JP7821066B2 - Rotating Electric Machine System - Google Patents

Description

The present invention relates to a rotating electrical machine system that includes a rotor and a stator, in which the rotor is driven to rotate when power is supplied.

Patent Document 1 discloses a rotating electrical machine system having an inner stator and an outer rotor. The outer rotor is positioned inside the inner stator. A center shaft is connected to the center of the hub of the outer rotor. The center of the center shaft has an intake passage through which air supplied from a blower flows. The intake passage extends along the axial direction of the center shaft and then opens radially outward through a hole in the hub.

When air is supplied to the intake passage, it flows axially along the center shaft, flows radially outward through the hole in the hub, and then flows axially along the iron core located on the outside of the outer rotor and is supplied into the space.

JP 2009-148047 A

In the rotating electrical machine system of Patent Document 1, when air is introduced from the inlet passage between the inner stator and outer rotor, the air flow path is complex, spanning axial, radial, and axial directions, increasing flow resistance and making it difficult to ensure smooth flow. When the center shaft rotates with the outer rotor, centrifugal force generated by the rotation reduces the efficiency of air compression. This requires the use of an air supply device such as a blower to supply air, which increases the size of the device and increases manufacturing costs.

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

One aspect of the present invention is a rotating electrical machine system comprising a rotor having magnets, a stator surrounding the rotor, and a housing containing the rotor and the stator, with a cooling passage through which a cooling gas flows inside the rotor. The cooling passage has an inlet through which the gas is introduced and an outlet through which the gas is discharged, the inlet and the outlet being positioned axially spaced apart from each other, and the outlet being positioned radially outward from the axial center relative to the inlet.

According to the present invention, negative pressure is generated in the cooling passage from the inlet to the outlet by centrifugal force acting when the rotor rotates, thereby promoting the flow of gas toward the outlet of the cooling passage. This allows for smooth gas flow through the rotor's cooling passage with a simple configuration.

FIG. 1 is a perspective view showing the appearance of a compound power system including a rotating electrical machine system according to an embodiment of the present invention. FIG. 2 is a perspective view showing the appearance of a rotating electrical machine system that constitutes the compound power system of FIG. FIG. 3 is a schematic cross-sectional side view of the rotating electrical machine system of FIG. FIG. 4 is an enlarged cross-sectional view of the vicinity of the rotating shaft of the rotating electrical machine system of FIG. FIG. 5 is an enlarged view of a main portion of the rotary electric machine system shown in FIG. 3, showing the vicinity of the inlet-side straightening member. FIG. 6 is an enlarged view of a main portion showing the vicinity of the outlet-side straightening member of the rotary electric machine system shown in FIG. FIG. 7 is a front view of the inlet-side flow straightening member as viewed from the axial direction. FIG. 8 is a front view of the outlet side flow straightening member as viewed from the axial direction. FIG. 9 is a perspective view of the appearance of the inlet-side flow straightening member. FIG. 10 is a perspective view of the appearance of the outlet-side flow rectifying member. FIG. 11 is a schematic diagram showing the configuration of a current converter provided in a housing of a rotating electrical machine. FIG. 12 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. 13 is a schematic cross-sectional side view of a gas turbine engine that constitutes a combined power system. FIG. 14 is an enlarged view of a main part of the gas turbine engine of FIG. FIG. 15 is a schematic side cross-sectional view of a gas supply source that uses an externally provided compressor pump.

As shown in Figure 1, the rotating electrical machine system 10 according to this embodiment is used in a combined power system 400 that is integrally combined with an internal combustion engine. Figure 1 is a schematic overall perspective view of the combined power system 400 according to this embodiment.

In the following, "left," "right," "bottom," and "top" refer to the left, right, bottom, and top directions, respectively, in Figures 3 to 6, 13, and 14. 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.

The combined power system 400 comprises a rotating electric machine system 10 and a gas turbine engine 200. An axis passing through the diameter center of the rotating electric machine system 10 and extending along the longitudinal direction (axial direction) coincides with an axis passing through the diameter center 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. The 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. An accommodation chamber 22 is formed inside the side walls of the main housing 16. Most of the rotating electric machine 12 is housed in the accommodation chamber 22.

A spiral cooling jacket 24 is 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 form part of the main housing 16. In other words, the first casing 26 and the second casing 28 are arranged 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.

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, a stator 36 surrounding the outer periphery of the rotor 34, and a rectifying structure 37.

The rotor 34 includes a magnet 38, a rotating shaft 39, an expanded diameter portion 40, a cooling passage 41, and first and second magnet holders 70a, 70b. The rotating shaft 39 has an inner shaft 42 and a hollow cylindrical outer shaft 44. Both ends of the main body portion 44a of the outer shaft 44 are open ends. That is, the main body portion 44a has a left open end 441 (see Figure 5) and a right open end 442 (see Figure 6). The left open end 441 is located at the left end, which is one axial end of the main body portion 44a. The right open end 442 is located at the right end, which is the other axial end of the main body portion 44a.

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. 5), and a right end 423 (see FIG. 6). The left end 422 is connected 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 is connected 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 close 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, described below. 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 FIG. 5 , the first external thread portion 48, flange portion 50, stopper portion 52, and second external thread portion 54 are arranged in this order toward the right on the left end 422 of the inner shaft 42. The outer diameters of the first external thread portion 48, flange portion 50, stopper portion 52, and 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 stopped 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. Note that 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. 6, 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. 13).

As shown in FIG. 3 , the outer shaft 44 has a main body portion 44a, an intermediate portion 44b, and a cooling passage 41. The main body portion 44a extends in the axial direction of the outer shaft 44. The left and right ends of the main body portion 44a are rotatably supported by the first and second sub-housings 18 and 20, respectively. A first internal spline 66 is formed on the outer peripheral wall of the right open end 442 of the main body portion 44a. The first internal spline 66 extends along the axial direction (left-right direction) of the rotating electrical machine system 10.

The expanded diameter section 40 is composed of the intermediate section 44b of the outer shaft 44, portions of the first and second magnet holders 70a and 70b, the first and second retaining plates 45a and 45b, and the magnet 38. The intermediate section 44b is located in the axial center of the outer shaft 44. In the axial direction of the rotor 34, the intermediate section 44b is located in the middle section between the left and right ends of the main body section 44a. The intermediate section 44b expands radially outward from the main body section 44a. The outer diameter of the outer shaft 44 is greatest at the intermediate section 44b.

A plurality of magnets 38 are held on the outer periphery of the intermediate portion 44b. The magnets 38 are positioned radially outward on the rotor 34. The left end of the magnet 38 is held by the first magnet holder 70a. The right end of the magnet 38 is held by the second magnet holder 70b. The first magnet holder 70a has a cylindrical portion 711a and a retaining portion 712a. The second magnet holder 70b has a cylindrical portion 711b and a retaining portion 712b. Each cylindrical portion 711a, 711b is attached to the outer periphery of the main body portion 44a of the outer shaft 44. Each retaining portion 712a, 712b protrudes radially outward from the end of the cylindrical portion 711a, 711b, respectively. Each retaining portion 712a, 712b is annular and perpendicular to the cylindrical portions 711a, 711b.

As shown in Figure 4, the first magnet holder 70a faces the left end of the magnet 38. The retaining portion 712a of the first magnet holder 70a holds the left end of the magnet 38 via the first retaining plate 45a. The first retaining plate 45a is positioned between the retaining portion 712a and the middle portion 44b.

The retaining portion 712a has a first upstream hole 713a. The first upstream hole 713a constitutes part of the cooling passage 41. The first upstream hole 713a extends in the axial direction of the rotating shaft 39 and passes through the retaining portion 712a. The first upstream hole 713a communicates with the second upstream hole 451a of the first holding plate 45a. The second upstream hole 451a extends in the axial direction of the rotating shaft 39 and passes through the first holding plate 45a. The second upstream hole 451a constitutes part of the cooling passage 41. The first upstream hole 713a and the second upstream hole 451a are arranged in a straight line along the axial direction of the rotating shaft 39.

The second magnet holder 70b faces the right end of the magnet 38. The retaining portion 712b of the second magnet holder 70b holds the right end of the magnet 38 via the second retaining plate 45b. The second retaining plate 45b is positioned between the retaining portion 712b and the middle portion 44b.

The retaining portion 712b has a first downstream hole 713b. The first downstream hole 713b constitutes part of the cooling passage 41. The first downstream hole 713b extends in the axial direction of the rotating shaft 39 and passes through the retaining portion 712b. The first downstream hole 713b communicates with the second downstream hole 451b of the second holding plate 45b. The second downstream hole 451b extends in the axial direction of the rotating shaft 39 and passes through the second holding plate 45b. The second downstream hole 451b constitutes part of the cooling passage 41. The first downstream hole 713b and the second downstream hole 451b are arranged in a straight line along the axial direction of the rotating shaft 39.

The cylindrical portions 711a, 711b of the first and second magnet holders 70a, 70b are held on the outer peripheral surface of the main body portion 44a. The first and second magnet holders 70a, 70b and the magnets 38 rotate together with the rotating shaft 39 as part of the rotor 34. Adjacent magnets 38 have opposite polarities facing outward. As the rotating shaft 39 rotates, the magnets 38 move along a predetermined circumference around the center of rotation of the rotating shaft 39. In the rotor 34, the boundaries between the intermediate portion 44b including the magnets 38, the first and second magnet holders 70a, 70b, the first and second retaining plates 45a, 45b, and the main body portion 44a are formed in a stepped shape.

The expanded diameter portion 40 has a first wall surface 44c facing toward the left of the rotor 34. The first wall surface 44c is positioned on the retaining portion 712a of the first magnet holder 70a, which constitutes the left end of the expanded diameter portion 40. The first wall surface 44c is an annular end surface. The expanded diameter portion 40 has a second wall surface 44d facing toward the right of the rotor 34. The second wall surface 44d is positioned on the retaining portion 712b of the second magnet holder 70b, which constitutes the right end of the expanded diameter portion 40. The second wall surface 44d is an annular end surface.

A gas flow path 72 is provided radially outward of the magnets 38 of the rotor 34. The gas flow path 72 is a clearance between the magnets 38 and the stator 36 (electromagnetic coil 110), which is positioned radially outward of the magnets 38. The gas flow path 72 is annular and extends along the rotational axis of the rotating shaft 39. The gas flow path 72 is positioned between the left and right ends of the magnets 38. Compressed air, which serves as cooling gas, flows through the gas flow path 72. The compressed air is supplied from the gas turbine engine 200, which will be described later.

The cooling passage 41 is a flow path through which compressed air, which is a cooling gas, flows. The compressed air is supplied from the gas turbine engine 200, which will be described later. The gas turbine engine 200 is a gas supply mechanism that can supply compressed air to the cooling passage 41 and the gas flow path 72. The gas turbine engine 200 is provided separately from the rotor 34.

The cooling passage 41 is disposed inside the middle portion 44b of the rotating shaft 39 and the first and second magnet holders 70a, 70b. In a cross section perpendicular to the axis of the rotating shaft 39 shown in Figures 7 and 8, the cooling passage 41 is circular. The cooling passage 41 extends in the direction of the rotational axis of the outer shaft 44. The cooling passage 41 is an internal rotor cooling passage disposed inside the rotor 34.

As shown in Figures 7 and 8, multiple cooling passages 41 are provided. The multiple cooling passages 41 are arranged radially offset from the center of the rotational axis of the rotor 34 (outer shaft 44). The multiple cooling passages 41 are equally spaced from one another circumferentially around the rotational axis of the rotor 34. The multiple cooling passages 41 are arranged on the same circle of the outer shaft 44 centered on the rotational axis of the rotating shaft 39. The number of cooling passages 41 is preferably four or more, for example. Below, we will explain the case where the rotor 34 has eight cooling passages 41.

As shown in Figure 4, the cooling passage 41 opens to the first and second wall surfaces 44c, 44d of the expanded diameter portion 40 in the rotor 34. The cooling passage 41 has first and second openings 411, 412 (see Figures 5 and 6).

As shown in FIG. 5, the first opening 411 is located at the upstream end of the cooling passage 41. That is, the first opening 411 is the inlet 413 through which compressed air is introduced. The first opening 411 is located on the first wall surface 44c of the expanded diameter section 40. The first opening 411, which is the upstream end of the cooling passage 41, opens to the outer surface of the rotor 34 (first magnet holder 70a). The first opening 411 is located in the first upstream hole portion 713a of the first magnet holder 70a.

As shown in FIG. 6, the second opening 412 is located at the downstream end of the cooling passage 41. In other words, the second opening 412 is the outlet 414 through which compressed air flows out of the cooling passage 41. The second opening 412 is located on the second wall surface 44d of the expanded diameter section 40. The second opening 412, which is the downstream end of the cooling passage 41, opens to the outer surface of the rotor 34 (second magnet holder 70b) through the second opening 412. The second opening 412 is located in the first downstream hole 713b of the second magnet holder 70b.

As shown in Figures 5 and 6, the first and second openings 411, 412 are positioned radially offset from the center of the rotational axis of the rotor 34. In the radial direction of the rotor 34, the second opening 412 may be located between the inner and outer peripheries of the magnet 38.

As shown in FIG. 4, the cooling passage 41 includes a parallel portion 455 and an inclined portion 456. The parallel portion 455 extends along the rotational axis direction of the outer shaft 44. The parallel portion 455 is arranged parallel to the rotational axis of the outer shaft 44. The parallel portion 455 is arranged in the intermediate portion 44b. The parallel portion 455 is arranged radially inward of the magnet 38. As shown in FIG. 5, the upstream end of the parallel portion 455 is the first opening 411 (inlet 413). The upstream end of the parallel portion 455 is defined by the first upstream hole 713a of the first magnet holder 70a and the second downstream hole 451a of the first holding plate 45a. The cooling passage 41 may be formed in a spiral shape from the upstream end to the downstream end of the cooling passage 41.

As shown in FIG. 4, the upstream end of the inclined portion 456 is connected to the downstream end of the parallel portion 455. As shown in FIG. 6, the inclined portion 456 is inclined radially outward relative to the parallel portion 455 from the downstream end (right end) of the parallel portion 455 toward the second opening 412 (outlet 414). The downstream end of the inclined portion 456 is the second opening 412 (outlet 414). The inclined portion 456 is formed by the first downstream hole 713b of the second magnet holder 70b and the second downstream hole 451b of the second holding plate 45b.

The position of the inclined portion 456 is not limited to being located at the downstream end of the parallel portion 455. The inclined portion 456 may be located at a portion of the cooling passage 41 in the extension direction. Multiple inclined portions 456 may be located in the cooling passage 41. The cooling passage 41 may not have a parallel portion 455, and may be configured with inclined portions 456 throughout the entire extension direction of the cooling passage 41 from the upstream end to the downstream end.

As shown in FIG. 5, the left end of the main body portion 44a of the rotating shaft 39 is rotatably supported in the first sub-housing 18 via a first bearing 74. 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 left end of the main body 44a of the outer shaft 44. The first bearing 74 is sandwiched between the first outer stopper 81 and the first inner stopper 82. The first bearing 74 is positioned and fixed by being sandwiched between the first outer stopper 81 and the first inner stopper 82. 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 39 is passed 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 39 is further exposed outside the cylindrical protrusion 76 (hollow recess 118). Hereinafter, the portion of the rotating shaft 39 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.

As shown in Figure 6, the right end of the rotating shaft 39 is rotatably supported in the second sub-housing 20 via a second bearing 84. As shown in Figure 6, the second bearing 84 is inserted between the outer shaft 44 and the second sub-housing 20, which has a generally circular plate shape.

As shown in FIG. 4, the rectifying structure 37 is housed inside the main housing 16. The rectifying structure 37 is capable of rectifying the flow of compressed air circulating within the main housing 16. The rectifying structure 37 includes an inlet-side rectifying member 851 and an outlet-side rectifying member 852.

As shown in FIG. 5, the inlet-side rectifying member 851 rectifies the compressed air flowing into the gas flow path 72 and the cooling passage 41. The inlet-side rectifying member 851 is disposed in the first space 853a. The first space 853a is a space surrounded by the first magnet holder 70a, the first bearing 74, the first sub-housing 18, and the insulating base material 112 described below. The inlet-side rectifying member 851 faces the inlet 413 (first opening 411) of the cooling passage 41. The inlet-side rectifying member 851 faces the inlet of the gas flow path 72. In other words, the inlet-side rectifying member 851 faces the upstream ends of the cooling passage 41 and the gas flow path 72. The inlet-side rectifying member 851 faces the cylindrical protrusion 76 of the first sub-housing 18. The inlet-side rectifying member 851 is disposed between the magnet 38 and the first bearing 74. The inlet-side rectifying member 851 is arranged inside the insulating substrate 112.

As shown in Figure 7, the inlet-side straightening member 851 has a cylindrical first body 854a and multiple inlet-side fins 855a.

As shown in FIG. 5, the outer peripheral surface of the first body 854a is held in contact with the insulating substrate 112, which will be described later. The left end of the first body 854a is held in contact with the end face of the cylindrical protrusion 76. The right end of the first body 854a is held in contact with the left end of the electromagnetic coil 110, which will be described later. The first body 854a is positioned radially outward from the first magnet holder 70a. The first body 854a is positioned radially outward from the gas flow path 72.

As a result, the inlet-side rectifying member 851 is held axially and radially inside the main housing 16 by the non-rotating insulating substrate 112, the cylindrical protrusion 76, and the electromagnetic coil 110.

The left end of the first body 854a has multiple communication holes 856. The communication holes 856 penetrate the first body 854a in the radial direction. The multiple communication holes 856 are spaced apart from one another along the circumferential direction of the first body 854a (see Figure 9). When the inlet-side rectifying member 851 is placed in the first space 853a, the clearance between the insulating substrate 112 and the first sub-housing 18 faces the communication holes 856 (see Figure 5). The clearance and the communication holes 856 are in communication.

The multiple inlet-side fins 855a straighten the flow of compressed air supplied to the first space 853a in the circumferential direction (rotational direction) of the rotor 34.

As shown in FIG. 7, multiple inlet side fins 855a are arranged on the inner circumferential surface of the first body 854a. Each inlet side fin 855a is positioned closer to the magnet 38 than the communication hole 856. Each inlet side fin 855a protrudes radially inward from the inner circumferential surface of the first body 854a. The multiple inlet side fins 855a are arranged to surround the center of the rotation axis of the rotor 34 (main body portion 44a). The multiple inlet side fins 855a are equally spaced apart along the circumferential direction of the first body 854a. Each inlet side fin 855a faces the expanded diameter portion 40 (first wall surface 44c) of the rotor 34 and the retaining portion 71b of the first magnet holder 70a (see FIG. 5).

A first imaginary circle D1 connecting the centers of the first openings 411 of the cooling passage 41 faces the multiple inlet fins 855a in the axial direction. The left end of the gas flow path 72 faces the multiple inlet fins 855a in the axial direction (see Figure 5).

As shown in FIG. 9 , each inlet-side fin 855a has a direction change portion 857a, a first fin end 858a, and a second fin end 859a. The direction change portion 857a curves from one axial end of the first body 854a to the other axial end, changing its direction from the axial direction to the circumferential direction of the first body 854a. The first fin end 858a is located at one end of the direction change portion 857a in the axial direction of the first body 854a. The first fin end 858a is the upstream end of the inlet-side fin 855a. The first fin end 858a faces the axial direction of the first body 854a. The second fin end 859a is located at the other end of the direction change portion 857a in the axial direction of the first body 854a. The second fin end 859a is the downstream end of the inlet-side fin 855a. The second fin end 859a extends circumferentially around the first body 854a toward the first fin end 858a.

When the inlet-side straightening member 851 shown in FIG. 5 is positioned in the first space 853a, the first fin end 858a faces the first bearing 74 and the cylindrical protrusion 76. The second fin end 859a faces the first wall surface 44c of the expanded diameter section 40. The second fin end 859a faces the gas flow path 72 and the first opening 411 (inlet 413) of the cooling passage 41.

The direction changer 857a curves from the first fin end 858a to the second fin end 859a in the rotation direction R of the rotating shaft 39. Below, we will explain the case where the rotation direction R of the rotor 34 is counterclockwise when viewed from the left end of the rotating shaft 39 shown in Figure 7. When compressed air is supplied to the inlet-side straightening member 851, the direction changer 857a of the multiple inlet-side fins 855a changes the direction of the compressed air toward the downstream side (right) in the rotation direction R of the rotor 34.

As shown in FIG. 6, the outlet-side rectifying member 852 rectifies the compressed air flowing out of the gas flow path 72 and the cooling passage 41. The outlet-side rectifying member 852 is disposed in the second space 853b. The second space 853b is a space surrounded by the second magnet holder 70b, the second sub-housing 20, and the insulating base material 112 described below. The outlet-side rectifying member 852 faces the outlet 414 (second opening 412) of the cooling passage 41 of the expanded diameter portion 40. The outlet-side rectifying member 852 faces the outlet of the gas flow path 72. In other words, the outlet-side rectifying member 852 faces the downstream ends of the cooling passage 41 and the gas flow path 72. The outlet-side rectifying member 852 faces the cylindrical portion 87 of the second sub-housing 20. The outlet-side rectifying member 852 is disposed between the magnet 38 and the second bearing 84. The outlet-side rectifying member 852 is arranged inside the insulating substrate 112.

As shown in FIG. 8, the outlet-side straightening member 852 has a cylindrical second body 854b and multiple outlet-side fins 855b. As shown in FIG. 6, the outer peripheral surface of the second body 854b is held in contact with the insulating substrate 112, which will be described later. The right end of the second body 854b is held in contact with the end face of the cylindrical portion 87 of the second sub-housing 20. The left end of the second body 854b is held in contact with the right end of the electromagnetic coil 110, which will be described later. The second body 854b is positioned radially outward from the second magnet holder 70b. The second body 854b is positioned radially outward from the gas flow path 72.

As a result, inside the main housing 16, the outlet-side straightening member 852 is held axially and radially by the non-rotating insulating substrate 112, cylindrical portion 87, and electromagnetic coil 110. The multiple outlet-side fins 855b straighten the flow of compressed air flowing out of the cooling passage 41 and gas flow path 72 toward the axial direction of the rotor 34.

As shown in FIG. 8, multiple outlet side fins 855b are arranged on the inner circumferential surface of the second body 854b. Each outlet side fin 855b protrudes radially inward from the inner circumferential surface of the second body 854b. The multiple outlet side fins 855b are arranged to surround the center of the rotational axis of the rotor 34. The multiple outlet side fins 855b are equally spaced apart along the circumferential direction of the second body 854b. Each outlet side fin 855b faces the expanded diameter portion 40 (second wall surface 44d) of the rotor 34 and the retaining portion 71b of the second magnet holder 70b.

The second imaginary circle D2 connecting the centers of the second openings 412 of the cooling passage 41 shown in Figure 8 faces the multiple outlet-side fins 855b in the axial direction. The right end of the gas flow path 72 faces the multiple outlet-side fins 855b in the axial direction (see Figure 6).

As shown in FIG. 10, each outlet-side fin 855b has a direction change portion 857b, a first fin end 858b, and a second fin end 859b. The direction change portion 857b curves from one axial end of the second body 854b to the other axial end, changing its direction from the axial direction to the circumferential direction of the second body 854b. The first fin end 858b is located at one end of the direction change portion 857b in the axial direction of the second body 854b. The first fin end 858b is the upstream end of the outlet-side fin 855b. The first fin end 858b faces the axial direction of the second body 854b. The second fin end 859b is located at the other end of the direction change portion 857b in the axial direction of the second body 854b. The second fin end 859b is the downstream end of the outlet-side fin 855b. The second fin end 859b extends circumferentially around the second body 854b toward the first fin end 858b.

When the outlet-side straightening member 852 shown in FIG. 6 is positioned in the second space 853b, the second fin end 859b faces the second magnet holder 70b and the second wall surface 44d of the expanded diameter portion 40. The second fin end 859b faces the right end of the gas flow path 72 and the second opening 412 (outlet 414) of the cooling passage 41. The first fin end 858b faces the cylindrical portion 87 of the second sub-housing 20.

The direction changer 857b curves from the second fin end 859b to the first fin end 858a in the rotational direction of the rotary shaft 39. When compressed air flows out of the cooling passage 41 and the gas flow path 72 into the second space 853b, the direction changer 857b of the multiple outlet-side fins 855b causes the compressed air swirling in the rotational direction of the rotor 34 to change direction downstream toward the axial direction of the rotor 34.

Note that the inlet-side straightening member 851 and the outlet-side straightening member 852 are not limited to being disposed at the first and second openings 411, 412 of the cooling passage 41, respectively. Only one of the inlet-side straightening member 851 and the outlet-side straightening member 852 may be disposed facing the cooling passage 41.

As shown in FIG. 3, the second sub-housing 20 is connected to the main housing 16 via bolts (not shown). The center of the second sub-housing 20 has a cylindrical portion 87. As shown in FIG. 6, a second insertion hole 86 is formed in the cylindrical portion 87. 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 guide member 96 is connected to the end face of the second sub-housing 20 facing the gas turbine engine 200. The guide 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 guide 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 port 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 port 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 rotation shaft 39. As a result, 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. These coils 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 inlet-side rectifying member 851 is held radially by the inner circumferential surface of the insulating substrate 112 located at the left end of the stator 36. The outlet-side rectifying member 852 is held radially by the inner circumferential surface of the insulating substrate 112 located at the right end of the stator 36.

The stator 36 is housed in the housing chamber 22. The second sub-housing 20 serves as a stator holder. Specifically, an annular recess 114 is formed in the second sub-housing 20. The insulating substrate 112 included in the stator 36 engages with the 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.

As shown in FIG. 5, a first space 853a is formed between the outer wall of the cylindrical protrusion 76 and the insulating substrate 112. A gas flow path 72 is provided between the outer wall of the magnet 38 and the inner wall of the electromagnetic coil 110. Compressed air flows through the first space 853a and the gas flow path 72. In other words, the first space 853a and the gas flow path 72 are part of the compressed air flow path.

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).

A small cylindrical portion 122 is provided to the left of the flange-shaped stopper 120 of the resolver holder 30. 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 accommodates 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. 11.

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.

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

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 11, 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 pipe section 1601, the second hollow pipe section 1602, and the third hollow pipe section 1603 are relay communication passages through which compressed air flows. In other words, in this embodiment, three relay communication passages are formed in the rotating electrical machine housing 14.

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.

Next, we will explain the compressed air flow path provided in the rotating electrical machine system 10.

As shown in FIG. 12, an annular collecting passage 162 consisting of an annular recess is formed on the end face of the second sub-housing 20 facing the gas turbine engine 200. As described below, a portion 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 and compressed air that enters the second downstream communication holes 1701-1703.

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

The first hollow tube 1601 to the third hollow tube 1603 extend along the axial direction of the main housing 16. The hollow interior of the first hollow tube 1601 is connected to the internal space of the second casing 28. The hollow interiors of the second hollow tube 1602 and the third hollow tube 1603 are connected to the internal space of the first casing 26. As will be described later, diverted air that has flowed through the hollow interior of the first hollow tube 1601 flows into the internal space of the second casing 28. The diverted air that has flowed through the hollow interiors of the second hollow tube 1602 and the third hollow tube 1603 flows into the internal space of the first casing 26. As can be seen from this, the first casing 26 and the second casing 28 are disposed downstream of the portions of the first hollow tube 1601 to the third hollow tube 1603 that are located outside the cooling jacket 24.

As described above, the internal space of the first casing 26 and the internal space of the second casing 28 are connected via an interconnecting hole. The internal space of the first casing 26 is also 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 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.

As shown in FIG. 5, the compressed air that flows into the accommodating chamber 22 is then divided into compressed air flowing toward the first insertion hole 78 and compressed air flowing toward the second insertion hole 86. Specifically, the compressed air flows through the first space 853a between the first sub-housing 18 and the rotor 34 and is introduced into the interior of the inlet-side straightening member 851 through multiple communication holes 856. In this way, the first space 853a is the first branch path L (see FIG. 3). Some of the compressed air flows from the left end of the inlet-side straightening member 851 toward the first insertion hole 78. The compressed air flowing toward the first insertion hole 78 forms an air curtain that seals off the lubricating oil supplied to the first bearing 74.

Meanwhile, the remaining portion of the compressed air is rectified by passing through the multiple inlet-side fins 855a of the inlet-side rectifying member 851, and then flows through the gas flow path 72 and cooling passage 41 toward the second insertion hole 86. The gas flow path 72 is a second branch path M that branches off from the first branch path L.

Specifically, a portion of the remaining compressed air passes through the interior of the first body 854a from the left end of the inlet-side straightening member 851. As it flows from the left end to the right end of the first body 854a, the direction changers 857a of the multiple inlet-side fins 855a change the compressed air flow from an axial direction to a circumferential direction. At this time, when the compressed air flows out downstream of the inlet-side straightening member 851, it becomes a swirling flow. The swirling direction of the compressed air is the rotational direction R of the rotor 34 (counterclockwise in Figure 7). The swirling compressed air is introduced into the cooling passage 41 through the multiple first openings 411 (inlets 413). At the same time, the swirling compressed air is introduced into the annular gas flow passage 72 from the left end of the gas flow passage 72.

After flowing along the cooling passage 41 and the gas flow path 72, the compressed air flows from the cooling passage 41 through the second opening 412 (outlet 414) into the second space 853b. The compressed air flows out from the right end of the gas flow path 72 into the second space 853b. In the second space 853b, the compressed air passes between the outlet-side fins 855b of the outlet-side straightening member 852. The direction change portions 857b of the outlet-side fins 855b change the flow of compressed air from a swirling state to an axial flow. The axially flowing compressed air reaches the third sub-branch passage 941 (the second distal end 861 of the second insertion hole 86) from the cooling passage 41 and the gas flow path 72, forming an air curtain that seals off the lubricating oil supplied to the second bearing 84. In this way, the compressed air that flows into the housing chamber 22 functions as an air curtain.

As shown in FIG. 6, three inlets 104 are formed in the bottom portion 98 of the guide member 96. FIG. 6 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 guide 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 diverted air decreases as the compressed air flows through the relay chamber 106.

The outlet 414 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 172 (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 172.

The rotating electrical machine system 10 is cooled by circulating lubricating oil through a lubricating oil flow path (not shown) to the first and second bearings 74, 84. The lubricating oil used to lubricate and cool the first and second bearings 74, 84 is discharged to the outside of the main housing 16. The compressed air and lubricating oil supplied to the interior of the rotating electrical machine housing 14 are recovered in a gas-liquid separator (not shown). The gas-liquid mixture is separated into lubricating oil and air. The lubricating oil is discharged from the gas-liquid separator (not shown) by a circulation pump (not shown) and resupplied to the lubricating oil flow path. Meanwhile, the compressed air is released into the atmosphere through an exhaust port (not shown).

Next, the gas turbine engine 200 will be described. As shown in FIG. 13, 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 main body.

As shown in Figures 1 and 12, 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 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 12 and 13, bleed passages 216 are individually formed inside the six leg portions 210. The inlets 413 of the bleed passages 216 are individually formed at the connection points of the leg portions 210 with the cylindrical cover portion 212. The outlets 414 of the bleed passages 216 are individually formed on the end surface of the first annular portion 206 facing the second sub-housing 20. All of the outlets 414 of the bleed passages 216 are located on the circumference of an imaginary circle. Therefore, all of the outlets 414 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 13, 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.

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 guide member 96. The small-diameter left end of the shroud case 220 faces the guide 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 guide member 96 extends into the interior of the left end of the shroud case 220. An annular blocking flange 232 is provided on the curved side peripheral wall of the shroud case 220. The outer edge of the blocking flange 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 inlet 413 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 39 and output shaft 204. That is, as shown in FIG. 6, the compressor wheel 222 has a small-diameter cylindrical portion 242 at its left end. The small-diameter cylindrical portion 242 enters the insertion hole 108 formed in the guide member 96. A first external spline 239 is formed on the inner wall of the small-diameter cylindrical portion 242. The 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 39) 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 through hole 240 at the left end. 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 provided on 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 39. A male thread 252 is formed on the left end of the output shaft 204. The male thread 252 is threaded into a female thread 64 formed on the inner wall of the connecting hole 62. This threading connects the rotating shaft 39 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. 13, 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. 14, 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 13). 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. 13 , 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 path 274 is formed between the combustor 228 and the outer housing 2022. The combustion air flow path 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 relay holes 276 that connect the combustion air flow path 274 to 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 path 274, and the relay holes 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. Below, we will explain the case where the rotor 34 of the rotating electrical machine system 10 rotates counterclockwise (rotation direction R) when viewed from the left end of the rotor 34 shown in Figure 7.

First, DC current is supplied from the battery 146. The conversion circuit 152 of the current converter 150 shown in Figures 2 and 11 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 the 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 magnet 38 of the rotor 34. As a result, the rotating shaft 39 begins to rotate in the rotation direction R. Alternatively, the rotating shaft 39 may be rotated by a known starter (not shown).

As shown in FIG. 6 , 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 39 is quickly transmitted to the output shaft 204 via the compressor wheel 222.

In other words, when the rotating shaft 39 begins to rotate in the rotational direction R, the output shaft 204 also begins to rotate integrally with the rotating shaft 39. 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 39 can be sufficiently transmitted to the output shaft 204.

In addition, the right end of the rotating shaft 39 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 39 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. 14, 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. 13, air is drawn into the shroud case 220 through the intake space 214 between the legs 210 of the inner housing 2021. Here, the guide member 96 is located at the diametric center of the inner housing 2021. As described above, the guide member 96 has a mountain-like shape that narrows in diameter as it approaches the shroud case 220. Furthermore, the surface of the narrowing diameter portion 100 is smooth. Therefore, the guide member 96 straightens the drawn air toward the shroud case 220. Because the right end of the guide member 96 enters the left end opening of the shroud case 220, the air is efficiently guided into the shroud case 220. In this way, by giving the guide 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, a portion of the compressed air is diverted from the air bleed port 234 and flows into the chamber 236. The chamber 236 is annular and has a volume larger than the volume of the air bleed port 234. As a result, the diverted 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 diverted air may differ. However, in this embodiment, the compressed air that passes through bleed port 234 flows into a single annular chamber 236. This makes the pressure of the diverted air within chamber 236 uniform. In other words, the pressure of the diverted air is made uniform. In this way, chamber 236 is a pressure adjustment chamber that adjusts the pressure of the diverted air to a substantially constant level.

As mentioned above, the diverted 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 diverted air diffuses as it flows into the chamber 236. This reduces the pressure of the diverted 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 pressure of the diverted air 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 413 of the bleed passages 216, which are individually formed in each of the six legs 210, open. Therefore, the diverted air in the chamber 236 then flows individually through the six bleed passages 216, thereby proceeding toward the second sub-housing 20. As described above, the pressure of the diverted air is approximately constant at this point.

As shown in Figure 12, the outlets 414 of the six bleed passages 216 all overlap the collecting passage 162. Therefore, the diverted 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 diverted air is further equalized.

The diverted 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 diverted air is then discharged from the first downstream communication holes 1681-1683. The remainder of the diverted air is discharged from the second downstream communication holes 1701-1703. Hereinafter, the diverted air discharged from the first downstream communication holes 1681-1683 will be referred to as "first diverted air." The diverted 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 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 section 1601 to the third hollow pipe section 1603 are located on the outer periphery of the cooling jacket 24. A cooling medium is already flowing through the cooling jacket 24. Therefore, as the first diverted air flows along the first hollow pipe section 1601 to the third hollow pipe section 1603, the heat of the first diverted air is sufficiently conducted to the cooling medium. This results in the first diverted air having a relatively low temperature. In other words, in this embodiment, the first diverted air can be lowered in temperature by the cooling jacket 24, which cools the rotating electric machine 12, the current converter 150, etc. Therefore, there is no need to provide separate cooling equipment for cooling the curtain air in the gas turbine engine 200 or the rotating electric machine system 10. This eliminates the need to provide separate cooling equipment for cooling the curtain air in the gas turbine engine 200 or the rotating electric machine system 10. This allows the combined power system 400 to be more compact.

The first diverted air that has flowed through the first hollow tube section 1601 flows into the internal space of the second casing 28, as shown in Figure 2. This forms an air curtain inside the second casing 28. The excess first diverted air flows into the hollow interior (internal space) of the first casing 26 via the interconnecting holes. Meanwhile, the first diverted air that has flowed through each of the second hollow tube section 1602 and the third hollow tube section 1603 flows into the internal space of the first casing 26. Therefore, an air curtain is formed inside the first casing 26 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 Figure 3, the excess first diverted air in the first casing 26 flows into the storage chamber 22 formed in the main housing 16. As can be seen from this, the internal spaces of the first casing 26 and the second casing 28 are upstream in the flow path of the first diverted air. The storage chamber 22 of the main housing 16 is downstream in the flow path of the first diverted air.

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 accommodating 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.

The first diverted air flow is then introduced into the inlet-side rectifying member 851 arranged in the first branch channel L (first space 853a) through the communication hole 856. A portion of the first diverted air flow flows from the left end of the first body 854a of the inlet-side rectifying member 851 toward the first insertion hole 78. A portion of the first diverted air flow that has flowed toward the first insertion hole 78 reaches the first proximal end 782 of the first insertion hole 78. At this first proximal end 782, a portion of the first diverted air becomes an air curtain for the first bearing 74. A portion of the first diverted air flow is not rectified by the inlet-side rectifying member 851.

The remainder of the first diverted air flows through the interior of the first body 854a from the left end to the right end of the inlet-side straightening member 851. The first diverted air is introduced axially into the inlet-side straightening member 851. The first diverted air flows from the first fin end 858a of the multiple inlet-side fins 855a along the direction change portion 857a toward the second fin end 859a. As a result, the first diverted air becomes a swirling flow that gradually swirls counterclockwise when viewed from the left end of the rotating shaft 39 shown in Figures 7 and 9. The first diverted air is discharged downstream from the second fin end 859a of the inlet-side fin 855a while swirling. In other words, as the first diverted air passes through the inlet-side straightening member 851, the first diverted air swirls in the same direction as the rotation direction R of the rotor 34. The remainder of the swirling first diverted air is supplied to the gas flow path 72, which is the second branch path M, and is also supplied to the cooling passages 41 of the rotating shaft 39. The remainder of the first diverted air flows along the annular gas flow path 72 toward the right end of the rotating shaft 39. The remainder of the first diverted air is introduced into each cooling passage 41 through the first openings 411 (inlets 413) and flows along the cooling passages 41 toward the right end of the rotating shaft 39. Because the first diverted air swirls in the same direction as the rotation of the rotor 34, the first diverted air flows smoothly into each cooling passage 41 and the gas flow path 72.

The remainder of the first diverted air flows axially toward the right end of the gas flow path 72. The remainder of the first diverted air flows axially from the first openings 411 (inlets 413) of the multiple cooling passages 41 along the parallel portion 455. At this time, centrifugal force generated by the rotation of the rotor 34 generates negative pressure from the inclined portion 456 toward the second openings 412 (outlet 414). This negative pressure promotes the flow of compressed air from the parallel portion 455 toward the inclined portion 456, allowing it to flow smoothly toward the outlet 414.

The first diverted air flows out from the right end of the gas flow path 72 and the second opening 412 of the cooling passage 41 into the interior of the outlet-side straightening member 852 in the second space 853b. As a result, the rotor 34 and magnets 38 are effectively cooled by the first diverted air flowing through the multiple cooling passages 41. The rotor 34 and stator 36, including the magnets 38, are effectively cooled by the first diverted air flowing through the gas flow path 72.

In the second space 853b, the remainder of the first diverted air flows from the second fin end 859b of the outlet fin 855b of the outlet rectifying member 852 along the direction change portion 857b toward the first fin end 858b. The remainder of the first diverted air is rectified by the multiple outlet fins 855b, and the swirling force of the compressed air flowing in the same direction as the rotational direction R of the rotor 34 gradually decreases. The remainder of the first diverted air changes to a linear flow along the axial direction and flows downstream. After being rectified by the outlet rectifying member 852, the first diverted air passes through the third sub-branch channel 941 and reaches the second distal end 861 of the second insertion hole 86. At this second distal end 861, the remainder of the first diverted air becomes an air curtain for the second bearing 84.

In this way, the first diverted air flows 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 first diverted air then reaches the exhaust passage 172 of the main housing 16 along with the second diverted air described below.

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 guide member 96. Therefore, the second diverted air flows into the relay chamber 106 (the hollow interior of the guide member 96) through the inlets 104.

As described above, the outlet 414 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 172. 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 172. The first diverted air and second diverted air that reach the exhaust path 172 are collected in a gas-liquid separator (not shown).

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 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.

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. 13 , 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 path 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 and fine holes formed in the combustor 228, 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 39 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 serves as a sealing member that seals the gap between the two wheels 222, 224. Furthermore, as shown in FIG. 14 , multiple labyrinth-forming protrusions 264 are formed on the outer peripheral wall of the ring member 256. The 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 described above, the pressure of the compressed air is higher than the pressure of the combustion gas. This prevents the combustion gas from passing through the labyrinth-forming protrusions 264 and flowing into the compressor wheel 222. For these reasons, burned fuel is prevented from entering the through-hole 240, for example, between the two wheels 222, 224.

In Figure 13, when the output shaft 204 begins to rotate at high speed, the supply of current from the battery 146 (see Figure 11) 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 39 rotates at high speed integrally with the turbine wheel 224 and output shaft 204. Even at this time, for the same reason as above, sufficient rotational torque is transmitted from the output shaft 204 to the rotating shaft 39.

In Figure 3, it is preferable that the rotation direction of the output shaft 204 and the rotating shaft 39 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 39 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 39 holds the magnet 38, an AC current is generated in the electromagnetic coil 110 surrounding the magnet 38. The AC current is sent to the current converter 150 shown in Figures 2 and 11 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 to 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 11) 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. A portion of the first diverted air flowing through the first space 853a contacts the left end of the stator 36. The remainder of the first diverted air, which passes through the gas flow path 72 of the housing chamber 22 and heads toward the second space 853b (second insertion hole 86), contacts the inner wall of the stator 36 and the outer periphery of the rotor 34. The remainder of the first diverted air, which passes through the multiple cooling passages 41 and heads toward the second space 853b, contacts the interior of the rotor 34. Therefore, the stator 36 and rotor 34 (magnets 38) are 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.

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, magnet 38, 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, magnet 38, 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 from each other. As a result, 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 39 rotates, the rotation angle (rotation parameter) of the rotating shaft 39 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 39. 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 39 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 39, 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 39 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.

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 opposite direction to that shown in Figure 13. 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 multi-stage compressor wheel and multi-stage turbine wheel that combines centrifugal and axial flow types 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 39 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.

The above-described embodiment illustrates an example in which a portion of the compressed air generated by the gas turbine engine 200 is supplied to the rotating electrical machine housing 14. Alternatively, as shown in Figure 15, an externally installed compression pump 320 or the like can be used as the gas supply source.

In this case, for example, a flow hole 322 is formed in the first casing 26. Compressed air sent from the compression pump 320 flows into this flow hole 322. In addition, a communication hole 324 that connects to the upstream communication hole 164 is formed in the second sub-housing 20. The communication hole 324 is closed with a plug 326. In this state, the compression pump 320 compresses the atmosphere, etc., to obtain compressed air. This compressed air is supplied to the first hollow tube portion 1601 to the third hollow tube portion 1603.

In this case, the entire amount of compressed air can be used as combustion air.

As described above, in this embodiment of the present invention, a cooling passage 41 through which compressed air, a cooling gas, flows is provided inside the rotor 34 of the rotating electrical machine system 10, and the outlet 414 of the cooling passage 41 is positioned radially outward of the inlet 413 of the cooling passage 41. This allows negative pressure to be generated within the cooling passage 41 toward the outlet 414 by centrifugal force acting when the rotor 34 rotates. This promotes the flow of compressed air from the inlet 413 toward the outlet 414 of the cooling passage 41. As a result, with the simple configuration of forming the cooling passage 41 in the rotor 34, gas can be smoothly circulated through the cooling passage 41.

By locating the cooling passage 41 in the middle section 44b of the rotor 34, which holds the magnet 38, the area around the magnet 38, which tends to generate heat when the rotor 34 rotates, can be effectively cooled by compressed air flowing through the cooling passage 41.

By arranging multiple cooling passages 41 at equal intervals around the rotor 34, the rotor 34 can be effectively cooled by compressed air flowing through the multiple cooling passages 41.

The inlet 413 of the cooling passage 41 opens on the first wall surface 44c facing left of the rotor 34, and the outlet 414 opens on the second wall surface 44d facing right of the rotor 34. As a result, the inlet 413 and outlet 414 open on the first wall surface 44c and the second wall surface 44d, respectively, which are not on the outer peripheral surface of the rotor 34, thereby preventing a decrease in the rigidity of the rotor 34.

The first wall surface 44c of the rotor 34 is the annular end surface at the left end of the expanded diameter section 40, and the second wall surface 44d is the annular end surface at the right end of the expanded diameter section 40. Therefore, the first wall surface 44c, which is an annular end surface, can reinforce the area around the inlet 413, and the second wall surface 44d, which is an annular end surface, can reinforce the area around the outlet 414.

In the axial direction of the rotor 34, at least one of the inlet 413 and outlet 414 of the cooling passage 41 is arranged to face the inlet-side fins 855a and outlet-side fins 855b of the flow straightening structure 37. This makes it possible to straighten at least one of the compressed air flows entering the cooling passage 41 from the inlet 413 and the compressed air flows leaving the cooling passage 41 through the outlet 414, thereby enhancing the cooling effect of the rotor 34.

The above embodiments can be summarized as follows:

The above embodiment includes a rotor (34) having magnets (38);
a stator (36) surrounding the rotor;
a housing (14) that accommodates the rotor and the stator;
Equipped with
A rotating electrical machine system (10) including a cooling passage (41) through which a cooling gas flows inside the rotor,
The cooling passage has an inlet (413) through which the gas is introduced and an outlet (414) through which the gas is discharged, the inlet and the outlet being arranged at positions spaced apart from each other in the axial direction;
The outlet is disposed radially outward from the axial center relative to the inlet.

The rotor includes a main body portion (44a) supported by the housing;
an expanded diameter portion (40) that expands radially outward from the main body portion and holds the magnet;
Equipped with
The cooling passage is disposed in the expanded diameter portion.

The cooling passages are arranged radially offset from the axial center of the rotor and are arranged in multiple numbers on the rotor so as to be equally spaced apart circumferentially.

The rotor has a first wall surface (44c) facing one side in the axial direction of the rotor;
a second wall surface (44d) facing the other side in the axial direction;
and
The inlet opens into the first wall surface, and the outlet opens into the second wall surface.

The first wall surface is one annular end surface of the enlarged diameter portion in the axial direction, and the second wall surface is the other annular end surface of the enlarged diameter portion in the axial direction.

a rectifying structure (37) having a plurality of fins (855a, 855b) capable of rectifying the flow of the gas;
The multiple fins are arranged at intervals around the circumferential direction of the rotor so as to surround the axial center of the rotor, and the multiple fins face at least one of the inlet and the outlet in the axial direction of the rotor.

The cooling passage has a parallel portion (455) connected to the inlet and extending parallel to the axial direction of the rotor;
and a sloped portion (456) that slopes radially outward from the downstream end of the parallel portion toward the outlet.

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.

REFERENCE SIGNS LIST 10... Rotating electric machine system 12... Rotating electric machine 14... Rotating electric machine housing 34... Rotor 36... Stator 38... Magnet 41... Cooling passage 40... Expanded diameter portion 413... Inlet 414... Outlet 455... Parallel portion 456... Inclined portion

Claims (8)

a rotor having a magnet;
a stator surrounding the rotor;
a housing that accommodates the rotor and the stator;
Equipped with
a rotating electrical machine system including a cooling passage through which a cooling gas flows inside the rotor,
the cooling passage has an inlet through which the gas is introduced and an outlet through which the gas is discharged, the inlet and the outlet being disposed at positions spaced apart from each other in the axial direction;
the outlet is disposed radially outward from the axial center relative to the inlet ;
a rectifying structure having a plurality of fins capable of rectifying the flow of the gas;
the plurality of fins are arranged at intervals in the circumferential direction of the rotor so as to surround the axial center of the rotor,
The plurality of fins are
a plurality of inlet-side fins facing the inlet in the axial direction of the rotor;
a plurality of outlet-side fins facing the outlet in the axial direction;
and
the cooling passage further includes a first plate and a second plate through which the cooling passage passes, the first plate being arranged to overlap a first magnet holder that holds one end of the magnet in the axial direction, and the second plate being arranged to overlap a second magnet holder that holds the other end of the magnet in the axial direction;
the first magnet holder has a first cylindrical portion facing radial ends of the plurality of inlet-side fins, and a disk-shaped first pressing portion protruding radially outward from the first cylindrical portion and facing the axial ends of the inlet-side fins,
the second magnet holder includes a second cylindrical portion facing radial ends of the plurality of outlet-side fins, and a disk-shaped second pressing portion protruding radially outward from the second cylindrical portion and facing the axial ends of the outlet-side fins;
the axial end portion and the radial end portion of the inlet side fin are surrounded by the first pressing portion and the first cylindrical portion,
The axial end and the radial end of the outlet-side fin are surrounded by the second pressing portion and the second cylindrical portion . 2. The rotating electrical machine system according to claim 1,
The rotor includes a main body supported by the housing;
an expanded diameter portion that expands radially outward from the main body portion and holds the magnet;
Equipped with
The cooling passage is disposed in the expanded diameter portion. 3. The rotating electrical machine system according to claim 1,
a plurality of the cooling passages are arranged on the rotor so as to be radially offset from the axial center of the rotor and spaced at equal intervals in the circumferential direction of the rotor; 3. The rotating electrical machine system according to claim 2,
The rotor includes a first wall surface facing one side in the axial direction of the rotor;
a second wall surface facing the other side in the axial direction;
and
The inlet opens into the first wall surface, and the outlet opens into the second wall surface. 5. The rotating electrical machine system according to claim 4,
a rotating electric machine system, wherein the first wall surface is one annular end surface of the enlarged diameter portion in the axial direction, and the second wall surface is the other annular end surface of the enlarged diameter portion in the axial direction; 2. The rotating electrical machine system according to claim 1,
The cooling passage includes a parallel portion connected to the inlet and extending parallel to the axial direction of the rotor;
a sloped portion that slopes radially outward from the downstream end of the parallel portion toward the outlet. 3. The rotating electrical machine system according to claim 1,
The cooling passage is
an internal rotor cooling passage disposed within the rotor;
a gas flow path disposed between the rotor and the stator through which the gas flows;
and
a first space provided upstream of the gas flow path and the rotor internal cooling passage, the first space communicating with the gas flow path and the rotor internal cooling passage;
a second space provided downstream of the gas flow path and the rotor internal cooling passage, the second space communicating with the gas flow path and the rotor internal cooling passage;
and
the gas supplied to the first space is divided into the gas flow path and the rotor internal cooling passage,
the gas flowing through the gas flow path and the gas flowing through the rotor internal cooling passage join together in the second space;
a rotating electric machine system, wherein each of the plurality of fins is disposed in the first space and the second space; 2. The rotating electrical machine system according to claim 1,
The cooling passage is
an inlet flow passage connected to the inlet and extending along the axial direction;
an inclined portion provided downstream of the inlet flow path and inclined radially outward toward the outlet;
A rotating electric machine system comprising: