Combined Power System

Abstract

To achieve cooling of a rotary electric machine and simplification of a structure of a composite power system.SOLUTION: A composite power system includes: a rotary electric machine system 10; and a gas turbine engine. The rotary electric machine system 10 has a rotary electric machine housing 14. The gas turbine engine has an engine housing. Compressed air generated by the gas turbine engine circulates through an air feeding passage 314 of a heat exchanger 310 provided at the rotary electric machine housing 14. Subsequently, the compressed air flows from the air feeding passage 314 into a housing chamber of the rotary electric machine housing 14.SELECTED DRAWING: Figure 3

Description

[Technical Field]

[0001] The present invention relates to a hybrid power system in which a rotating electrical machine system and an internal combustion engine are integrally combined. [Background technology]

[0002] A rotating electric machine includes a rotor with a rotating shaft and a stator positioned on the outer periphery of the rotor. Recently, it has been proposed to combine a rotating electric machine with a gas turbine engine to create a hybrid power system. In this case, the rotating shaft of the rotating electric machine and the output shaft of the gas turbine engine are connected on the same axis. Therefore, the rotating shaft and the output shaft rotate integrally.

[0003] A permanent magnet is held on the rotating shaft. When the rotating shaft rotates integrally with the output shaft, an alternating magnetic field is generated by the permanent magnet and the electromagnetic coil in the stator. As a result, an induced current is generated in the electromagnetic coil. In other words, in this case, the rotating electric machine functions as a generator.

[0004] When an induced current continues to occur in a rotating electric machine, the rotating electric machine heats up. As a result, the temperature of the permanent magnets rises. As the temperature of the permanent magnets approaches the Curie temperature, the magnetic force of the permanent magnets decreases. To avoid this, rotating electric machines are sometimes cooled. For example, in the technology described in Patent Document 1, compressed air obtained by a turbocharger is cooled in an aftercooler (heat exchanger). The cooled compressed air is supplied to the rotor through a duct provided in the stator of the rotating electric machine (high-speed rotating machine). This cools the stator and rotor.

[0005] Patent Document 2 describes forming a cooling jacket (water-cooled jacket) on the outer periphery of the stator. In this case, cooling water supplied to the cooling jacket removes heat from the rotating electrical machine. [Prior art documents] [Patent documents]

[0006] [Patent Document 1] Japanese Patent Application Laid-Open No. 2007-159277 [Patent Document 2] Japanese Patent Application Laid-Open No. 2012-39816 Summary of the Invention [Problem to be solved by the invention]

[0007] Compressed air is generated in a gas turbine engine. One possible approach is to send this compressed air to a rotating electrical machine and use the compressed air to cool the rotating electrical machine. However, the compressed air generated by a gas turbine engine is at a relatively high temperature. Therefore, there is a concern that using this compressed air may result in insufficient cooling of the rotating electrical machine.

[0008] The present invention aims to solve the above-mentioned problems. [Means for solving the problem]

[0009] According to one embodiment of the present invention, there is provided a compound power system including a rotating electric machine system having a rotating electric machine and a rotating electric machine housing that rotatably supports a rotating shaft of the rotating electric machine, and a gas turbine engine having an output shaft that rotates integrally with the rotating shaft and provided at one end of the rotating electric machine housing, the compound power system including a compressor wheel that is provided on the output shaft and compresses outside air to obtain compressed air, a shroud case that surrounds the compressor wheel, an engine housing that houses the compressor wheel and the shroud case, a terminal casing that is provided on an outer wall of the rotating electric machine housing and houses an electric terminal portion for transmitting and receiving electric power between the rotating electric machine and an external device, and a terminal casing formed by the gas turbine engine and the terminal casing on the outer wall of the rotating electric machine housing. and a heat exchanger disposed in a recess formed in the shroud case for lowering the temperature of the compressed air, wherein the rotating electric machine has a storage chamber that houses the rotating electric machine housing, the shroud case is formed with an air bleed port for taking the compressed air to the outside of the shroud case, the engine housing is formed with an air bleed passage through which the compressed air that has flowed into the air bleed port flows, the rotating electric machine housing is formed with a cooling jacket that surrounds the rotating electric machine from the outer periphery, the heat exchanger has a shell and an air inlet passage that is provided inside the shell and communicates with the storage chamber of the rotating electric machine housing, a cooling medium that has circulated through the cooling jacket is supplied to the inside of the shell, and the storage chamber of the rotating electric machine housing is downstream of the heat exchanger in the flow direction of the compressed air. [Effects of the Invention]

[0010] In the present invention, compressed air generated by a gas turbine engine passes through a heat exchanger and flows into the housing of the rotating electrical machine. In the heat exchanger, heat from the compressed air is absorbed by a cooling medium, thereby lowering the temperature of the compressed air. The compressed air, whose temperature has been lowered in this way, flows into the housing. Therefore, the rotating electrical machine housed in the housing is efficiently cooled.

[0011] For these reasons, the temperature of the permanent magnets constituting the rotating electric machine is prevented from reaching the Curie point. This prevents the magnetic force of the permanent magnets from decreasing. As a result, a predetermined magnetic force is generated in the alternating magnetic field formed between the permanent magnets and the electromagnetic coil. This allows the rotor to maintain high-speed rotation.

[0012] As described above, according to the present invention, the rotating electrical machine can be cooled using compressed air generated by the gas turbine engine. Therefore, it is not necessary to supply cooling air for cooling the rotating electrical machine to the housing chamber separately from the compressed air. This allows the configuration of the hybrid power system to be simplified while still cooling the rotating electrical machine. Moreover, even with this configuration, the rotor can be rotated at high speed. [Brief explanation of the drawings]

[0013] [Figure 1] FIG. 1 is a schematic overall perspective view of a combined power system according to an embodiment of the present invention. [Figure 2] FIG. 2 is a schematic perspective view of the entire rotating electrical machine system that constitutes the compound power system. [Figure 3] FIG. 3 is a schematic cross-sectional side view of the rotating electrical machine system. [Figure 4] FIG. 4 is an enlarged view of the main part of FIG. [Figure 5] FIG. 5 is an enlarged view of a main part of FIG. 3 at a location different from that of FIG. [Figure 6] FIG. 6 is a schematic diagram of a current converter provided in a housing of a rotating electrical machine. [Figure 7] FIG. 7 is a schematic perspective view of a second sub-housing that constitutes the rotary electric machine housing and an inner housing in the engine housing. [Figure 8] FIG. 8 is a schematic cross-sectional side view of the rotating electrical machine system in a phase different from that of FIG. [Figure 9] FIG. 9 is a schematic system diagram showing a compressed air flow path and a lubricating oil flow path in a rotary electric machine system. [Figure 10] FIG. 10 is a schematic cross-sectional side view of a gas turbine engine that constitutes a combined power system. [Figure 11] FIG. 11 is an enlarged view of the main part of FIG. DETAILED DESCRIPTION OF THE INVENTION

[0014] In the following description, "left," "right," "bottom," and "top" refer to the left, right, bottom, and top directions, respectively, in particular in Figures 3 to 5, 10, and 11. However, these directions are merely used for convenience to simplify the description 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.

[0015] 1 is a schematic overall perspective view of a combined power system 400 according to this embodiment. The combined power system 400 includes a rotating electric machine system 10 and a gas turbine engine 200. An axis passing through the center of the diameter of the rotating electric machine system 10 and extending along the longitudinal direction (axial direction) coincides with an axis passing through the center of the diameter of the gas turbine engine 200 and extending along the longitudinal direction (axial direction). In other words, the rotating electric machine system 10 and the gas turbine engine 200 are arranged side by side on the same axis.

[0016] Hereinafter, the left end in the axial direction of each of the rotating electric machine system 10 and the gas turbine engine 200 may be referred to as a first end. Similarly, the right end in the axial direction of each of the rotating electric machine system 10 and the gas turbine engine 200 may be referred to as a second end. That is, in the rotating electric machine system 10, the left end remote 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 remote 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.

[0017] The combined power system 400 is used as a propulsion power source in, for example, an air vehicle, a ship, or an automobile. Suitable examples of the air vehicle include a drone or a multicopters. When mounted on an air vehicle, the combined power system 400 serves as a power drive source that rotates a propeller, a ducted fan, or the like. 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.

[0018] The combined power system 400 can also be used as a power source for auxiliary power supplies in aircraft, ships, buildings, etc. In addition, the combined power system 400 can also be used as a gas turbine power generation facility.

[0019] As will be described later, the gas turbine engine 200 is an internal combustion engine and a gas supply device that supplies compressed air (gas).

[0020] First, the rotating electric machine system 10 will be described. Fig. 2 is a schematic overall perspective view of the rotating electric machine system 10. Fig. 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.

[0021] 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 has a generally cylindrical shape, and both a first end and a second end are open ends. 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.

[0022] The main housing 16 has thick side walls extending in the left-right direction. A hollow interior is formed in the main housing 16. This hollow interior is a storage chamber 22. Most of the rotating electrical machine 12 is housed in the storage chamber 22.

[0023] A cooling jacket 24 is formed in a spiral shape 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.

[0024] A first casing 26 and a second casing 28 are provided on the outer surface (outer wall) of the side wall of the main housing 16 near the edge of the first end. The first casing 26 and the second casing 28 are part of the main housing 16. In other words, the first casing 26 and the second casing 28 are provided integrally with the main housing 16. As will be described later, the first casing 26 is a terminal casing. The second casing 28 is a meter casing.

[0025] The first casing 26 has a first internal space 29. The second casing 28 has a second internal space (not shown). The first internal space 29 and the second internal space are in communication with each other via an interconnecting hole (not shown). The first internal space 29 is also in communication with the storage chamber 22.

[0026] A holding member that holds a rotation parameter detector is connected to the first sub-housing 18. In this embodiment, a resolver 132 is exemplified as the rotation parameter detector. Therefore, hereinafter, the holding member for the detector will be referred to as a "resolver holder 30." As will be described later, a cap cover 32 is connected to the resolver holder 30 via screws.

[0027] The rotating electric machine 12 includes a rotor 34 and a stator 36 that surrounds the outer periphery of the rotor 34 .

[0028] The rotor 34 includes a rotating shaft 40. The rotating shaft 40 has an inner shaft 42 and a hollow cylindrical outer shaft 44. Both ends of the outer shaft 44 are open ends. That is, the outer shaft 44 has a left open end 441 (see FIG. 4) and a right open end 442 (see FIG. 5). The inner shaft 42 is removably inserted into the outer shaft 44.

[0029] The inner shaft 42 is longer than the outer shaft 44. The inner shaft 42 has a cylindrical portion 421, a left end 422 (see FIG. 4), and a right end 423 (see FIG. 5). The left end 422 is connected to the left side of the cylindrical portion 421. Therefore, the left end 422 is an 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 side of the cylindrical portion 421. Therefore, the right end 423 is an 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 those of the left end 422 and the right end 423. Furthermore, the diameter of the right end 423 is smaller than that of the left end 422.

[0030] A part of the left end 422 is exposed from a left open end 441 of the outer shaft 44. The part exposed from the left open end 441 is a protruding tip 46, which will be described later. In the example shown in the figure, 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.

[0031] As shown in detail in FIG. 4 , the left end 422 of the inner shaft 42 is provided with a first external thread portion 48, a flange portion 50, a stopper portion 52, and a second external thread portion 54, in this order, toward the right. The outer diameters of the first external thread portion 48, the flange portion 50, the stopper portion 52, and the second external thread portion 54 increase in this order. The outer diameter of the second external thread portion 54 is larger than the inner diameter of the outer shaft 44. Therefore, the right end of the second external thread portion 54 is blocked by the edge of the left open end 441 of the outer shaft 44. Therefore, the portion of the inner shaft 42 to the left of the second external thread portion 54 cannot be inserted into the outer shaft 44.

[0032] A resolver rotor 56 is attached to the flange 50. A small cap nut 58 is screwed onto the first externally threaded portion 48. The right end of the resolver rotor 56 is positioned by the stopper portion 52. The left end of the resolver rotor 56 is pressed by the small cap nut 58. In this way, the resolver rotor 56 is positioned and fixed to the flange 50.

[0033] Furthermore, 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 so-called reverse threads. Therefore, the small cap nut 58 and the large cap nut 60 are rotated counterclockwise when threaded together. 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.

[0034] As shown in Fig. 5, a connecting hole 62 is formed in the right end 423, which is the second end, of the inner shaft 42. The connecting hole 62 extends toward the left end 422, which is the first end. An internal thread portion 64 is formed in the inner circumferential 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 coupled to the inner shaft 42 by being threaded into the internal thread portion 64. The output shaft 204 holds a compressor wheel 222 and a turbine wheel 224 (see Fig. 10).

[0035] A first internal spline 66 is formed on the outer peripheral wall of the right open end 442 of the outer shaft 44. The first internal spline 66 extends along the axial direction of the rotary electric machine system 10 (left-right direction).

[0036] As shown in Figure 3, the outer diameter of the outer shaft 44 is greatest at approximately the middle part in the longitudinal direction. A plurality of permanent magnets 72 are held in this large-diameter middle part via magnet holders 70. Adjacent permanent magnets 72 have opposite polarities facing outward. As the rotating shaft 40 rotates, the permanent magnets 72 move around the rotation center of the rotating shaft 40 on the circumference of a predetermined imaginary circle.

[0037] The left end (first end) of the rotating shaft 40 is rotatably supported by the first sub-housing 18 via a first bearing 74. As shown in FIG. 3 , the first bearing 74 is inserted between the outer shaft 44 and the first sub-housing 18. Specifically, the first sub-housing 18 has a cylindrical protrusion 76 that protrudes toward the main housing 16. A first insertion hole 78 is formed in the cylindrical protrusion 76. A first bearing holder 80 that holds the first bearing 74 is inserted into the first insertion hole 78. Therefore, the first bearing 74 is disposed in the first insertion hole 78.

[0038] 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."

[0039] A first outer stopper 81 located at a first distal end 781 and a first inner stopper 82 located at a first proximal end 782 are attached to the small-diameter left end of the outer shaft 44. The first bearing 74 is sandwiched between the first outer stopper 81 and the first inner stopper 82. The first bearing 74 is positioned and fixed based on this sandwiching. A clearance is formed between the first outer stopper 81 and the cylindrical protrusion 76.

[0040] The tip of the left end of the rotating shaft 40 is passed through the inner hole of the first bearing 74 and then passes through the first insertion hole 78. The tip of the left end of the rotating shaft 40 is further exposed outside the cylindrical protrusion 76 (hollow recess 118). Hereinafter, the portion of the rotating shaft 40 that protrudes from the left end of the first bearing 74 will be referred to as the "protruding tip 46." The protruding tip 46 includes the first externally threaded portion 48, the flange portion 50, the stopper portion 52, and the second externally threaded portion 54 of the left end 422 of the inner shaft 42 (see FIG. 4).

[0041] The right end (second end) of the rotating shaft 40 is rotatably supported by the second sub-housing 20 via a second bearing 84. As shown in Fig. 5, the second bearing 84 is inserted between the outer shaft 44 and the second sub-housing 20, which has a substantially circular plate shape.

[0042] The second sub-housing 20 is connected to the main housing 16 via bolts (not shown). The center of the second sub-housing 20 is a thick-walled cylindrical portion. A second insertion hole 86 is formed in the cylindrical portion. The second insertion hole 86 extends in the left-right direction. The left end of the second insertion hole 86 is farther from the output shaft 204 than the right end of the second insertion hole 86. Hereinafter, the left end of the second insertion hole 86 will also be referred to as the "second distal end 861." On the other hand, the right end of the second insertion hole 86 is closer to the output shaft 204 than the left end (second distal end 861) of the second insertion hole 86. Hereinafter, the right end of the second insertion hole 86 will also be referred to as the "second proximal end 862."

[0043] A second bearing holder 88 holding a second bearing 84 is inserted into the second insertion hole 86. Thus, the second bearing 84 is disposed in the second insertion hole 86. The second bearing 84 is sandwiched 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 sandwiching, the second bearing 84 is positioned and fixed.

[0044] 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 a third sub-branch path 941.

[0045] As shown in FIG. 2 , a flow straightening member 96 is connected to the end surface of the second sub-housing 20 facing the gas turbine engine 200. The flow straightening member 96 has a bottom portion 98, a reduced diameter portion 100, and a top portion 102. The bottom portion 98 facing the second sub-housing 20 is in the shape of a large-diameter, thin-walled cylindrical plate. The top portion 102 facing the gas turbine engine 200 is in the shape of a small-diameter, relatively long cylindrical plate. The reduced diameter portion 100 between the bottom portion 98 and the top portion 102 has a diameter that gradually decreases. Therefore, the flow straightening member 96 has a mountain-like shape or a cup-like shape without a bottom. The outer surface of the reduced diameter portion 100 is smooth and has low surface roughness.

[0046] An inlet 104 is formed in the end surface of the bottom portion 98 facing the second sub-housing 20. The reduced diameter portion 100 is hollow. That is, a relay chamber 106 is formed inside the reduced diameter portion 100. The inlet 104 is an input port for compressed air to enter the relay chamber 106.

[0047] An insertion hole 108 is formed in the top portion 102 along the left-right direction. The diameter (opening diameter) of the insertion hole 108 is larger than the outer diameter of the portion of the second outer stopper 92 that extends along the rotating shaft 40. Therefore, the portion of the second outer stopper 92 that has entered the insertion hole 108 and the outer peripheral wall are spaced apart from the inner wall of the insertion 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 insertion hole 108. This clearance is the fourth sub-branch passage 942. The width of the relay chamber 106 increases as it approaches the insertion hole 108 and the fourth sub-branch passage 942.

[0048] Furthermore, the diameter (opening diameter) of the insertion hole 108 is larger than the outer diameter of the left end (small diameter cylindrical portion 242), which has a relatively small diameter, of the compressor wheel 222. Therefore, the small diameter cylindrical portion 242 that has entered 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 path 943.

[0049] 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.

[0050] The stator 36, together with the rotor 34, constitutes the rotating electric machine 12. The stator 36 has an electromagnetic coil 110 and a plurality of insulating substrates 112. The electromagnetic coils 110 include three types of coils: a U-phase coil, a V-phase coil, and a W-phase coil, which are wound around the insulating substrates 112. When the rotating electric machine 12 is a generator, the rotating electric machine 12 is a so-called three-phase power supply. The plurality of insulating substrates 112 are arranged in an annular shape. This arrangement forms an inner hole in the stator 36.

[0051] The stator 36 is housed in the housing chamber 22. Here, the second sub-housing 20 serves as a stator holder. That is, the second sub-housing 20 has an annular recess 114 formed therein. An insulating base material 112 included in the stator 36 is engaged with the annular recess 114. This engagement positions and fixes the stator 36. Furthermore, the columnar protrusion 76 enters the left opening of the inner hole of the stator 36.

[0052] The inner wall of the storage chamber 22 and the electromagnetic coil 110 are spaced apart from each other by a small distance. This space electrically insulates the main housing 16 and the electromagnetic coil 110.

[0053] A clearance is formed between the outer peripheral wall of the cylindrical protrusion 76 and the insulating substrate 112. A clearance is also formed between the outer wall of the permanent magnet 72 and the inner wall of the electromagnetic coil 110. As will be described later, compressed air, which is a gas, flows through these clearances. In other words, these clearances are part of the compressed air flow path.

[0054] 4, the first sub-housing 18 has an annular protrusion 116 that protrudes in an annular shape. The inside of the annular protrusion 116 forms a hollow recess 118. The protruding tip 46, which is a part of the left end 422 of the inner shaft 42, extends into the hollow recess 118.

[0055] The resolver holder 30 is provided 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 via, for example, a mounting bolt (not shown) or the like.

[0056] In the resolver holder 30, a small cylindrical portion 122 is provided to the left of the flange-shaped stopper 120. In addition, 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. By this fitting, the resolver stator 130 is held in the resolver holder 30.

[0057] 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 a 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.

[0058] An engagement hole 134 is formed in the flange-shaped stopper 120. A transmitting connector 136 is engaged with the engagement hole 134. The resolver stator 130 and the transmitting connector 136 are electrically connected via a signal line 138. A 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 a signal emitted by the resolver 132.

[0059] The small cylindrical portion 122 is provided with a plurality of tab portions 140 (omitted in FIG. 1). One tab portion 140 is shown in FIG. 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.

[0060] 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 an external device (external load or external power source) is electrically connected. Electric power generated by the rotating electric machine 12 is supplied to the external device. An example of the external load is a motor (not shown). An example of the external device is a battery 146 shown in FIG. 6.

[0061] 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 drawn out from the second casing 28 and then connected to the electromagnetic coil 110. A harness 149 connected to the thermistor 148 is drawn out from the second casing 28 to the outside.

[0062] 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 FIG. 6, the current converter 150 has a conversion circuit 152, a capacitor 154, and a control circuit 156. The conversion circuit 152, the capacitor 154, and the 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 pipe portion 1601, the second hollow pipe portion 1602, and the third hollow pipe portion 1603 (see FIG. 1).

[0063] The hollow interiors of the first hollow pipe portion 1601, the second hollow pipe portion 1602, and the third hollow pipe portion 1603 are compressed air flow paths through which compressed air flows. That is, in this embodiment, three compressed air flow paths are formed in the rotating electrical machine housing 14. The first hollow pipe portion 1601 and the third hollow pipe portion 1603 are formed as hollow bulging portions that bulge from the outer peripheral wall of the main housing 16.

[0064] The conversion circuit 152 includes a power module 161. The conversion circuit 152 converts the AC current generated in the electromagnetic coil 110 into a 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 the DC current sent from the battery 146 into an 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.

[0065] 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 of which is shown) via an AC-DC converter, for example.

[0066] As shown in FIGS. 1 to 3, a heat exchanger 310 is installed on the outer peripheral wall of the main housing 16. The heat exchanger 310 is located on the outer peripheral wall of the main housing 16, between the gas turbine engine 200 and the first casing 26. A recess is formed in the main housing 16 by the second sub-housing 20 and the first casing 26. The heat exchanger 310 is disposed in this recess. The heat exchanger 310 is housed within the recess and does not protrude beyond the first casing 26 and the second sub-housing 20. In other words, the heat exchanger 310 is not exposed from the recess. This prevents the combined power system 400 from becoming larger due to the provision of the heat exchanger 310.

[0067] The heat exchanger 310 has a shell 312. The hollow interior (not shown) of the shell 312 is an inner chamber. A tube 314 is housed in the inner chamber. The inner hole of the tube 314 serves as an air inlet path. Although not specifically shown, the tube 314 is bent into a serpentine shape.

[0068] The second hollow tube portion 1602 has one end portion 160a connected to the tube 314 at the second end side of the heat exchanger 310. The one end portion 160a extends from the second sub-housing 20 toward the heat exchanger 310. The second hollow tube portion 1602 has the other end portion 160b connected to the tube 314 at the first end side of the heat exchanger 310. The other end portion 160b extends from the heat exchanger 310 toward the first casing 26. The hollow interior of the other end portion 160b communicates with the first internal space 29 of the first casing 26.

[0069] The inner chamber of the shell 312 communicates with the cooling jacket 24 via the communication passage 171 shown in Figure 3. Therefore, the cooling medium that has circulated through the cooling jacket 24 passes through the communication passage 171 and then flows into the inner chamber of the shell 312. In the inner chamber, the cooling medium comes into contact with the tubes 314. An exhaust pipe 172 is provided on the side of the shell 312. The cooling medium is exhausted to the outside of the shell 312 via the exhaust pipe 172.

[0070] One end 160a and the other end 160b of the second hollow tube portion 1602 are tube members that extend along the outer peripheral wall of the main housing 16. One end 160a and the other end 160b (tube members) may abut against the outer peripheral wall of the main housing 16 or may be separated from it. Alternatively, one end 160a and the other end 160b are hollow bulging portions that bulge out from the outer peripheral wall of the main housing 16.

[0071] The first hollow pipe 1601, the second hollow pipe 1602, and the third hollow pipe 1603 are spaced apart from one another at a predetermined interval (a predetermined phase difference) along the circumferential direction of the outer peripheral wall of the main housing 16. The first hollow pipe 1601 and the third hollow pipe 1603 are provided at positions that do not interfere with the heat exchanger 310. The first hollow pipe 1601 and the third hollow pipe 1603 are not located within the recess formed by the first casing 26 and the second sub-housing 20.

[0072] The rotating electrical machine system 10 configured as above is provided with a compressed air flow path (first supply path) and a lubricating oil flow path (second supply path). First, the compressed air flow path will be described.

[0073] As shown in Fig. 7, the second sub-housing 20 has an annular collecting passage 162 formed as an annular recess on its end surface facing the gas turbine engine 200. As will be described later, part of the compressed air generated by the gas turbine engine 200 flows through the collecting passage 162. Three upstream communication holes 164 are formed in the bottom wall of the collecting passage 162 (annular recess). The upstream communication holes 164 are inlets for compressed air.

[0074] Air relay paths 166 are provided inside the second sub-housing 20. The air relay paths 166 extend radially along the diameter direction of the second sub-housing 20. The air relay paths 166 communicate with the collecting flow path 162 on the outer side in the diameter direction via the upstream communication holes 164. Furthermore, three first downstream communication holes 1681 to 1683 are formed in the end face of the second sub-housing 20 facing the rotating electric machine 12. The first downstream communication holes 1681 to 1683 are first output ports of the air relay path 166. The collecting flow path 162 and the air relay paths 166 form a distribution path.

[0075] Three second downstream communicating holes 1701-1703 are formed in the end face of the second sub-housing 20 facing the gas turbine engine 200. The second downstream communicating holes 1701-1703 are second output ports of the air relay passage 166. The second downstream communicating holes 1701-1703 are located radially inward of the first downstream communicating holes 1681-1683. Therefore, the compressed air that has flowed through the air relay passage 166 is divided into compressed air that enters the first downstream communicating holes 1681-1683 (relay communicating passages) and compressed air that enters the second downstream communicating holes 1701-1703.

[0076] As shown in Fig. 2, a first hollow pipe 1601, a second hollow pipe 1602, and a third hollow pipe 1603 are provided on the outer surface of the side wall of the main housing 16. The first downstream communication holes 1681 to 1683 individually open toward the first hollow pipe 1601 to the third hollow pipe 1603, respectively. As can be seen from this, the air relay path 166 communicates between the collecting flow path 162 and the hollow interiors of the first hollow pipe 1601 to the third hollow pipe 1603. As shown in Fig. 3, the first hollow pipe 1601 to the third hollow pipe 1603 are located diametrically outward of the cooling jacket 24 formed inside the side wall of the main housing 16.

[0077] The first hollow pipe 1601 to the third hollow pipe 1603 extend along the axial direction of the main housing 16. The hollow interior of the first hollow pipe 1601 communicates with the second internal space of the second casing 28. As described above, the second hollow pipe 1602 extends from the second end facing the gas turbine engine 200 toward the first casing 26 (or the first end). The second hollow pipe 1602 passes through the inner chamber of the shell 312 along the way. The hollow interiors of the second hollow pipe 1602 and the third hollow pipe 1603 communicate with the first internal space 29 of the first casing 26.

[0078] As will be described later, the compressed air that has flowed through the hollow interior of first hollow pipe section 1601 forms an air curtain in the second internal space of second casing 28. The curtain air that has flowed through the hollow interiors of second hollow pipe section 1602 and third hollow pipe section 1603 flows into first internal space 29 of first casing 26. As can be seen from this, in the flow direction of compressed air, first casing 26 and second casing 28 are downstream of first hollow pipe section 1601 to third hollow pipe section 1603.

[0079] As described above, the first internal space 29 of the first casing 26 and the second internal space of the second casing 28 are in communication with each other via the interconnecting hole. In addition, the first internal space 29 of the first casing 26 is in communication with the storage chamber 22. Therefore, the compressed air that has flowed through the first hollow pipe portion 1601 to the third hollow pipe portion 1603 flows into the storage chamber 22 via the first internal space 29 of the first casing 26.

[0080] In this embodiment, the case where first hollow tube portion 1601 to third hollow tube portion 1603 are provided is illustrated, but the number of hollow tube portions is determined appropriately depending on the flow rate or flow speed required for the curtain air formed from compressed air. That is, the number of hollow tube portions is not limited to three. Similarly, the cross-sectional area of ​​the hollow tube portions is also determined appropriately depending on the flow rate or flow speed required for the curtain air.

[0081] The compressed air that has flowed into the storage 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, a portion of the compressed air flows through the clearance between the first sub-housing 18 and the rotor 34 and flows toward the first insertion hole 78. In this manner, the clearance between the first sub-housing 18 and the rotor 34 is the first branch path L. On the other hand, the remaining portion of the compressed air flows mainly through the clearance between the outer wall of the permanent magnet 72 and the inner wall of the electromagnetic coil 110 and flows toward the second insertion hole 86. In this manner, the clearance between the outer wall of the permanent magnet 72 and the inner wall of the electromagnetic coil 110 is the second branch path M.

[0082] The compressed air that reaches the first branch path L forms an air curtain that seals in the lubricating oil supplied to the first bearing 74. Moreover, the compressed air that reaches the third sub-branch path 941 (the second distal end 861 of the second insertion hole 86) from the second branch path M forms an air curtain that seals in the lubricating oil supplied to the second bearing 84. In this way, the compressed air that flows into the storage chamber 22 functions as curtain air.

[0083] As shown in Fig. 5, three inlets 104 are formed in the bottom portion 98 of the flow straightening member 96. Fig. 5 shows only one of the inlets. One of the inlets 104 communicates with a second downstream communicating hole 1701 (not shown). Another of the inlets 104 communicates with a second downstream communicating hole 1702 (shown). Another of the inlets 104 communicates with a second downstream communicating hole 1703 (not shown). Therefore, compressed air output from the second downstream communicating holes 1701 to 1703 enters the relay chamber 106 of the reduced diameter portion 100 of the flow straightening member 96 via the inlets 104.

[0084] 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. Therefore, as the compressed air flows through the relay chamber 106, the pressure of the curtain air decreases.

[0085] The outlet of the relay chamber 106 faces the small diameter cylindrical portion 242 of the compressor wheel 222. Therefore, the compressed air that enters the relay chamber 106 comes into contact with the small diameter cylindrical portion 242 of the compressor wheel 222. The compressed air is then divided into compressed air that flows toward the fourth sub-branch path 942 and compressed air that flows toward the outlet path 943. As a result, the pressure of the compressed air that flows along the fourth sub-branch path 942 toward the second proximal end 862 of the second insertion hole 86 decreases.

[0086] 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. In addition, the compressed air that flows into the outlet passage 943 is guided toward the inside of the first end (open end) of the shroud case 220. This compressed air is sucked back into the compressor wheel 222.

[0087] An exhaust path 173 (first exhaust path) is formed in the main housing 16. The compressed air that has reached the first branch path L and the compressed air that has reached the second branch path M are exhausted to the outside of the main housing 16 via the exhaust path 173.

[0088] Next, the lubricating oil flow path (second supply path) will be described. Fig. 8 is a schematic side cross-sectional view of the rotating electrical machine system 10. Note that Fig. 8 shows a phase different from that in Fig. 3.

[0089] An input passage 174 for supplying lubricating oil is formed in the side wall of the main housing 16. The input passage 174 is formed at a position closer to the first end than the axial center of the main housing 16. The input passage 174 extends along the diameter of the main housing 16 and communicates with a main oil passage 176. The main oil passage 176 is formed on the outer periphery of the cooling jacket 24 and extends along the axial direction of the main housing 16. The main oil passage 176 branches at the point where it communicates with the input passage 174 into a third branch passage N leading to the first sub-housing 18 and a fourth branch passage R leading to the second sub-housing 20.

[0090] A first inlet hole 178 is formed in the first sub-housing 18 at a location facing the third branch passage N. Furthermore, a first sub-oil passage 180 is formed inside the first sub-housing 18, extending radially inward of the first sub-housing 18. The first sub-oil passage 180 bends in two locations before reaching the first bearing holder 80.

[0091] A first oil supply hole 182 communicating with the first auxiliary oil passage 180 is formed in the first bearing holder 80. The outlet of the first oil supply hole 182 is formed at the first distal end 781 of the first insertion hole 78. Therefore, the lubricating oil that flows from the main oil passage 176 into the first auxiliary oil passage 180 flows from the first oil supply hole 182 to the first distal end 781 of the first insertion hole 78 and comes into contact with the first bearing 74.

[0092] 3, a first drain path 184 (one of the second discharge paths) is formed in the first sub-housing 18. The first drain path 184 discharges lubricating oil from the hollow recess 118 formed by the annular protrusion 116 of the first sub-housing 18 and the resolver holder 30.

[0093] Three third branch passages N, three first inlet holes 178, three first auxiliary oil passages 180, and three first oil supply holes 182 are formed. Similarly, three fourth branch passages R are formed. Fig. 8 shows one each of the third branch passage N, one first inlet hole 178, one first auxiliary oil passage 180, one first oil supply hole 182, and one fourth branch passage R.

[0094] 7, three oil receiving holes 186 are formed in the end face of the second sub-housing 20 facing the rotating electrical machine system 10. The oil receiving holes 186 are positioned radially outward of the first downstream communicating holes 1681 to 1683. The oil receiving holes 186 are inlets for lubricating oil.

[0095] Three second sub-oil passages 188 are provided inside the second sub-housing 20 as oil supply passages. The second sub-oil passages 188 extend radially along the diameter direction of the second sub-housing 20. However, the second sub-oil passages 188 are formed in a phase different from the phase of the air relay passage 166. In addition, three oil outflow holes 190 are formed in the end face of the second sub-housing 20 facing the gas turbine engine 200. Hollow pin portions 193 of an oil distributor 192 are fitted into the oil outflow holes 190.

[0096] A first guide passage 1941 and a second guide passage 1942 are formed inside the oil distributor 192. The lubricating oil that has passed through the second sub-oil passage 188 is separated into lubricating oil that flows through the first guide passage 1941 and lubricating oil that flows through the second guide passage 1942. The outlet of the first guide passage 1941 is located at the second proximal end 862 of the second insertion hole 86. Therefore, the lubricating oil that flows out from the first guide passage 1941 comes into contact with the second bearing 84 from the second proximal end 862.

[0097] The second guide path 1942 branches off midway from the first guide path 1941. The outlet of the second guide path 1942 is connected to the second oil supply hole 195 formed in the second bearing holder 88. Therefore, the lubricating oil that has passed through the second guide path 1942 flows out from the second oil supply hole 195 and comes into contact with the second bearing 84.

[0098] As shown in Fig. 7, two drain ports 197 and two second drain paths 196 (separate second discharge paths) are formed in the second sub-housing 20. As shown in Fig. 8, the space formed by the flow rectifying member 96 and the second outer stopper 92 communicates with the second drain paths 196 via the drain ports 197. Therefore, lubricating oil that has entered the space is discharged from the second drain paths 196 via the drain ports 197.

[0099] As shown in FIG. 9, the first drain path 184 is connected to a gas-liquid separation device 302 (one of the recovery devices / oil supply devices) via a first relay pipe 3001. The second drain path 196 is connected to the gas-liquid separation device 302 via a second relay pipe 3002. The exhaust path 173 is connected to the gas-liquid separation device 302 via a third relay pipe 3003. That is, the compressed air and lubricating oil supplied to the inside of the rotating electrical machine housing 14 are recovered in the gas-liquid separation device 302. The gas-liquid separation device 302 is provided with a circulation supply line 304 (circulation path) and a discharge line 306 (discharge path). The circulation supply line 304 is provided with a circulation pump 308, which is one of the oil supply devices.

[0100] As will be described later, the lubricating oil flowing out from the first drain path 184 and the second drain path 196 contains compressed air. That is, the lubricating oil flowing into the gas-liquid separator 302 is a gas-liquid mixture. In the gas-liquid separator 302, the gas-liquid mixture is separated into lubricating oil and air. The lubricating oil is discharged from the gas-liquid separator 302 by the circulation pump 308 and resupplied to the input path 174 via the circulation supply line 304. Meanwhile, the air is discharged to the atmosphere via the discharge line 306.

[0101] Next, the gas turbine engine 200 will be described. As shown in Fig. 10 , the gas turbine engine 200 includes an engine housing 202 and an output shaft 204 that rotates within the engine housing 202. The engine housing 202 includes an inner housing 2021 and an outer housing 2022. The inner housing 2021 is connected to the second sub-housing 20 of the rotating electrical machine system 10. The outer housing 2022 is connected to the inner housing 2021. The outer housing 2022 is a housing main body.

[0102] 1 and 7 , the inner housing 2021 has a first annular portion 206, a second annular portion 208, and a plurality of leg portions 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 leg portions 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 machine system 10. That is, the number of legs 210 is not limited to six as in the illustrated example.

[0103] A cylindrical cover portion 212 protrudes from a central opening of the second annular portion 208 toward the rotating electrical machine system 10. The right ends of the leg portions 210 are connected to both cylindrical cover portions 212. An intake space 214 is formed between the leg portions 210.

[0104] As shown in Figures 7 and 10, bleed passages 216 are individually formed inside the six leg portions 210. The inlets of the bleed passages 216 are individually formed in the leg portions 210 at the connection points with the cylindrical cover portion 212. The outlets of the bleed passages 216 are individually formed in the end surface of the first annular portion 206 facing the second sub-housing 20. All of the outlets of the bleed passages 216 are located on the circumference of an imaginary circle. Therefore, all of the outlets of the bleed passages 216 overlap with the collecting passage 162, which is formed in an annular shape. In other words, all of the multiple bleed passages 216 are communicated with the collecting passage 162. In this way, compressed air from the multiple bleed passages 216 flows into and collects in the collecting passage 162.

[0105] 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 essential to form the air vent hole 217.

[0106] 10, an annular engaging recess 218 is formed on the right end surface of the second annular portion 208. The engaging recess 218 positions and fixes the shroud case 220 and the diffuser 226 (described later).

[0107] As shown in FIG. 10, the gas turbine engine 200 further includes a shroud case 220 , a compressor wheel 222 , a turbine wheel 224 , a diffuser 226 , a combustor 228 , and a nozzle 230 .

[0108] The shroud case 220 is hollow and larger than the airflow straightening member 96. The small-diameter left end of the shroud case 220 faces the airflow straightening member 96. The large-diameter right end of the shroud case 220 is inserted into the cylindrical cover portion 212 of the inner housing 2021. The diameter of the shroud case 220 gradually decreases from the right end to the left end, but the tip of the left end is curved so as to widen outward in the radial direction.

[0109] The left end of the shroud case 220 is exposed to the intake space 214. The top portion 102 of the airflow straightening member 96 extends into the interior of the left end of the shroud case 220. An annular closing flange portion 232 is provided on the curved side peripheral wall of the shroud case 220. The outer edge of the closing flange portion 232 abuts against the inner walls of the cylindrical cover portion 212 and the leg portion 210.

[0110] 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 an entrance to the chamber 236 through which compressed air enters the chamber 236.

[0111] The chamber 236 is interposed 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 an air vent hole 217.

[0112] 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 closing 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 that is surrounded by the leg portion 210, the cylindrical cover portion 212, the second annular portion 208, the closing flange portion 232 of the shroud case 220, the side peripheral wall, and the first engagement protrusion 238. The chamber 236 forms an annular shape surrounding the shroud case 220.

[0113] The compressor wheel 222 and the turbine wheel 224 can rotate integrally with the rotary shaft 40 and the output shaft 204. That is, as shown in detail in FIG. 5 , 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 flow straightening 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.

[0114] The right open end 442 of the outer shaft 44 is press-fitted into the hollow interior of the small diameter cylindrical portion 242. Therefore, the inner peripheral wall of the left opening of the small diameter cylindrical portion 242 presses the outer peripheral wall of the right open end 442 of the outer shaft 44 radially inward. The compressor wheel 222 is connected to the outer shaft 44 (rotating shaft 40) by the above-mentioned meshing and press-fitting.

[0115] A through hole 240 extending in the left-right direction is formed in the diametric center of the compressor wheel 222. A second external spline 246 is engraved on the inner wall of the left end of this through hole 240. The diameter of the through hole 240 at a portion that communicates with the hollow interior of the small-diameter cylindrical portion 242 is slightly smaller than other portions. For this reason, an inner flange portion 248 is provided in the compressor wheel 222 near the opening of the through hole 240 on the side of the small-diameter cylindrical portion 242. The diameter of the through hole 240 is smallest at the portion where the inner flange portion 248 is provided.

[0116] 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 40. A male thread portion 252 is formed on the left end of the output shaft 204. The male thread portion 252 is threadedly engaged with a female thread portion 64 formed on the inner wall of the connecting hole 62. This threaded engagement connects the rotating shaft 40 and the output shaft 204.

[0117] 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. In addition, the left end of the output shaft 204 is press-fitted into the inner flange portion 248.

[0118] 10, a ring member 256 is interposed between the compressor wheel 222 and the turbine wheel 224. The ring member 256 is made of a heat-resistant metal material such as a nickel-based alloy.

[0119] 11 , a fitting hole 258 extending from the compressor wheel 222 to the turbine wheel 224 is formed in the ring member 256. Furthermore, a plurality of (e.g., three) labyrinth-forming protrusions 264 are formed in the outer peripheral wall of the ring member 256. The labyrinth-forming protrusions 264 protrude radially outward from the ring member 256 and extend along the circumferential direction of the outer peripheral wall. As will be described later, the labyrinth-forming protrusions 264 prevent the burned fuel (exhaust gas) generated in the combustor 228 from flowing back into the compressor wheel 222.

[0120] 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 surrounding 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. In this state, a portion of each of the compressor wheel 222 and the turbine wheel 224 is 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.

[0121] The labyrinth-forming protrusion 264 is surrounded by an intermediate plate 266 within the hollow interior of the outer housing 2022 (see FIG. 10 ). The labyrinth-forming protrusion 264 is inserted into a hole 272 formed in the intermediate plate 266. A labyrinth flow path is formed by the inner wall of the hole 272 and the labyrinth-forming protrusion 264 abutting against this inner wall. Compressed air generated by the compressor wheel 222 reaches the labyrinth-forming protrusion 264 via the back surface of the compressor wheel 222. Meanwhile, combustion gas from the turbine wheel 224 reaches the labyrinth-forming protrusion 264. Because the pressure of the compressed air is higher than the pressure of the combustion gas, the combustion gas can be prevented from passing through the labyrinth-forming protrusion 264 and flowing into the space surrounding the compressor wheel 222.

[0122] 10 , within the hollow interior of the outer housing 2022, portions of the shroud case 220 and the compressor wheel 222, and 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, is engaged with the engagement recess 218. This engagement positions and fixes the diffuser 226 to the inner housing 2021.

[0123] Within 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 passage 274 is formed between the combustor 228 and the outer housing 2022. The combustion air passage 274 is a passage through which combustion air flows. A fuel supply nozzle 275 is positioned and fixed to the right end face of the outer housing 2022. The fuel supply nozzle 275 supplies fuel to the combustor 228.

[0124] The combustor 228 is formed with relay holes 276 that connect the combustion air flow passage 274 with the interior of the combustor 228. As will be described later, combustion air compressed by the compressor wheel 222 passes through the diffuser 226, the combustion air flow passage 274, and the relay holes 276 and reaches the interior of the combustor 228. The combustor 228 is also formed with fine holes (not shown). The air discharged from the fine holes forms an air curtain that cools the interior of the combustor 228.

[0125] The nozzle 230 has a portion surrounding the largest diameter portion of the turbine wheel 224. This portion is formed with a delivery hole (not shown) for supplying combusted fuel together with combustion air to the turbine wheel 224. Note that, hereinafter, combusted fuel will also be referred to as "burned fuel." "Burned fuel" is synonymous with "combustion gas" or "exhaust gas after combustion."

[0126] An exhaust port 280 opens at the right ends of the outer housing 2022 and the nozzle 230. The burned fuel passes through the delivery holes and enters the nozzle 230, and is then 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 a discharge pipe for discharging the burned fuel.

[0127] 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 described.

[0128] First, a direct current is supplied from the battery 146. The conversion circuit 152 of the current converter 150 shown in FIGS. 2 and 6 converts this direct current into alternating current. The alternating current is supplied to the electromagnetic coils 110 (U-phase coil, V-phase coil, and W-phase coil) via the U-phase terminal 1441, the V-phase terminal 1442, and the W-phase terminal 1443. When the alternating current flows through the electromagnetic coils 110, an alternating magnetic field is generated in the stator 36. Therefore, an attractive force and a repulsive force act alternately between the electromagnetic coil 110 and the permanent magnets 72 of the rotor 34. As a result, the rotating shaft 40 starts to rotate. Alternatively, the rotating shaft 40 may be rotated by a known starter (not shown).

[0129] As shown in FIG. 5 , a first internal spline 66 is formed on the outer peripheral wall of the right open end 442 of the outer shaft 44, and a first external spline 239 is formed on the inner wall of the small-diameter cylindrical portion 242 of the compressor wheel 222. The first internal spline 66 and the first external spline 239 mesh with each other. Furthermore, a second internal spline 254 is formed on the output shaft 204, and a second external spline 246 is formed on the inner wall of the through hole 240 of the compressor wheel 222. The second internal spline 254 and the second external spline 246 mesh with each other. Therefore, the rotational torque of the rotating shaft 40 is quickly transmitted to the output shaft 204 via the compressor wheel 222.

[0130] That is, when the rotating shaft 40 starts to rotate, the output shaft 204 also starts to rotate integrally with the rotating shaft 40. Accordingly, the compressor wheel 222 and the turbine wheel 224 supported on the output shaft 204 rotate integrally with the output shaft 204. As described above, by meshing the first internal spline 66 with the first external spline 239 and meshing the second internal spline 254 with the second external spline 246, the rotational torque of the rotating shaft 40 can be sufficiently transmitted to the output shaft 204.

[0131] Moreover, the right end of the rotating shaft 40 is press-fitted into the hollow interior of the small-diameter cylindrical portion 242 of the compressor wheel 222. In addition, the left end of the output shaft 204 is press-fitted into the inner flange portion 248 of the compressor wheel 222. Therefore, the axis of the rotating shaft 40 and the axis of the output shaft 204 are precisely aligned. This sufficiently prevents the output shaft 204 from rotating eccentrically or vibrating.

[0132] In addition, as shown in FIG. 11, a ring member 256 is interposed between the compressor wheel 222 and the turbine wheel 224. An annular protrusion 268 on the right end surface of the compressor wheel 222 and a mating protrusion 270 on the left end surface of the turbine wheel 224 are fitted into a fitting hole 258 of the ring member 256. This fitting also contributes to suppressing eccentric rotation (vibration) of the output shaft 204. Therefore, there is no need to provide a mechanism for suppressing 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.

[0133] Furthermore, a frictional force is generated between the right end surface of the compressor wheel 222 and the left end surface of the ring member 256. A frictional force is also generated between the right end surface of the ring member 256 and the left end surface of the turbine wheel 224. This frictional force causes the compressor wheel 222, the ring member 256, and the turbine wheel 224 to adhere to one another. Therefore, rotational misalignment between the two wheels 222, 224 is prevented.

[0134] Furthermore, when assembling the compound power system 400, the above-described fitting allows the compressor wheel 222 and the 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 fitting holes 258 of the ring member 256. This makes it easy to center the compressor wheel 222 and the turbine wheel 224 with respect to the output shaft 204.

[0135] As a result of the rotation, as shown in FIG. 10 , air is drawn into the shroud case 220 through the air intake space 214 between the legs 210 of the inner housing 2021. The rectifying member 96 is located at the diametric center of the inner housing 2021. As described above, the rectifying member 96 has a mountain-like shape that narrows in diameter toward the shroud case 220. Furthermore, the surface of the narrowing diameter portion 100 is smooth. Therefore, the suctioned air is rectified by the rectifying member 96 so as to be directed toward the shroud case 220. Because the right end of the rectifying member 96 enters the left end opening of the shroud case 220, the air is efficiently guided into the shroud case 220. By shaping the rectifying member 96 as described above and by having the top portion 102 enter the shroud case 220, the air can be efficiently collected by the shroud case 220.

[0136] 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.

[0137] An air bleed port 234 is formed in the shroud case 220. As a result, a portion of the compressed air flows from the air bleed port 234 into a chamber 236. In other words, the compressed air is diverted. The chamber 236 is annular, and has a volume larger than the volume of the air bleed port 234. As a result, the compressed air that flows into the chamber 236 is temporarily stored in the chamber 236.

[0138] Since a plurality of bleed passages 216 are formed, compressed air is distributed from the chamber 236 to each bleed passage 216. In this case, the pressure of the distributed curtain air may differ. However, in this embodiment, the compressed air (curtain air) that has passed through the bleed port 234 flows into the single annular chamber 236. This makes the pressure of the curtain air in the chamber 236 uniform. In other words, the pressure of the curtain air is made uniform. In this way, the chamber 236 is a pressure adjustment chamber that adjusts the pressure of the curtain air to a substantially constant value.

[0139] As described above, the curtain air flowing in from the bleed port 234 is part of the compressed air and is under high pressure. Here, since the volume of the chamber 236 is larger than the volume of the bleed port 234, the curtain air diffuses as it flows into the chamber 236. This reduces the pressure of the curtain air. As can be seen from this, the chamber 236 also serves as a buffer chamber that reduces the pressure of the compressed air.

[0140] 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 to the outside of the gas turbine engine 200 (to the atmosphere) through the air vent hole 217. This prevents the pressure of the curtain air in the chamber 236 from increasing excessively. In other words, the air vent hole 217 makes it possible to easily adjust the pressure in the chamber 236.

[0141] The inlets of the bleed passages 216 formed individually in each of the six legs 210 open within the chamber 236. Therefore, the curtain air within the chamber 236 then flows individually through the six bleed passages 216, and thereby travels toward the second sub-housing 20. As described above, the pressure of the curtain air is approximately constant at this point.

[0142] 7, the outlets of the six bleed passages 216 all overlap with the collecting passage 162. Therefore, the curtain air that has flowed through the six bleed passages 216 flows into and collects in the collecting passage 162, and then diffuses in an annular shape along the collecting passage 162. In this process, the pressure of the curtain air is further uniformed.

[0143] The curtain air further flows from the collecting flow path 162 into the three upstream communication holes 164 individually, and circulates along the three air relay paths 166 individually. Then, a portion of the curtain air is discharged from the first downstream communication holes 1681-1683. The remainder of the curtain air is discharged from the second downstream communication holes 1701-1703. Hereinafter, the curtain air discharged from the first downstream communication holes 1681-1683 will be referred to as "first diverted air." The curtain air discharged from the second downstream communication holes 1701-1703 will be referred to as "second diverted air."

[0144] The path of the first diverted air will be described. The first downstream communicating hole 1681 is connected to the hollow interior of the first hollow pipe portion 1601. The first downstream communicating hole 1682 is connected to the hollow interior of one end portion 160a of the second hollow pipe portion 1602. The first downstream communicating hole 1683 is connected to the hollow interior of the third hollow pipe portion 1603. Therefore, the first diverted air flows through the hollow interiors of the first hollow pipe portion 1601 to the third hollow pipe portion 1603 shown in FIG. 1 etc., and flows from the second end to the first end of the rotating electric machine housing 14.

[0145] The first hollow pipe 1601 and the third hollow pipe 1603 are located on the outer periphery of the cooling jacket 24. A cooling medium has been flowing through the cooling jacket 24 in advance. Therefore, while the first diverted air flows along the first hollow pipe 1601 and the third hollow pipe 1603, heat of the first diverted air is sufficiently conducted to the cooling medium. This reduces the temperature of the first diverted air to a relatively low temperature. That is, in this embodiment, the cooling jacket 24, which cools the rotating electric machine 12, the current converter 150, etc., can reduce the temperature of the first diverted air.

[0146] One end 160a and the other end 160b of the second hollow tube portion 1602 are close to the cooling jacket 24. Therefore, the heat of the first diverted air flowing through the one end 160a and the other end 160b is transferred to the cooling medium flowing through the cooling jacket 24, in the same manner as described above.

[0147] In addition, as shown in FIGS. 3 and 9, one end 160a and the other end 160b are connected to tubes 314 (see FIG. 3) that constitute the heat exchanger 310. That is, the compressed air that has flowed through one end 160a flows into the tubes 314. As described above, the cooling medium that has flowed through the cooling jacket 24 flows into the inner chamber of the shell 312 via the communication path 171. Therefore, the heat of the first diverted air flowing through the tubes 314 is transferred to the cooling medium flowing through the inner chamber of the shell 312. This further lowers the temperature of the first diverted air flowing through the hollow interior of the second hollow pipe portion 1602. In this way, the heat exchanger 310 can further lower the temperature of a portion of the first diverted air.

[0148] For the reasons described above, there is no need to provide a separate cooling facility for cooling the curtain air in the gas turbine engine 200 or the rotating electrical machine system 10. Therefore, the size of the combined power system 400 can be reduced.

[0149] Furthermore, the cooling medium that has circulated through the cooling jacket 24 is supplied to the inner chamber of the shell 312 of the heat exchanger 310. That is, the same cooling medium is used in the cooling jacket 24 and the heat exchanger 310. Therefore, it is not necessary to supply the cooling medium separately to each of the cooling jacket 24 and the heat exchanger 310. This makes it possible to simplify the mechanism for supplying or circulating the cooling medium.

[0150] The first diverted air that has flowed through the first hollow pipe portion 1601 flows into the second internal space of the second casing 28, as shown in Fig. 2. This forms an air curtain inside the second casing 28. Excess first diverted air flows into the first internal space 29 of the first casing 26 through the interconnecting hole.

[0151] The first diverted air flow that has flowed through the second hollow pipe portion 1602 and the third hollow pipe portion 1603 flows into the first internal space 29 of the first casing 26. Therefore, in the first internal space 29, an air curtain is formed by the first diverted air flow that has flowed through the first hollow pipe portion 1601 to the third hollow pipe portion 1603.

[0152] 3, the excess first diverted air flows from the first internal space 29 into the storage chamber 22 of the main housing 16. As can be understood from this, the first internal space 29 and the second internal space are upstream in the flow direction of the first diverted air. In other words, the storage chamber 22 and the rotating electrical machine 12 are located downstream of the first casing 26 and the second casing 28 in the flow direction of the first diverted air.

[0153] 9 shows only the first diverted air flow passing through the heat exchanger 310. However, after flowing into the storage chamber 22, the first diverted air flowing through the first hollow pipe portion 1601 and the third hollow pipe portion 1603 also flows through the same route as the first diverted air flowing through the heat exchanger 310.

[0154] 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 in from the left end of the storage chamber 22. The first diverted air then enters the clearance between the outer peripheral wall of the cylindrical protrusion 76 and the insulating base material 112. This clearance is the inner hole of the stator 36.

[0155] A portion of the first diverted air then flows toward the first insertion hole 78 via the first branch path L. The remainder of the first diverted air flows toward the second insertion hole 86 via the second branch path M, along the clearance between the outer wall of the permanent magnet 72 and the inner wall of the electromagnetic coil 110. In this way, the first diverted air branches into compressed air flowing toward the first insertion hole 78 at the left end (first end) and compressed air flowing toward the second insertion hole 86 at the right end (second end).

[0156] The first diverted air flows along the clearance between the outer wall of the permanent magnet 72 and the inner wall of the electromagnetic coil 110, thereby cooling the rotating electric machine 12. Here, as described above, the temperature of the first diverted air is sufficiently reduced by the cooling jacket 24 and the heat exchanger 310. Therefore, the rotating electric machine 12 is efficiently cooled.

[0157] In other words, the first diverted air flow prevents the temperature of the permanent magnets 72 from rising. This prevents the temperature of the permanent magnets 72 from reaching the Curie temperature. This prevents the magnetic force of the permanent magnets 72 from decreasing. As a result, a predetermined magnetic force is generated in the alternating magnetic field formed between the permanent magnets 72 and the electromagnetic coil 110. This allows the rotor 34 to maintain high-speed rotation.

[0158] Furthermore, in this embodiment, the rotating electric machine 12 is cooled using compressed air generated by the gas turbine engine 200. Therefore, there is no need to supply cooling air to the housing 22 to cool the rotating electric machine 12. This allows the rotating electric machine 12 to be cooled while simplifying the configuration of the combined power system 400.

[0159] A portion of the first diverted air flowing toward the first insertion hole 78 reaches the first proximal end 782 of the first insertion hole 78. At this first proximal end 782, this portion of the first diverted air becomes an air curtain for the first bearing 74. Meanwhile, the remainder of the first diverted air flowing toward the second insertion hole 86 passes through the third sub-branch path 941 and reaches the second distal end 861 of the second insertion hole 86. At this second distal end 861, this portion of the first diverted air becomes an air curtain for the second bearing 84.

[0160] The path of the second diverted air will now be described. The second downstream communication holes 1701-1703 overlap with three inlets 104 formed in the bottom portion 98 of the rectifying member 96. Therefore, the second diverted air flows into the relay chamber 106 (the hollow interior of the rectifying member 96) through the inlets 104.

[0161] As described above, the outlet of the relay chamber 106 opens at a position facing the small diameter cylindrical portion 242 of the compressor wheel 222. Therefore, the second diverted air that flows into the relay chamber 106 comes into contact with the small diameter cylindrical portion 242. A portion of the second diverted air then flows toward the fourth sub-branch path 942. The remainder of the second diverted air flows toward the outlet path 943.

[0162] A portion of the second diverted air reaches the second proximal end 862 of the second insertion hole 86 via the fourth sub-branch passage 942. At the second proximal end 862, the portion of the second diverted air forms an air curtain around the second bearing 84. In this manner, 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.

[0163] The remainder of the second diverted air is discharged through the outlet passage 943 to the inside of the left end of the shroud case 220. As described above, air is being drawn into the opening at the left end of the shroud case 220. Therefore, the remainder of the second diverted air is compressed by the compressor wheel 222 together with the drawn-in atmospheric air.

[0164] The excess first diverted air passes through the storage chamber 22 and reaches the exhaust path 173. The excess second diverted air flows from the second end to the first end of the main housing 16, for example, via a clearance between the inner wall of the storage chamber 22 and the electromagnetic coil 110. Thereafter, the excess second diverted air reaches the exhaust path 173. The first diverted air and second diverted air that have reached the exhaust path 173 are collected in the gas-liquid separator 302 (collection device) via the third relay pipe 3003.

[0165] As described above, the pressure of the curtain air is made uniform by the chamber 236 provided between the inner housing 2021 and the shroud case 220. Therefore, the occurrence of pressure distribution in the curtain air is avoided. Furthermore, the occurrence of surging in the curtain air is also avoided. Therefore, it is possible to supply the curtain air to the periphery of the first bearing 74 and the second bearing 84 while maintaining the pressure of the curtain air substantially constant.

[0166] As described above, the width of the relay chamber 106 increases as it approaches the fourth sub-branch path 942. Moreover, 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 remainder that flows toward the outlet path 943. Therefore, the pressure of the second diverted air that has reached 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 has reached the second distal end 861 and the pressure of the second diverted air that has reached the second proximal end 862 are balanced.

[0167] In the above, a so-called shell-and-tube heat exchanger is used as the heat exchanger 310. Alternatively, a so-called plate-fin heat exchanger can be used as the heat exchanger 310. Since plate-fin heat exchangers are well known, they are not specifically illustrated and will only be described briefly.

[0168] In this case, a stack of plate fins is housed inside the hollow interior of the shell 312. An outgoing pipe and a returning pipe are provided in the stack. The outgoing pipe and the returning pipe extend parallel to each other along the stacking direction of the stack. One end of the outgoing pipe and one end of the returning pipe communicate with each other.

[0169] The cooling medium that has passed through the cooling jacket 24 passes through the outgoing pipe, thereby circulating in the stacking direction of the laminate. Thereafter, the cooling medium passes through the return pipe, thereby circulating in the stacking direction of the laminate in the opposite direction to the direction in which it passed through the outgoing pipe.

[0170] While the cooling medium flows through the outgoing pipe and the return pipe in this manner, compressed air that has flowed through one end 160a of second hollow tube portion 1602 flows into the interior of shell 312. The compressed air passes through the gaps between adjacent plate fins in the interior of shell 312. That is, in this case, the gaps between the plate fins are air inlet paths through which the compressed air passes.

[0171] At this time, the heat of the compressed air is transferred to the cooling medium. As a result, the temperature of the compressed air drops. Therefore, the cooled compressed air flows into the other end 160b of the second hollow tube portion 1602. Thereafter, the compressed air flows into the storage chamber 22 in the same manner as described above.

[0172] Next, the route of the lubricating oil will be described. The lubricating oil is supplied to the first bearing 74 and the second bearing 84 as a lubricant.

[0173] The lubricating oil is recovered in the gas-liquid separator 302 (oil recovery device) shown in FIG. 9 and separated from the curtain air, and is then pushed out by a circulation pump 308. The lubricating oil is supplied to an input passage 174 formed in the main housing 16 via a circulation supply line 304. The lubricating oil flows from the input passage 174 into a main oil passage 176. The main oil passage 176 branches into a third branch passage N leading to the first sub-housing 18 and a fourth branch passage R leading to the second sub-housing 20. Therefore, the lubricating oil is separated into lubricating oil flowing along the third branch passage N and lubricating oil flowing along the fourth branch passage R. Hereinafter, the lubricating oil flowing along the third branch passage N will be referred to as the "first branch oil." The lubricating oil flowing along the fourth branch passage R will be referred to as the "second branch oil."

[0174] The first diverted oil flows into the first auxiliary oil passage 180 via the first inlet hole 178 formed in the first sub-housing 18. The first diverted oil is then supplied to the first distal end 781 of the first insertion hole 78 via the first oil supply hole 182 formed in the first bearing holder 80. The first diverted oil further enters the inner hole of the first bearing 74 and lubricates the first bearing 74.

[0175] The first diverted oil that flows from the first distal end 781 to the first proximal end 782 is blocked by the first diverted air (air curtain) that reaches the first proximal end 782. This prevents the first diverted oil from flowing toward the first branch path L. This also prevents the first diverted oil from entering between the rotating shaft 40 and the electromagnetic coil 110. This prevents the rotating electric machine 12 from being contaminated with the first diverted oil.

[0176] The excess first divided oil flows into the hollow recess 118. A first drain path 184 is provided in the hollow recess 118. Therefore, the first divided oil in the hollow recess 118 is collected in the gas-liquid separator 302 via the first drain path 184.

[0177] The second branched oil that has flowed through the fourth branched passage R flows into the second auxiliary oil passage 188 via an oil receiving hole 186 formed in the second sub-housing 20. The second branched oil that has flowed through the second auxiliary oil passage 188 is branched into a first guide passage 1941 and a second guide passage 1942 formed inside the oil distributor 192. A portion of the second branched oil that flows out from the outlet of the first guide passage 1941 is supplied to the second proximal end 862 of the second insertion hole 86. The remainder of the second branched oil that has passed through the second guide passage 1942 is supplied to the second bearing 84 via a second oil supply hole 195 formed in the second bearing holder 88. The second branched oil enters the inner bore of the second bearing 84 and lubricates the second bearing 84.

[0178] The second diverted oil that has entered the inner hole of the second bearing 84 is surrounded by the first diverted air supplied to the second distal end 861 and the second diverted air supplied to the second proximal end 862. As described above, the pressure of the first diverted air supplied to the second distal end 861 and the pressure of the second diverted air supplied to the second proximal end 862 are balanced. This prevents the second diverted oil from flowing toward the third sub-branch channel 941 or the fourth sub-branch channel 942. This prevents the second diverted oil from entering between the rotating shaft 40 and the electromagnetic coil 110. This also prevents the second diverted oil from entering the relay chamber 106 of the rectifying member 96. This prevents the rotating electric machine 12 and the rectifying member 96 from being contaminated with the second diverted oil.

[0179] As described above, the pressure of the curtain air is adjusted to a substantially constant level. Therefore, an air curtain of a predetermined pressure is continuously formed around the first bearing 74 and the second bearing 84. This prevents lubricating oil from leaking from the first bearing 74 and the second bearing 84.

[0180] The excess second diverted oil flows into a space formed by the rectifying member 96 and the second outer stopper 92. A drain port 197 and a second drain path 196 are formed in the second sub-housing 20. The second diverted oil that flows into the space is collected in the gas-liquid separator 302 via the drain port 197 and the second drain path 196.

[0181] As described above, the curtain air and lubricating oil are recovered in the gas-liquid separator 302. Here, since the lubricating oil is blocked by the air curtain inside the rotary electric machine housing 14, the curtain air exhausted from the exhaust path 173 contains lubricating oil. In other words, the curtain air exhausted from the exhaust path 173 is substantially a gas-liquid mixture.

[0182] In this embodiment, the recovery device also serves as the gas-liquid separator 302. Therefore, the gas-liquid mixture is separated into air and lubricating oil. The air is discharged to the atmosphere via a discharge line 306 provided in the gas-liquid separator 302. Meanwhile, the lubricating oil is pushed out of the gas-liquid separator 302 by a circulation pump 308. The lubricating oil is further resupplied from the gas-liquid separator 302 to the first bearing 74 and the second bearing 84 via a circulation supply line 304. While the rotating shaft 40 rotates, the first bearing 74 and the second bearing 84 are cooled by the lubricating oil.

[0183] In this way, by separating the gas-liquid mixture into lubricating oil and air by the gas-liquid separator 302, it is possible to prevent so-called air entrapment from occurring in the circulation supply line 304 and the circulation pump 308. Therefore, it is possible to resupply the lubricating oil to the first bearing 74 and the second bearing 84 at an appropriate discharge pressure or flow rate. As a result, the first bearing 74 and the second bearing 84 are sufficiently lubricated. As a result, it is possible to prevent the first bearing 74 and the second bearing 84 from seizing.

[0184] Moreover, air curtains are formed in the second branch path M, the third sub-branch path 941, and the fourth sub-branch path 942. These air curtains prevent the lubricating oil from entering the first internal space 29 and the second internal space. This prevents the lubricating oil from adhering to the U-phase terminal 1441, the V-phase terminal 1442, the W-phase terminal 1443, the thermistor 148, and the like. In other words, it is possible to prevent the electrical terminals, the measuring device (thermistor 148), and the like from being soiled with the lubricating oil.

[0185] As described above, the curtain air (first diverted air and second diverted air) prevents the lubricating oil from scattering from the first bearing 74 and the second bearing 84. The curtain air is then discharged to the outside of the rotating electric machine housing 14 as described above. Therefore, even if lubricating oil leaks from the first bearing 74 or the second bearing 84, the leaked lubricating oil is carried along with the curtain air and discharged to the outside of the rotating electric machine housing 14. This prevents the leaked lubricating oil from flowing toward the rotor 34. It also prevents the leaked lubricating oil from remaining in the rotor 34.

[0186] As described above, the pressure of the curtain air continuously supplied to the rotating electrical machine housing 14 is substantially constant. Therefore, it is possible to continuously prevent the lubricating oil from scattering. Furthermore, even if the lubricating oil leaks, the leaked lubricating oil can be continuously discharged to the outside of the rotating electrical machine housing 14.

[0187] Compressed air that passes between the shroud case 220 and the compressor wheel 222 without entering the bleed port 234 becomes combustion air. As shown in Fig. 10, the combustion air flows into the diffuser 226. The combustion air flows from an outlet hole formed in the wall of the diffuser 226 into a combustion air flow passage 274 between the combustor 228 and the outer housing 2022. The combustion air further flows into the combustion chamber (the hollow interior of the combustor 228) through a relay hole 276 formed in the combustor 228, the fine holes, the clearance between the combustor 228 and the fuel supply nozzle 275, and the like.

[0188] 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, producing high-temperature burned fuel. When this burned fuel is supplied into the nozzle 230 from the delivery holes, it expands within the nozzle 230. This causes the turbine wheel 224 to begin rotating at a high speed.

[0189] 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 integrally at high speed. At the same time, the rotating shaft 40 also rotates at high speed. The burned fuel is discharged to the outside of the outer housing 2022 through a discharge pipe (not shown) provided at the discharge port 280.

[0190] The ring member 256 interposed between the compressor wheel 222 and the turbine wheel 224 also serves as a sealing member that seals the gap between the two wheels 222, 224. Furthermore, as shown in FIG. 11 , a plurality of 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 passes through the back surface of the compressor wheel 222 and reaches the labyrinth-forming protrusions 264. 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 the reasons described above, the burnt fuel is prevented from entering the through-hole 240 from between the wheels 222, 224, for example.

[0191] 10, when output shaft 204 starts to rotate at high speed, the supply of current from battery 146 (see FIG. 6) to electromagnetic coil 110 is stopped. However, because turbine wheel 224 is already rotating at high speed as described above, rotating shaft 40 rotates at high speed integrally with turbine wheel 224 and output shaft 204. Even at this time, for the same reason as described above, sufficient rotational torque is transmitted from output shaft 204 to rotating shaft 40.

[0192] 3, the rotation direction of the output shaft 204 and the rotating shaft 40 is preferably opposite to the rotation direction of the small cap nut 58, the large cap nut 60, and the male threaded portion 252 when they are screwed together. In this case, the small cap nut 58, the large cap nut 60, and the male threaded portion 252 are prevented from loosening during rotation of the rotating shaft 40. Note that the small cap nut 58, the large cap nut 60, or the male threaded portion 252 may be provided with a mechanism to prevent loosening.

[0193] Because the rotating shaft 40 holds the permanent magnet 72, an AC current is generated in the electromagnetic coil 110 surrounding the permanent magnet 72. The AC current is sent to the current converter 150 shown in FIGS. 2 and 6 via a U-phase terminal 1441, a V-phase terminal 1442, and a W-phase terminal 1443. A conversion circuit 152 of the current converter 150 converts this AC current into a DC current. When a 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, the control circuit 156 supplies a DC current to the battery 146 (see FIG. 6) via a capacitor 154. This charges the battery 146.

[0194] During this process, the current converter 150, particularly the conversion circuit 152 and the capacitor 154, become heated. However, in this embodiment, the conversion circuit 152 and the capacitor 154 in the device case 158 are located close to the cooling jacket 24. Therefore, the heat of the conversion circuit 152 and the capacitor 154 is quickly conducted to the cooling medium in the cooling jacket 24. This prevents the conversion circuit 152 and the capacitor 154 from becoming excessively hot.

[0195] The electromagnetic coil 110 generates heat as current flows through it. Here, a portion of the first diverted air comes into contact with the left end of the stator 36. Furthermore, the remaining portion of the first diverted air, which passes through the storage chamber 22 and heads toward the second insertion hole 86, comes into contact with the outer and inner walls of the stator 36. Therefore, the stator 36 is cooled by the first diverted air. Furthermore, a cooling medium flows through the cooling jacket 24 provided on the main housing 16. The rotating electric machine 12 is quickly cooled by this cooling medium. This also allows the alternating magnetic field formed between the permanent magnet 72 and the electromagnetic coil 110 to generate a predetermined magnetic force.

[0196] 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, the V-phase terminal 1442, and the W-phase terminal 1443 are provided separately. Therefore, the heat generated in the stator 36 in the main housing 16 is unlikely to affect the U-phase terminal 1441, the V-phase terminal 1442, and the W-phase terminal 1443 in the first casing 26. Note that the U-phase terminal 1441, the V-phase terminal 1442, and the W-phase terminal 1443 also generate heat when current is applied. However, the U-phase terminal 1441, the V-phase terminal 1442, and the W-phase terminal 1443 are quickly cooled by the first diverted air flow supplied to the first casing 26.

[0197] In this way, the first diverted air also serves to cool heat-generating locations in the rotating electric machine system 10. Because the electrical terminals (U-phase terminal 1441, V-phase terminal 1442, and W-phase terminal 1443), the electromagnetic coil 110, the permanent magnet 72, etc. are cooled, the influence of heat on the output control of the rotating electric machine system 10, etc. is avoided. In addition, a decrease in the excitation of the electromagnetic coil 110, the permanent magnet 72, etc. due to heat is also avoided. As a result, the reliability of the rotating electric machine system 10 is improved.

[0198] 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, the V-phase terminal 1442, and the W-phase terminal 1443 are provided separately, the rotating electric machine 12 and the electrical terminals are spaced apart from each other. Therefore, the U-phase terminal 1441, the V-phase terminal 1442, and the 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, the V-phase terminal 1442, and the 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.

[0199] While the rotating shaft 40 is rotating, the rotation angle (rotation parameter) of the rotating shaft 40 is detected by the resolver 132. Specifically, the resolver rotor 56 fitted onto the left end 422 of the inner shaft 42 rotates integrally with the rotating shaft 40. As a result, an electrical signal generated in the resolver stator 130 is transmitted to the receiver via the transmission connector 136. The receiver reads the electrical signal and calculates the rotation angle of the rotating shaft 40 based on the electrical signal. The receiver sends the calculation result to a control device or the like (not shown). The control device or the like calculates the rotation speed based on this rotation angle.

[0200] The resolver 132 is disposed on the rotating shaft 40 at the protruding tip 46 exposed from the rotating electric machine housing 14. Therefore, the resolver 132 is less likely to be affected by heat generated in the electromagnetic coil 110 of the stator 36 inside the rotating electric machine housing 14. The resolver 132 is also less likely to be affected by vibrations generated as the rotor 34 rotates. In addition, the first bearing 74 and the second bearing 84 that support the rotating shaft 40 are provided inside the rotating electric machine housing 14. Therefore, the rotating electric machine housing 14 suppresses vibration of the first bearing 74 and the second bearing 84. This also makes it less likely that the resolver 132 will be affected by vibrations.

[0201] As described above, in this embodiment, the transmission of heat, vibrations, and the like to the resolver 132 is suppressed. This results in accurate detection of the rotation angle by the resolver 132. In addition, the life of the resolver 132 is also extended.

[0202] There may be cases where the resolver 132 is replaced with another resolver having a larger inner diameter and outer diameter. If a single solid rotating shaft is used as the rotating shaft, replacing it with a resolver having a larger inner diameter and outer diameter requires replacing it with a larger-diameter solid rotating shaft. In this case, it is not easy to pass the large-diameter solid rotating shaft through the first bearing 74 and the second bearing 84.

[0203] In this embodiment, the rotating shaft 40 is made up of the outer shaft 44 and the inner shaft 42. The outer shaft 44 is passed through the first bearing 74 and the second bearing 84, and the resolver rotor 56 is provided on the inner shaft 42 at a portion exposed from the outer shaft 44. Therefore, when replacing the resolver 132 with another resolver having larger inner and outer diameters, this can be achieved by simply replacing the inner shaft 42 with an inner shaft having a larger diameter at the left end 422. As can be seen from this, according to this embodiment, by replacing the inner shaft 42, it is possible to accommodate resolvers with various inner and outer diameters.

[0204] 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 flow is supplied from the first sub-branch channel to the first distal end 781, and a portion of the first diverted air flow 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.

[0205] In the gas turbine engine 200, the compressor wheel 222 and the turbine wheel 224 may be arranged in the opposite direction to that shown in Figure 10. In this case, a through hole 240 may be formed in the turbine wheel 224, and the compressor wheel 222 may be provided with the output shaft 204. Alternatively, the compressor wheel 222 and the turbine wheel 224 may be of a centrifugal type or an axial flow type. As long as the compressor wheel 222 and the turbine wheel 224 are arranged on the same axis, a combination of a centrifugal type and an axial type multi-stage compressor wheel and a multi-stage turbine wheel may be used.

[0206] 3, the rotating electric machine 12 constituting the rotating electric machine system 10 may be a motor in which the rotating shaft 40 rotates when current is applied to the electromagnetic coil 110. In this case, the U-phase terminal 1441, the V-phase terminal 1442, and the W-phase terminal 1443 are electrical terminal portions that receive power from the battery 146.

[0207] As described above, this embodiment relates to a compound power system (400) including a rotating electric machine system (10) having a rotating electric machine (12) and a rotating electric machine housing (14) that rotatably supports a rotating shaft (40) of the rotating electric machine, and a gas turbine engine (200) having an output shaft (204) that rotates integrally with the rotating shaft and that is provided at one end of the rotating electric machine housing, the compound power system (400) including a compressor wheel (222) that is provided on the output shaft and compresses outside air to obtain compressed air, a shroud case (220) that surrounds the compressor wheel, an engine housing (202) that houses the compressor wheel and the shroud case, a terminal casing (26) that is provided on the outer wall of the rotating electric machine housing and that houses electrical terminal units (1441-1443) for transmitting and receiving electric power between the rotating electric machine and an external device, and a terminal casing (26) that is provided on the outer wall of the rotating electric machine housing and that houses the electrical terminal units (1441-1443) for transmitting and receiving electric power between the rotating electric machine and an external device, and a gas turbine engine (200) that is provided on the outer wall of the rotating electric machine housing. and a heat exchanger (310) disposed in a recess formed by the gin and the terminal casing for lowering the temperature of the compressed air, wherein the rotating electric machine has a storage chamber (22) for accommodating the rotating electric machine housing, the shroud case is formed with an air bleed port (234) for taking the compressed air out of the shroud case, the engine housing is formed with an air bleed passage (216) through which the compressed air that has flowed into the air bleed port flows, the rotating electric machine housing is formed with a cooling jacket (24) surrounding the rotating electric machine from the outer periphery, the heat exchanger has a shell (312) and an air inlet passage (314) provided inside the shell and communicating with the storage chamber of the rotating electric machine housing, a cooling medium that has circulated through the cooling jacket is supplied to the inside of the shell, and the storage chamber of the rotating electric machine housing is downstream of the heat exchanger in the flow direction of the compressed air.

[0208] In this configuration, compressed air generated by the gas turbine engine passes through the heat exchanger and flows into the storage chamber of the rotating electrical machine housing. In the heat exchanger, heat from the compressed air is absorbed by the cooling medium, thereby lowering the temperature of the compressed air. The cooled compressed air then flows into the storage chamber. This allows efficient cooling of the rotating electrical machine housed in the storage chamber.

[0209] This cooling prevents the temperature of the permanent magnets that make up the rotating electrical machine from reaching the Curie point. This prevents the magnetic force of the permanent magnets from decreasing. As a result, a predetermined magnetic force is generated in the alternating magnetic field formed between the permanent magnets and the electromagnetic coil. This allows the rotor to maintain high-speed rotation.

[0210] As described above, according to the present invention, the rotating electrical machine can be cooled using compressed air generated by the gas turbine engine. Therefore, it is not necessary to supply cooling air for cooling the rotating electrical machine to the housing chamber separately from the compressed air. This allows the configuration of the hybrid power system to be simplified while still cooling the rotating electrical machine. Moreover, even with this configuration, the rotor can be rotated at high speed.

[0211] The heat exchanger is disposed in a recess formed by the gas turbine engine and the terminal casing. That is, the heat exchanger is contained within the recess and is not exposed from the recess. This prevents the combined power system from becoming larger in size due to the heat exchanger being provided on the outer wall of the rotating electrical machine housing.

[0212] Furthermore, the cooling medium that has circulated through the cooling jacket is supplied to the heat exchanger, eliminating the need to separately supply cooling medium to the cooling jacket and the heat exchanger, thereby simplifying the mechanism for supplying or circulating the cooling medium.

[0213] This embodiment discloses a composite power system in which the terminal casing has an internal space (29), the air supply path is connected to the storage chamber of the rotating electric machine housing via the internal space of the terminal casing, and the storage chamber of the rotating electric machine housing is downstream of the internal space of the terminal casing in the flow direction of the compressed air.

[0214] In this case, an air curtain is formed in the internal space of the terminal casing. This air curtain protects the electrical terminal portion. Therefore, the electrical terminal portion is prevented from being contaminated with, for example, lubricating oil supplied to the bearing. In addition, the air curtain can cool the electrical terminal portion.

[0215] This embodiment discloses a composite power system that includes a first bearing (74) and a second bearing (84) for rotatably supporting the rotating shaft in the rotating electric machine housing, and compressed air that has passed through the air supply passage is supplied to the first bearing and the second bearing within the rotating electric machine housing.

[0216] The compressed air supplied to the first bearing and the second bearing cools the first bearing and the second bearing, thereby preventing the first bearing and the second bearing from seizing.

[0217] This embodiment discloses a compound power system in which the first bearing and the second bearing are lubricated by lubricating oil.

[0218] The compressed air supplied to the first bearing and the second bearing forms an air curtain around the first bearing and the second bearing. This air curtain seals the lubricating oil supplied to the first bearing and the second bearing. This prevents the lubricating oil from leaking outside a predetermined area. This prevents the rotating electrical machine, measuring instruments, rotation parameter detectors, terminals, etc. from being contaminated with the lubricating oil.

[0219] In addition, because the air curtain seals out the lubricating oil, there is no need for a sealing member, which reduces the number of components (parts), making it possible to make the combined power system smaller and simpler.

[0220] This embodiment discloses a composite power system in which compressed air flow passages (1601, 1603) are formed in the outer wall of the rotating electric machine housing at a position that does not interfere with the heat exchanger, and a distribution passage is formed in the rotating electric machine housing for distributing the compressed air that has circulated through the bleed passage to the air inlet passage of the heat exchanger and the compressed air flow passage.

[0221] The compressed air generated by the gas turbine engine is at high pressure. By distributing this high-pressure air to a plurality of compressed air flow passages, the pressure of the compressed air supplied to the housing of the rotating electrical machine can be sufficiently reduced.

[0222] This embodiment discloses a compound power system in which a plurality of bleed passages including the bleed passage are formed, and the compressed air that has flowed through the plurality of bleed passages flows into the distribution passage.

[0223] In this case, the compressed air is distributed to each of the plurality of bleed passages, and therefore the pressure of the compressed air can be reduced before the compressed air flows into the distribution passage.

[0224] This embodiment discloses a compound power system in which the distribution passage has one collecting passage (162) into which compressed air from the plurality of bleed passages individually flows in, and a plurality of relay communication passages that individually communicate the one collecting passage with each of the plurality of compressed air flow passages.

[0225] Since all outlets of the multiple bleed passages are connected to the collecting passage, the compressed air that has flowed through the multiple bleed passages is collected in the collecting passage. The compressed air then diffuses along the collecting passage. In this process, the pressure of the compressed air is equalized. Furthermore, since multiple relay communication passages are provided, it is possible to supply compressed air to multiple destinations.

[0226] This embodiment discloses a compound power system in which the collecting passage is annular, and the plurality of relay communication passages are arranged radially.

[0227] With this configuration, the plurality of bleed passages can be easily connected to the compressed air flow passage.

[0228] This embodiment discloses a composite power system in which the rotating shaft has a hollow cylindrical outer shaft (44) and an inner shaft (42) that is longer than the outer shaft and is removably inserted inside the outer shaft, and one end of the inner shaft is exposed from the outer shaft.

[0229] For example, when replacing a rotation parameter detector with another rotation parameter detector having a larger inner diameter and outer diameter, the inner shaft can be replaced with an inner shaft having a larger diameter at one end exposed from the outer shaft. In other words, with this configuration, by replacing the inner shaft, it is possible to accommodate rotation parameter detectors having a variety of different inner and outer diameters.

[0230] The present invention is not limited to the above disclosure, and various configurations can be adopted without departing from the gist of the present invention. [Explanation of symbols]

[0231] 10... Rotating electric machine system 12... Rotating electric machine 14... Rotating electric machine housing 22... Storage room 24...Cooling jacket 26...First casing 28... Second casing 29... First internal space 30...Resolver holder 34...Rotor 36... Stator 40... Rotating shaft 42...Inner shaft 44...Outer shaft 46...Protruding tip 56...Resolver rotor 72...Permanent magnet 74...First bearing 84... Second bearing 96... Flow straightening member 106...Relay room 108...Through hole 110... electromagnetic coil 130... resolver stator 132...Resolver 136...Transmission connector 146...Battery 148...Thermistor 150...current converter 152...conversion circuit 154... Capacitor 156... Control circuit 161...power module 162...collecting flow path 164...Upstream communication hole 166...Air relay path 171...Connecting passage 172...Exhaust pipe 173...Exhaust passage 174...Input passage 176…Main oilway 180…1st sub-oilway 184...First drain passage 188...Second auxiliary oil passage 192...Oil distributor 196...Second drain path 197...Drain port 200...Gas turbine engine 202...engine housing 204...output shaft 210... Leg 214... Intake space 216... Bleed passage 217... Air vent hole 220...Shroud case 222...Compressor wheel 224...Turbine wheel 226...Diffuser 228...combustor 230...nozzle 234...Air extraction port 236...Chamber 256...Ring member 274...Combustion air flow passage 275...Fuel supply nozzle 276...Relay hole 302...gas-liquid separator 304...circulation supply line 308...Circulation pump 310...Heat exchanger 312...Shell 314...Tube 400...Composite power system 781...First distal end 782...First proximal end 861...Second distal end 862...Second proximal end 941...Third sub-branch 942...Fourth sub-branch 1441...U-phase terminal 1442...V phase terminal 1443...W phase terminal 1601...First hollow tube section 1602...Second hollow tube section 1603...Third hollow pipe section 1681~1683...First downstream communication hole 1701~1703...Second downstream communication hole 2021...Inner housing 2022...Outer housing 3001...First relay pipe 3002...Second relay pipe 3003...Third relay pipe L...First fork M...Second fork N...3rd fork R...4th fork

Claims

1. a rotating electric machine system including a rotating electric machine and a rotating electric machine housing that rotatably supports a rotating shaft of the rotating electric machine; a gas turbine engine having an output shaft that rotates integrally with the rotary shaft and that is provided at one end of the rotary electric machine housing; A combined power system comprising: a compressor wheel provided on the output shaft and compressing outside air to obtain compressed air; a shroud case surrounding the compressor wheel; an engine housing that houses the compressor wheel and the shroud case; a terminal casing provided on an outer wall of the rotary electric machine housing and accommodating an electric terminal portion for transmitting and receiving electric power between the rotary electric machine and an external device; a heat exchanger disposed in a recess formed by the gas turbine engine and the terminal casing in the outer wall of the rotary electric machine housing, for lowering a temperature of the compressed air; Equipped with the rotating electric machine has a storage chamber that houses the rotating electric machine housing, an air bleed port for extracting the compressed air to the outside of the shroud case is formed in the shroud case; a bleed passage through which the compressed air that has flowed into the bleed port flows is formed in the engine housing; a cooling jacket is formed in the rotating electric machine housing to surround the rotating electric machine from an outer periphery side; the heat exchanger has a shell and an air inlet passage provided inside the shell and communicating with the storage chamber of the rotating electrical machine housing, and a cooling medium that has circulated through the cooling jacket is supplied to the inside of the shell; In a hybrid power system, the storage chamber of the rotating electrical machine housing is located downstream of the heat exchanger in the flow direction of the compressed air.

2. 2. The compound power system according to claim 1, wherein the terminal casing has an internal space, and the air supply passage communicates with the storage chamber of the rotating electrical machine housing through the internal space of the terminal casing; In a compound power system, the storage chamber of the rotating electrical machine housing is located downstream of the internal space of the terminal casing in the flow direction of the compressed air.

3. 2. The combined power system according to claim 1, further comprising a first bearing and a second bearing for rotatably supporting the rotary shaft in the rotary electric machine housing, A compound power system in which compressed air that has passed through the air inlet passage is supplied to the first bearing and the second bearing within the rotating electrical machine housing.

4. 4. The compound power system of claim 3, wherein said first bearing and said second bearing are lubricated with lubricating oil.

5. 2. The combined power system according to claim 1, wherein a compressed air flow passage is formed in an outer wall of the rotating electrical machine housing at a position that does not interfere with the heat exchanger, and a distribution passage is formed in the rotating electrical machine housing for distributing the compressed air that has circulated through the air bleed passage to the air inlet passage of the heat exchanger and the compressed air flow passage.

6. 6. A compound power system according to claim 5, wherein a plurality of bleed passages including said bleed passage are formed, and said compressed air having flowed through said plurality of bleed passages flows into said distribution passage.

7. 7. A compound power system according to claim 6, wherein the distribution passage has one collecting passage into which compressed air from the plurality of bleed passages individually flows, and a plurality of relay communication passages individually communicating the one collecting passage with each of the plurality of compressed air flow passages.

8. 8. A compound power system according to claim 7, wherein said collecting passage is annular, and said plurality of relay communication passages are arranged radially.

9. 9. A compound power system according to claim 1, wherein the rotating shaft comprises a hollow cylindrical outer shaft and an inner shaft that is longer than the outer shaft and is removably inserted into the outer shaft, and one end of the inner shaft is exposed from the outer shaft.

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