 310. That is, compressed air that has flowed through one end 160a flows into the tubes 314. As described above, the cooling medium that has flowed through the cooling jacket 24 flows into the interior of the shell 312 via the communication path 171. Therefore, the heat of the first diverted air flowing through the tubes 314 is transferred to the cooling medium flowing through the interior of the shell 312. This further cools the temperature of the first diverted air flowing through the hollow interior of the second hollow tube section 1602. In this way, the heat exchanger 310 can further reduce the temperature of a portion of the first diverted air.

For the reasons stated above, there is no need to provide separate cooling equipment for cooling the curtain air in the gas turbine engine 200 or the rotating electrical machine system 10. This allows for the combined power system 400 to be made more compact.

In addition, the cooling medium that has circulated through the cooling jacket 24 is supplied to the interior of the shell 312 of the heat exchanger 310. In other words, the same cooling medium is used in the cooling jacket 24 and the heat exchanger 310. Therefore, there is no need to supply cooling medium separately to the cooling jacket 24 and the heat exchanger 310. This makes it possible to simplify the mechanism for supplying or circulating the cooling medium.

The first diverted air that has flowed through the first hollow tube portion 1601 flows into the second internal space of the second casing 28, as shown in Figure 2. This forms an air curtain inside the second casing 28. Excess first diverted air flows into the first internal space 29 of the first casing 26 through the interconnecting hole.

The first diverted air that has flowed through the second hollow tube section 1602 and the third hollow tube section 1603 flows into the first internal space 29 of the first casing 26. Therefore, in the first internal space 29, an air curtain is formed by the first diverted air that has flowed through the first hollow tube section 1601 to the third hollow tube section 1603.

As shown in FIG. 3, the excess first diverted air flows from the first internal space 29 into the storage chamber 22 of the main housing 16. As can be seen from this, the first internal space 29 and the second internal space are upstream in the flow direction of the first diverted air. In other words, the storage chamber 22 and the rotating electrical machine 12 are located downstream of the first casing 26 and the second casing 28 in the flow direction of the first diverted air.

Note that Figure 9 only shows the first diverted air passing through the heat exchanger 310. However, after flowing into the storage chamber 22, the first diverted air that has flowed through the first hollow tube section 1601 and the third hollow tube section 1603 also flows along the same path as the first diverted air that has passed through the heat exchanger 310.

The first casing 26 and the second casing 28 are disposed at the first end (left end) of the main housing 16. Therefore, the first diverted air flows into the left end of the storage chamber 22. The first diverted air then enters the clearance between the outer wall of the cylindrical protrusion 76 and the insulating substrate 112. This clearance is the inner hole of the stator 36.

A portion of the first diverted air then flows toward the first insertion hole 78 via the first branch path L. The remainder of the first diverted air flows toward the second insertion hole 86 via the second branch path M, along the clearance between the outer wall of the permanent magnet 72 and the inner wall of the electromagnetic coil 110. In this way, the first diverted air branches into compressed air flowing toward the first insertion hole 78 at the left end (first end) and compressed air flowing toward the second insertion hole 86 at the right end (second end).

The rotating electric machine 12 is cooled by the first diverted air flowing along the clearance between the outer wall of the permanent magnet 72 and the inner wall of the electromagnetic coil 110. As described above, the temperature of the first diverted air is sufficiently reduced by the cooling jacket 24 and the heat exchanger 310. Therefore, the rotating electric machine 12 is efficiently cooled.

In other words, the first diverted air flow prevents the temperature of the permanent magnet 72 from rising. This prevents the temperature of the permanent magnet 72 from reaching the Curie temperature. This prevents the magnetic force of the permanent magnet 72 from decreasing. As a result, a predetermined magnetic force is generated in the alternating magnetic field formed between the permanent magnet 72 and the electromagnetic coil 110. This allows the rotor 34 to maintain high-speed rotation.

Furthermore, in this embodiment, the rotating electric machine 12 is cooled using compressed air generated by the gas turbine engine 200. Therefore, there is no need to supply cooling air to the storage chamber 22 to cool the rotating electric machine 12. This allows the configuration of the combined power system 400 to be simplified while still cooling the rotating electric machine 12.

A portion of the first diverted air that flows toward the first insertion hole 78 reaches the first proximal end 782 of the first insertion hole 78. At this first proximal end 782, this portion forms an air curtain around the first bearing 74. Meanwhile, the remainder of the first diverted air that flows toward the second insertion hole 86 passes through the third sub-branch path 941 and reaches the second distal end 861 of the second insertion hole 86. At this second distal end 861, this portion forms an air curtain around the second bearing 84.

The path of the second diverted air will now be explained. The second downstream communication holes 1701-1703 overlap with three inlets 104 formed in the bottom portion 98 of the straightening member 96. Therefore, the second diverted air flows into the relay chamber 106 (the hollow interior of the straightening member 96) through the inlets 104.

As described above, the outlet of the relay chamber 106 opens at a position facing the small diameter cylindrical portion 242 of the compressor wheel 222. Therefore, the second diverted air that flows into the relay chamber 106 comes into contact with the small diameter cylindrical portion 242. A portion of the second diverted air then flows toward the fourth sub-branch path 942. The remainder of the second diverted air flows toward the outlet path 943.

A portion of the second diverted air reaches the second proximal end 862 of the second insertion hole 86 via the fourth sub-branch channel 942. At this second proximal end 862, this portion forms an air curtain around the second bearing 84. In this way, the second bearing 84 is sandwiched between the remainder of the second diverted air that has reached the second proximal end 862 and the portion of the first diverted air that has reached the second distal end 861.

The remainder of the second diverted air is discharged through outlet passage 943 into the interior of the left end of shroud case 220. As described above, air is being drawn into the left end opening of shroud case 220. Therefore, the remainder of the second diverted air is compressed by compressor wheel 222 together with the drawn-in atmospheric air.

The excess first diverted air passes through the storage chamber 22 and reaches the exhaust path 173. The excess second diverted air flows from the second end to the first end of the main housing 16, for example, via the clearance between the inner wall of the storage chamber 22 and the electromagnetic coil 110. The excess second diverted air then reaches the exhaust path 173. The first diverted air and second diverted air that have reached the exhaust path 173 are collected in the gas-liquid separator 302 (collection device) via the third relay pipe 3003.

As described above, the chamber 236 provided between the inner housing 2021 and the shroud case 220 equalizes the pressure of the curtain air. This prevents pressure distribution in the curtain air. It also prevents surging of the curtain air. This makes it possible to supply the curtain air around the first bearing 74 and the second bearing 84 while maintaining a substantially constant pressure.

As described above, the relay chamber 106 becomes wider as it approaches the fourth sub-branch path 942. Furthermore, the second diverted air flowing out of the relay chamber 106 is divided into a portion that flows toward the fourth sub-branch path 942 and a portion that flows toward the outlet path 943. Therefore, the pressure of the second diverted air that reaches the second proximal end 862 is lower than the pressure of the second diverted air before it flows into the relay chamber 106. As a result, the pressure of the first diverted air that reaches the second distal end 861 and the pressure of the second diverted air that reaches the second proximal end 862 are balanced.

In the above, a so-called shell-and-tube heat exchanger is used as the heat exchanger 310. Alternatively, a so-called plate-fin heat exchanger can be used as the heat exchanger 310. Since plate-fin heat exchangers are well known, they are not specifically illustrated and will only be described in general terms.

In this case, a stack of plate fins is housed within the hollow interior of the shell 312. An outgoing pipe and a returning pipe are provided in the stack. The outgoing pipe and the returning pipe extend parallel to each other along the stacking direction of the stack. One end of the outgoing pipe and one end of the returning pipe are connected to each other.

After passing through the cooling jacket 24, the cooling medium passes through the outgoing pipe, circulating along the stacking direction of the laminate. The cooling medium then passes through the return pipe, circulating along the stacking direction of the laminate in the opposite direction to the direction it passed through the outgoing pipe.

While the cooling medium flows through the outbound and inbound pipes in this manner, compressed air that has flowed through one end 160a of the second hollow tube section 1602 flows into the interior of the shell 312. In the interior of the shell 312, the compressed air passes through the gaps between adjacent plate fins. In other words, in this case, the gaps between the plate fins are air inlet paths through which the compressed air passes.

At this time, the heat of the compressed air is transferred to the cooling medium. As a result, the temperature of the compressed air drops. Therefore, the cooled compressed air flows into the other end 160b of the second hollow tube portion 1602. Thereafter, the compressed air flows into the storage chamber 22 in the same manner as described above.

Next, we will explain the lubricating oil path. The lubricating oil is supplied to the first bearing 74 and the second bearing 84 as a lubricant.

The lubricating oil, which has been recovered in the gas-liquid separator 302 (oil recovery device) shown in Figure 9 and separated from the curtain air, is pushed out by the circulation pump 308. The lubricating oil is supplied to the input passage 174 formed in the main housing 16 via the circulation supply line 304. The lubricating oil flows from the input passage 174 into the main oil passage 176. The main oil passage 176 branches into a third branch passage N leading to the first sub-housing 18 and a fourth branch passage R leading to the second sub-housing 20. Therefore, the lubricating oil is divided into lubricating oil flowing along the third branch passage N and lubricating oil flowing along the fourth branch passage R. Hereinafter, the lubricating oil flowing along the third branch passage N will be referred to as "first branch oil." The lubricating oil flowing along the fourth branch passage R will be referred to as "second branch oil."

The first diverted oil flows into the first auxiliary oil passage 180 through the first inlet hole 178 formed in the first sub-housing 18. The first diverted oil is then supplied to the first distal end 781 of the first insertion hole 78 through the first oil supply hole 182 formed in the first bearing holder 80. The first diverted oil further enters the inner bore of the first bearing 74 and lubricates the first bearing 74.

The first diverted oil flowing from the first distal end 781 to the first proximal end 782 is blocked by the first diverted air (air curtain) that reaches the first proximal end 782. This prevents the first diverted oil from flowing toward the first branch path L. This also prevents the first diverted oil from penetrating between the rotating shaft 40 and the electromagnetic coil 110. This prevents the rotating electric machine 12 from becoming contaminated with the first diverted oil.

Excess first diverted oil flows into the hollow recess 118. The hollow recess 118 is provided with a first drain path 184. Therefore, the first diverted oil in the hollow recess 118 is collected in the gas-liquid separator 302 via the first drain path 184.

The second diverted oil that flows through the fourth branch passage R flows into the second auxiliary oil passage 188 via the oil receiving hole 186 formed in the second sub-housing 20. The second diverted oil that flows through the second auxiliary oil passage 188 is divided into the first guide passage 1941 and the second guide passage 1942 formed inside the oil distributor 192. A portion of the second diverted oil that flows out from the outlet of the first guide passage 1941 is supplied to the second proximal end 862 of the second insertion hole 86. The remainder of the second diverted oil that passes through the second guide passage 1942 is supplied to the second bearing 84 via the second oil supply hole 195 formed in the second bearing holder 88. The second diverted oil enters the inner bore of the second bearing 84 and lubricates it.

The second diverted oil that enters the inner bore of the second bearing 84 is surrounded by the first diverted air supplied to the second distal end 861 and the second diverted air supplied to the second proximal end 862. As described above, the pressure of the first diverted air supplied to the second distal end 861 and the pressure of the second diverted air supplied to the second proximal end 862 are balanced. This prevents the second diverted oil from flowing toward the third sub-branch path 941 or the fourth sub-branch path 942. This prevents the second diverted oil from entering between the rotating shaft 40 and the electromagnetic coil 110. It also prevents the second diverted oil from entering the relay chamber 106 of the rectifying member 96. This prevents the rotating electric machine 12 and the rectifying member 96 from becoming contaminated with the second diverted oil.

As described above, the curtain air pressure is adjusted to a substantially constant level. Therefore, an air curtain of a predetermined pressure is continuously formed around the first bearing 74 and the second bearing 84. This prevents lubricating oil from leaking from the first bearing 74 and the second bearing 84.

Excess second diverted oil flows into the space formed by the straightening member 96 and the second outer stopper 92. A drain port 197 and a second drain path 196 are formed in the second sub-housing 20. The second diverted oil that flows into this space is collected in the gas-liquid separator 302 via the drain port 197 and the second drain path 196.

As described above, the curtain air and lubricating oil are recovered in the gas-liquid separator 302. Because the air curtain blocks the lubricating oil inside the rotating electrical machine housing 14, the curtain air exhausted from the exhaust path 173 contains lubricating oil. In other words, the curtain air exhausted from the exhaust path 173 is essentially a gas-liquid mixture.

In this embodiment, the recovery device also serves as the gas-liquid separator 302. Therefore, the gas-liquid mixture is separated into air and lubricating oil. The air is released into the atmosphere via a discharge line 306 provided in the gas-liquid separator 302. Meanwhile, the lubricating oil is pushed out of the gas-liquid separator 302 by a circulation pump 308. The lubricating oil is then resupplied from the gas-liquid separator 302 to the first bearing 74 and the second bearing 84 via a circulation supply line 304. While the rotating shaft 40 rotates, the first bearing 74 and the second bearing 84 are cooled by the lubricating oil.

In this way, by separating the gas-liquid mixture into lubricating oil and air using the gas-liquid separator 302, so-called air entrapment is prevented from occurring in the circulation supply line 304 and circulation pump 308. Therefore, lubricating oil can be resupplied to the first bearing 74 and the second bearing 84 at an appropriate discharge pressure or flow rate. This ensures that the first bearing 74 and the second bearing 84 are sufficiently lubricated. As a result, seizure of the first bearing 74 and the second bearing 84 can be suppressed.

In addition, air curtains are formed in the second branch path M, the third sub-branch path 941, and the fourth sub-branch path 942. These air curtains prevent lubricating oil from entering the first internal space 29 and the second internal space. This prevents lubricating oil from adhering to the U-phase terminal 1441, V-phase terminal 1442, W-phase terminal 1443, thermistor 148, etc. In other words, it is possible to prevent the electrical terminals and measuring devices (thermistor 148), etc. from being contaminated with lubricating oil.

As described above, the curtain air (first diverted air and second diverted air) prevents lubricating oil from scattering from the first bearing 74 and the second bearing 84. The curtain air is then discharged to the outside of the rotating electrical machine housing 14 as described above. Therefore, even if lubricating oil leaks from the first bearing 74 or the second bearing 84, the leaked lubricating oil is entrained by the curtain air and discharged to the outside of the rotating electrical machine housing 14. This prevents the leaked lubricating oil from flowing toward the rotor 34. It also prevents the leaked lubricating oil from remaining within the rotor 34.

As described above, the pressure of the curtain air continuously supplied to the rotating electrical machine housing 14 is approximately constant. This makes it possible to continuously prevent the lubricating oil from scattering as described above. Furthermore, even if lubricating oil leaks, the leaked lubricating oil can be continuously discharged to the outside of the rotating electrical machine housing 14.

Compressed air that passes between the shroud case 220 and the compressor wheel 222 without entering the bleed port 234 becomes combustion air. As shown in FIG. 10, the combustion air flows into the diffuser 226. The combustion air flows from an outlet hole formed in the wall of the diffuser 226 into the combustion air flow passage 274 between the combustor 228 and the outer housing 2022. The combustion air then flows into the combustion chamber (the hollow interior of the combustor 228) via the relay hole 276 formed in the combustor 228, the fine holes, and the clearance between the combustor 228 and the fuel supply nozzle 275.

The combustor 228 is preheated. Therefore, the combustion chamber is also at a high temperature. Fuel is supplied to the high-temperature combustion chamber from the fuel supply nozzle 275. The fuel burns together with the combustion air, becoming high-temperature burned fuel. When this burned fuel is supplied into the nozzle 230 from the delivery hole, it expands within the nozzle 230. This causes the turbine wheel 224 to begin rotating at high speed.

The output shaft 204 holds a turbine wheel 224. A compressor wheel 222 is also provided on the output shaft 204. Therefore, as the turbine wheel 224 rotates at high speed, the output shaft 204 and the compressor wheel 222 rotate together at high speed. At the same time, the rotating shaft 40 also rotates at high speed. The burned fuel is discharged outside the outer housing 2022 via an exhaust pipe (not shown) provided at the exhaust port 280.

The ring member 256 interposed between the compressor wheel 222 and the turbine wheel 224 also serves as a sealing member that seals the gap between the two wheels 222, 224. Furthermore, as shown in FIG. 11 , multiple labyrinth-forming protrusions 264 are formed on the outer peripheral wall of the ring member 256. These labyrinth-forming protrusions 264 abut against the inner walls of holes 272 formed in the intermediate plate 266. Compressed air generated by the compressor wheel 222 reaches the labyrinth-forming protrusions 264 via the back surface of the compressor wheel 222. Furthermore, combustion gas from the turbine wheel 224 reaches the labyrinth-forming protrusions 264. As mentioned above, the pressure of the compressed air is higher than the pressure of the combustion gas. Therefore, the combustion gas is prevented from passing through the labyrinth-forming protrusions 264 and flowing into the compressor wheel 222. For the reasons above, burned fuel is prevented from entering the through-hole 240, for example, from between the wheels 222, 224.

In Figure 10, when the output shaft 204 begins to rotate at high speed, the supply of current from the battery 146 (see Figure 6) to the electromagnetic coil 110 is stopped. However, as described above, because the turbine wheel 224 is already rotating at high speed, the rotating shaft 40 rotates at high speed integrally with the turbine wheel 224 and output shaft 204. Even at this time, for the same reasons as above, sufficient rotational torque is transmitted from the output shaft 204 to the rotating shaft 40.

In Figure 3, it is preferable that the rotation direction of the output shaft 204 and the rotating shaft 40 be opposite to the rotation direction of the small cap nut 58, large cap nut 60, and male thread portion 252 when they are threaded together. This is because loosening of the small cap nut 58, large cap nut 60, and male thread portion 252 during rotation of the rotating shaft 40 is prevented. Note that a mechanism to prevent loosening may be provided on the small cap nut 58, large cap nut 60, or male thread portion 252.

Since the rotating shaft 40 holds the permanent magnet 72, an AC current is generated in the electromagnetic coil 110 surrounding the permanent magnet 72. The AC current is sent to the current converter 150 shown in Figures 2 and 6 via the U-phase terminal 1441, V-phase terminal 1442, and W-phase terminal 1443. The conversion circuit 152 of the current converter 150 converts this AC current into DC current. When the control circuit 156 of the current converter 150 determines that the output of an external load (e.g., a motor) electrically connected to the battery 146 has decreased, it supplies DC current to the battery 146 (see Figure 6) via the capacitor 154. This charges the battery 146.

During this process, the current converter 150, particularly the conversion circuit 152 and capacitor 154, becomes heated. However, in this embodiment, the conversion circuit 152 and capacitor 154 inside the device case 158 are located close to the cooling jacket 24. This allows the heat from the conversion circuit 152 and capacitor 154 to be quickly conducted to the cooling medium inside the cooling jacket 24. This prevents the conversion circuit 152 and capacitor 154 from becoming excessively hot.

The electromagnetic coil 110 generates heat as current flows through it. Here, a portion of the first diverted air comes into contact with the left end of the stator 36. Furthermore, the remainder of the first diverted air, which passes through the storage chamber 22 and heads toward the second insertion hole 86, comes into contact with the outer and inner walls of the stator 36. Therefore, the stator 36 is cooled by the first diverted air. A cooling medium also flows through the cooling jacket 24 provided on the main housing 16. The rotating electric machine 12 is quickly cooled by this cooling medium. This also allows the alternating magnetic field formed between the permanent magnet 72 and the electromagnetic coil 110 to generate a predetermined magnetic force.

In this embodiment, the rotating electric machine housing 14 (main housing 16) that houses the rotating electric machine 12 and the first casing 26 that houses the U-phase terminal 1441, V-phase terminal 1442, and W-phase terminal 1443 are provided separately. Therefore, the heat generated in the stator 36 in the main housing 16 is less likely to affect the U-phase terminal 1441, V-phase terminal 1442, and W-phase terminal 1443 in the first casing 26. Furthermore, when current is applied, the U-phase terminal 1441, V-phase terminal 1442, and W-phase terminal 1443 also generate heat. However, the U-phase terminal 1441, V-phase terminal 1442, and W-phase terminal 1443 are quickly cooled by the first diverted air supplied to the first casing 26.

In this way, the first diverted air also serves to cool heat-generating locations in the rotating electric machine system 10. By cooling the electrical terminals (U-phase terminal 1441, V-phase terminal 1442, and W-phase terminal 1443), electromagnetic coil 110, permanent magnet 72, etc., the effects of heat on the output control of the rotating electric machine system 10 are avoided. Furthermore, a reduction in the excitation of the electromagnetic coil 110, permanent magnet 72, etc. due to heat is also avoided. As a result, the reliability of the rotating electric machine system 10 is improved.

Furthermore, because the main housing 16 that houses the rotating electric machine 12 and the first casing 26 that houses the U-phase terminal 1441, V-phase terminal 1442, and W-phase terminal 1443 are provided separately, the rotating electric machine 12 and the electrical terminals are spaced apart. Therefore, the U-phase terminal 1441, V-phase terminal 1442, and W-phase terminal 1443 are less susceptible to the effects of vibrations that occur as the rotor 34 rotates. In other words, the U-phase terminal 1441, V-phase terminal 1442, and W-phase terminal 1443 are protected from vibrations. Furthermore, as described above, the lubricating oil in the first bearing 74 and the second bearing 84 prevents seizure. Therefore, the rotating electric machine system 10 has excellent durability.

As the rotating shaft 40 rotates, the rotation angle (rotation parameter) of the rotating shaft 40 is detected by the resolver 132. Specifically, the resolver rotor 56, which is fitted onto the left end 422 of the inner shaft 42, rotates integrally with the rotating shaft 40. As a result, an electrical signal generated in the resolver stator 130 is transmitted to the receiver via the transmission connector 136. The receiver reads the electrical signal and calculates the rotation angle of the rotating shaft 40 based on the electrical signal. The receiver sends the calculation result to a control device or the like (not shown). The control device or the like performs an arithmetic operation based on this rotation angle to determine the rotation speed.

The resolver 132 is disposed on the protruding tip 46 of the rotating shaft 40, which is exposed from the rotating electric machine housing 14. Therefore, the resolver 132 is less susceptible to the heat generated in the electromagnetic coil 110 of the stator 36 inside the rotating electric machine housing 14. The resolver 132 is also less susceptible to the vibrations generated by the rotation of the rotor 34. In addition, the first bearing 74 and second bearing 84 that support the rotating shaft 40 are provided inside the rotating electric machine housing 14. Therefore, the rotating electric machine housing 14 suppresses the vibrations of the first bearing 74 and second bearing 84. This also makes it difficult for the vibrations to affect the resolver 132.

As described above, in this embodiment, the transmission of heat, vibrations, etc. to the resolver 132 is suppressed. This results in more accurate detection of the rotation angle by the resolver 132. Furthermore, the life of the resolver 132 is also extended.

There may be cases where the resolver 132 is replaced with another resolver having a larger inner and outer diameter. If a single solid rotating shaft is used as the rotating shaft, replacing it with a resolver having a larger inner and outer diameter requires replacing it with a larger-diameter solid rotating shaft. In this case, it is not easy to pass the large-diameter solid rotating shaft through the first bearing 74 and the second bearing 84.

In this embodiment, the rotating shaft 40 is made up of the outer shaft 44 and the inner shaft 42. The outer shaft 44 is passed through the first bearing 74 and the second bearing 84, and the resolver rotor 56 is provided on the inner shaft 42 at a portion exposed from the outer shaft 44. Therefore, when replacing the resolver 132 with another resolver having larger inner and outer diameters, this can be accommodated by simply replacing the inner shaft 42 with an inner shaft having a larger diameter at the left end 422. As can be seen from this, according to this embodiment, by replacing the inner shaft 42, it is possible to accommodate resolvers with various inner and outer diameters.

For example, in this embodiment, a third sub-branch channel 941 and a fourth sub-branch channel 942 are provided. Alternatively, the first branch channel L may be branched into a first sub-branch channel and a second sub-branch channel. In this case, a portion of the first diverted air is supplied from the first sub-branch channel to the first distal end 781, and a portion of the first diverted air is supplied from the second sub-branch channel to the first proximal end 782. Alternatively, the first branch channel L may be branched into a first sub-branch channel and a second sub-branch channel, and a third sub-branch channel 941 and a fourth sub-branch channel 942 may be provided.

In the gas turbine engine 200, the compressor wheel 222 and turbine wheel 224 can also be arranged in the reverse order to that shown in Figure 10. In this case, a through hole 240 can be formed in the turbine wheel 224, and the compressor wheel 222 can be provided with an output shaft 204. Alternatively, the compressor wheel 222 and turbine wheel 224 can be centrifugal or axial flow types. As long as the compressor wheel 222 and turbine wheel 224 are arranged on the same axis, a combination of a centrifugal type and an axial type multi-stage compressor wheel and a multi-stage turbine wheel can also be used.

In FIG. 3, the rotating electric machine 12 constituting the rotating electric machine system 10 may be a motor in which the rotating shaft 40 rotates when current is applied to the electromagnetic coil 110. In this case, the U-phase terminal 1441, the V-phase terminal 1442, and the W-phase terminal 1443 are electrical terminals that receive power from the battery 146.

As described above, this embodiment is a compound power system (400) comprising a rotating electric machine system (10) having a rotating electric machine (12) and a rotating electric machine housing (14) that rotatably supports the rotating shaft (40) of the rotating electric machine, and a gas turbine engine (200) having an output shaft (204) that rotates integrally with the rotating shaft and is provided at one end of the rotating electric machine housing, the compound power system (400) comprising a compressor wheel (222) provided on the output shaft that compresses outside air to obtain compressed air, a shroud case (220) that surrounds the compressor wheel, an engine housing (202) that houses the compressor wheel and the shroud case, a terminal casing (26) provided on the outer wall of the rotating electric machine housing and that houses electrical terminal units (1441-1443) for transmitting and receiving power between the rotating electric machine and external equipment, and a terminal casing (26) provided on the outer wall of the rotating electric machine housing that houses the gas turbine engine. and a heat exchanger (310) disposed in a recess formed by the gin and the terminal casing for lowering the temperature of the compressed air. The rotating electric machine has a storage chamber (22) that houses the rotating electric machine housing. The shroud case is formed with an air bleed port (234) for extracting the compressed air to the outside of the shroud case. The engine housing is formed with an air bleed passage (216) through which the compressed air that has flowed into the air bleed port flows. The rotating electric machine housing is formed with a cooling jacket (24) that surrounds the rotating electric machine from the outer periphery. The heat exchanger has a shell (312) and an air inlet passage (314) that is provided inside the shell and communicates with the storage chamber of the rotating electric machine housing. A cooling medium that has circulated through the cooling jacket is supplied to the inside of the shell. The storage chamber of the rotating electric machine housing is downstream of the heat exchanger in the flow direction of the compressed air.

In this configuration, compressed air generated by the gas turbine engine passes through a heat exchanger and flows into the storage chamber of the rotating electrical machine housing. In the heat exchanger, the heat of the compressed air is absorbed by the cooling medium, thereby lowering the temperature of the compressed air. The cooled compressed air then flows into the storage chamber. This allows the rotating electrical machine housed in the storage chamber to be efficiently cooled.

This cooling prevents the temperature of the permanent magnets that make up the rotating electric machine from reaching the Curie point. This prevents the magnetic force of the permanent magnets from decreasing. As a result, a predetermined magnetic force is generated in the alternating magnetic field formed between the permanent magnets and the electromagnetic coil. This allows the rotor to maintain high-speed rotation.

In this way, according to the present invention, the rotating electrical machine can be cooled using compressed air generated by the gas turbine engine. Therefore, there is no need to supply cooling air for cooling the rotating electrical machine to the storage chamber separately from the compressed air. This allows for a simplified configuration of the combined power system while still cooling the rotating electrical machine. Moreover, even with this configuration, the rotor can be rotated at high speed.

The heat exchanger is also placed in a recess formed by the gas turbine engine and the terminal casing. That is, the heat exchanger is contained within the recess and is not exposed from the recess. This prevents the combined power system from becoming larger, which would be otherwise required if the heat exchanger were mounted on the outer wall of the rotating electrical machine housing.

Furthermore, the cooling medium that has circulated through the cooling jacket is supplied to the heat exchanger. This eliminates the need to supply cooling medium separately to the cooling jacket and the heat exchanger. This simplifies the mechanism for supplying or circulating the cooling medium.

This embodiment discloses a hybrid power system in which the terminal casing has an internal space (29), the air inlet path communicates with the storage chamber of the rotating electrical machine housing via the internal space of the terminal casing, and the storage chamber of the rotating electrical machine housing is downstream of the internal space of the terminal casing in the direction of compressed air flow.

In this case, an air curtain is formed in the internal space of the terminal casing. This air curtain protects the electrical terminal portion. This prevents the electrical terminal portion from becoming contaminated with, for example, lubricating oil supplied to the bearing. The air curtain also serves to cool the electrical terminal portion.

This embodiment discloses a composite power system that includes a first bearing (74) and a second bearing (84) for rotatably supporting the rotating shaft in the rotating electric machine housing, and in which compressed air that has passed through the air inlet passage is supplied to the first bearing and the second bearing within the rotating electric machine housing.

The compressed air supplied to the first and second bearings cools them, thereby preventing the first and second bearings from seizing.

This embodiment discloses a compound power system in which the first bearing and the second bearing are lubricated with lubricating oil.

The compressed air supplied to the first and second bearings forms an air curtain around the first and second bearings. This air curtain seals the lubricating oil supplied to the first and second bearings. This prevents the lubricating oil from leaking outside the specified area. This prevents the rotating electrical machine, measuring instruments, rotation parameter detectors, terminals, etc. from becoming contaminated with the lubricating oil.

In addition, because the air curtain seals out the lubricating oil, there is no need to provide sealing members. This reduces the number of components (parts), allowing for the compactness and simplification of the combined power system.

This embodiment discloses a hybrid power system in which compressed air flow passages (1601, 1603) are formed in the outer wall of the rotating electrical machine housing at positions that do not interfere with the heat exchanger, and a distribution passage is formed in the rotating electrical machine housing for distributing the compressed air that has circulated through the bleed passage to the air inlet passage of the heat exchanger and the compressed air flow passage.

The compressed air generated by the gas turbine engine is at high pressure. By distributing this high-pressure air into multiple compressed air flow passages, the pressure of the compressed air supplied to the rotating electrical machine housing can be sufficiently reduced.

This embodiment discloses a hybrid power system in which multiple bleed passages, including the bleed passage, are formed, and the compressed air that has flowed through the multiple bleed passages flows into the distribution passage.

In this case, compressed air is distributed to each of the multiple bleed passages. Therefore, the pressure of the compressed air can be reduced before it flows into the distribution passage.

This embodiment discloses a composite power system in which the distribution passage includes a single collecting passage (162) into which compressed air from the multiple bleed passages individually flows, and multiple relay communication passages that individually connect the single collecting passage with each of the multiple compressed air flow passages.

Since all outlets of the multiple bleed passages are connected to the collecting passage, the compressed air that has flowed through the multiple bleed passages is collected in the collecting passage. The compressed air then diffuses along the collecting passage. In this process, the pressure of the compressed air is equalized. In addition, since multiple relay communication passages are provided, it is possible to supply compressed air to multiple destinations.

This embodiment discloses a hybrid power system in which the collecting passage is annular in shape and the multiple relay communication passages are arranged radially.

This configuration makes it easy to connect multiple bleed passages to the compressed air flow passage.

This embodiment discloses a composite power system in which the rotating shaft includes a hollow cylindrical outer shaft (44) and an inner shaft (42) that is longer than the outer shaft and is removably inserted inside the outer shaft, with one end of the inner shaft exposed from the outer shaft.

For example, when replacing a rotation parameter detector with another rotation parameter detector with larger inner and outer diameters, this can be accommodated by replacing the inner shaft with an inner shaft with one having a larger diameter at one end exposed from the outer shaft. In other words, with this configuration, by replacing the inner shaft, it is possible to accommodate rotation parameter detectors with a variety of different inner and outer diameters.

The present invention is not limited to the above disclosure, and various configurations may be adopted without departing from the spirit of the present invention.

10...Rotating electric machine system 12...Rotating electric machine 14...Rotating electric machine housing 22...Storage chamber 24...Cooling jacket 26...First casing 28...Second casing 29...First internal space 30...Resolver holder 34...Rotor 36...Stator 40...Rotating shaft 42...Inner shaft 44...Outer shaft 46...Protruding tip 56...Resolver rotor 72...Permanent magnet 74...First bearing 84...Second bearing 96...Rectifying member 106...Relay chamber 108...Insertion hole 110...Electromagnetic coil 130...Resolver stator 132...Resolver 136...Transmitting connector 146...Battery 148...Thermistor 150...Current converter 152...Conversion circuit 154...Capacitor 156...Control circuit 161...Power module 162...Collecting flow path 164...Upstream communication hole 166...Air relay path 171...Communication path 172...Exhaust pipe 173...Exhaust passage 174...Input passage 176...Main oil passage 180...First auxiliary oil passage 184...First drain passage 188...Second auxiliary oil passage 192...Oil distributor 196...Second drain passage 197...Drain port 200...Gas turbine engine 202...Engine housing 204...Output shaft 210...Leg 214...Intake space 216...Bleed passage 217...Air vent hole 220...Shroud case 222...Compressor wheel 224...Turbine wheel 226...Diffuser 228...Combustor 230...Nozzle 234...Bleed port 236...Chamber 256...Ring member 274...Combustion air flow passage 275...Fuel supply nozzle 276...Relay hole 302...Gas-liquid separator 304...Circulation supply line 308...Circulation pump 310...Heat exchanger 312...Shell 314...Tube 400...Compound power system 781...First distal end 782...First proximal end 861...Second distal end 862...Second proximal end 941...Third sub-branch path 942...Fourth sub-branch path 1441...U-phase terminal 1442...V-phase terminal 1443...W-phase terminal 1601...First hollow tube section 1602...Second hollow tube section 1603...Third hollow tube section 1681-1683...First downstream communicating hole 1701-1703...Second downstream communicating hole 2021...Inner housing 2022...Outer housing 3001...First relay pipe 3002...Second relay pipe 3003...Third relay pipe L...First branch path M...Second branch path N...Third branch path R...Fourth fork

Claims (9)

a rotating electric machine system including a rotating electric machine and a rotating electric machine housing that rotatably supports a rotating shaft of the rotating electric machine;
a gas turbine engine having an output shaft that rotates integrally with the rotary shaft and that is provided at one end of the rotary electric machine housing;
A combined power system comprising:
a compressor wheel provided on the output shaft and compressing outside air to obtain compressed air;
a shroud case surrounding the compressor wheel;
an engine housing that houses the compressor wheel and the shroud case;
a terminal casing provided on an outer wall of the rotary electric machine housing and accommodating an electric terminal portion for transmitting and receiving electric power between the rotary electric machine and an external device;
a heat exchanger disposed in a recess formed by the gas turbine engine and the terminal casing in the outer wall of the rotary electric machine housing, for lowering a temperature of the compressed air;
Equipped with
the rotating electric machine has a storage chamber that houses the rotating electric machine housing,
an air bleed port for extracting the compressed air to the outside of the shroud case is formed in the shroud case;
a bleed passage through which the compressed air that has flowed into the bleed port flows is formed in the engine housing;
a cooling jacket is formed in the rotating electric machine housing to surround the rotating electric machine from an outer periphery side;
the heat exchanger has a shell and an air inlet passage provided inside the shell and communicating with the storage chamber of the rotating electrical machine housing, and a cooling medium that has circulated through the cooling jacket is supplied to the inside of the shell;
In a hybrid power system, the storage chamber of the rotating electrical machine housing is located downstream of the heat exchanger in the flow direction of the compressed air. 2. The compound power system according to claim 1, wherein the terminal casing has an internal space, and the air supply passage communicates with the storage chamber of the rotating electrical machine housing through the internal space of the terminal casing;
In a compound power system, the storage chamber of the rotating electrical machine housing is located downstream of the internal space of the terminal casing in the flow direction of the compressed air. 2. The combined power system according to claim 1, further comprising a first bearing and a second bearing for rotatably supporting the rotary shaft in the rotary electric machine housing,
A compound power system in which compressed air that has passed through the air inlet passage is supplied to the first bearing and the second bearing within the rotating electrical machine housing. The combined power system of claim 3, wherein the first bearing and the second bearing are lubricated with lubricating oil. In the combined power system described in claim 1, a compressed air flow passage is formed in the outer wall of the rotating electrical machine housing at a position that does not interfere with the heat exchanger, and a distribution passage is formed in the rotating electrical machine housing for distributing the compressed air that has circulated through the bleed passage to the air inlet passage of the heat exchanger and the compressed air flow passage. The compound power system according to claim 5, wherein a plurality of bleed passages including the bleed passage are formed, and the compressed air that has flowed through the plurality of bleed passages flows into the distribution passage. A compound power system according to claim 6, wherein the distribution passage has a single collecting passage into which compressed air from the multiple bleed passages individually flows, and multiple relay communication passages that individually connect the single collecting passage with each of the multiple compressed air flow passages. The combined power system of claim 7, wherein the collecting passage is annular, and the multiple relay communication passages are arranged radially. A compound power system according to any one of claims 1 to 8, wherein the rotating shaft comprises a hollow cylindrical outer shaft and an inner shaft that is longer than the outer shaft and is removably inserted inside the outer shaft, with one end of the inner shaft exposed from the outer shaft.