JP7531456B2 - Pumping equipment - Google Patents

Description

The present disclosure relates to a pump device for pumping liquid.

There is known a turbomachine that uses a turbine to drive a liquid pump such as a fuel pump (see, for example, Patent Document 1). Patent Document 1 discloses a turbomachine in which a fuel pump is connected to one side of a drive shaft and a turbine is connected to the other side of the drive shaft, with a generator attached to the center of the drive shaft.

JP 2007-205353 A

As described in Patent Document 1, a turbomachine in which a fuel pump is connected to one side of a drive shaft and a turbine is connected to the other side of the drive shaft has a large axial length, which may lead to an increase in size and weight. If such a turbomachine is configured to have a device for recovering power (rotational force of the drive shaft) such as a generator or a device for applying power (rotational force of the drive shaft) such as an electric motor attached to the drive shaft, the axial length of the drive shaft will be large and the number of bearings and seals attached to the drive shaft will be large.

In addition, the high temperature of the working fluid in the turbine may cause the bearings and seals attached to the drive shaft to deteriorate or lose performance due to heat, so it is necessary to provide a cooling structure to cool the bearings and seals attached to the drive shaft. This increases the size, weight, and number of parts of the turbomachinery, which may reduce the reliability of the turbomachinery.

In view of the above circumstances, an object of at least one embodiment of the present disclosure is to provide a pump device that can reduce the axial length of the rotating shaft of the pump device and suppress a decrease in the reliability of the pump device.

In order to achieve the above object, a pump device according to at least one embodiment of the present disclosure comprises:
A pump device including a rotating body and a casing that houses the rotating body,
The rotating body is
A hub portion,
a plurality of centrifugal pump vanes provided on an outer peripheral surface of the hub portion at intervals in a circumferential direction of the rotor;
an annular shroud wall portion formed along the circumferential direction so as to connect to tips of the centrifugal pump vanes;
an annular disk portion formed along the circumferential direction so as to protrude from an outer circumferential surface of the shroud wall portion to an outer side in a radial direction of the rotor;
a plurality of axial flow turbine blades provided at intervals in the circumferential direction on an outer peripheral surface of the disk portion;
Equipped with
a liquid flow passage is formed on an inner peripheral side of the shroud wall portion, through which liquid flowing from one side to the other side in the axial direction of the rotor flows into the centrifugal pump impeller;
a gas flow passage through which gas flowing from the other side to the one side passes through the axial flow turbine blades is formed on the outer circumferential side of the disk portion,
the shroud wall portion includes a second outer peripheral surface that is located on the second side in the axial direction relative to the disk portion and faces an inner peripheral surface of the casing with a first gap therebetween,
the disk portion includes a one-side end surface that is an end surface on the one side in the axial direction and a other-side end surface that is an end surface on the other side in the axial direction,
a first seal portion that seals a second-side gap, which is a gap in the axial direction between the second-side end face of the disk portion and the casing, is provided radially outward of the first gap;
At least one through hole penetrating in the axial direction is formed in the disk portion, radially inward from the first seal portion.

At least one embodiment of the present disclosure provides a pump device that can reduce the axial length of the rotating shaft of the pump device and suppress deterioration of the reliability of the pump device.

1 is a schematic cross-sectional view showing a cross section along a rotation axis LA in a pump system 10 including a pump device 1 according to an embodiment of the present disclosure. FIG. 2 is a diagram showing an example of the configuration of the pump device 1 shown in FIG. 1, and is a schematic cross-sectional view showing an enlarged cross section taken along a rotation axis LA of the pump device 1. 3 is a diagram for explaining pressures at various parts of the pump device 1 shown in FIG. 2, and is a schematic cross-sectional view showing an enlarged cross section taken along the rotation axis LA of the pump device 1. FIG. FIG. 4 is a schematic cross-sectional view showing a modified example of the pump device 1 shown in FIGS. 2 and 3, and is an enlarged cross-sectional view taken along the rotation axis LA of the pump device 1. FIG. 4 is a schematic cross-sectional view showing a modified example of the pump device 1 shown in FIGS. 2 and 3, and is an enlarged cross-sectional view taken along the rotation axis LA of the pump device 1. FIG. 5 is a schematic cross-sectional view showing a modified example of the pump device 1 shown in FIG. 4, and is an enlarged cross-sectional view taken along the rotation axis LA of the pump device 1. FIG. 4 is a schematic cross-sectional view showing a modified example of the pump device 1 shown in FIGS. 2 and 3, and is an enlarged cross-sectional view taken along the rotation axis LA of the pump device 1. FIG. 4 is a schematic cross-sectional view showing a modified example of the pump device 1 shown in FIGS. 2 and 3, and is an enlarged cross-sectional view taken along the rotation axis LA of the pump device 1. FIG. 5 is a schematic cross-sectional view showing a modified example of the pump device 1 shown in FIG. 4, and is an enlarged cross-sectional view taken along the rotation axis LA of the pump device 1. FIG. 4 is a schematic cross-sectional view showing a modified example of the pump device 1 shown in FIGS. 2 and 3, and is an enlarged cross-sectional view taken along the rotation axis LA of the pump device 1. FIG. 5 is a schematic cross-sectional view showing a modified example of the pump device 1 shown in FIG. 4, and is an enlarged cross-sectional view taken along the rotation axis LA of the pump device 1. FIG. 4 is a schematic cross-sectional view showing a modified example of the pump device 1 shown in FIGS. 2 and 3, and is an enlarged cross-sectional view taken along the rotation axis LA of the pump device 1. FIG. 5 is a schematic cross-sectional view showing a modified example of the pump device 1 shown in FIG. 4, and is an enlarged cross-sectional view taken along the rotation axis LA of the pump device 1. FIG. 4 is a schematic cross-sectional view showing a modified example of the pump device 1 shown in FIGS. 2 and 3, and is an enlarged cross-sectional view taken along the rotation axis LA of the pump device 1. FIG. 5 is a schematic cross-sectional view showing a modified example of the pump device 1 shown in FIG. 4, and is an enlarged cross-sectional view taken along the rotation axis LA of the pump device 1.

Hereinafter, some embodiments of the present disclosure will be described with reference to the accompanying drawings. However, the dimensions, materials, shapes, relative arrangements, etc. of components described as the embodiments or shown in the drawings are merely illustrative examples and are not intended to limit the scope of the invention.
For example, expressions expressing relative or absolute configuration, such as "in a certain direction,""along a certain direction,""parallel,""orthogonal,""center,""concentric," or "coaxial," not only express such a configuration strictly, but also express a state in which there is a relative displacement with a tolerance or an angle or distance to the extent that the same function is obtained.
For example, expressions indicating that things are in an equal state, such as "identical,""equal," and "homogeneous," not only indicate a state of strict equality, but also indicate a state in which there is a tolerance or a difference to the extent that the same function is obtained.
For example, expressions describing shapes such as a rectangular shape or a cylindrical shape do not only refer to rectangular shapes, cylindrical shapes, etc. in the strict geometric sense, but also refer to shapes that include uneven portions, chamfered portions, etc., to the extent that the same effect is obtained.
On the other hand, the expressions "comprise,""include,""have,""includes," or "have" of one element are not exclusive expressions excluding the presence of other elements.

(Overall configuration of pump system)
Fig. 1 is a schematic cross-sectional view showing a cross section along a rotation axis LA of a pump system 10 including a pump device 1 according to an embodiment of the present disclosure. Fig. 2 is a schematic cross-sectional view showing an example of the configuration of the pump device 1 shown in Fig. 1, which is an enlarged cross-sectional view of the pump device 1 along the rotation axis LA.

For example, as shown in FIG. 1, the pump system 10 includes at least a pump device 1. The pump device 1 includes a rotating body 25 and a casing 26 that houses the rotating body 25.

The rotor 25 comprises a rotor shaft 2, an annular hub portion 3 provided on the rotor shaft 2, a plurality of centrifugal pump vanes 4 provided at intervals in the circumferential direction on the outer circumferential surface 31 of the hub portion 3, an annular shroud wall portion 34 formed along the circumferential direction of the rotor 25 so as to connect to the tips 41 of the plurality of centrifugal pump vanes 4, an annular disk portion 35 protruding radially outward from the outer circumferential surface 36 of the shroud wall portion 34 and formed along the circumferential direction of the rotor 25, and a plurality of axial flow turbine vanes 6 provided at intervals in the circumferential direction of the rotor 25 on the outer circumferential surface 51 of the annular disk portion 35.

The outer peripheral surface 31 of the hub portion 3 includes a concave curved surface 31A that is concavely curved in a cross section along the rotation axis LA of the rotating body 25. The concave curved surface 31A is configured so that the distance from the rotation axis LA increases from one end (front end) 32 in the axial direction of the rotating body 25 toward the other end (rear end) 33 in the axial direction.

In the following, the axial direction of the rotor 25, i.e., the direction in which the rotation axis of the rotating shaft 2 (rotation axis of the rotor 25) LA extends, is simply referred to as the "axial direction", the circumferential direction of the rotor 25, i.e., the circumferential direction of the rotating shaft 2, is simply referred to as the "circumferential direction", and the radial direction of the rotor 25, i.e., the radial direction of the rotating shaft 2, is simply referred to as the "radial direction".

The side where the front end 32 is located relative to the rear end 33 of the concave curved surface 31A in the axial direction (the right side in the figure) is defined as the front side, and the side opposite the front side in the axial direction (the other side, the left side in the figure) is defined as the rear side.

For example, as shown in FIG. 2, the pump device 1 has a centrifugal flow path 11 formed by a convex curved surface 52A formed on the inner circumferential surface 52 of the shroud wall portion 34 and a concave curved surface 31A of the hub portion 3, and the centrifugal flow path 11 is for causing liquid introduced along the axial direction to flow radially outward.

A liquid flow passage 12 is formed on the inner circumferential side of the shroud wall portion 34, through which liquid flowing from one side (front side) to the other side (rear side) in the axial direction flows into the centrifugal pump blades 4, and a gas flow passage 13 is formed on the outer circumferential side of the disk portion 35, through which gas flowing from the other side (rear side) to the one side (front side) passes through the axial turbine blades 6.

The liquid flow path 12 is connected to the centrifugal flow path 11 from the front side. Liquid flowing through the liquid flow path 12 toward the rear side is introduced into the centrifugal flow path 11 from the front side. The axial flow turbine blades 6 are rotated by the introduction of gas flowing from the rear side to the front side. The hub portion 3, centrifugal pump blades 4, shroud wall portion 34, disk portion 35 and axial flow turbine blades 6 rotate integrally with the rotating shaft 2 as the axial flow turbine blades 6 rotate. The suction force generated by the rotation of the centrifugal pump blades 4 sucks the liquid from the liquid flow path 12 into the centrifugal flow path 11 and increases the pressure.

For example, as shown in FIG. 1, the casing 26 includes a main body casing 7 that houses the rotor 25, and an inlet casing 8 that is fastened to the front side of the main body casing 7. Inside the inlet casing 8, a liquid inlet passage 81 for introducing liquid into the centrifugal pump impeller 4 and a gas discharge passage 82 formed on the outer periphery of the liquid inlet passage 81 for discharging gas that has passed through the axial turbine impeller 6 are formed.

In the illustrated embodiment, the liquid flow path 12 includes a main body side axial flow path 12A connected to the centrifugal flow path 11 and a liquid introduction path 81 connected to the main body side axial flow path 12A, and the inner circumferential surface 52 of the shroud wall portion 34 includes the above-mentioned convex curved surface 52A and a guide surface 52B formed forward of the front end 521 of the convex curved surface 52A. The guide surface 52B forms the main body side axial flow path 12A extending along the axial direction. The liquid introduction path 81 includes an inlet side axial flow path 81A extending forward along the axial direction from the rear end face 83 of the inlet side casing 8, and the front end portion 341 of the shroud wall portion 34 is inserted inside the inner surface 811 forming the inlet side axial flow path 81A in the inlet side casing 8, so that the inlet side axial flow path 81A is connected to the main body side axial flow path 12A. In the illustrated exemplary embodiment, the inner surface 811 of the inlet side casing 8 includes an inner circumferential surface 93 that faces the outer circumferential surface of the front end portion 341 of the shroud wall portion 34, a flow passage wall surface 810 of the inlet side axial flow passage 81A, and a step surface 812 that connects the inner circumferential surface 93 and the flow passage wall surface 810, and the guide surface 52B and the flow passage wall surface 810 are formed flush. The flow passage wall surface 810 is formed radially inward from the inner circumferential surface 93.

1, the inlet casing 8 is formed with a liquid introduction hole 85 for introducing liquid into the liquid introduction passage 81. The liquid introduction hole 85 has an inner opening end 851 formed on the inner surface 811 forming the liquid introduction passage 81 in the inlet casing 8, and an outer opening end 852 formed on the outer peripheral surface 86 of the inlet casing 8. The inner opening end 851 is located forward of the front end 341 of the shroud wall 34. The liquid introduction hole 85 and the gas discharge passage 82 are formed at different positions in the circumferential direction. The liquid introduced from the outer opening end 852 flows rearward through the inlet axial passage 81A and the main body axial passage 12A and is guided to the centrifugal pump impeller 4.

A liquid discharge passage 71 for discharging the liquid that has passed through the centrifugal pump impeller 4 and a gas introduction passage 72 for introducing gas into the axial turbine impeller 6 are formed inside the main body casing 7. The main body casing 7 includes a liquid discharge passage forming section 710 that forms the liquid discharge passage 71, and a gas introduction passage forming section 720 that forms the gas introduction passage 72.

The liquid discharge passage 71 includes a scroll passage 71A formed in a scroll shape on the outer circumferential side of the centrifugal passage 11 described above. The liquid discharge passage 71 has a liquid discharge port 74 formed on the outer circumferential surface 73 of the main body casing 7. The liquid discharge port 74 opens toward the outside in the radial direction. After flowing through the liquid discharge passage 71, the liquid that has passed through the centrifugal pump impeller 4 is discharged from the liquid discharge port 74 to the outside of the main body casing 7.

The gas flow path 13 described above includes a gas inlet path 72 and a gas exhaust path 82. Gas introduced from the gas inlet 721 of the main body casing 7 flows through the gas inlet path 72 and is then guided to the axial turbine blade 6. Gas that has passed through the axial turbine blade 6 flows through the gas exhaust path 82 and is then exhausted from a gas exhaust port (not shown).

In the illustrated embodiment, a nozzle (stator vane) 14 of an axial turbine 10A is provided in the gas introduction passage 72. The axial turbine 10A may be any of an impulse turbine, a reaction turbine, or an impulse reaction turbine.

In the illustrated embodiment, the inlet casing 8 includes a flange portion 87 that protrudes radially outward from the outer peripheral surface 86 at the rear side. The inlet casing 8 is fastened to the main body casing 7 by fastening the flange portion 87 to the front end portion 76 of the main body casing 7 with a plurality of fastening members 15 (fastening bolts in the illustrated example) spaced apart in the circumferential direction.

In this way, the pump device 1 includes an axial turbine 10A including axial turbine blades 6 and a centrifugal pump 10B including centrifugal pump blades 4, and the axial turbine 10A and the centrifugal pump 10B are integrated in the radial direction.

2, the shroud wall 34 is cylindrical and has an inner peripheral surface 52 including a convex curved surface 52A that is convexly curved in a cross section along the rotation axis LA. The convex curved surface 52A is configured so that the distance from the rotation axis LA increases from the front end 521 to the rear end 522 in the axial direction. The centrifugal pump impeller 4 has its base end provided on the concave curved surface 31A of the hub portion 3, and its tip end 41 located opposite to the base end is connected to the convex curved surface 52A of the shroud wall 34. The convex curved surface 52A of the shroud wall 34 is located radially outward from the concave curved surface 31A of the hub portion 3, and is disposed with a gap between it and the concave curved surface 31A. The shroud wall 34 includes a rear outer peripheral surface 56 that faces the inner peripheral surface 79 of the main body casing 7 via a gap 22, rearward of the disk portion 35.

The annular disk portion 35 includes an outer peripheral surface 51, a front side surface 78 (one side surface) facing the front side (the one side) in the axial direction, and a rear side surface 80 (the other side surface) facing the rear side (the other side) in the axial direction. In the illustrated exemplary form, the axial thickness of the outer peripheral portion 65 of the disk portion 35 facing the gas flow path 13 described below is greater than the axial thickness of the inner peripheral portion 66 of the disk portion 35 that connects to the shroud wall portion 34. The outer peripheral portion 65 and the inner peripheral portion 66 of the disk portion 35 are connected by a tapered portion 67, and the thickness of the tapered portion 67 in the axial direction increases toward the outside in the radial direction.

A front gap (one-side gap) 17, which is an axial gap, is formed between the front end face (one-side end face) 53, which is the front end face of the outer periphery 65 of the annular disk portion 35, and the stationary wall 16 that faces the front end face 53 of the casing 26.

In the illustrated embodiment, the front end surface 53 of the annular disk portion 35 extends radially inward from the front end of the outer peripheral surface 51 to which the axial turbine blades 6 are attached. The stationary wall 16 is made of the rear end surface 83 of the inlet casing 8, which is disposed opposite the front end surface 53. In the illustrated embodiment, the front gap 17 is formed between the end surface 83 of the inlet casing 8 and the front end surface 53 of the disk portion 35. The front gap 17 is connected to the front side (downstream side) of the axial turbine blades 6 in the gas flow path 13 and the rear side (upstream side) of the gas discharge path 82.

The front space 20 is a space formed between the annular disk portion 35 and the inlet casing 8 on the inner circumferential side of the front gap 17. The front space 20 is connected to the liquid flow path 12 formed on the inner circumferential side.

A rear side gap (other side gap) 19, which is an axial gap, is formed between the rear side end face (other side end face) 54, which is the rear side end face of the outer periphery 65 of the annular disk portion 35, and the stationary wall 18 that faces the rear side end face 54 of the casing 26. The rear side gap 19 is located radially outward of the gap 22.

In the illustrated embodiment, the rear end surface 54 of the annular disk portion 35 extends radially inward from the rear end of the outer peripheral surface 51 to which the axial turbine blades 6 are attached. The stationary wall 18 is made of the front end surface 77 of the main body casing 7, which is disposed opposite the rear end surface 54. That is, in the illustrated embodiment, the rear gap 19 is formed between the rear end surface 54 of the disk portion 35 and the end surface 77 of the main body casing. The rear gap 19 leads forward (downstream) of the nozzle 14 in the gas flow path 13 and rearward (upstream) of the axial turbine blades 6.

The shroud wall portion 34 has a rear outer peripheral surface 56 located rearward of the outer peripheral surface 51 of the disk portion 35 to which the axial turbine blades 6 are attached and radially inward of the outer peripheral surface 51, and an annular recess 57 recessed radially inward from the rear outer peripheral surface 56 between the outer peripheral surface 51 and the rear outer peripheral surface 56 in the axial direction. The rear space 21 is a space formed on the inner peripheral side of the rear gap 19 and includes a space facing the annular recess 57. The rear space 21 is connected to the outlet of the centrifugal flow path 11 through the gap 22. The inner peripheral surface 79 extends axially rearward from the radially inner end of the end face 77.

(Sealing part)
The pump device 1 includes a first seal portion 62 that seals the rear gap 19, located radially outward of the gap 22. The first seal portion 62 includes a fin set 63, and the fin set 63 includes a plurality of fins 64 spaced apart in the radial direction. In the illustrated example, the first seal portion 62 includes the fin set 63 that is made up of two fins 64 spaced apart in the radial direction. Each of the fins 64 is formed in an annular shape along the circumferential direction. Each of the fins 64 is configured to protrude forward from the stationary wall 18 of the casing 26. In this manner, the first seal portion 62 is configured as a labyrinth seal.

The pump device 1 includes a second seal portion 68 that seals the front gap 17, located radially outward of the gap 22. The second seal portion 68 includes a fin set 90, which includes a plurality of fins 91 spaced apart in the radial direction. In the illustrated example, the second seal portion 68 includes a fin set 90 consisting of two fins 91 spaced apart in the radial direction. Each of the fins 91 is formed in an annular shape along the circumferential direction. Each of the fins 91 is configured to protrude rearward from the stationary wall 16 in the casing 26. In this manner, the second seal portion 68 is configured as a labyrinth seal.

The pump device 1 includes a third seal portion 69 that seals a radial gap 94 between the outer peripheral surface 36 of the shroud wall portion 34 and the inner peripheral surface 93 of the inlet side casing 8, located forward of the disk portion 35. In the illustrated example, the gap 94 is formed between the outer peripheral surface of the front end portion 341 of the shroud wall portion 34 and the inner peripheral surface 93 of the inlet side casing 8. The third seal portion 69 includes a fin set 95, and the fin set 95 includes a plurality of fins 96 that are spaced apart in the axial direction. In the illustrated example, the third seal portion 69 includes a fin set 95 consisting of three fins 96 that are spaced apart in the axial direction. Each of the fins 96 is formed in an annular shape along the circumferential direction. Each of the fins 96 is located forward of the disk portion 35 and is configured to protrude radially outward from the outer peripheral surface 36 of the shroud wall portion 34. In this manner, the third seal portion 69 is configured by a labyrinth seal.

(Through hole)
The disk portion 35 is formed with a plurality of through holes 55 penetrating the disk portion 35 in the axial direction. The plurality of through holes 55 are arranged at intervals in the circumferential direction, radially inward from the first seal portion 62 (radially inward from the fin set 63). Each of the through holes 55 communicates with the front side gap 17 or a front side space (one side space) 20 connected to the front side gap 17, and the rear side space (the other side space) 21 connected to the rear side gap 19 or the rear side gap 19. In the illustrated example, each of the through holes 55 is configured to penetrate the tapered portion 67 in the axial direction.

The through hole 55 has a front opening end 551 formed on the front side of the disk portion 35 and a rear opening end 552 formed on the rear side of the disk portion 35. In the illustrated embodiment, the front opening end 551 is formed on a surface 58 (the front surface 58 of the tapered portion 67 in the illustrated example) continuing to the inner periphery of the front end surface 53 on the front side surface 78 of the disk portion 35, and the rear opening end 552 is formed on a surface 59 (the rear surface 59 of the tapered portion 67 in the illustrated example) continuing to the inner periphery of the rear end surface 54 on the rear side surface 80 of the disk portion 35. The front opening end 551 is connected to the front space 20, and the rear opening end 552 is connected to the rear space 21. In some other embodiments, the front opening end 551 may be formed on the front end face 53 and connected to the front gap 17, and the rear opening end 552 may be formed on the rear end face 54 and connected to the rear gap 19. In the illustrated embodiment, the through hole 55 has a distance between the center of the front opening end 551 and the rotation axis LA that is the same as the distance between the center of the rear opening end 552 and the rotation axis LA.

According to the above configuration, the pump device 1 includes a shroud wall portion 34 formed in a ring shape along the circumferential direction so as to connect to the tips 41 of the centrifugal pump vanes 4, a disk portion 35 formed in a ring shape along the circumferential direction and projecting radially from the outer circumferential surface 36 of the shroud wall portion 34, and a plurality of axial turbine vanes 6 provided at intervals in the circumferential direction on the outer circumferential surface 51 of the disk portion 35. By integrating the axial turbine 10A and the centrifugal pump 10B in the radial direction, the pump device 1 can be made compact and lightweight, and its axial length can be reduced.

In addition, according to the above configuration, the pump device 1 has a liquid flow path 12 formed on the inner circumferential side of the shroud wall portion 34, through which the liquid flowing from the front side to the rear side flows into the centrifugal pump blades 4, and a gas flow path 13 formed on the outer circumferential side of the disk portion 35, through which the gas flowing from the rear side to the front side passes through the axial turbine blades 6. According to this configuration, the shroud wall portion 34, the disk portion 35, and the axial turbine blades 6 are cooled by the liquid flowing through the liquid flow path 12 and passing through the centrifugal pump blades 4, so that their heat resistance can be improved. In addition, the heat of the gas flowing through the gas flow path 13 is insulated by the liquid flowing through the liquid flow path 12 and passing through the centrifugal pump blades 4, so that the heat can be suppressed from being transmitted to the hub portion 3 and the rotating shaft 2 through the disk portion 35 and the shroud wall portion 34. This can suppress deterioration and performance degradation due to heat of the bearings and seals attached to the rotating shaft 2. Therefore, the pump device 1 can eliminate or simplify the cooling structure for cooling the bearings and seals attached to the rotating shaft 2, suppressing the increase in size, weight, and number of parts of the pump device 1, and suppressing the decrease in reliability that accompanies the increase in size, weight, and number of parts of the pump device 1.

Furthermore, according to the above configuration, the pump device 1 includes a main body casing 7 and an inlet casing 8 fastened to the front side of the main body casing 7, and inside the inlet casing 8, a liquid introduction passage 81 and a gas discharge passage 82 formed on the outer periphery of the liquid introduction passage 81 are formed. This allows the axial length of the inlet casing 8 to be reduced, thereby enabling the pump device 1 to be made more compact and smaller and lighter.

According to the above configuration, the liquid passing through the centrifugal pump impeller 4 is pressurized by the centrifugal force exerted by the driving of the pump device 1. A part of this pressurized liquid flows into the rear gap 19 and the rear space 21 through the gap 22.

Here, as shown in FIG. 3, if the pressure of the liquid flowing through the liquid flow path 12 is P1 (pump inlet pressure), the pressure of the liquid that has passed through the centrifugal pump blade 4 is P2 (pump outlet pressure), the pressure of the gas at the inlet of the axial turbine blade 6 is P3 (pressure between the nozzle 14 and the axial turbine blade 6), the pressure between the two fins 64 in the rear gap 19 is P4 (rear gap pressure), the pressure of the gas in the gas discharge path 82 (turbine outlet pressure) is P5, and the pressure in the front space 20 is P6, then under the design conditions of the pump device 1 such that P1<P2>P3>P5>P1 is satisfied, a pressure P4 (an intermediate pressure between P2 and P3) that satisfies P2>P4>P3>P6 can be obtained. Therefore, the liquid (pump leak liquid) that has flowed into the rear gap 19 or the rear space 21 is prevented by the first seal portion 62 from flowing through the rear gap 19 into the gas flow path 13, and is sent through the through hole 55 to the front gap 17 or the front space 20 by the drive of the pump device 1. That is, since the first seal portion 62 is provided in the rear gap 19 and the through hole 55 is formed in the disk portion 35, the liquid (pump leak liquid) that has flowed into the rear gap 19 or the rear space 21 is prevented by the first seal portion 62 from flowing through the rear gap 19 into the gas flow path 13, and is sent through the through hole 55 to the front gap 17 or the front space 20 by the drive of the pump device 1. This liquid can cool the axial turbine blades 6, the annular disk portion 35, the inlet casing 8, and the front portion of the shroud wall portion 34.

Therefore, while suppressing leakage of liquid from the inner periphery of the shroud wall 34 to the outer periphery of the disk 35 during storage of the pump device 1, the power consumption at the start of the pump device 1 is reduced, and the turbine outlet side (the disk 35 and the side forward of the disk 35) can be effectively cooled by the liquid passing through the through hole 55. Therefore, while suppressing a decrease in pump efficiency, the level of heat resistance required for the turbine outlet side can be lowered, and the material cost of various parts can be reduced. If a labyrinth seal is provided in the gap 22, the amount of liquid leaking from the gap 22 to the turbine side is reduced, and the cooling effect of the turbine outlet side by the liquid passing through the through hole 55 is limited. Therefore, in the above embodiment, the turbine outlet side can be effectively cooled by sealing the front side gap 17 instead of the gap 22 with the first seal portion 62.

In addition, by providing the through hole 55, the pressure difference between the front and rear of the disk portion 35 can be reduced, and the thrust load acting on the bearing (not shown) that rotatably supports the rotor 25 can be reduced, thereby improving the reliability of the pump device 1.

In addition, according to the above configuration, the fluid present in the rear side gap 19 and the rear side space 21 flows into the front side gap 17 and the front side space 20 through the through hole 55, so the pressure in the front side gap 17 and the front side space 20 can be increased compared to when the through hole 55 is not formed. In addition, since the second seal portion 68 is provided in the front side gap 17, under the above design conditions where P5>P1 is satisfied for the pressures P1 to P6, a pressure P6 (an intermediate pressure between P1 and P5) that satisfies P5>P6>P1 can be obtained, so that the gas that has passed through the axial turbine blade 6 can be prevented from passing through the front side gap 17 and the front side space 20 and flowing into the liquid flow path 12 compared to when the second seal portion 68 is not present. By preventing the gas that has passed through the axial turbine blade 6 from flowing into the liquid flow path 12, the occurrence of cavitation in the liquid flow path 12 or the centrifugal flow path 11 can be suppressed.

In addition, since the third seal portion 69 that seals the radial gap 94 is provided, it is possible to suppress the gas that has passed through the axial turbine blade 6 from passing through the space between the front side surface 78 of the disk portion 35 and the inlet side casing 8 (the front gap 17 and the front space 20) and flowing into the liquid flow path 12, compared to a case in which the third seal portion 69 is not provided. By suppressing the flow of the gas that has passed through the axial turbine blade 6 into the liquid flow path 12, the occurrence of cavitation in the liquid flow path 12 can be suppressed.

(Modification of the pump device)
Next, several other embodiments of the pump device 1 shown in Fig. 1 will be described. In the several embodiments described below, reference numerals common to the components of the pump device 1 described above indicate the same components as those of the pump device 1 described above unless otherwise specified, and description thereof will be omitted.

FIG. 4 is a diagram showing a modified example of the pump device 1 shown in FIGS. 2 and 3, and is a schematic sectional view showing an enlarged cross section taken along the rotation axis LA of the pump device 1. In FIG.
In some embodiments, as shown in Fig. 4, for example, the fin set 63 of the first seal portion 62 may be provided on the disk portion 35. In the configuration shown in Fig. 4, each of the fins 64 of the fin set 63 is configured to protrude rearward (toward the stationary wall 18) from the rear end surface 54 of the disk portion 35.

As a result, similar to the configuration shown in Figures 2 and 3, it is possible to effectively cool the turbine outlet side (the disk section 35 and the side forward of the disk section 35) by the liquid passing through the through hole 55 while suppressing leakage of liquid from the inner peripheral side of the shroud wall section 34 to the outer peripheral side of the disk section 35.

In some embodiments, as shown in FIG. 4, for example, the fin set 90 of the second seal portion 68 may be provided on the disk portion 35. In the configuration shown in FIG. 4, each of the fins 91 of the fin set 90 is configured to protrude forward (toward the stationary wall 16) from the front end surface 53 of the disk portion 35.

As a result, similar to the configuration shown in Figures 2 and 3, it is possible to prevent gas that has passed through the axial turbine blade 6 from passing through the front gap 17 or the front space 20 and flowing into the liquid flow path 12, compared to a case in which the second seal portion 68 is not provided. By preventing the gas that has passed through the axial turbine blade 6 from flowing into the liquid flow path 12, it is possible to prevent the occurrence of cavitation in the liquid flow path 12 or the centrifugal flow path 11.

Figure 5 is a diagram showing a modified example of the pump device 1 shown in Figures 2 and 3, and is a schematic cross-sectional view enlarging a cross section along the rotation axis LA of the pump device 1. Figure 6 is a diagram showing a modified example of the pump device 1 shown in Figure 4, and is a schematic cross-sectional view enlarging a cross section along the rotation axis LA of the pump device 1.

In some embodiments, as shown in, for example, Figures 5 and 6, the pump device 1 includes wax 88 arranged to close the rear gap 19. For example, in the configuration shown in Figure 5, the wax 88 is embedded between the fins 64 and also between the fins 64 and the rear end surface 54 of the disk portion 35. For example, in the configuration shown in Figure 6, the wax 88 is embedded between the fins 64 and also between the fins 64 and the end surface 77 (static wall 18) of the main body casing 7.

In this configuration, when the pump device 1 is at rest (when the pump device 1 is new), the rear side gap 19 is sealed with wax, and when the pump device 1 is started, the wax 88 is pushed toward the gas flow path 13 by the centrifugal force of the rotor 25 as shown by arrow a1, or the wax 88 is melted by the heat of the high-temperature gas flowing through the gas flow path 13 as shown by arrow a2, forming an appropriate clearance between the fin 64 of the first seal portion 62 and the disk portion 35 or the main body casing 7. This makes it possible to suppress leakage of liquid from the inner periphery of the shroud wall portion 34 to the outer periphery of the disk portion 35 when the pump device 1 is at rest, thereby reducing the power consumed on the axial turbine 10A side due to liquid accumulating on the gas flow path 13 side when the pump device 1 is started. In addition, after the pump device 1 is started, an appropriate clearance is formed between the fins 64 of the first seal portion 62 and the disk portion 35 or the main body casing 7, so the turbine outlet side can be effectively cooled by the liquid that has passed through the through hole 55 while allowing the rotor 25 to rotate.

In some embodiments, as shown in, for example, Figures 5 and 6, the pump device 1 includes wax 89 arranged to close the front gap 17. For example, in the configuration shown in Figure 5, the wax 89 is embedded between the fins 91 and also between the fins 91 and the front end surface 53 of the disk portion 35. For example, in the configuration shown in Figure 6, the wax 89 is embedded between the fins 91 and also between the fins 91 and the end surface 83 (static wall 16) of the inlet casing 8.

In this configuration, when the pump device 1 is at rest (when the pump device 1 is new), the front gap 17 is sealed with wax 89, and when the pump device 1 is started, the wax 89 is pushed toward the gas flow path 13 by the centrifugal force of the rotor 25 as shown by arrow a3, or the wax 89 is melted by the heat of the high-temperature gas flowing through the gas flow path 13 as shown by arrow a4, forming an appropriate clearance between the fin 91 of the second seal portion 68 and the disk portion 35 or the inlet-side casing 8. This makes it possible to suppress leakage of liquid from the inner periphery of the shroud wall portion 34 to the outer periphery of the disk portion 35 when the pump device 1 is at rest, thereby reducing the power consumed on the axial turbine 10A side due to liquid accumulating on the gas flow path 13 side when the pump device 1 is started. In addition, after the pump device 1 is started, an appropriate clearance is formed between the fin 91 of the second seal portion 68 and the disk portion 35 or the inlet side casing 8, so the turbine outlet side can be effectively cooled by the liquid that has passed through the through hole 55 while allowing the rotor 25 to rotate.

FIG. 7 is a diagram showing a modification of the pump device 1 shown in FIGS. 2 and 3, and is a schematic cross-sectional view showing an enlarged cross section taken along the rotation axis LA of the pump device 1. As shown in FIG.
7 , the pump device 1 may include an abradable coating layer 641 formed on the tips of the multiple fins 64 and an abradable coating layer 911 formed on the tips of the multiple fins 91. In the illustrated configuration, the abradable coating layer 641 abuts against the rear end face 54 of the disk portion 35 and closes the gap between the multiple fins 64 and the disk portion 35. The abradable coating layer 911 abuts against the front end face 53 of the disk portion 35 and closes the gap between the multiple fins 91 and the disk portion 35.

In this configuration, when the pump device 1 is at rest, the front gap 17 is sealed by the abradable coating layer 911, and when the pump device 1 is started, the abradable coating layer 911 is worn away by friction as the rotor 25 rotates, forming an appropriate clearance between the fin 91 of the second seal portion 68 and the disk portion 35. Also, when the pump device 1 is at rest, the rear gap 19 is sealed by the abradable coating layer 641, and when the pump device 1 is started, the abradable coating layer 641 is worn away by friction as the rotor 25 rotates, forming an appropriate clearance between the fin 64 of the first seal portion 62 and the disk portion 35.

This makes it possible to prevent liquid from leaking from the inner periphery of the shroud wall 34 to the outer periphery of the disk 35 when the pump device 1 is at rest, thereby reducing the power consumed on the axial turbine 10A side due to liquid accumulating on the gas flow path 13 side when the pump device 1 is started. In addition, while preventing liquid from leaking from the inner periphery of the shroud wall 34 to the outer periphery of the disk 35, the turbine outlet side can be effectively cooled by the liquid that has passed through the through hole 55.

In another embodiment, for example, in the configuration shown in FIG. 4, the pump device 1 may have an abradable coating layer (not shown) formed on the tips of the fins 64 and an abradable coating layer (not shown) formed on the tips of the fins 91. In this case, when the pump device 1 is stationary, the abradable coating layer formed on the tips of the fins 64 abuts against the end face 77 of the main body casing 7 so as to close the gap between the fins 64 and the end face 77 of the main body casing 7, and the abradable coating layer formed on the tips of the fins 91 abuts against the end face 83 of the inlet casing 8 so as to close the gap between the fins 91 and the end face 83 of the inlet casing 8. In this case, the same effect as the configuration shown in FIG. 7 can be obtained.

Figures 8, 10, 12, and 14 are diagrams showing several modified examples of the pump device 1 shown in Figures 2 and 3, and are schematic cross-sectional views enlarging a cross section along the rotation axis LA of the pump device 1. Figures 9, 11, 13, and 15 are diagrams showing several modified examples of the pump device 1 shown in Figure 4, and are schematic cross-sectional views enlarging a cross section along the rotation axis LA of the pump device 1.

In some embodiments shown in Figures 8, 10, 12, and 14, the fin set 63 of the first seal portion 62 and the fin set 90 of the second seal portion 68 are provided on the casing 26, similar to the pump device 1 shown in Figures 2 and 3. In some embodiments shown in Figures 9, 11, 13, and 15, the fin set 63 of the first seal portion 62 and the fin set 90 of the second seal portion 68 are provided on the disk portion 35, similar to the pump device 1 shown in Figure 4.

In some embodiments, as shown in Figures 8 to 15, for example, in a cross section along the axial direction, the outer surface 351 of the disk portion 35 includes a rearward extension portion 352 that extends rearward along the axial direction from the rearward side surface 80 and connects to the shroud wall portion 34, radially inward of the through hole 55. In the illustrated example, the rearward extension portion 352 is formed flush with the rearward outer peripheral surface 56.

Compared to the configuration shown in FIG. 2 in which an annular recess 57 is formed, this configuration reduces the volume filled with liquid fuel when the pump device 1 is stored, thereby making it possible to reduce losses caused by liquid pooling when the pump device 1 is started.

In some embodiments, as shown in Figures 10 to 15, for example, in a cross section along the axial direction, the outer surface 351 of the disk portion 35 includes a forward extension portion 353 that extends axially forward from one side surface 78 radially inward of the through hole 55, and a step portion 354 that extends radially inward from the forward end of the forward extension portion 353 in the axial direction and connects to the outer peripheral surface 36 of the shroud wall portion 34.

This configuration, compared to the configuration shown in FIG. 2 in which the forward extension 353 is not provided, reduces the volume filled with liquid fuel when the pump device 1 is stored, thereby making it possible to reduce losses caused by liquid pooling when the pump device 1 is started.

In some embodiments, as shown in, for example, Figures 10 to 15, the disk portion 35 includes at least one hollow portion 451 in addition to the through hole 55.

With this configuration, by making part of the disk portion 35 hollow, the weight of the rotor 25 can be reduced, and axial vibration and power consumption can be reduced.

In some embodiments, as shown in Figures 12 and 13, for example, the at least one hollow portion 451 of the disk portion 35 includes a hollow portion 451 formed at a position different from the through hole 55 in the circumferential direction, from a position inside the through hole 55 to a position outside the through hole in the radial direction. In this case, the disk portion 35 may be provided with a plurality of hollow portions 451 spaced apart in the circumferential direction at positions different from the through hole 55 in the circumferential direction.

In this configuration, compared to the configuration shown in Figures 10 and 11, the range in which the hollow portion 451 is formed is expanded in the radial direction, thereby further reducing the weight of the rotor 25 and enhancing the effect of reducing axial vibration and power consumption. In addition, by arranging the hollow portion 451 and the through hole 55 at different positions in the circumferential direction, it is possible to prevent leakage liquid from the pump side from flowing into the hollow portion 451 through the through hole 55, thereby reducing the power consumption when the pump is started.

In some embodiments, the at least one hollow portion 451 includes a hollow portion 451 configured in a lattice pattern, as shown in, for example, FIGS. 14 and 15.

With this configuration, the hollow portion 451 is configured in a lattice pattern, which increases the strength of the disk portion 35, making it possible to use the pump device 1 even under severe operating conditions in terms of stress caused by high-speed rotation.

(Rotational Force Recovery Device or Rotational Force Imparting Device)
1 , the pump system 10 includes the pump device 1 and either a rotational force recovery device 96 configured to recover rotational force of the rotating shaft 2 or a rotational force imparting device 98 configured to impart rotational force to the rotating shaft 2. The rotational force recovery device 96 or the rotational force imparting device 98 is attached to the rotating shaft 2. The rotational force recovery device 96 may be, for example, a generator, and the rotational force imparting device 98 may be, for example, an electric motor.

With this configuration, if the pump system 10 is equipped with a rotational force recovery device 96, it can recover the rotational force of the rotating shaft 2, and if the pump system 10 is equipped with a rotational force imparting device 98, it can assist the rotation of the rotating shaft 2.

The present disclosure is not limited to the above-described embodiments, but also includes variations of the above-described embodiments and appropriate combinations of these embodiments.

For example, the disk portion 35 described above has multiple through holes 55 spaced apart in the circumferential direction, but the number of through holes 55 in the disk portion 35 is not limited, and may be, for example, one, and no through holes may be provided radially outward of the inner peripheral surface 60 of the annular disk portion 35.

The contents described in each of the above embodiments can be understood, for example, as follows:

(1) At least one embodiment of the pump device according to the present disclosure (e.g., the pump device 1 described above) includes:
A pump device including a rotating body (e.g., the above-mentioned rotating body 25) and a casing (e.g., the above-mentioned casing 26) that houses the rotating body,
The rotating body is
A hub portion (e.g., the above-mentioned hub portion 3),
a plurality of centrifugal pump vanes (e.g., the above-mentioned centrifugal pump vanes 4) provided at intervals in the circumferential direction of the rotor on the outer circumferential surface of the hub portion;
an annular shroud wall portion (e.g., the above-mentioned shroud wall portion 34) formed along the circumferential direction so as to connect to tips of the plurality of centrifugal pump vanes;
an annular disk portion (e.g., the disk portion 35 described above) formed along the circumferential direction so as to protrude from an outer circumferential surface of the shroud wall portion toward the outside in the radial direction of the rotor;
a plurality of axial flow turbine blades (e.g., the above-mentioned axial flow turbine blades 6) provided at intervals in the circumferential direction on the outer circumferential surface of the disk portion;
Equipped with
a liquid flow passage (e.g., the above-mentioned liquid flow passage 12) through which liquid flowing from one side to the other side in the axial direction of the rotor flows into the centrifugal pump impeller is formed on the inner peripheral side of the shroud wall portion;
a gas flow passage (e.g., the above-mentioned gas flow passage 13) through which gas flowing from the other side to the one side passes through the axial flow turbine blade is formed on the outer circumferential side of the disk portion;
the shroud wall portion includes a second outer peripheral surface (e.g., the rear side outer peripheral surface 56) facing an inner peripheral surface of the casing via a first gap (e.g., the gap 22) on the second side in the axial direction relative to the disk portion,
the disk portion includes a one-side end face (e.g., the above-mentioned front-side end face 53) that is an end face on the one side in the axial direction, and a other-side end face (e.g., the above-mentioned rear-side end face 54) that is an end face on the other side in the axial direction,
a first seal portion (e.g., the above-mentioned first seal portion 62) that seals a second-side gap (e.g., the above-mentioned rear-side gap 19), which is a gap in the axial direction between the second-side end face of the disk portion and the casing, is provided radially outward of the first gap;
At least one through hole (for example, the above-mentioned plurality of through holes 55) penetrating in the axial direction is formed in the disk portion radially inward of the first seal portion.

According to the pump device described in (1) above, the rotor of the pump device includes an annular shroud wall portion formed along the circumferential direction so as to connect to the tips of the centrifugal pump blades, an annular disk portion fixed to the outer peripheral surface of the shroud wall portion, and a plurality of axial turbine blades provided at intervals in the circumferential direction on the outer peripheral surface of the disk portion. That is, in such a pump device, the rotor of the axial turbine and the rotor of the centrifugal pump are integrated in the radial direction. This allows the axial length of the pump device to be reduced, making the pump device more compact and reducing its size and weight.

In addition, a liquid flow path is formed on the inner circumferential side of the shroud wall, through which the liquid flowing from one side to the other side flows into the centrifugal pump blade, and a gas flow path is formed on the outer circumferential side of the disk portion, through which the gas flowing from the other side to the one side passes through the axial turbine blade. With this configuration, the shroud wall portion, the disk portion, and the axial turbine blade are cooled by the liquid flowing through the liquid flow path and passing through the centrifugal pump blade, so that their heat resistance can be improved. In addition, the heat of the gas flowing through the gas flow path is insulated by the liquid flowing through the liquid flow path and passing through the centrifugal pump blade, so that the heat can be prevented from being transmitted to the hub portion through the disk portion and the shroud wall portion. This can prevent deterioration and performance degradation due to heat of the bearings and seals. Therefore, the pump device can eliminate or simplify the cooling structure for cooling the bearings and seals, and can prevent the pump device from becoming larger, heavier, and more numerous, and can prevent the reliability from decreasing due to the increase in size, weight, and number of parts of the pump device.

The liquid passing through the centrifugal pump impeller is pressurized by the centrifugal force applied by the driving of the pump device. A part of the pressurized liquid flows into a space between the other side surface of the disk part in the axial direction and the casing or the shroud wall part through the first gap. Since the first seal part is provided in the other side gap and the disk part has a through hole, the liquid (pump leakage liquid) that flows into the space between the other side surface of the disk part and the casing or the shroud wall part (e.g., the rear side gap 19 or the rear side space 21) is prevented by the first seal part from flowing through the other side gap into the gas flow path, and is sent through the through hole by the driving of the pump device to the space between the one side surface of the disk part and the casing (e.g., the front side gap 17 or the front side space 20).
This liquid can cool the axial turbine blades, the annular disk section, the casing, and the one side of the shroud wall section. Therefore, the liquid passing through the through holes can effectively cool the turbine outlet side (the disk section and one side of the disk section) while suppressing leakage of liquid from the inner periphery side of the shroud wall section to the outer periphery side of the disk section. Therefore, the level of heat resistance required for the turbine outlet side can be lowered while suppressing a decrease in pump efficiency, thereby reducing the material costs of various parts.

In addition, by providing a through hole, the pressure difference between the front and rear of the disk portion can be reduced, and the thrust load acting on the bearing (not shown) that rotatably supports the rotor can be reduced, thereby improving the reliability of the pump device.

(2) In some embodiments, in the pump device described in (1) above,
A second seal portion (for example, the above-mentioned second seal portion 68) is provided to seal the one-side gap, which is the gap in the axial direction between the one-side end face of the disk portion and the casing.

According to the pump device described in (2) above, since a second seal portion that seals the one-side gap is provided, it is possible to suppress the gas that has passed through the axial turbine blades from passing through the space between the one side surface of the disk portion and the casing (e.g., the front side gap 17 or the front side space 20) and flowing into the liquid flow path, compared to a case in which the second seal portion is not provided. By suppressing the flow of the gas that has passed through the axial turbine blades into the liquid flow path, it is possible to suppress the occurrence of cavitation in the liquid flow path.

(3) In some embodiments, in the pump device described in (1) or (2) above,
A third seal portion (e.g., the above-mentioned third seal portion 69) that seals the radial gap between the outer peripheral surface of the shroud wall portion and the inner peripheral surface of the casing is provided on one side in the axial direction from the disk portion.

According to the pump device described in (3) above, since a third seal portion that seals the radial gap is provided, it is possible to suppress the gas that has passed through the axial turbine blades from passing through the space between one side surface of the disk portion and the casing (e.g., the forward gap 17 or the forward space 20) and flowing into the liquid flow path, compared to a case in which the third seal portion is not provided. By suppressing the flow of gas that has passed through the axial turbine blades into the liquid flow path, it is possible to suppress the occurrence of cavitation in the liquid flow path.

(4) In some embodiments, in the pump device described in (2) above,
At least one of the first seal portion and the second seal portion has a fin set (e.g., the above-mentioned fin set 63 or fin set 90) including a plurality of fins (e.g., the above-mentioned plurality of fins 64 or a plurality of fins 91) spaced apart in the radial direction.

According to the pump device described in (4) above, a radial pressure gradient is formed in at least one of the one-side gap and the other-side gap, and the pressure between the multiple fins can be set to an intermediate pressure in the region with the pressure gradient. This can enhance the effects described in (1) or (2) above.

(5) In some embodiments, in the pump device described in (4) above,
The fin set is provided on the casing.

According to the pump device described in (5) above, a radial pressure gradient is formed in at least one of the one-side gap and the other-side gap by the fin set provided in the casing, and the pressure between the multiple fins can be set to an intermediate pressure in the region with the pressure gradient. This can enhance the effects described in (1) or (2) above.

(6) In some embodiments, in the pump device described in (4) above,
The fin set is provided on the disk portion.

According to the pump device described in (6) above, a radial pressure gradient is formed in at least one of the one-side gap and the other-side gap by the fin set provided in the disk portion, and the pressure between the multiple fins can be set to an intermediate pressure in the region with the pressure gradient. This can enhance the effects described in (1) or (2) above.

(7) In some embodiments, in the pump device according to any one of (4) to (6),
The fixing device further includes wax (for example, the above-mentioned wax 88 or wax 89) arranged to fill at least one of the one-side gap and the other-side gap.

According to the pump device described in (7) above, when the pump device is at rest (when the pump device is new), at least one of the gaps on one side and the gap on the other side is blocked by wax, and when the pump device is started, the wax is pushed out to the gas flow path by the centrifugal force of the rotor, or melted by the heat of the high-temperature gas flowing through the gas flow path, forming an appropriate clearance between the fin and the disk section or the casing. This makes it possible to suppress leakage of liquid from the inner periphery of the shroud wall to the outer periphery of the disk section when the pump device is at rest, thereby reducing the power consumed on the axial turbine side due to liquid accumulating on the gas flow path side when the pump device is started. In addition, since an appropriate clearance is formed between the fin and the disk section or the casing after the pump device is started, the turbine outlet side can be effectively cooled by the liquid that has passed through the through hole while allowing the rotor to rotate.

(8) In some embodiments, in the pump device according to any one of (4) to (6),
The blade further includes an abradable coating layer (such as the above-mentioned abradable coating layer 641 or 911) formed on the tips of the plurality of fins.

According to the pump device described in (8) above, when the pump device is stationary, at least one of the one-side gap and the other-side gap is sealed by the abradable coating layer, and when the pump device is started, the abradable coating layer is worn away by friction as the rotating body rotates, thereby forming an appropriate clearance between the fin and the disk portion.
This makes it possible to suppress leakage of liquid from the inner periphery of the shroud wall to the outer periphery of the disk when the pump device is at rest, thereby reducing the power consumed on the axial turbine side due to liquid accumulating on the gas flow path side when the pump device is started. Also, since an appropriate clearance is formed between the fins and the disk or the casing after the pump device is started, the turbine outlet side can be effectively cooled by the liquid that has passed through the through holes while allowing the rotor to rotate.

(9) In some embodiments, in the pump device according to any one of (1) to (8),
The outer surface of the disk portion includes a second side surface (e.g., the rear side surface 80) facing the second side in the axial direction,
In a cross section along the axial direction, the outer surface of the disk portion includes a other-side extending portion (e.g., the above-mentioned rear side extending portion 352) extending from the other-side side surface along the axial direction to the other side, inside the through hole in the radial direction of the rotating body, and connecting to the outer peripheral edge portion of the shroud wall portion.

The pump device described in (9) above reduces the volume filled with liquid fuel during storage of the pump device compared to the configuration shown in FIG. 2 in which the other-side extension portion is not provided, thereby making it possible to reduce losses due to liquid pooling during startup of the pump device.

(10) In some embodiments, in the pump device according to any one of (1) to (9),
The outer surface of the disk portion includes a side surface (e.g., the front side surface 78) facing the one side in the axial direction,
In a cross section along the axial direction, the outer surface of the disk portion includes a one-side extending portion (e.g., the above-mentioned front side extending portion 353) extending from the one-side side surface along the axial direction to the one side, radially inwardly of the rotating body relative to the through hole, and a step portion (e.g., the above-mentioned step portion 354) extending radially inward from the one-side end of the one-side extending portion in the axial direction to connect to the outer peripheral surface of the shroud wall portion.

The pump device described in (10) above reduces the volume filled with liquid fuel during storage of the pump device compared to the configuration shown in FIG. 2 in which no one-side extension is provided, thereby making it possible to reduce losses due to liquid pooling during startup of the pump device.

(11) In some embodiments, in the pump device according to any one of (1) to (10),
The disk portion includes at least one hollow portion (such as the hollow portion 451 described above) in addition to the through hole.

According to the pump device described in (11) above, by making part of the disk section hollow, the weight of the rotor can be reduced, and shaft vibration and power consumption can be reduced.

(12) In some embodiments, in the pump device described in (11) above,
The at least one hollow portion includes a hollow portion formed at a position different from the through hole in the circumferential direction, from a position inside the through hole to a position outside the through hole in the radial direction of the rotating body.

According to the pump device described in (12) above, by expanding the range in which the hollow portion is formed in the radial direction, the weight of the rotor can be further reduced, and the effect of reducing axial vibration and power consumption can be enhanced. In addition, by arranging the hollow portion and the through hole at different positions in the circumferential direction, it is possible to prevent leakage liquid from the pump side from flowing into the hollow portion through the through hole, thereby effectively reducing power consumption.

(13) In some embodiments, in the pump device according to any one of (11) above,
The at least one hollow portion includes a hollow portion configured in a lattice pattern.

According to the pump device described in (13) above, the hollow portion is configured in a lattice shape, which increases the strength of the disk portion, making it possible to use the pump device even under severe operating conditions in terms of stress due to high-speed rotation.

1 Pump device 2 Rotating shaft 3 Hub portion 4 Centrifugal pump blade 6 Axial turbine blade 7 Main body side casing 8 Inlet side casing 10 Pump system 10A Axial turbine 10B Centrifugal pump 11 Centrifugal flow path 12 Liquid flow path 12A Main body side axial flow path 13 Gas flow path 14 Nozzle 15 Fastening member 16, 18 Stationary wall 17 Front side gap 19 Rear side gap 20 Front side space 21 Rear side space 22, 94 Gap 25 Rotor 26 Casing 31, 36, 51, 73, 86 Outer peripheral surface 31A Concave curved surface 32 Front side end 33 Rear side end 34 Shroud wall portion 35 Disk portion 41 Tip 52, 79, 93 Inner peripheral surface 52A Convex curved surface 52B Guide surface 53 Front side end surface 54 Rear side end surface 55 Through hole 56 Rear side outer peripheral surface 57 Annular recess 58, 59 Surface 62 First seal portion 63, 90, 95 Fin set 64, 91, 96 Fin 65 Outer periphery 66 Inner periphery 67 Tapered portion 68 Second seal portion 69 Third seal portion 71 Liquid discharge passage 71A Scroll passage 72 Gas introduction passage 74 Liquid discharge port 76 End portion 77, 83 End face 78 Front side surface 80 Rear side surface 81 Liquid introduction passage 81A Inlet side axial passage 82 Gas discharge passage 85 Liquid introduction hole 87 Flange portion 88, 89 Wax 341 Front end portion 351 Outer surface 352 Rear extension portion 353 Front extension portion 354 Step portion 451 Hollow portion 521 Front end 522 Rear end 551 Front opening end 552 Rear opening end 641, 911 Abradable coating layer 710 Liquid discharge path forming portion 720 Gas introduction path forming portion 721 Gas introduction port 811 Inner surface 851 Inner opening end 852 Outer opening end LA Rotation axis

Claims (13)

A pump device including a rotating body and a casing that houses the rotating body,
The rotating body is
A hub portion,
a plurality of centrifugal pump vanes provided on an outer peripheral surface of the hub portion at intervals in a circumferential direction of the rotor;
an annular shroud wall portion formed along the circumferential direction so as to connect to tips of the centrifugal pump vanes;
an annular disk portion formed along the circumferential direction so as to protrude from an outer circumferential surface of the shroud wall portion to an outer side in a radial direction of the rotor;
a plurality of axial flow turbine blades provided at intervals in the circumferential direction on an outer peripheral surface of the disk portion;
Equipped with
a liquid flow passage is formed on an inner peripheral side of the shroud wall portion, through which liquid flowing from one side to the other side in the axial direction of the rotor flows into the centrifugal pump impeller;
a gas flow passage through which gas flowing from the other side to the one side passes through the axial flow turbine blades is formed on the outer circumferential side of the disk portion,
the shroud wall portion includes a second outer peripheral surface that is located on the second side in the axial direction relative to the disk portion and faces an inner peripheral surface of the casing with a first gap therebetween,
the disk portion includes a one-side end surface that is an end surface on the one side in the axial direction and a other-side end surface that is an end surface on the other side in the axial direction,
a first seal portion that seals a second-side gap, which is a gap in the axial direction between the second-side end face of the disk portion and the casing, is provided radially outward of the first gap;
The pump device, wherein at least one through hole penetrating in the axial direction is formed in the disk portion radially inward of the first seal portion. The pump device according to claim 1, further comprising a second seal portion that seals the axial gap between the one-side end face of the disk portion and the casing. The pump device according to claim 1 or 2, wherein a third seal portion that seals the radial gap between the outer peripheral surface of the shroud wall portion and the inner peripheral surface of the casing is provided on the one side in the axial direction from the disk portion. The pump device according to claim 2, wherein at least one of the first seal portion and the second seal portion is provided with a fin set including a plurality of fins spaced apart in the radial direction. The pump device according to claim 4, wherein the fin set is provided on the casing. The pump device according to claim 4, wherein the fin set is provided on the disk portion. The pump device according to any one of claims 4 to 6, further comprising wax arranged to seal at least one of the one-side gap and the other-side gap. The pump device according to any one of claims 4 to 6, further comprising an abradable coating layer formed on the tips of the fins. an outer surface of the disk portion includes a second side surface facing the second side in the axial direction,
9. The pump device according to claim 1, wherein, in a cross section along the axial direction, an outer surface of the disk portion includes a second-side extending portion extending from the second-side side surface along the axial direction to the second side, inwardly of the through hole in the radial direction of the rotating body, and connected to an outer peripheral edge portion of the shroud wall portion. an outer surface of the disk portion includes a side surface facing the one side in the axial direction;
10. The pump device according to claim 1, wherein, in a cross section along the axial direction, an outer surface of the disk portion includes: a one-side extending portion extending from the one-side side surface along the axial direction to the one side, radially inwardly of the rotating body relative to the through hole; and a step portion extending radially inward from an end of the one-side extending portion in the axial direction to connect to an outer peripheral surface of the shroud wall portion. The pump device according to any one of claims 1 to 10, wherein the disk portion includes at least one hollow portion in addition to the through hole. The pump device according to claim 11, wherein the at least one hollow portion includes a hollow portion formed at a position different from the through hole in the circumferential direction, from a position inside the through hole to a position outside the through hole in the radial direction of the rotor. The pump device according to claim 11, wherein the at least one hollow portion includes a hollow portion configured in a lattice pattern.

Images