Hybrid system

Abstract

A hybrid system is disclosed. A compressor impeller (222) is provided on an output shaft. A suction port (234) is formed on a shroud case (220) that surrounds the compressor impeller. A plurality of suction passages (216) are formed on an engine case (202) that surrounds the shroud case. An annular chamber (236) for storing compressed air sucked from the suction port is formed between the suction port and the suction passages. Accordingly, the pressure of the compressed air can be homogenized in the chamber.

Description

TECHNICAL FIELD

[0001] The present application relates to a hybrid power system in which a rotary electric machine system and an internal combustion engine are combined. BACKGROUND

[0002] A rotary electric machine has a rotor and a stator, wherein the rotor has a rotation axis; the stator is located at the outer periphery of the rotor. A hybrid power system is disclosed in Japanese Patent Application Publication No. 2002-147250 and Japanese Patent Application Publication No. 2003-120210, which combines such a rotary electric machine and a gas turbine engine as one of internal combustion engines. In this case, the rotation axis of the rotary electric machine and the output shaft of the gas turbine engine are connected on the same axis. Therefore, the rotation axis and the output shaft rotate integrally.

[0003] Most of the rotary electric machine is housed in a rotary electric machine housing. A bearing is interposed between the rotation axis and the rotary electric machine housing. Through the bearing, the rotation axis is rotatably supported to the rotary electric machine housing. As described in Japanese Patent Application Publication No. 2016-174443, lubricating oil is supplied to the bearing.

[0004] A permanent magnet is held on the rotation axis. In the technology described in Japanese Patent Application Publication No. 2016-174443, a cover member is arranged between the stator and the rotor in order to avoid the lubricating oil from adhering to the permanent magnet (see, in particular, Japanese Patent Application Publication No. 2016-174443 Figure 1 ). An O-ring is mounted on the cover member. The O-ring seals between the cover member and the stator. Through the sealing, the lubricating oil is prevented from being immersed from between the cover member and the stator. SUMMARY

[0005] Compressed air is generated in the gas turbine engine. It can be considered to lead the compressed air to the rotary electric machine so as to form an air curtain around the bearing. In this case, the air curtain functions as a seal, and thus it is desired that the O-ring is no longer needed.

[0006] The pressure of the compressed air generated in the gas turbine engine can vary. For example, when the compressed air with reduced pressure is supplied to the rotary electric machine, the sealing based on the air curtain can not be sufficient.

[0007] An object of the present application is to solve the above-described technical problem.

[0008] According to an embodiment of the present application, there is provided a hybrid power system having a rotary electric machine system and an internal combustion engine, wherein

[0009] The rotating electric machine system has a rotating electric machine and a rotating electric machine housing that supports a rotating shaft of the rotating electric machine in such a manner that the rotating shaft is rotatable;

[0010] The internal combustion engine has an output shaft that rotates integrally with the rotating shaft,

[0011] The hybrid system has a compressor impeller, a shroud housing, a turbine impeller, a diffuser, and an engine housing, wherein

[0012] The compressor impeller is provided to the output shaft and obtains compressed air by compressing outside air;

[0013] The shroud housing surrounds the compressor impeller;

[0014] The turbine impeller is provided to the output shaft;

[0015] The diffuser diffuses the compressed air that passes between the compressor impeller and the shroud housing;

[0016] The engine housing surrounds the shroud housing, the diffuser, and the compressor impeller,

[0017] An air intake port for taking out the compressed air to the outside of the shroud housing is formed on the shroud housing,

[0018] A plurality of air intake passages are formed on the engine housing, and the compressed air taken out from the air intake port flows through the plurality of air intake passages,

[0019] An annular chamber for storing the compressed air is formed between the air intake port and the plurality of air intake passages.

[0020] In the case where the compressed air is distributed from the air intake port to the plurality of air intake passages, the distributed compressed air can be different in pressure from each other. However, in the present application, the compressed air that passes through the air intake port flows into a single chamber that is annular. Accordingly, the pressure of the compressed air in the chamber is uniform. That is, the pressure of the compressed air is homogenized.

[0021] In addition, when the compressed air that passes through the air intake port flows into the chamber, the compressed air diffuses in the chamber. By this diffusion, the pressure of the compressed air decreases.

[0022] Therefore, the compressed air is prevented from generating a pressure distribution. In addition, the compressed air is also prevented from generating a pressure fluctuation (variation). Therefore, it is possible to keep the pressure of the compressed air substantially constant. Such compressed air can be used, for example, as air curtain air that surrounds a bearing in a rotating electric machine housing.

[0023] The above objects, features and advantages will be easily understood from the following description of the embodiments with reference to the attached drawings. BRIEF DESCRIPTION OF DRAWINGS

[0024] Figure 1 is a schematic overall perspective view of a hybrid system to which an embodiment of the present application pertains.

[0025] Figure 2 is a schematic overall perspective view of a rotary electric machine system that constitutes the hybrid system.

[0026] Figure 3 is a schematic side cross-sectional view of the rotary electric machine system.

[0027] Figure 4 is a main part enlarged view of Figure 3 .

[0028] Figure 5 is a main part enlarged view of Figure 4 , Figure 3 part different from .

[0029] Figure 6 is a schematic structural view of a converter provided to a rotary electric machine housing.

[0030] Figure 7 is a schematic perspective view of a second sub-housing and an inner housing in an engine housing that constitute the rotary electric machine housing.

[0031] Figure 8 is a schematic side cross-sectional view of the rotary electric machine system in a phase different from that of Figure 3 .

[0032] Figure 9 is a schematic system view that schematically represents a lubricating oil flow path (second supply path) in the rotary electric machine system.

[0033] Figure 10 is a schematic side cross-sectional view of a gas turbine engine that constitutes the hybrid system.

[0034] Figure 11 is a main part enlarged view of Figure 10 .

[0035] Figure 12 is a schematic side cross-sectional view in a case where a compression pump provided externally is used as a gas supply source. DETAILED DESCRIPTION

[0036] The following "left", "right", "lower" and "upper" each refer to Figures 3-5 , Figure 10 , Figure 11left, right, lower, and upper in the drawings. However, these directions are convenient directional designations for ease of understanding, and are not necessarily the directions when the hybrid system is actually used.

[0037] Figure 1 is a schematic overall perspective view of the hybrid system 400 to which the present embodiment pertains. The hybrid system 400 has the rotary electric machine system 10 and the gas turbine engine 200. The axis that passes through the diametric center of the rotary electric machine system 10 and extends in the lengthwise direction (axial direction) and the axis that passes through the diametric center of the gas turbine engine 200 and extends in the lengthwise direction (axial direction) coincide. In other words, the rotary electric machine system 10 and the gas turbine engine 200 are juxtaposed on the same axis.

[0038] Hereinafter, the left end of the axial direction of each of the rotary electric machine system 10 and the gas turbine engine 200 will be referred to as the first end. Likewise, the right end of the axial direction of each of the rotary electric machine system 10 and the gas turbine engine 200 will be referred to as the second end. That is, in the rotary electric machine system 10, the left end portion away from the gas turbine engine 200 is the first end. In the rotary electric machine system 10, the right end portion close to the gas turbine engine 200 is the second end. In addition, in the gas turbine engine 200, the left end portion close to the rotary electric machine system 10 is the first end. In the gas turbine engine 200, the right end portion away from the rotary 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 rotary electric machine system 10. The rotary electric machine system 10 is disposed at the first end of the gas turbine engine 200.

[0039] The hybrid system 400 is used as a power source for propulsion, for example, in a flying body, a ship, a motor vehicle, or the like. As a preferred specific example of a flying body, a drone or a multicopter, or the like can be cited. The hybrid system 400 is used as a power driving source that drives a propeller, a ducted propeller, or the like in rotation, for example, when mounted on a flying body. The hybrid system 400 is used as a propeller-rotating force generating device when mounted on a ship. The hybrid system 400 is used as a power driving source that drives a motor in rotation when mounted on a motor vehicle.

[0040] The hybrid system 400 can also be used as a power source for an auxiliary power source in an aircraft, a ship, a building, or the like. In addition to this, the hybrid system 400 can be used as a gas turbine power generation device.

[0041] As will be described later, the gas turbine engine 200 is an internal combustion engine. In addition, the gas turbine engine 200 is a gas supply device that supplies compressed air (gas).

[0042] First, the rotating electric machine system 10 will be described. Figure 2 is a schematic overall perspective view of the rotating electric machine system 10. Figure 3 is a schematic side cross-sectional view of the rotating electric machine system 10. The rotating electric machine system 10 has a rotating electric machine 12 (e.g., a generator) and a rotating electric machine case 14 that houses the rotating electric machine 12.

[0043] The rotating electric machine case 14 has a main case 16, a first sub-case 18, and a second sub-case 20. The main case 16 is substantially cylindrical in shape, and both a first end and a second end are open ends. The first sub-case 18 is connected to the first end (left open end) of the main case 16. The second sub-case 20 is connected to the second end (right open end) of the main case 16. In this way, the first end and the second end of the main case 16 are closed.

[0044] The main case 16 has a thick side wall that extends in the left-right direction. A housing cavity 22 is formed in the inside of the side wall. Most of the rotating electric machine 12 is housed in the housing cavity 22.

[0045] A spiral-shaped cooling jacket 24 is formed in the inside of the side wall of the main case 16. A cooling medium flows through the cooling jacket 24. As a specific example of the cooling medium, cooling water can be given. In this case, the cooling jacket 24 is a water jacket.

[0046] On the outer surface (outer side wall) of the side wall of the main case 16, near the edge portion of the first end, a first outer case 26 and a second outer case 28 are provided. The first outer case 26 and the second outer case 28 are parts of the main case 16. That is, the first outer case 26 and the second outer case 28 are provided integrally with the main case 16. As will be described later, the first outer case 26 is a terminal outer case. The second outer case 28 is a gauge outer case.

[0047] On the first sub-case 18, a holding member for holding a rotating parameter detector is connected. In the present embodiment, the rotating parameter detector is exemplified by a resolver 132. Therefore, hereafter, the holding member for the detector will be referred to as a "resolver holder 30". As will be described later, a cover 32 is connected to the resolver holder 30 by a screw.

[0048] The rotating electric machine 12 has a rotor 34 and a stator 36 that surrounds the outer periphery of the rotor 34.

[0049] 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 Figure 4 ) and a right open end 442 (see Figure 5 ). The inner shaft 42 is inserted into the inside of the outer shaft 44 in a pluggable manner.

[0050] The inner shaft 42 is longer than the outer shaft 44. The inner shaft 42 has a cylindrical portion 421 and a left end portion 422 (see reference). Figure 4 ) and right end 423 (refer to) Figure 5 The left end portion 422 is connected to the left side of the cylindrical portion 421. Therefore, the left end portion 422 is the end of the inner shaft 42 furthest from the gas turbine engine 200 (first end). The right end portion 423 is connected to the right side of the cylindrical portion 421. Therefore, the right end portion 423 is the end of the inner shaft 42 closest to the gas turbine engine 200 (second end). The diameter of the cylindrical portion 421 is smaller than that of both the left end portion 422 and the right end portion 423. Furthermore, the diameter of the right end portion 423 is smaller than that of the left end portion 422.

[0051] A portion of the left end portion 422 protrudes from the left opening end 441 of the outer shaft 44. The portion protruding from the left opening end 441 is the protruding tip 46, which will be described later. Additionally, in the illustrated example, the right end portion 423 of the inner shaft 42 and the right opening end 442 of the outer shaft 44 are coplanar. However, the right end portion 423 may also be located slightly towards the second end from the right opening end 442.

[0052] like Figure 4 As shown in detail, at the left end 422 of the inner shaft 42, a first external thread portion 48, a flange portion 50, a limiting portion 52, and a second external thread portion 54 are sequentially arranged to the right. The outer diameters of the first external thread portion 48, the flange portion 50, the limiting portion 52, and the second external thread portion 54 increase sequentially. 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 opening end 441 of the outer shaft 44. Therefore, the portion of the inner shaft 42 that is to the left of the second external thread portion 54 will not be inserted into the outer shaft 44.

[0053] A rotary transformer rotor 56 is mounted on the flange portion 50. Additionally, a small cap nut 58 is threaded onto the first external thread portion 48. The right end of the rotary transformer rotor 56 is blocked by a limiting portion 52. The left end of the rotary transformer rotor 56 is pressed by the small cap nut 58. Accordingly, the rotary transformer rotor 56 is positioned and fixed to the flange portion 50.

[0054] Furthermore, the large cap nut 60 is screwed into 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. Accordingly, the left end portion 422 of the inner shaft 42 is restricted by the left open end 441 of the outer shaft 44. In addition, 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 rotate counterclockwise when screwed in. Preferably, after screwing in, a portion of the threads of the small cap nut 58 and the large cap nut 60 are deformed. Accordingly, the small cap nut 58 and the large cap nut 60 are prevented from loosening.

[0055] likeFigure 5 As shown, a connecting hole 62 is formed at the second end, i.e., the right end 423, of the inner shaft 42. The connecting hole 62 extends toward the left end 422, which is the first end. An internal thread 64 is engraved on the inner peripheral wall of the connecting hole 62. The left end of the output shaft 204 is inserted into the connecting hole 62. The left end of the output shaft 204 is connected to the inner shaft 42 by screwing it with the internal thread 64. The output shaft 204 holds the compressor wheel 222 and the turbine wheel 224 (see reference). Figure 10 ).

[0056] Furthermore, a first internal spline 66 is formed on the outer peripheral wall of the right opening end 442 of the outer shaft 44. The first internal spline 66 extends along the axial direction (left-right direction) of the rotary motor system 10.

[0057] like Figure 3 As shown, the outer diameter of the outer shaft 44 is largest approximately at its midpoint along its length. At the midpoint of this large diameter, a plurality of permanent magnets 72 are held by a magnet holder 70. Adjacent permanent magnets 72 have opposite polarities facing outwards. The permanent magnets 72 move around a defined imaginary circle about the center of rotation of the rotation shaft 40 as the shaft rotates.

[0058] The left end (first end) of the rotating shaft 40 is rotatably supported on the first sub-housing 18 by the first bearing 74. Figure 3 As shown, 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 protruding towards the main housing 16. A first insertion hole 78 is formed in the cylindrical protrusion 76. A first bearing cage 80 holding 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.

[0059] 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 (first distal end 781) of the first insertion hole 78. Hereinafter, the right end of the first insertion hole 78 will also be referred to as the "first proximal end 782".

[0060] A first outer limiting portion 81 located at the first distal end 781 and a first inner limiting portion 82 located at the first proximal end 782 are installed at the left end of the minor diameter of the outer shaft 44. The first bearing 74 is clamped by the first outer limiting portion 81 and the first inner limiting portion 82. Based on this clamping, the first bearing 74 is positioned and fixed. A gap is formed between the first outer limiting portion 81 and the cylindrical protrusion 76.

[0061] The top end of the left end portion of the rotation shaft 40 passes through the first insertion hole 78 after passing through the inner hole of the first bearing 74. The top end of the left end portion of the rotation shaft 40 also emerges to the outside (hollow recess 118) of the cylindrical protrusion 76. Hereinafter, the portion of the rotation shaft 40 that protrudes from the left end of the first bearing 74 will be referred to as the "protruding top end 46". The protruding top end 46 includes the first external thread portion 48 in the left end portion 422 of the inner shaft 42, the flange portion 50, the stop portion 52, and the second external thread portion 54 (refer to Figure 4 ) in the right end portion 424 of the inner shaft 42.

[0062] The right end (second end) of the rotation shaft 40 is rotatably supported by the second bearing 84 to the second sub-housing 20. As shown in Figure 5 , the second bearing 84 is inserted between the outer shaft 44 and the substantially circular plate-shaped second sub-housing 20.

[0063] The second sub-housing 20 is connected to the main housing 16 by bolts, not shown. The center of the second sub-housing 20 is a thick cylindrical portion. The second insertion hole 86 is formed in the thick 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".

[0064] The second bearing holder 88 that holds the second bearing 84 is inserted into the second insertion hole 86. Therefore, the second bearing 84 is disposed in the second insertion hole 86. The second bearing 84 is clamped by the second inner stop portion 90 at the second distal end 861 and the second outer stop portion 92 at the second proximal end 862. Based on this clamping, the second bearing 84 is positioned and fixed.

[0065] In addition, at the second distal end 861, a gap is formed between the second inner stop portion 90 and the second bearing holder 88. This gap is the third sub-branch path 941.

[0066] As shown in Figure 2As shown, a flow straightener 96 is connected to the end face of the second sub-casing 20 facing the gas turbine engine 200. The flow straightener 96 has a lower end 98, a reduced diameter end 100, and a top end 102. The lower end 98 facing the second sub-casing 20 is a large-diameter and relatively thin cylindrical plate shape. The top end 102 facing the gas turbine engine 200 is a small-diameter and relatively long cylindrical plate shape. The diameter of the reduced diameter end 100 between the lower end 98 and the top end 102 gradually decreases. Therefore, the flow straightener 96 is a mountain-shaped body or a bottomless cup-shaped body. The outer surface of the reduced diameter end 100 is a smooth surface with low surface roughness.

[0067] An inlet 104 is formed on the end face of the lower hem 98 facing the second sub-casing 20. Furthermore, the reduced diameter section 100 is hollow. That is, a relay chamber 106 is formed inside the reduced diameter section 100. The inlet 104 is an inlet for supplying compressed air into the relay chamber 106.

[0068] At the top 102, a through hole 108 is formed in the left-right direction. The diameter (opening diameter) of the through hole 108 is larger than the outer diameter of the portion of the second outer limiting portion 92 extending along the rotation axis 40. Therefore, the portion of the second outer limiting portion 92 that enters the through hole 108 and its outer peripheral wall are far from the inner wall of the through hole 108. In other words, a gap is formed between the outer peripheral wall of the second outer limiting portion 92 and the inner wall of the through hole 108. This gap is the fourth sub-branch path 942. The relay chamber 106 widens as it approaches the through hole 108 and the fourth sub-branch path 942.

[0069] Furthermore, the diameter (opening diameter) of the through-hole 108 is larger than the outer diameter of the smaller left end (small-diameter cylindrical portion 242) of the compressor impeller 222. Therefore, the small-diameter cylindrical portion 242 entering the through-hole 108 is also located away from the inner wall of the through-hole 108. In other words, a gap is formed between the outer peripheral wall of the small-diameter cylindrical portion 242 and the inner wall of the through-hole 108. This gap is the outlet path 943.

[0070] like Figure 3 As shown, the first insertion hole 78 and the third branch path 941 are connected to the receiving cavity 22. Therefore, the first bearing 74 and the second bearing 84 are exposed to the receiving cavity 22.

[0071] The stator 36, together with the rotor 34 described above, constitutes the rotary motor 12. The stator 36 has electromagnetic coils 110 and multiple insulating substrates 112. The electromagnetic coils 110 have three types of coils: U-phase coils, V-phase coils, and W-phase coils, which are wound around the insulating substrates 112. In the case where the rotary motor 12 is a generator, it is a so-called three-phase power supply. The multiple insulating substrates 112 are arranged in a circular ring shape. This arrangement forms an inner hole in the stator 36.

[0072] The stator 36 is housed in the housing cavity 22. Here, the second housing 20 functions as a stator retainer. Specifically, an annular recess 114 is formed in the second housing 20. The insulating substrate 112 included in the stator 36 engages with this annular recess 114. Through this engagement, the stator 36 is positioned and fixed. Furthermore, the cylindrical protrusion 76 enters the left opening of the inner bore of the stator 36.

[0073] The inner wall of the receiving cavity 22 and the electromagnetic coil 110 are slightly separated from each other. Through this separation, the main housing 16 and the electromagnetic coil 110 are electrically insulated.

[0074] A gap is formed between the outer peripheral wall of the cylindrical protrusion 76 and the insulating substrate 112. A gap 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, as a gas, flows through these gaps. In other words, these gaps are part of the compressed air flow path.

[0075] like Figure 4 As shown, the first housing 18 has an annular protrusion 116 that protrudes in a circular shape. The inner side of the annular protrusion 116 forms a hollow recess 118. The protruding tip 46, which is part of the left end 422 of the inner shaft 42, enters the hollow recess 118.

[0076] A rotary transformer holder 30 is provided on the annular protrusion 116. The rotary transformer holder 30 has a flange-shaped limiting portion 120 protruding outward in the diametrical direction. The diameter of the flange-shaped limiting portion 120 is larger than the inner diameter of the annular protrusion 116. Therefore, the flange-shaped limiting portion 120 abuts against the annular protrusion 116. Through this abutment, the rotary transformer holder 30 is positioned. In this state, the rotary transformer holder 30 is connected to the first sub-housing 18, for example, by mounting bolts (not shown).

[0077] A small cylindrical portion 122 is provided on the left side of the flange-shaped limiting portion 120 of the rotary transformer cage 30. A large cylindrical portion 124 is provided on the right side of the flange-shaped limiting portion 120. The diameter of the large cylindrical portion 124 is larger than that of the small cylindrical portion 122. A retaining hole 126 is formed in the rotary transformer cage 30. Most of the rotary transformer stator 130 is fitted into the retaining hole 126. Through this fitting, the rotary transformer stator 130 is held in the rotary transformer cage 30.

[0078] When the large cylindrical portion 124 enters the hollow recess 118 and the flange-like stop portion 120 abuts against the annular protrusion 116, the resolver rotor 56 is positioned in the inner hole of the resolver stator 130. The resolver 132 is configured of the resolver stator 130 and the resolver rotor 56. The resolver 132 is a rotation parameter detector. In the present embodiment, the resolver 132 detects the rotation angle of the inner shaft 42. In addition, as described above, the resolver rotor 56 is held by the flange portion 50 of the left end portion 422 of the inner shaft 42.

[0079] The flange-like stop portion 120 is formed with an engagement hole 134. A transmission connector 136 is engaged with the engagement hole 134. The resolver stator 130 and the transmission connector 136 are electrically connected by a signal line 138. In addition, a reception connector of a receiver (not shown) is inserted into the transmission connector 136. The resolver 132 and the receiver are electrically connected by the transmission connector 136 and the reception connector. The receiver receives a signal emitted from the resolver 132.

[0080] A plurality of lug portions 140 (one of which is shown in Figure 1 ) are provided in the small cylindrical portion 122. One of the lug portions 140 is shown in Figure 3 . Further, a cover 32 covers the small cylindrical portion 122. The cover 32 closes the left opening of the small cylindrical portion 122 and shields the left end portion 422 of the inner shaft 42. In addition, the cover 32 is connected to the lug portion 140 by a connection bolt 142.

[0081] As described above, the first housing 26 and the second housing 28 are integrally provided in the side wall near the left end of the main housing 16. The U-phase terminal 1441, the V-phase terminal 1442, and the W-phase terminal 1443 are housed in the first housing 26. 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 terminal portions to which an external device (an external load or an external power supply) is electrically connected. The electrical power generated by the rotary electric machine 12 is supplied to the external device. As the external load, for example, an electric motor (not shown) can be mentioned. In addition, as the external device, for example, a battery 146 shown in Figure 6 can be mentioned.

[0082] The second housing 28 is adjacent to the first housing 26. A thermistor 148 as a temperature measurer is housed in the second housing 28. The measurement terminal of the thermistor 148 is connected to the electromagnetic coil 110 after being led out of the second housing 28, but is not particularly shown. A wire harness 149 connected to the thermistor 148 is led out of the second housing 28 to the outside.

[0083] The interior space of the second housing 28 and the interior space of the first housing 26 are communicated through a not-illustrated intercommunication hole. In addition, the interior space of the first housing 26 is communicated with the accommodation cavity 22.

[0084] As shown in Figure 1 and As shown in Figure 2 , a converter 150 is provided to the outer peripheral wall of the main casing 16. The converter 150 is located closer to the gas turbine engine 200 than the first housing 26. As shown in Figure 6 , the converter 150 has a conversion circuit 152, a capacitor 154, and a control circuit 156. These conversion circuit 152, capacitor 154, and control circuit 156 are accommodated in an equipment housing 158. The equipment housing 158 is, for example, arranged at a position of the outer peripheral wall of the main casing 16 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 Figure 1 ).

[0085] The hollow interiors of the first hollow pipe portion 1601, the second hollow pipe portion 1602, and the third hollow pipe portion 1603 are relay communication paths for the passage of compressed air. That is, in the present embodiment, three relay communication paths are formed in the rotating electric machine casing 14.

[0086] The conversion circuit 152 includes a power supply module 161. The conversion circuit 152 converts the alternating current generated by the electromagnetic coil 110 into direct current. At this time, the capacitor 154 temporarily stores the direct current converted by the conversion circuit 152 as electric charge. The conversion circuit 152 also functions to convert the direct current delivered from the battery 146 into alternating current. In this case, the capacitor 154 temporarily stores the direct current delivered from the battery 146 to the electromagnetic coil 110 as electric charge.

[0087] The control circuit 156 controls the current density of the direct current flowing from the capacitor 154 to the battery 146, or the direct current flowing in the opposite direction, and the like. In addition, the direct current from the battery 146 is supplied to a motor (none of which is illustrated) via an alternating current-direct current converter, for example.

[0088] In the rotating electric machine system 10 configured as described above, a compressed air flow path (first supply path) and a lubricating oil flow path (second supply path) are provided. First, the compressed air flow path will be described.

[0089] As shown in Figure 7As shown, an annular flow path 162, consisting of annular recesses, is formed on the end face of the second housing 20 facing the gas turbine engine 200. As described later, a portion of the compressed air generated by the gas turbine engine 200 flows through the flow path 162. Upstream communication holes 164 are formed at three locations on the bottom wall of the flow path 162 (annular recesses). The upstream communication holes 164 are the input ports for compressed air.

[0090] An air relay path 166 is provided inside the second sub-housing 20. The air relay path 166 extends radially along the diameter of the second sub-housing 20. The air relay path 166 is connected to the collection flow path 162 via an upstream communication hole 164 on its outer diameter side. In addition, three first downstream communication holes 1681 to 1683 are formed on the end face of the second sub-housing 20 facing the rotary motor 12. The first downstream communication holes 1681 to 1683 are the first output ports of the air relay path 166. A distribution path is formed through the collection flow path 162 and the air relay path 166.

[0091] Three second downstream communication holes 1701-1703 are formed on the end face of the second housing 20 facing the gas turbine engine 200. The second downstream communication holes 1701-1703 are the second output ports of the air relay path 166. The second downstream communication holes 1701-1703 are located diametrically inward of the first downstream communication holes 1681-1683. Therefore, the compressed air flowing through the air relay path 166 is divided into compressed air entering the first downstream communication holes 1681-1683 and compressed air entering the second downstream communication holes 1701-1703.

[0092] like Figure 2 As shown, first hollow tube sections 1601 to 3 hollow tube sections 1603 are provided on the outer surface of the side wall of the main housing 16. First downstream connecting holes 1681 to 1683 are individually opened on the first hollow tube sections 1601 to 3 hollow tube sections 1603, respectively. Therefore, the air relay path 166 connects the collecting flow path 162 and the hollow interiors of the first hollow tube sections 1601 to 3 hollow tube sections 1603. Figure 3 As shown, the first hollow tube section 1601 to the third hollow tube section 1603 are located outside the diameter direction of the cooling jacket 24 formed inside the side wall of the main housing 16.

[0093] The first to third hollow pipe portions 1601 to 1603 extend in the axial direction of the main housing 16. The hollow interior of the first hollow pipe portion 1601 communicates with the interior space of the second housing 28. The hollow interiors of the second and third hollow pipe portions 1602 and 1603 communicate with the interior space of the first housing 26. As will be described later, the air curtain air that has flowed through the hollow interior of the first hollow pipe portion 1601 flows into the interior space of the second housing 28. The air curtain air that has flowed through the hollow interiors of the second and third hollow pipe portions 1602 and 1603 flows into the interior space of the first housing 26. It will thus be understood that the first and second housings 26 and 28 are disposed at positions downstream of the portions of the first to third hollow pipe portions 1601 to 1603 that are located outside the cooling jacket 24.

[0094] As described above, the interior space of the first housing 26 and the interior space of the second housing 28 communicate with each other through the communication hole. In addition, the interior space of the first housing 26 communicates with the accommodation chamber 22. Therefore, the compressed air that has flowed through the first to third hollow pipe portions 1601 to 1603 flows into the accommodation chamber 22 via the first housing 26.

[0095] In the present embodiment, the case where the first to third hollow pipe portions 1601 to 1603 are provided is exemplified, but the number of hollow pipe portions is appropriately determined in accordance with the flow rate or flow velocity or the like of the air curtain air to be formed by the compressed air. That is, the number of hollow pipe portions is not limited to three. In addition, the cross-sectional area of the hollow pipe portions is also appropriately determined in accordance with the flow rate or flow velocity or the like of the air curtain air.

[0096] The compressed air that has flowed into the accommodation chamber 22 is then divided into compressed air that flows toward the first insertion hole 78 and compressed air that flows toward the second insertion hole 86. Specifically, a portion of the compressed air flows toward the first insertion hole 78 through the gap between the first sub-housing 18 and the rotor 34. In this way, the gap 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 toward the second insertion hole 86 mainly through the gap between the outer wall of the permanent magnet 72 and the inner wall of the electromagnetic coil 110. In this way, the gap between the outer wall of the permanent magnet 72 and the inner wall of the electromagnetic coil 110 is the second branch path M.

[0097] The compressed air that has reached the first branch path L forms an air curtain that seals the lubricating oil supplied to the first bearing 74. In addition, the compressed air that has reached 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 the lubricating oil supplied to the second bearing 84. In this way, the compressed air that has flowed into the accommodation chamber 22 functions as an air curtain.

[0098] As Figure 5As shown, three guide inlets 104 are formed in the lower flap portion 98 of the rectifying member 96. One of them is shown in Fig. 6. One guide inlet 104 is connected to the second downstream communication hole 1701 (not shown). Another guide inlet 104 is connected to the second downstream communication hole 1702 (shown). Further, another guide inlet 104 is connected to the second downstream communication hole 1703 (not shown). Thus, the compressed air output from the second downstream communication holes 1701 to 1703 enters the relay chamber 106 of the reduced diameter portion 100 of the rectifying member 96 via the guide inlets 104. Figure 5 One of them is shown in Fig. 6. One guide inlet 104 is connected to the second downstream communication hole 1701 (not shown). Another guide inlet 104 is connected to the second downstream communication hole 1702 (shown). Further, another guide inlet 104 is connected to the second downstream communication hole 1703 (not shown). Thus, the compressed air output from the second downstream communication holes 1701 to 1703 enters the relay chamber 106 of the reduced diameter portion 100 of the rectifying member 96 via the guide inlets 104.

[0099] The relay chamber 106 is connected to the through-hole 108 formed in the top portion 102. Here, the relay chamber 106 becomes wider as it approaches the through-hole 108 and the fourth sub-branch path 942. Thus, the pressure of the air curtain air decreases as the compressed air flows in the relay chamber 106.

[0100] The outlet of the relay chamber 106 faces the small-diameter cylindrical portion 242 of the compressor impeller 222. Thus, the compressed air entering the relay chamber 106 comes into contact with the small-diameter cylindrical portion 242 of the compressor impeller 222. Thereafter, the compressed air is divided into the compressed air flowing toward the fourth sub-branch path 942 and the compressed air flowing toward the outlet path 943. As a result, the pressure of the compressed air flowing toward the second proximal end 862 of the second insertion hole 86 along the fourth sub-branch path 942 decreases.

[0101] The compressed air reaching the second proximal end 862 of the second insertion hole 86 from the fourth sub-branch path 942 forms an air curtain that seals the lubricating oil supplied to the second bearing 84. Further, the compressed air flowing into the outlet path 943 is guided to the inside of the first end (open end) of the shroud case 220. This compressed air is again sucked into the compressor impeller 222.

[0102] The main housing 16 is formed with an exhaust path 172 (first discharge path). The compressed air reaching the first branch path L and the compressed air reaching the second branch path M are exhausted to the outside of the main housing 16 via the exhaust path 172.

[0103] Next, the lubricating oil flow path (second supply path) will be described. Figure 8 is a schematic side cross-sectional view of the rotating electric machine system 10. Further, in Figure 8 is shown in a phase different from that of Figure 3

[0104] ​An input path 174 for supplying lubricating oil is formed in the side wall of the main housing 16. The input path 174 is formed at a position closer to the first end than the middle in the axial direction of the main housing 16. The input path 174 extends in the diametrical direction of the main housing 16 and communicates with a main oil passage 176. The main oil passage 176 is formed in the outer periphery of the cooling jacket 24 and extends in the axial direction of the main housing 16. The main oil passage 176 is branched 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, with the communication position with the input path 174 as a boundary.

[0105] A first inflow hole 178 is formed in the first sub-housing 18 at a position facing the third branch passage N. Also, a first sub-oil passage 180 is formed in the first sub-housing 18 to lead to the inside in the diametrical direction of the first sub-housing 18. The first sub-oil passage 180 is bent at two places before reaching the first bearing holder 80.

[0106] A first oil supply hole 182 is formed in the first bearing holder 80 to communicate with the first sub-oil passage 180. The outlet of the first oil supply hole 182 is formed in the first distal end 781 of the first insertion hole 78. Therefore, lubricating oil flowing into the first sub-oil passage 180 from the main oil passage 176 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.

[0107] As shown in Fig. 1, three first inflow holes 178, three first sub-oil passages 180, three first oil supply holes 182, and three third branch passages N are formed in the first sub-housing 18. Figure 3

[0108] The third branch passage N, the first inflow hole 178, the first sub-oil passage 180, and the first oil supply hole 182 are each formed in three. The fourth branch passage R is also formed in three. In Fig. 1, one of the third branch passages N, one of the first inflow holes 178, one of the first sub-oil passages 180, one of the first oil supply holes 182, and one of the fourth branch passages R are each shown. Figure 8

[0109] As shown in Fig. 1, three first inflow holes 178, three first sub-oil passages 180, three first oil supply holes 182, and three third branch passages N are formed in the first sub-housing 18. Figure 7

[0110] ​​​In the interior of the second sub-housing 20, three second sub-oil passages 188 are provided as oil supply paths. The second sub-oil passages 188 extend radially with respect to the diameter direction of the second sub-housing 20. However, the second sub-oil passages 188 are formed in a phase different from that of the air relay passage 166. Further, three oil outflow holes 190 are formed in the end surface of the second sub-housing 20 facing the gas turbine engine 200. The hollow pin portion 193 of the oil distributor 192 is fitted in the oil outflow hole 190.

[0111] In the interior of the oil distributor 192, a first guide passage 1941 and a second guide passage 1942 are formed. The lubricating oil that has passed through the second sub-oil passages 188 is divided into lubricating oil that flows through the first guide passage 1941 and lubricating oil that flows through the second guide passage 1942. The outlet of the first guide passage 1941 is located at the second proximal end 862 of the second insertion hole 86. Therefore, the lubricating oil that flows out of the first guide passage 1941 comes into contact with the second bearing 84 from the second proximal end 862.

[0112] The second guide passage 1942 branches from the middle of the first guide passage 1941. The second oil supply hole 195 formed in the second bearing retainer 88 is connected to the outlet of the second guide passage 1942. Therefore, the lubricating oil that flows through the second guide passage 1942 flows out of the second oil supply hole 195 to come into contact with the second bearing 84.

[0113] As shown in FIG. 9, two drain ports 197 and two second drain passages 196 (another second discharge passage) are formed in the second sub-housing 20. Figure 7 As shown in FIG. 10, the space formed by the flow regulating member 96 and the second outer limit portion 92 communicates with the second drain passage 196 via the drain port 197. Therefore, the lubricating oil that enters the space is discharged from the second drain passage 196 via the drain port 197. Figure 8

[0114] As shown in FIG. 11, the first drain passage 184 is connected to the gas-liquid separation device 302 (one of the recovery device / oil supply device) via a first relay pipe 3001. The second drain passage 196 is connected to the gas-liquid separation device 302 via a second relay pipe 3002. The air discharge passage 172 is connected to the gas-liquid separation device 302 via a third relay pipe 3003. That is, the compressed air and the lubricating oil that are supplied to the interior of the rotary electric machine housing 14 are recovered to the gas-liquid separation device 302. A circulation supply line 304 (circulation passage) and a release line 306 (release passage) are provided on the gas-liquid separation device 302. A circulation pump 308 that is one of the oil supply devices is provided on the circulation supply line 304. Figure 9

[0115] ​​As described later, the compressed air is contained in the lubricating oil flowing out from the first discharge passage 184 and the second discharge passage 196. That is, the lubricating oil flowing into the gas-liquid separation device 302 is a gas-liquid mixture. In the gas-liquid separation device 302, the gas-liquid mixture is separated into the lubricating oil and the air. The lubricating oil is discharged from the gas-liquid separation device 302 by the circulation pump 308, and is supplied to the input passage 174 again via the circulation supply line 304. On the other hand, the air is discharged to the atmosphere via the release line 306.

[0116] Next, the gas turbine engine 200 will be described. As shown in FIG. 2, the gas turbine engine 200 has an engine case 202 and an output shaft 204 rotating within the engine case 202. The engine case 202 includes an inner case 2021 and an outer case 2022. The inner case 2021 is connected to the second sub case 20 of the rotating electric machine system 10. The outer case 2022 is connected to the inner case 2021. The outer case 2022 is a case main body. Figure 10

[0117] As shown in FIG. 3, the inner case 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 case 20. The second annular portion 208 has a larger diameter than 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 the leg portions 210 is six. However, the number of the leg portions 210 is determined in accordance with the required strength of the coupling between the gas turbine engine 200 and the rotating electric machine system 10. That is, the number of the leg portions 210 is not limited to six in the illustrated example. Figure 1 Figure 7 As shown in FIG. 4, the cylindrical cover portion 212 protrudes from the center opening of the second annular portion 208 toward the rotating electric machine system 10. The right ends of the leg portions 210 are connected to the cylindrical cover portion 212. The leg portions 210 form an air intake space 214 therebetween.

[0118] As shown in FIG. 5, the air intake passages 216 are separately formed inside the six leg portions 210. The inlets of the air intake passages 216 are separately formed at the connection portions of the leg portions 210 to the cylindrical cover portion 212. The outlets of the air intake passages 216 are separately formed on the end surface of the first annular portion 206 facing the second sub case 20. All the outlets of the air intake passages 216 are located on the circumference of an imaginary circle. Therefore, all the outlets of the air intake passages 216 overlap the collective flow passage 162 formed in the annular shape. That is, the plurality of air intake passages 216 are all communicated to the collective flow passage 162. In this way, the compressed air from the plurality of air intake passages 216 flows into the collective flow passage 162 and is collected in the collective flow passage 162.

[0119] Figure 7 Figure 10

[0120] ​​​​​An exhaust hole 217 is formed in the leg portion 210. The exhaust hole 217 extends linearly from the inner wall to the outer wall of the cylindrical cover portion 212. The exhaust hole 217 can also extend from the inner wall of the cylindrical cover portion 212 to the outer wall of the leg portion 210. The exhaust hole 217 can be one or a plurality. In addition, it is not necessary to form the exhaust hole 217.

[0121] As shown in FIG. 2, the gas turbine engine 200 has a first annular portion 206, a second annular portion 208, a leg portion 210, and a cylindrical cover portion 212. Figure 10 As shown in FIG. 2, the gas turbine engine 200 has a first annular portion 206, a second annular portion 208, a leg portion 210, and a cylindrical cover portion 212.

[0122] As shown in FIG. 2, the gas turbine engine 200 has a first annular portion 206, a second annular portion 208, a leg portion 210, and a cylindrical cover portion 212. Figure 10 As shown in FIG. 2, the gas turbine engine 200 has a first annular portion 206, a second annular portion 208, a leg portion 210, and a cylindrical cover portion 212.

[0123] The shroud case 220 is a hollow body and is large compared to the flow regulating member 96. The small-diameter left end of the shroud case 220 faces the flow regulating member 96. The large-diameter right end of the shroud case 220 is inserted into the cylindrical cover portion 212 of the inner housing 2021. The shroud case 220 gradually decreases in diameter from the right end to the left end, but the left end tip is curved in a manner that flares out to the outside in the diameter direction.

[0124] The left end of the shroud case 220 is exposed to the suction space 214. The top portion 102 of the flow regulating member 96 enters the inside of the left end of the shroud case 220. An annular closed flange portion 232 is provided on the curved side wall of the shroud case 220. The outer edge of the closed flange portion 232 abuts against the inner walls of the cylindrical cover portion 212 and the leg portion 210.

[0125] An air intake port 234 is formed in the side wall of the shroud case 220 between the closed flange portion 232 and the first engagement protrusion 238. The air intake port 234 extends from the inner surface to the outer surface of the side wall of the shroud case 220. The air intake port 234 is an entrance to a chamber 236 through which compressed air enters the chamber 236.

[0126] The chamber 236 is located between the air intake port 234 and the air intake passage 216. That is, the chamber 236 communicates the air intake port 234 and the air intake passage 216. In addition, the chamber 236 is open to the atmosphere via the exhaust hole 217.

[0127] The first engaging protrusion 238 protrudes from the right end of the shroud housing 220 toward the second annular portion 208. The first engaging protrusion 238 engages the engaging recess 218 of the second annular portion 208. The shroud housing 220 is positioned and fixed to the inner housing 2021 by the engagement and by the abutment of the outer edge of the closing flange portion 232 against the inner wall of the cylindrical cover portion 212 and the leg portion 210. At the same time, a chamber 236 surrounded by the leg portion 210, the cylindrical cover portion 212, and the second annular portion 208 and the closing flange portion 232, the side peripheral wall, and the first engaging protrusion 238 of the shroud housing 220 is formed. The chamber 236 is annular and surrounds the shroud housing 220.

[0128] The compressor impeller 222 and the turbine impeller 224 are capable of rotating integrally with the rotating shaft 40 and the output shaft 204. That is, as shown in detail in FIG. 6, the compressor impeller 222 is connected to the outer shaft 44 (the rotating shaft 40) by the engagement of the first outer spline 239 with the first inner spline 66 and by the press-fitting of the small-diameter cylindrical portion 242 into the insertion hole 108 of the fairing member 96. Figure 5 As shown in detail, the compressor impeller 222 has a small-diameter cylindrical portion 242 at the left end. The small-diameter cylindrical portion 242 enters the insertion hole 108 formed in the fairing member 96. The first outer spline 239 is formed in the inner wall of the small-diameter cylindrical portion 242. The first outer spline 239 engages the first inner spline 66 formed in the right open end 442 of the outer shaft 44.

[0129] 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 toward the inside in the diameter direction. The compressor impeller 222 is connected to the outer shaft 44 (the rotating shaft 40) by the engagement and the press-fitting described above.

[0130] A through hole 240 extending in the left-right direction is formed in the diameter center of the compressor impeller 222. In the through hole 240, a second outer spline 246 is engraved in the inner wall at the left end. In addition, the hole diameter of the portion of the through hole 240 that is connected to the hollow interior of the small-diameter cylindrical portion 242 is slightly smaller than the other portions. Therefore, an inner flange portion 248 is provided near the opening of the small-diameter cylindrical portion 242 side of the through hole 240 of the compressor impeller 222. The hole diameter (diameter) of the through hole 240 is smallest at the portion where the inner flange portion 248 is provided.

[0131] The output shaft 204 provided to the turbine impeller 224 is inserted into the through hole 240. The left end tip of the output shaft 204 extends to approximately the same position as the left end tip of the small-diameter cylindrical portion 242 of the compressor impeller 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 connection hole 62 of the rotating shaft 40. An outer threaded portion 252 is engraved in the left end of the output shaft 204. The outer threaded portion 252 is screwed to the inner threaded portion 64 formed in the inner wall of the connection hole 62. By the screwing, the rotating shaft 40 and the output shaft 204 are connected together.

[0132] A second internal spline 254 is formed near the left end of the output shaft 204. The second internal spline 254 engages with a second external spline 246 formed on the inner peripheral wall of the through hole 240. In addition, the left end of the output shaft 204 is pressed into the inner flange portion 248.

[0133] like Figure 10 As shown, an annular component 256 is sandwiched between the compressor impeller 222 and the turbine impeller 224. The annular component 256 is made of a heat-resistant metal material such as a nickel-based alloy.

[0134] like Figure 11 As shown, a fitting hole 258 is formed on the annular member 256, extending from the compressor impeller 222 to the turbine impeller 224. Furthermore, a plurality of (e.g., three) labyrinth-forming protrusions 264 are formed on the outer peripheral wall of the annular member 256. The labyrinth-forming protrusions 264 protrude outwards in the diametrical direction of the annular member 256 and extend along the circumferential direction of the outer peripheral wall. As described later, the labyrinth-forming protrusions 264 prevent the backflow of burned fuel (exhaust gas) generated by the combustor 228 towards the compressor impeller 222.

[0135] An annular protrusion 268 protrudes from the right end face of the compressor impeller 222 facing the turbine impeller 224. When the left end face of the annular member 256 sits on the right end face of the compressor impeller 222, the annular protrusion 268 engages with the engagement hole 258. On the other hand, the output shaft 204 extends from the left end face of the turbine impeller 224 facing the compressor impeller 222. Furthermore, an engagement protrusion 270 surrounding the output shaft 204 is formed protruding from this left end face. When the right end face of the annular member 256 sits on the left end face of the turbine impeller 224, the top surface of the engagement protrusion 270 engages with the engagement hole 258. Accordingly, a portion of each of the compressor impeller 222 and the turbine impeller 224 engages with the engagement hole 258. In this state, the annular member 256 is held between the compressor impeller 222 and the turbine impeller 224.

[0136] The labyrinth forms a protrusion 264 on the outer shell 2022 (see reference). Figure 10 The hollow interior of the compressor impeller 222 is surrounded by an intermediate plate 266. A labyrinth-forming protrusion 264 is inserted into a hole 272 formed in the intermediate plate 266. A labyrinth flow path is formed through the inner wall of the hole 272 and the labyrinth-forming protrusion 264 abutting against the inner wall. Compressed air generated by the compressor impeller 222 reaches the labyrinth-forming protrusion 264 via the back of the compressor impeller 222. On the other hand, combustion gas reaches the labyrinth-forming protrusion 264 from the turbine impeller 224. The pressure of the compressed air is higher than the pressure of the combustion gas, therefore, it is possible to prevent the combustion gas from flowing into the space surrounding the compressor impeller 222 through the labyrinth-forming protrusion 264.

[0137] like Figure 10As shown, in the hollow interior of the outer case 2022, a portion of each of the shroud case 220 and the compressor impeller 222 and the intermediate plate 266 are surrounded by the diffuser 226. A second engagement protrusion 273 is formed at the left end of the diffuser 226. The second engagement protrusion 273 engages with the first engagement protrusion 238 of the shroud case 220 in the engagement recess 218. By this engagement, the diffuser 226 is positioned and fixed to the inner case 2021.

[0138] In the hollow interior of the outer case 2022, the turbine impeller 224 is surrounded by the nozzle 230, and the nozzle 230 is surrounded by the combustor 228. An annular combustion gas flow passage 274 is formed between the combustor 228 and the outer case 2022. The combustion gas flow passage 274 is a passage through which combustion air flows. A fuel supply nozzle 275 is positioned and fixed to the right end surface of the outer case 2022. The fuel supply nozzle 275 supplies fuel to the combustor 228.

[0139] A relay hole 276 for communicating the combustion gas flow passage 274 and the inside of the combustor 228 is formed in the combustor 228. As will be described later, combustion air compressed by the compressor impeller 222 reaches the inside of the combustor 228 via the diffuser 226, the combustion gas flow passage 274, and the relay hole 276. A micro hole, not shown, is also formed in the combustor 228. Air discharged from the micro hole forms an air curtain that cools the inside of the combustor 228.

[0140] The nozzle 230 has a portion that surrounds a portion of the maximum diameter of the turbine impeller 224. In this portion, a delivery hole, not shown, for supplying fuel burned together with the combustion air to the turbine impeller 224 is formed. Hereinafter, the burned fuel will also be referred to as "burned fuel". The "burned fuel" is synonymous with "combustion gas" or "burned exhaust gas".

[0141] An exhaust port 280 is formed in the right end of the outer case 2022 and the nozzle 230. After the burned fuel travels into the nozzle 230 through the delivery hole, it is blown out to the outside of the outer case 2022 via the exhaust port 280 by the rotating turbine impeller 224. In addition, an exhaust pipe for exhausting the burned fuel is provided at the exhaust port 280, but is not particularly shown.

[0142] The hybrid system 400 according to the present embodiment is basically configured as described above. Next, the effects of the hybrid system 400 will be described.

[0143] First, a direct current is supplied from the battery 146. Figure 2 and Figure 6The converter 150 shown has a conversion circuit 152 that converts the 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, V-phase terminal 1442, and W-phase terminal 1443. The alternating current flowing through the electromagnetic coils 110 generates an alternating magnetic field in the stator 36. Consequently, attractive and reactive forces act alternately between the electromagnetic coils 110 and the permanent magnets 72 of the rotor 34. As a result, the rotating shaft 40 begins to rotate. Alternatively, the rotating shaft 40 can also be rotated using a known starting device (not shown).

[0144] Here, as Figure 5 As shown, a first internal spline 66 is formed on the outer peripheral wall of the right opening 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 impeller 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 impeller 222. The second internal spline 254 and the second external spline 246 mesh with each other. Therefore, the torque of the rotating shaft 40 is rapidly transmitted to the output shaft 204 via the compressor impeller 222.

[0145] That is, when the rotating shaft 40 starts to rotate, the output shaft 204 also starts to rotate integrally with the rotating shaft 40. Along with this, the compressor impeller 222 and turbine impeller 224, supported on the output shaft 204, rotate integrally with the output shaft 204. As described above, by engaging the first internal spline 66 and the first external spline 239, and engaging the second internal spline 254 and the second external spline 246, the torque of the rotating shaft 40 can be sufficiently transmitted to the output shaft 204.

[0146] Furthermore, the right end of the rotating shaft 40 is pressed into the hollow interior of the small-diameter cylindrical portion 242 of the compressor impeller 222. Additionally, the left end of the output shaft 204 is pressed into the inner flange portion 248 of the compressor impeller 222. Therefore, the axis of the rotating shaft 40 and the axis of the output shaft 204 are precisely aligned. This effectively suppresses the output shaft 204 from rotating while eccentrically positioned or vibrating.

[0147] In addition, such as Figure 11 As shown, an annular component 256 is sandwiched between the compressor impeller 222 and the turbine impeller 224. The annular protrusion 268 on the right end face of the compressor impeller 222 and the mating protrusion 270 on the left end face of the turbine impeller 224 are fitted into the mating hole 258 of the annular component 256. These fits also help suppress the eccentric rotation (vibration) of the output shaft 204. Therefore, there is no need to provide a mechanism for suppressing vibration. Furthermore, there is no need to increase the diameter of the output shaft 204. Accordingly, miniaturization of the hybrid power system 400 can be achieved.

[0148] Furthermore, friction is generated between the right end face of the compressor impeller 222 and the left end face of the annular component 256. Friction is also generated between the right end face of the annular component 256 and the left end face of the turbine impeller 224. Through this friction, the compressor impeller 222, the annular component 256, and the turbine impeller 224 are kept in close contact with each other. Therefore, rotational misalignment of the compressor impeller 222 and the turbine impeller 224 is prevented.

[0149] Furthermore, when assembling the hybrid power system 400, the compressor impeller 222 and turbine impeller 224 are aligned (centered) relative to the output shaft 204 through the aforementioned fitting. Preferably, an annular member 256 is provided between the compressor impeller 222 and the turbine impeller 224, and a portion of the compressor impeller 222 and turbine impeller 224 are individually fitted into the fitting holes 258 of the annular member 256. This facilitates the centering of the compressor impeller 222 and turbine impeller 224 relative to the output shaft 204.

[0150] Through the above rotation, as Figure 10 As shown, air is drawn into the outer casing 220 through the air intake space 214 between the legs 210 of the inner casing 2021. Here, the rectifier 96 is located at the center of the diameter of the inner casing 2021. As described above, the rectifier 96 has a mountain-shaped form with its diameter decreasing as it approaches the outer casing 220. Furthermore, the surface of the reduced diameter portion 100 is smooth. Therefore, the drawn-in air is rectified by the rectifier 96 to flow towards the outer casing 220. The right end of the rectifier 96 enters from the left end opening of the outer casing 220, thus the air is effectively guided into the outer casing 220. In this way, by making the rectifier 96 the shape described above and allowing its top 102 to enter the outer casing 220, the air can be effectively captured by the outer casing 220.

[0151] The air drawn into the casing 220 flows between the compressor impeller 222 and the casing 220. The space between the compressor impeller 222 and the casing 220 is sufficiently narrow compared to the left opening of the casing 220; therefore, the air is compressed during this flow, i.e., compressed air is generated.

[0152] An air intake 234 is formed in the outer casing 220. Therefore, a portion of the compressed air is diverted from the air intake 234 as curtain air and flows into the chamber 236. The chamber 236 is annular and has a volume larger than that of the air intake 234. Therefore, the curtain air flowing into the chamber 236 is temporarily stored within the chamber 236.

[0153] Since multiple intake passages 216 are formed, compressed air is distributed from chamber 236 to each intake passage 216. In this case, the pressure of the distributed curtain air may differ from one another. However, in this embodiment, compressed air (curtain air) flows into a single annular chamber 236 through intake port 234. Accordingly, the pressure of the curtain air within chamber 236 is uniform. In other words, the pressure of the curtain air is homogenized. Thus, chamber 236 is a pressure regulating chamber that adjusts the pressure of the curtain air to approximately a constant level.

[0154] As described above, the curtain air flowing in from the intake port 234 is part of the compressed air and is under high pressure. Here, the volume of chamber 236 is larger than the volume of the intake port 234; therefore, the curtain air diffuses as it flows into chamber 236. Consequently, the pressure of the curtain air decreases. As thus understood, chamber 236 also serves as a buffer chamber to reduce the pressure of the compressed air.

[0155] In addition to the intake passage 216, an exhaust port 217 is also formed in the inner housing 2021. Excess compressed air is released to the outside (atmosphere) of the gas turbine engine 200 through the exhaust port 217. Therefore, excessive pressure rise of the curtain air in the chamber 236 is avoided. That is, the pressure in the chamber 236 can be easily regulated through the exhaust port 217.

[0156] Within chamber 236, each of the six legs 210 has an entrance to a separately formed air intake passage 216. Therefore, the curtain air within chamber 236 then flows individually through the six air intake passages 216, thereby traveling towards the second sub-shell 20. As described above, at this point in time, the pressure of the curtain air is approximately constant.

[0157] like Figure 7 As shown, the outlets of all six intake passages 216 overlap with the collecting flow path 162. Therefore, the curtain air flowing through the six intake passages 216 flows into the collecting flow path 162 and collects there, then diffuses in a ring shape along the collecting flow path 162. During this process, the pressure of the curtain air is further homogenized.

[0158] The curtain air further flows separately from the collection flow path 162 into the three upstream connecting holes 164, and then flows separately along the three air relay paths 166. After this, a portion of the curtain air is discharged from the first downstream connecting holes 1681-1683. The remaining portion of the curtain air is discharged from the second downstream connecting holes 1701-1703. Hereinafter, the curtain air discharged from the first downstream connecting holes 1681-1683 will be referred to as "first branch air." The curtain air discharged from the second downstream connecting holes 1701-1703 will be referred to as "second branch air."

[0159] The path of the first bypass air will be described. The first downstream communication hole 1681 communicates with the hollow interior of the first hollow pipe portion 1601. The first downstream communication hole 1682 communicates with the hollow interior of the second hollow pipe portion 1602. The first downstream communication hole 1683 communicates with the hollow interior of the third hollow pipe portion 1603. Thus, the first bypass air flows through the hollow interiors of the first to third hollow pipe portions 1601 to 1603 from the second end to the first end of the rotating electric machine housing 14. Figure 1

[0160] The first to third hollow pipe portions 1601 to 1603 are located at the outer peripheral portion of the cooling jacket 24. The cooling medium flows through the cooling jacket 24 in advance. Thus, the heat of the first bypass air is sufficiently conducted to the cooling medium during the flow of the first bypass air along the first to third hollow pipe portions 1601 to 1603. Accordingly, the temperature of the first bypass air is relatively low. That is, in the present embodiment, the first bypass air is cooled by the cooling jacket 24 for cooling the rotating electric machine 12 and the inverter 150, and the like. Thus, it is not necessary to additionally provide a cooling device for cooling the air curtain air to the gas turbine engine 200 or the rotating electric machine system 10. Thus, the downsizing of the hybrid system 400 can be achieved.

[0161] As shown in FIG. 6, the first bypass air flowing through the first hollow pipe portion 1601 flows into the interior space of the second housing 28. Accordingly, the air curtain is formed in the second housing 28. The remaining first bypass air flows into the hollow interior (interior space) of the first housing 26 via the mutual communication holes. On the other hand, the first bypass air flowing through the second and third hollow pipe portions 1602 and 1603, respectively, flows into the interior space of the first housing 26. Thus, in the first housing 26, the air curtain is formed by the first bypass air flowing through the first to third hollow pipe portions 1601 to 1603. Figure 2

[0162] As shown in FIG. 6, the first bypass air flowing through the first hollow pipe portion 1601 flows into the interior space of the second housing 28. Accordingly, the air curtain is formed in the second housing 28. The remaining first bypass air flows into the hollow interior (interior space) of the first housing 26 via the mutual communication holes. On the other hand, the first bypass air flowing through the second and third hollow pipe portions 1602 and 1603, respectively, flows into the interior space of the first housing 26. Thus, in the first housing 26, the air curtain is formed by the first bypass air flowing through the first to third hollow pipe portions 1601 to 1603. Figure 3

[0163] The first and second housings 26 and 28 are disposed at the first end (left end) of the main housing 16. Thus, the first bypass air flows in from the left end of the accommodation cavity 22. Thereafter, the first bypass air enters the gap between the outer peripheral wall of the cylindrical protrusion portion 76 and the insulating base material 112. The gap is the inner hole of the stator 36.

[0164] ​​​After that, a part of the first shunt air flows to the first insertion hole 78 via the first branch path L. In addition, the remaining part of the first shunt air flows to the second insertion hole 86 via the second branch path M along the gap between the outer wall of the permanent magnet 72 and the inner wall of the electromagnetic coil 110. In this way, the first shunt air is branched into the compressed air flowing to the first insertion hole 78 at the left end (first end) and the compressed air flowing to the second insertion hole 86 at the right end (second end).

[0165] A part of the first shunt air flowing to the first insertion hole 78 reaches the first proximal end 782 of the first insertion hole 78. The part of the first shunt air becomes the air curtain of the first bearing 74 at the first proximal end 782. On the other hand, the remaining part of the first shunt air flowing to the second insertion hole 86 reaches the second distal end 861 of the second insertion hole 86 via the third sub-branch path 941. The remaining part of the first shunt air becomes the air curtain of the second bearing 84 at the second distal end 861.

[0166] The path of the second shunt air is described. The second downstream communication holes 1701 to 1703 individually overlap the three guide inlets 104 formed in the lower skirt portion 98 of the rectifying member 96, respectively. Therefore, the second shunt air flows into the relay chamber 106 (the hollow interior of the rectifying member 96) via the guide inlets 104.

[0167] As described above, the outlet of the relay chamber 106 is opened at the position facing the small-diameter cylindrical portion 242 of the compressor impeller 222. Therefore, the second shunt air flowing into the relay chamber 106 comes into contact with the small-diameter cylindrical portion 242. After that, a part of the second shunt air flows to the fourth sub-branch path 942. The remaining part of the second shunt air flows to the outlet path 943.

[0168] The part of the second shunt air reaches the second proximal end 862 of the second insertion hole 86 via the fourth sub-branch path 942. The part of the second shunt air becomes the air curtain of the second bearing 84 at the second proximal end 862. In this way, the second bearing 84 is sandwiched by the remaining part of the second shunt air reaching the second proximal end 862 and the part of the first shunt air reaching the second distal end 861.

[0169] The remaining part of the second shunt air is discharged to the inside of the left end of the shroud housing 220 via the outlet path 943. The left end of the shroud housing 220 is opened, and the suction is performed as described above. Therefore, the remaining part of the second shunt air is compressed together with the sucked atmosphere by the compressor impeller 222.

[0170] The remaining first diverted air reaches the exhaust path 172 via the receiving chamber 22. The remaining second diverted air flows from the second end to the first end of the main housing 16, for example, through the gap between the inner wall of the receiving chamber 22 and the electromagnetic coil 110. After this, the remaining second diverted air reaches the exhaust path 172. The first and second diverted air reaching the exhaust path 172 are recovered to the gas-liquid separator 302 (recovery device) via the third relay pipe 3003.

[0171] As described above, the pressure of the curtain air is uniformly distributed through the chamber 236 provided between the inner housing 2021 and the outer casing 220. Therefore, pressure distribution of the curtain air is avoided. Furthermore, pressure fluctuations in the curtain air are also prevented. Thus, the curtain air can be supplied to the vicinity of the first bearing 74 and the second bearing 84 while maintaining a substantially constant pressure.

[0172] As described above, the width of the relay chamber 106 increases as it approaches the fourth sub-branch path 942. Furthermore, the second branch of air flowing out of the relay chamber 106 consists of a portion flowing towards the fourth sub-branch path 942 and the remainder flowing towards the outlet path 943. Therefore, the pressure of the second branch air reaching the second proximal end 862 is lower than the pressure of the second branch air before it flows into the relay chamber 106. As a result, the pressure of the first branch air reaching the second distal end 861 and the pressure of the second branch air reaching the second proximal end 862 are balanced.

[0173] Next, the path of the lubricating oil will be explained. The lubricating oil is supplied as a lubricant to the first bearing 74 and the second bearing 84.

[0174] Recycled Figure 9 The lubricating oil separated from the air in the gas-liquid separation device 302 (oil recovery device) is discharged by the circulation pump 308. The lubricating oil is supplied to the input path 174 formed in the main housing 16 via the circulation supply line 304. The lubricating oil flows from the input path 174 into the main oil passage 176. The main oil passage 176 branches into a third branch path N leading to the first sub-housing 18 and a fourth branch path R leading to the second sub-housing 20. Therefore, the lubricating oil is branched into lubricating oil flowing along the third branch path N and lubricating oil flowing along the fourth branch path R. Hereinafter, the lubricating oil flowing along the third branch path N will be referred to as "first branch oil". The lubricating oil flowing along the fourth branch path R will be referred to as "second branch oil".

[0175] The first shunt oil flows into the first sub-oil passage 180 via a first inflow hole 178 formed in the first sub-housing 18. Thereafter, the first shunt oil is supplied to the first distal end 781 of the first insertion hole 78 via a first oil supply hole 182 formed in the first bearing retainer 80. The first shunt oil also enters the bore of the first bearing 74 to lubricate the first bearing 74.

[0176] The first shunt oil flowing from the first distal end 781 to the first proximal end 782 is blocked by the first shunt air (air curtain) reaching the first proximal end 782. Thus, the first shunt oil is prevented from flowing into the first branch path L. Thus, the first shunt oil is also prevented from penetrating between the rotating shaft 40 and the electromagnetic coil 110. Accordingly, the rotating electric machine 12 can be prevented from being contaminated by the first shunt oil.

[0177] The remaining first shunt oil flows into the hollow recess 118. The first discharge path 184 is provided in the hollow recess 118. Thus, the first shunt oil in the hollow recess 118 is recovered into the gas-liquid separation device 302 via the first discharge path 184.

[0178] The second shunt oil flowing through the fourth branch path R flows into the second sub-oil passage 188 via an oil receiving hole 186 formed in the second sub-housing 20. The second shunt oil flowing through the second sub-oil passage 188 is shunted by a first guide path 1941 and a second guide path 1942 formed in the interior of the oil distributor 192. A portion of the second shunt oil flowing out of the outlet of the first guide path 1941 is supplied to the second proximal end 862 of the second insertion hole 86. The remaining portion of the second shunt oil flowing through the second guide path 1942 is supplied to the second bearing 84 via a second oil supply hole 195 formed in the second bearing retainer 88. The second shunt oil enters the bore of the second bearing 84 to lubricate the second bearing 84.

[0179] The second shunt oil entering the bore of the second bearing 84 is surrounded by the first shunt air supplied to the second distal end 861 and the second shunt air supplied to the second proximal end 862. As described above, the pressure of the first shunt air supplied to the second distal end 861 and the pressure of the second shunt air supplied to the second proximal end 862 are equalized. Thus, the second shunt oil is prevented from flowing into the third sub-branch path 941 or the fourth sub-branch path 942. Thus, the second shunt oil is prevented from penetrating between the rotating shaft 40 and the electromagnetic coil 110. In addition, the second shunt oil is also prevented from penetrating into the relay chamber 106 of the rectifying member 96. Accordingly, the rotating electric machine 12 and the rectifying member 96 can be prevented from being contaminated by the second shunt oil.

[0180] As described above, the pressure of the air curtain air is regulated to be substantially constant. Thus, the air curtain of a prescribed pressure is continuously formed around the first bearing 74 and the second bearing 84. Thus, the lubricating oil is prevented from leaking from the first bearing 74 and the second bearing 84.

[0181] The remaining second diverted oil flows into the space formed by the rectifying component 96 and the second outer limiting part 92. A discharge port 197 and a second discharge path 196 are formed in the second sub-casing 20. The second diverted oil flowing into said space is recovered to the gas-liquid separator 302 via the discharge port 197 and the second discharge path 196.

[0182] As described above, the air curtain and lubricating oil are recycled to the gas-liquid separator 302. Here, the lubricating oil is blocked by the air curtain inside the rotary motor housing 14, so the air curtain air discharged from the exhaust path 172 contains lubricating oil. That is, the air curtain air discharged from the exhaust path 172 is essentially a gas-liquid mixture.

[0183] In this embodiment, the recovery device also functions as a gas-liquid separator 302. Therefore, the gas-liquid mixture is separated into air and lubricating oil. The air is released into the atmosphere via a release line 306 provided in the gas-liquid separator 302. On the other hand, the lubricating oil is discharged from the gas-liquid separator 302 by a circulation pump 308. The lubricating oil is further supplied from the gas-liquid separator 302 to the first bearing 74 and the second bearing 84 via a circulation supply line 304. During the rotation of the rotating shaft 40, the first bearing 74 and the second bearing 84 are cooled by the lubricating oil.

[0184] In this way, the gas-liquid mixture is separated into lubricating oil and air by the gas-liquid separator 302, thereby preventing so-called air ingress from occurring in the circulation supply line 304 and the circulation pump 308. Therefore, lubricating oil can be supplied to the first bearing 74 and the second bearing 84 again at a suitable discharge pressure or flow rate. Thus, the first bearing 74 and the second bearing 84 are adequately lubricated. As a result, burning of the first bearing 74 and the second bearing 84 can be prevented.

[0185] Furthermore, air curtains are formed in the second branch path M, the third sub-branch path 941, and the fourth sub-branch path 942. These air curtains prevent lubricating oil from entering the internal spaces of the first housing 26 and the second housing 28. Therefore, lubricating oil adhesion to the U-phase terminal 1441, V-phase terminal 1442, W-phase terminal 1443, and the thermistor 148 is suppressed. In other words, contamination of the electrical terminals and the measuring device (thermistor 148) by lubricating oil can be avoided.

[0186] As described above, the air curtain air (the first split air and the second split air) prevents the lubricating oil from flying, etc. from the first bearing 74 and the second bearing 84. After that, the air curtain air is discharged to the outside of the rotating electric machine case 14 as described above. Therefore, even in a case where the lubricating oil is assumed to leak from the first bearing 74 or the second bearing 84, the leaked lubricating oil is discharged to the outside of the rotating electric machine case 14 along with the air curtain air. Therefore, it is possible to avoid the leaked lubricating oil from flowing to the rotor 34. In addition, it is also possible to avoid the leaked lubricating oil from remaining in the rotor 34.

[0187] As described above, the pressure of the air curtain air which is continuously supplied to the rotating electric machine case 14 is substantially constant. Therefore, it is possible to continuously prevent the flying of the lubricating oil described above. In addition, even in a case where the lubricating oil leaks, it is possible to continuously discharge the leaked lubricating oil to the outside of the rotating electric machine case 14.

[0188] The compressed air which does not enter the air intake port 234 but passes between the shroud case 220 and the compressor impeller 222 becomes combustion air. As shown in FIG. 6, the combustion air flows into the diffuser 226. The combustion air flows out from the outlet holes formed in the wall portion of the diffuser 226 to the combustion gas flow passage 274 between the combustor 228 and the outer case 2022. The combustion air also flows into the combustion chamber (the hollow interior of the combustor 228) via the relay holes 276 formed in the combustor 228, the micro holes, and the gap between the combustor 228 and the fuel supply nozzle 275, etc. Figure 10

[0189] The combustor 228 is in a preheated state. Therefore, the combustion chamber also becomes high temperature. The fuel is supplied from the fuel supply nozzle 275 to the high temperature combustion chamber. The fuel burns together with the combustion air to become high temperature burned fuel. This burned fuel expands in the nozzle 230 when it is supplied from the delivery hole to the inside of the nozzle 230. In accordance with this, the turbine impeller 224 starts to rotate at high speed.

[0190] The output shaft 204 holds the turbine impeller 224. In addition, the compressor impeller 222 is provided on this output shaft 204. Therefore, along with the high speed rotation of the turbine impeller 224, the output shaft 204 and the compressor impeller 222 rotate at high speed in unison. The rotary shaft 40 also rotates at high speed. In addition, the burned fuel is discharged to the outside of the outer case 2022 via a not-shown discharge pipe provided to the discharge port 280.

[0191] The annular member 256 which intervenes between the compressor impeller 222 and the turbine impeller 224 also functions as a sealing member for sealing between the compressor impeller 222 and the turbine impeller 224. Also, as shown in FIG. 6, the annular member 256 is provided with a plurality of through holes 258. The through holes 258 are formed in the annular member 256 so as to be aligned with the micro holes of the combustor 228. The through holes 258 are formed so as to be aligned with the micro holes of the combustor 228. Figure 11 ​As shown, a plurality of labyrinth-forming protrusions 264 are formed in the outer peripheral wall of the annular member 256. The labyrinth-forming protrusions 264 abut against the inner wall of a hole portion 272 formed in an intermediate plate 266. Compressed air generated by the compressor impeller 222 reaches the labyrinth-forming protrusions 264 via the back surface of the compressor impeller 222. In addition, combustion gas reaches the labyrinth-forming protrusions 264 from the turbine impeller 224. As described above, the pressure of the compressed air is higher than that of the combustion gas. Therefore, the combustion gas is inhibited from flowing into the compressor impeller 222 through the labyrinth-forming protrusions 264. For the above reason, it is possible to avoid that the combusted fuel intrudes into the through hole 240, for example, from between the compressor impeller 222 and the turbine impeller 224.

[0192] In Figure 10 the case where the output shaft 204 starts high-speed rotation, the supply of electric current from the battery 146 (refer to Figure 6 ) to the electromagnetic coil 110 is stopped. However, as described above, since the turbine impeller 224 is already rotating at high speed, the rotation shaft 40 rotates at high speed integrally with the turbine impeller 224 and the output shaft 204. At this time, based on the same reason as described above, sufficient torque is transmitted from the output shaft 204 to the rotation shaft 40.

[0193] In Figure 3 the case where the output shaft 204 starts high-speed rotation, the supply of electric current from the battery 146 (refer to Figure 6 ) to the electromagnetic coil 110 is stopped. However, as described above, since the turbine impeller 224 is already rotating at high speed, the rotation shaft 40 rotates at high speed integrally with the turbine impeller 224 and the output shaft 204. At this time, based on the same reason as described above, sufficient torque is transmitted from the output shaft 204 to the rotation shaft 40.

[0194] The rotation shaft 40 holds the permanent magnet 72, and therefore the electromagnetic coil 110 that surrounds the permanent magnet 72 generates an alternating current. The alternating current is supplied to Figure 2 and Figure 6 the inverter 150 shown in FIG. 1 via the U-phase terminal 1441, the V-phase terminal 1442, and the W-phase terminal 1443. The conversion circuit 152 of the inverter 150 converts the alternating current into a direct current. The control circuit 156 of the inverter 150 supplies the direct current to the battery 146 (refer to Figure 6 ) via the capacitor 154 when it is determined that the output of an external load (for example, a motor) electrically connected to the battery 146 has decreased. Accordingly, the battery 146 is charged.

[0195] In this process, the inverter 150, particularly the conversion circuit 152 and the capacitor 154, generates heat. However, in the present embodiment, the conversion circuit 152 and the capacitor 154 in the device housing 158 are 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. Accordingly, the conversion circuit 152 and the capacitor 154 are prevented from being excessively hot.

[0196] The electromagnetic coil 110 generates heat along with the flow of current. Here, a part of the first shunt air contacts the left end of the stator 36. In addition, the remaining part of the first shunt air that flows to the second insertion hole 86 via the accommodation cavity 22 contacts the outer wall and the inner wall of the stator 36. Therefore, the stator 36 is cooled by the first shunt air. In addition, the cooling medium flows in the cooling jacket 24 provided to the main housing 16. The rotary electric machine 12 is quickly cooled by the cooling medium.

[0197] In the present embodiment, the rotary electric machine housing 14 (the main housing 16) for accommodating the rotary electric machine 12 and the first housing 26 for accommodating the U-phase terminal 1441, the V-phase terminal 1442, and the W-phase terminal 1443 are separately provided. Therefore, the influence of the heat generated by the stator 36 in the main housing 16 does not easily reach the U-phase terminal 1441, the V-phase terminal 1442, and the W-phase terminal 1443 in the first housing 26. In addition, the U-phase terminal 1441, the V-phase terminal 1442, and the W-phase terminal 1443 also generate heat along with the energization. However, the U-phase terminal 1441, the V-phase terminal 1442, and the W-phase terminal 1443 are quickly cooled by the first shunt air supplied to the first housing 26.

[0198] In this way, the first shunt air also functions to cool the heat generating portions in the rotary electric machine system 10. The electric terminal portions (the U-phase terminal 1441, the V-phase terminal 1442, and the W-phase terminal 1443), the electromagnetic coil 110, the permanent magnet 72, and the like are cooled, and therefore, the influence of the heat does not reach the output control and the like of the rotary electric machine system 10. In addition, the excitation and the like of the electromagnetic coil 110, the permanent magnet 72, and the like are also prevented from being reduced by the heat. As a result, the reliability of the rotary electric machine system 10 is improved.

[0199] Further, since the main housing 16 that houses the rotary electric machine 12 and the first housing 26 that houses the U-phase terminal 1441, the V-phase terminal 1442, and the W-phase terminal 1443 are separately provided, the rotary electric machine 12 and the electric terminal portion are separated from each other. Therefore, the U-phase terminal 1441, the V-phase terminal 1442, and the W-phase terminal 1443 are less likely to be affected by the vibration generated in association with the rotation of the rotor 34. In other words, the U-phase terminal 1441, the V-phase terminal 1442, and the W-phase terminal 1443 are protected from the vibration. In addition, as described above, in the first bearing 74 and the second bearing 84, the occurrence of scuffing is suppressed by the lubricating oil. Therefore, the durability of the rotary electric machine system 10 is excellent.

[0200] During the rotation of the rotary shaft 40, the rotation angle (rotation parameter) of the rotary shaft 40 is detected by the resolver 132. Specifically, the resolver rotor 56 that is fitted to the left end portion 422 of the inner shaft 42 rotates integrally with the rotary shaft 40. Accordingly, the electric signal generated by the resolver stator 130 is transmitted to a receiver via the transmission connector 136. The receiver that reads the electric signal calculates the rotation angle of the rotary shaft 40 on the basis of the electric signal. The receiver transmits the calculation result to a control device or the like that is not shown. The control device or the like calculates the number of revolutions on the basis of the rotation angle by arithmetic operation.

[0201] The resolver 132 is disposed at the protruding tip end 46 of the rotary shaft 40 that protrudes from the rotary electric machine housing 14. Therefore, the influence of the heat generated by the electromagnetic coil 110 of the stator 36 in the rotary electric machine housing 14 is less likely to reach the resolver 132. In addition, the influence of the vibration generated in association with the rotation of the rotor 34 is also less likely to reach the resolver 132. In addition to this, the first bearing 74 and the second bearing 84 that support the rotary shaft 40 are provided in the rotary electric machine housing 14. Therefore, the vibration of the first bearing 74 and the second bearing 84 is suppressed by the rotary electric machine housing 14. This also makes the influence of the vibration less likely to reach the resolver 132.

[0202] As described above, in the present embodiment, the transmission of heat and vibration and the like to the resolver 132 is suppressed. Accordingly, the detection result of the resolver 132 on the rotation angle becomes accurate. In addition, the life of the resolver 132 is also extended.

[0203] The resolver 132 can be replaced by another resolver having a larger inner diameter and a larger outer diameter. In the case where one solid rotary shaft is used as the rotary shaft, when the resolver is replaced by a resolver having a larger inner diameter and a larger outer diameter, a solid rotary shaft having a larger diameter needs to be replaced. At this time, it is not easy to pass the solid rotary shaft having a larger diameter through the first bearing 74 and the second bearing 84.

[0204] In the present embodiment, the rotating shaft 40 is configured by the outer shaft 44 and the inner shaft 42. In addition, the outer shaft 44 is made to pass through the first bearing 74 and the second bearing 84, and the resolver rotor 56 is provided at a portion of the inner shaft 42 that is exposed from the outer shaft 44. Therefore, when the resolver 132 is replaced by another resolver having a larger inner diameter and outer diameter, it is possible to cope with this by replacing the inner shaft 42 with an inner shaft having a larger diameter at the left end portion 422. As can be seen from the above, according to the present embodiment, by replacing the inner shaft 42, it is possible to cope with various kinds of resolvers having different inner diameters and outer diameters.

[0205] As described above, the present embodiment discloses a hybrid system (400) having a rotating electric machine system (10) and an internal combustion engine (200), wherein,

[0206] The rotating electric machine system (10) has a rotating electric machine (12) and a rotating electric machine housing (14) that supports a rotating shaft (40) of the rotating electric machine in such a manner that the rotating shaft (40) is rotatable;

[0207] The internal combustion engine (200) has an output shaft (204) that rotates integrally with the rotating shaft,

[0208] The hybrid system (400) has a compressor impeller (222), a shroud housing (220), a turbine impeller (224), a diffuser (226), and an engine housing (202), wherein,

[0209] The compressor impeller (222) is provided to the output shaft, and obtains compressed air by compressing external air;

[0210] The shroud housing (220) surrounds the compressor impeller;

[0211] The turbine impeller (224) is provided to the output shaft;

[0212] The diffuser (226) diffuses the compressed air that passes between the compressor impeller and the shroud housing;

[0213] The engine housing (202) surrounds the shroud housing, the diffuser, and the compressor impeller,

[0214] An air intake port (234) for taking out the compressed air to the outside of the shroud housing is formed on the shroud housing,

[0215] A plurality of air intake passages (216) through which the compressed air taken out from the air intake port flows are formed on the engine housing,

[0216] An annular chamber (236) for storing the compressed air is formed between the suction port and the plurality of suction passages.

[0217] Since the plurality of suction passages are formed, the compressed air is distributed to each of the suction passages. In this case, the distributed compressed air pressures can differ from each other. However, in the above-described structure, the compressed air that has passed through the suction port flows into a single chamber that is annular. As a result, the pressures of the compressed air in the chamber are uniform. That is, the pressures of the compressed air are homogenized.

[0218] In addition, when the compressed air that has passed through the suction port flows into the chamber, the compressed air diffuses in the chamber. Through this diffusion, the pressure of the compressed air decreases.

[0219] Therefore, it is possible to avoid the compressed air from generating a pressure distribution. In addition, it is also possible to avoid the compressed air from generating a pressure fluctuation. Thus, it is possible to keep the pressure of the compressed air substantially constant. Such compressed air can be used, for example, as air curtain air that surrounds a bearing in a rotating electric machine housing.

[0220] The present embodiment discloses a hybrid system, the engine housing has a housing body (2022) and a plurality of leg portions (210), wherein the housing body (2022) accommodates the shroud shell, the diffuser and the compressor impeller; the plurality of leg portions (210) are between the housing body and the rotating electric machine housing,

[0221] An intake space (214) surrounded by the plurality of leg portions is formed, and a part of the shroud shell is exposed to the intake space,

[0222] One of the plurality of leg portions individually forms one of the plurality of suction passages.

[0223] In this way, by providing the plurality of leg portions in the engine housing, the space between the leg portions can be effectively utilized as the intake space. In addition, by forming the suction passages in the interior of the plurality of leg portions, it is easy to deliver the intake air (compressed air) to the rotating electric machine housing. This is because the leg portions are located between the engine housing and the rotating electric machine housing. Moreover, in this case, it is not necessary to form the suction passages in other components.

[0224] The present embodiment discloses a hybrid system, a compressed air flow path is formed in the interior of the rotating electric machine housing, the compressed air that has passed through the plurality of suction passages flows in the compressed air flow path, and a relay communication path (1601-1603) that communicates the plurality of suction passages and the compressed air flow path is provided outside the rotating electric machine housing.

[0225] Thus, in the interior of the rotary electric machine case, the compressed air after the suction passage is circulated through the compressed air flow path. By bringing this compressed air into contact with, for example, a rotary electric machine housed in the interior of the rotary electric machine case, the rotary electric machine can be efficiently cooled.

[0226] Further, in a case where both the compressed air flow path and the relay communication path are provided in the interior or the exterior of the rotary electric machine case, it is necessary to avoid the compressed air flow path and the relay communication path from crossing. Thus, the positions where the compressed air flow path and the relay communication path are provided are limited. In contrast, in the present embodiment, since the relay communication path is provided in the exterior of the rotary electric machine case, the compressed air flow path and the relay communication path do not cross. Thus, the design freedom of the positions where the compressed air flow path and the relay communication path are provided is improved.

[0227] The present embodiment discloses a hybrid system, in the rotary electric machine case, a collection flow path (162) is provided, which is a relay path between the plurality of suction passages and the relay communication path, and which causes the compressed air flowing through the plurality of suction passages to converge.

[0228] In this case, the compressed air flowing through the plurality of suction passages separately converges in the collection flow path. Thus, as with the case where the compressed air passing through the suction ports converges in the chamber, the pressure of the compressed air passing through the plurality of suction passages separately can be substantially uniformized in the collection flow path. Thus, it is easier to substantially uniformize the pressure of the compressed air supplied to the rotary electric machine case.

[0229] The present embodiment discloses a hybrid system, having a plurality of the relay communication paths, and the collection flow path distributes the compressed air converging in the collection flow path to the plurality of the relay communication paths.

[0230] By providing a plurality of relay communication paths in this way, the compressed air can be supplied to a plurality of supply targets.

[0231] The present embodiment discloses a hybrid system, having a first bearing (74) and a second bearing (84) between the rotary electric machine case and the rotary shaft, and the compressed air passing through the compressed air flow path is supplied to the first bearing and the second bearing.

[0232] Lubricating oil is supplied to the bearings. Thus, the compressed air is used as, for example, air curtain air for preventing the lubricating oil from leaking from the bearings. Accordingly, it is not necessary to provide a sealing member such as an O-ring. Thus, the number of parts can be reduced.

[0233] Further, the present application is not limited to the above-described embodiments, and various structures can be employed within a range not departing from the gist of the present application.

[0234] For example, in this embodiment, a third sub-branch path 941 and a fourth sub-branch path 942 are provided. Alternatively, the first branch path L may be branched into a first sub-branch path and a second sub-branch path. In this case, a portion of the first diverted air is supplied from the first sub-branch path to the first distal end 781, and a portion of the first diverted air is supplied from the second sub-branch path to the first proximal end 782. Alternatively, the first branch path L may be branched into a first sub-branch path and a second sub-branch path, and a third sub-branch path 941 and a fourth sub-branch path 942 may be provided.

[0235] In the gas turbine engine 200, the compressor impeller 222 and the turbine impeller 224 can also be configured to be compatible with... Figure 10 The opposite configuration can be used. In this case, a through-hole 240 can be formed in the turbine impeller 224, and an output shaft 204 can be provided in the compressor impeller 222. Alternatively, the compressor impeller 222 and the turbine impeller 224 can be centrifugal or axial. If the compressor impeller 222 and the turbine impeller 224 are arranged on the same axis, it can also be a combination of centrifugal and axial multi-stage compressor impellers and multi-stage turbine impellers.

[0236] exist Figure 3 In this case, the rotary motor 12 constituting the rotary motor system 10 can also be a motor that rotates the rotating shaft 40 by energizing the electromagnetic coil 110. In this case, the U-phase terminal 1441, V-phase terminal 1442, and W-phase terminal 1443 are electrical terminals that receive electrical power from the battery 146.

[0237] In the above embodiment, an example is shown of supplying a portion of the compressed air generated by the gas turbine engine 200 to the rotary motor housing 14. Alternatively, such as Figure 12 As shown, an externally installed compressor pump 320 or similar device can also be used as a gas supply source.

[0238] In this case, for example, a flow hole 322 is formed in the first housing 26. Compressed air supplied from the compression pump 320 flows into this flow hole 322. Additionally, a communication hole 324 connected to the upstream communication hole 164 is formed in the second sub-housing 20. The communication hole 324 is blocked by a plug 326. In this state, compressed air is obtained by compressing atmosphere or the like by the compression pump 320. This compressed air is supplied to the first hollow tube section 1601 to the third hollow tube section 1603.

[0239] In this case, all the compressed air can be combustion air.

Claims

1. A hybrid system (400) having a rotary electric machine system (10) and an internal combustion engine (200), wherein the rotary electric machine system (10) has a rotary electric machine (12) and a rotary electric machine housing (14) that supports a rotary shaft (40) of the rotary electric machine (12) in a manner that enables the rotary shaft (40) to rotate; the internal combustion engine (200) has an output shaft (204) that rotates integrally with the rotary shaft, characterized in that the hybrid system (400) has a compressor impeller (222), a shroud housing (220), a turbine impeller (224), a diffuser (226), and an engine housing (202), wherein the compressor impeller (222) is provided to the output shaft, and obtains compressed air by compressing outside air; the shroud housing (220) encloses the compressor impeller; the turbine impeller (224) is provided to the output shaft; the diffuser (226) diffuses the compressed air that passes between the compressor impeller and the shroud housing; the engine housing (202) encloses the shroud housing, the diffuser, and the compressor impeller; an air intake port (234) for taking out the compressed air to the outside of the shroud housing is formed on the shroud housing; a plurality of air intake passages (216) through which the compressed air taken out from the air intake port flows are formed on the engine housing; an annular chamber (236) for storing the compressed air is formed between the air intake port and the plurality of air intake passages; the engine housing has a housing main body (2022) that houses the shroud housing, the diffuser, and the compressor impeller, and a plurality of leg portions (210) that intervene between the housing main body and the rotary electric machine housing; an air intake space (214) surrounded by the plurality of leg portions and in which a part of the shroud housing is exposed is formed; and one of the plurality of air intake passages is formed in one of the plurality of leg portions.

2. A hybrid system (400) having a rotary electric machine system (10) and an internal combustion engine (200), wherein the rotary electric machine system (10) has a rotary electric machine (12) and a rotary electric machine housing (14) that supports a rotary shaft (40) of the rotary electric machine (12) in a manner that enables the rotary shaft (40) to rotate; the internal combustion engine (200) has an output shaft (204) that rotates integrally with the rotary shaft, characterized in that the hybrid system (400) has a compressor impeller (222), a shroud housing (220), a turbine impeller (224), a diffuser (226), and an engine housing (202), wherein the compressor impeller (222) is provided to the output shaft, and obtains compressed air by compressing outside air; the shroud housing (220) encloses the compressor impeller; the turbine impeller (224) is provided to the output shaft; the diffuser (226) diffuses the compressed air that passes between the compressor impeller and the shroud housing; the engine housing (202) encloses the shroud housing, the diffuser, and the compressor impeller; an air intake port (234) for taking out the compressed air to the outside of the shroud housing is formed on the shroud housing; a plurality of air intake passages (216) through which the compressed air taken out from the air intake port flows are formed on the engine housing; an annular chamber (236) for storing the compressed air is formed between the air intake port and the plurality of air intake passages; the engine housing has a housing main body (2022) that houses the shroud housing, the diffuser, and the compressor impeller, and a plurality of leg portions (210) that intervene between the housing main body and the rotary electric machine housing; an air intake space (214) surrounded by the plurality of leg portions and in which a part of the shroud housing is exposed is formed; and one of the plurality of air intake passages is formed in one of the plurality of leg portions. ​ ​ ​ ​ ​ ​ ​ ​ ​ ​ ​ ​ ​ ​ ​ ​ ​ ​ ​ ​ The shroud case (220) encloses the compressor impeller; The turbine impeller (224) is provided to the output shaft; The diffuser (226) diffuses the compressed air passing between the compressor impeller and the shroud case; The engine case (202) encloses the shroud case, the diffuser, and the compressor impeller, An air intake (234) for sucking out the compressed air to the outside of the shroud case is formed on the shroud case, A plurality of air intake passages (216) through which the compressed air sucked out from the air intake passes are formed on the engine case, An annular chamber (236) for storing the compressed air is formed between the air intake and the plurality of air intake passages, A compressed air flow path through which the compressed air passing through the plurality of air intake passages passes is formed inside the rotary electric machine case, and a relay communication path (1601-1603) that communicates the plurality of air intake passages and the compressed air flow path is provided outside the rotary electric machine case.

3. The hybrid system according to claim 2, wherein A collective flow path (162) that relays between the plurality of air intake passages and the relay communication path and that causes the compressed air that has passed through the plurality of air intake passages to flow collectively is formed in the rotary electric machine case.

4. The hybrid system according to claim 3, wherein There are a plurality of the relay communication paths, and the collective flow path distributes the compressed air that has flowed collectively in the collective flow path to the plurality of relay communication paths.

5. The hybrid system according to claim 2, wherein There are a first bearing (74) and a second bearing (84) between the rotary electric machine case and the rotary shaft, and the first bearing and the second bearing are supplied with the compressed air that has passed through the compressed air flow path.

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