Rotating Electric Machine System

Abstract

To make it possible to suppress the radial enlargement of a rotor, to suppress vibration generation during rotor rotation, and to smoothly distribute cooling gas into a cooling passage of the rotor.SOLUTION: A rotor of a rotary electric machine system comprises a cooling passage 41 and a gas flow path 72 through which compressed air for cooling is distributed. The rotary electric machine system comprises a rectifying structure 37 having a plurality of fins capable of rectifying the flow of compressed air. The rectifying structure is fixed to a non-rotating portion in the main housing. The rectifying structure 37 faces the cooling passage 41 and the gas flow path 72.SELECTED DRAWING: Figure 4

Description

[Technical Field]

[0001] The present invention relates to a rotating electrical machine system that includes a rotor and a stator, and in which the rotor is rotationally driven by supplying electric power. [Background technology]

[0002] Patent Document 1 discloses a rotating electrical machine system having a stator and a rotor. The rotor has an air passage inside the rotor shaft. The air passage has an inlet opening through which air is introduced and an outlet opening from which the air is discharged. The inlet opening is open at the end of the rotor shaft. A plurality of fins are arranged inside the inlet opening.

[0003] When power is supplied to the rotating electric machine system and the rotor rotates, air is forcibly drawn into the air passage from the inlet opening through the multiple fins as the rotor rotates. When the air flows along the air passage to the outlet opening, heat is exchanged between the heated rotor (rotor shaft) and the air, cooling the rotor. [Prior art documents] [Patent documents]

[0004] [Patent Document 1] Japanese Patent Application Publication No. 2019-214257 Summary of the Invention [Problem to be solved by the invention]

[0005] In the rotating electrical machine system of Patent Document 1, multiple fins force air into the air passage as the rotor rotates. However, to draw air into the cooling passage at a predetermined flow rate, the outer diameter of the fins must be increased. Increasing the outer diameter of the fins increases the radial size of the rotor shaft in which the fins are housed. Housing multiple fins inside the rotor shaft also increases the risk of vibration when the rotor shaft is rotated at high speed.

[0006] The present invention aims to solve the above-mentioned problems. [Means for solving the problem]

[0007] One aspect of the present invention is a rotating electric machine system comprising a rotor having a magnet, a stator surrounding the rotor, and a housing that houses the rotor and the stator and supports the rotor so that it can rotate, wherein a cooling passage is provided in at least one of the interior or outer periphery of the rotor through which cooling gas supplied from a gas supply mechanism provided separately from the rotor flows, and the rotating electric machine system comprises a rectifying structure having a plurality of fins that can rectify the flow of the gas, and the rectifying structure is fixed to a non-rotating portion within the housing so as to face the cooling passage. [Effects of the Invention]

[0008] The present invention can prevent the rotor from becoming too large in the radial direction and can suppress vibrations during rotor rotation, compared to a structure in which fins are provided inside the rotor. Furthermore, the flow straightening structure straightens the gas, allowing the gas to flow smoothly through the cooling passages of the rotor. [Brief explanation of the drawings]

[0009] [Figure 1] FIG. 1 is an external perspective view of a compound power system including a rotating electrical machine system according to an embodiment of the present invention. [Figure 2] FIG. 2 is an external perspective view of a rotating electrical machine system that constitutes the compound power system of FIG. [Figure 3] FIG. 3 is a schematic cross-sectional side view of the rotating electrical machine system of FIG. [Figure 4] FIG. 4 is an enlarged cross-sectional view of the vicinity of the rotating shaft of the rotating electrical machine system of FIG. [Figure 5] 5 is an enlarged view of a main portion showing the vicinity of the inlet-side straightening member of the rotary electric machine system shown in FIG. [Figure 6]6 is an enlarged view of a main portion showing the vicinity of the outlet-side straightening member of the rotary electric machine system shown in FIG. [Figure 7] FIG. 7 is a front view of the inlet-side flow straightening member as viewed from the axial direction. [Figure 8] FIG. 8 is a front view of the outlet-side flow straightening member as viewed from the axial direction. [Figure 9] FIG. 9 is a perspective view of the appearance of the inlet-side flow straightening member. [Figure 10] FIG. 10 is an external perspective view of the outlet-side flow straightening member. [Figure 11] FIG. 11 is a schematic diagram of a current converter provided in a housing of a rotating electrical machine. [Figure 12] FIG. 12 is a schematic perspective view of a second sub-housing that constitutes the rotary electric machine housing and an inner housing in the engine housing. [Figure 13] FIG. 13 is a schematic cross-sectional side view of a gas turbine engine that constitutes a combined power system. [Figure 14] FIG. 14 is an enlarged view of a main part of the gas turbine engine of FIG. [Figure 15] FIG. 15 is a schematic side cross-sectional view of a gas supply source that uses an externally provided compressor pump. DETAILED DESCRIPTION OF THE INVENTION

[0010] As shown in Fig. 1, a rotating electrical machine system 10 according to this embodiment is used in a combined power system 400 integrally combined with an internal combustion engine. Fig. 1 is a schematic overall perspective view of the combined power system 400 according to this embodiment.

[0011] In the following description, "left," "right," "bottom," and "top" refer to the left, right, bottom, and top directions, respectively, in particular in Figures 3 to 6, 13, and 14. However, these directions are merely used for convenience to simplify the description and make it easier to understand. In other words, the directions described in the specification are not necessarily the directions when the combined power system is actually used.

[0012] The combined power system 400 includes a rotating electric machine system 10 and a gas turbine engine 200. An axis passing through the diameter center of the rotating electric machine system 10 and extending along the longitudinal direction (axial direction) coincides with an axis passing through the diameter center of the gas turbine engine 200 and extending along the longitudinal direction (axial direction). In other words, the rotating electric machine system 10 and the gas turbine engine 200 are arranged side by side on the same axis.

[0013] Hereinafter, the left end in the axial direction of each of the rotating electric machine system 10 and the gas turbine engine 200 may be referred to as a first end. Similarly, the right end in the axial direction of each of the rotating electric machine system 10 and the gas turbine engine 200 may be referred to as a second end. That is, in the rotating electric machine system 10, the left end remote from the gas turbine engine 200 is the first end. In the rotating electric machine system 10, the right end close to the gas turbine engine 200 is the second end. Also, in the gas turbine engine 200, the left end close to the rotating electric machine system 10 is the first end. In the gas turbine engine 200, the right end remote from the rotating electric machine system 10 is the second end. According to this definition, in the illustrated example, the gas turbine engine 200 is disposed at the second end of the rotating electric machine system 10. The rotating electric machine system 10 is disposed at the first end of the gas turbine engine 200.

[0014] The combined power system 400 is used as a propulsion power source in, for example, an air vehicle, a ship, or an automobile. Suitable examples of the air vehicle include a drone or a multicopters. When mounted on an air vehicle, the combined power system 400 serves as a power drive source that rotates a propeller, a ducted fan, or the like. When mounted on a ship, the combined power system 400 serves as a rotational force generator for a screw. When mounted on an automobile, the combined power system 400 serves as a power drive source that rotates a motor.

[0015] The combined power system 400 can also be used as a power source for auxiliary power supplies in aircraft, ships, buildings, etc. In addition, the combined power system 400 can also be used as a gas turbine power generation facility.

[0016] As will be described later, the gas turbine engine 200 is an internal combustion engine and a gas supply device that supplies compressed air (gas).

[0017] First, the rotating electric machine system 10 will be described. Fig. 2 is a schematic overall perspective view of the rotating electric machine system 10. Fig. 3 is a schematic side cross-sectional view of the rotating electric machine system 10. The rotating electric machine system 10 includes a rotating electric machine 12 (e.g., a generator) and a rotating electric machine housing 14 that houses the rotating electric machine 12.

[0018] The rotating electrical machine housing 14 has a main housing 16, a first sub-housing 18, and a second sub-housing 20. The main housing 16 has a generally cylindrical shape, and both a first end and a second end are open ends. The first sub-housing 18 is connected to the first end (left open end) of the main housing 16. The second sub-housing 20 is connected to the second end (right open end) of the main housing 16. As a result, the first and second ends of the main housing 16 are closed.

[0019] The main housing 16 has thick side walls extending in the left-right direction. An accommodation chamber 22 is formed inside the side walls of the main housing 16. Most of the rotating electrical machine 12 is accommodated in the accommodation chamber 22.

[0020] A spiral cooling jacket 24 is formed inside the side wall of the main housing 16. A cooling medium flows through the cooling jacket 24. A specific example of the cooling medium is cooling water. In this case, the cooling jacket 24 is a water jacket.

[0021] A first casing 26 and a second casing 28 are provided on the outer surface (outer wall) of the side wall of the main housing 16 near the edge of the first end. The first casing 26 and the second casing 28 form part of the main housing 16. In other words, the first casing 26 and the second casing 28 are disposed integrally with the main housing 16. As will be described later, the first casing 26 is a terminal casing. The second casing 28 is a meter casing.

[0022] A holding member that holds a rotation parameter detector is connected to the first sub-housing 18. In this embodiment, a resolver 132 is exemplified as the rotation parameter detector. Therefore, hereinafter, the holding member for the detector will be referred to as a "resolver holder 30." As will be described later, a cap cover 32 is connected to the resolver holder 30 via screws.

[0023] The rotating electric machine 12 includes a rotor 34 , a stator 36 surrounding the outer periphery of the rotor 34 , and a rectifying structure 37 .

[0024] The rotor 34 includes a magnet 38, a rotating shaft 39, an expanded diameter portion 40, a cooling passage 41, and first and second magnet holders 70a, 70b. The rotating shaft 39 has an inner shaft 42 and a hollow cylindrical outer shaft 44. Both ends of a main body portion 44a of the outer shaft 44 are open ends. That is, the main body portion 44a has a left open end 441 (see FIG. 5) and a right open end 442 (see FIG. 6). The left open end 441 is located at the left end, which is one axial end of the main body portion 44a. The right open end 442 is located at the right end, which is the other axial end of the main body portion 44a.

[0025] The inner shaft 42 is removably inserted into the outer shaft 44. The inner shaft 42 is longer than the outer shaft 44. The inner shaft 42 has a cylindrical portion 421, a left end 422 (see FIG. 5), and a right end 423 (see FIG. 6). The left end 422 is connected to the left side of the cylindrical portion 421. Therefore, the left end 422 is an end (first end) of the inner shaft 42 that is away from the gas turbine engine 200. The right end 423 is connected to the right side of the cylindrical portion 421. Therefore, the right end 423 is an end (second end) of the inner shaft 42 that is close to the gas turbine engine 200. The diameter of the cylindrical portion 421 is smaller than those of the left end 422 and the right end 423. The diameter of the right end 423 is also smaller than that of the left end 422.

[0026] A part of the left end 422 is exposed from the left open end 441 of the outer shaft 44. The part exposed from the left open end 441 is a protruding tip 46, which will be described later. In the illustrated example, the right end 423 of the inner shaft 42 and the right open end 442 of the outer shaft 44 are flush with each other. However, the right end 423 may be positioned slightly closer to the second end than the right open end 442.

[0027] As shown in FIG. 5 , the first external thread portion 48, the flange portion 50, the stopper portion 52, and the second external thread portion 54 are arranged in this order toward the right on the left end portion 422 of the inner shaft 42. The outer diameters of the first external thread portion 48, the flange portion 50, the stopper portion 52, and the second external thread portion 54 increase in this order. The outer diameter of the second external thread portion 54 is larger than the inner diameter of the outer shaft 44. Therefore, the right end of the second external thread portion 54 is blocked by the edge of the left open end 441 of the outer shaft 44. Therefore, the portion of the inner shaft 42 to the left of the second external thread portion 54 cannot be inserted into the outer shaft 44.

[0028] A resolver rotor 56 is attached to the flange 50. A small cap nut 58 is screwed onto the first externally threaded portion 48. The right end of the resolver rotor 56 is stopped by the stopper portion 52. The left end of the resolver rotor 56 is pressed by the small cap nut 58. In this way, the resolver rotor 56 is positioned and fixed to the flange 50.

[0029] A large cap nut 60 is threaded onto the second external thread portion 54. The right end of the large cap nut 60 covers the outer peripheral wall of the left open end 441 of the outer shaft 44. This restrains the left end 422 of the inner shaft 42 to the left open end 441 of the outer shaft 44. Note that both the first external thread portion 48 and the second external thread portion 54 are so-called reverse threads. Therefore, the small cap nut 58 and the large cap nut 60 are rotated counterclockwise when threaded together. After threading, it is preferable to deform part of the threads of the small cap nut 58 and the large cap nut 60. This prevents the small cap nut 58 and the large cap nut 60 from loosening.

[0030] As shown in Fig. 6, a connecting hole 62 is formed in the right end 423, which is the second end, of the inner shaft 42. The connecting hole 62 extends toward the left end 422, which is the first end. An internal thread portion 64 is formed in the inner circumferential wall of the connecting hole 62. The left end of the output shaft 204 is inserted into the connecting hole 62. The left end of the output shaft 204 is coupled to the inner shaft 42 by being threaded into the internal thread portion 64. The output shaft 204 holds a compressor wheel 222 and a turbine wheel 224 (see Fig. 13).

[0031] As shown in Fig. 3, the outer shaft 44 has a main body portion 44a, an intermediate portion 44b, and a cooling passage 41. The main body portion 44a extends in the axial direction of the outer shaft 44. The left and right ends of the main body portion 44a are rotatably supported by the first and second sub-housings 18 and 20, respectively. A first internal spline 66 is formed on the outer peripheral wall of the right open end 442 of the main body portion 44a. The first internal spline 66 extends along the axial direction (left-right direction) of the rotating electrical machine system 10.

[0032] The expanded diameter portion 40 is composed of the middle portion 44b of the outer shaft 44, parts of the first and second magnet holders 70a, 70b, the first and second retaining plates 45a, 45b, and the magnets 38. The middle portion 44b is located at the axial center of the outer shaft 44. In the axial direction of the rotor 34, the middle portion 44b is located in a middle position between the left and right ends of the main body portion 44a. The middle portion 44b expands radially outward from the main body portion 44a. The outer diameter of the outer shaft 44 is greatest at the middle portion 44b.

[0033] A plurality of magnets 38 are held on the outer periphery of the intermediate portion 44b. The magnets 38 are arranged at the outermost radial position of the rotor 34. The left end of the magnet 38 is held by the first magnet holder 70a. The right end of the magnet 38 is held by the second magnet holder 70b. The first magnet holder 70a has a cylindrical portion 711a and a retaining portion 712a. The second magnet holder 70b has a cylindrical portion 711b and a retaining portion 712b. Each of the cylindrical portions 711a, 711b is attached to the outer periphery of the main body portion 44a of the outer shaft 44. Each of the retaining portions 712a, 712b protrudes radially outward from the end of the cylindrical portions 711a, 711b, respectively. Each of the retaining portions 712a, 712b has an annular shape perpendicular to the cylindrical portions 711a, 711b.

[0034] 4, the first magnet holder 70a faces the left end of the magnet 38. The pressing portion 712a of the first magnet holder 70a holds the left end of the magnet 38 via the first holding plate 45a. The first holding plate 45a is disposed between the pressing portion 712a and the intermediate portion 44b.

[0035] The pressing portion 712a has a first upstream hole 713a. The first upstream hole 713a constitutes a part of the cooling passage 41. The first upstream hole 713a extends in the axial direction of the rotating shaft 39 and passes through the pressing portion 712a. The first upstream hole 713a communicates with the second upstream hole 451a of the first holding plate 45a. The second upstream hole 451a extends in the axial direction of the rotating shaft 39 and passes through the first holding plate 45a. The second upstream hole 451a constitutes a part of the cooling passage 41. The first upstream hole 713a and the second upstream hole 451a are arranged on a straight line along the axial direction of the rotating shaft 39.

[0036] The second magnet holder 70b faces the right end of the magnet 38. The pressing portion 712b of the second magnet holder 70b holds the right end of the magnet 38 via the second holding plate 45b. The second holding plate 45b is disposed between the pressing portion 712b and the intermediate portion 44b.

[0037] The pressing portion 712b has a first downstream hole 713b. The first downstream hole 713b constitutes a part of the cooling passage 41. The first downstream hole 713b extends in the axial direction of the rotating shaft 39 and passes through the pressing portion 712b. The first downstream hole 713b communicates with the second downstream hole 451b of the second holding plate 45b. The second downstream hole 451b extends in the axial direction of the rotating shaft 39 and passes through the second holding plate 45b. The second downstream hole 451b constitutes a part of the cooling passage 41. The first downstream hole 713b and the second downstream hole 451b are arranged on a straight line along the axial direction of the rotating shaft 39.

[0038] The cylindrical portions 711a, 711b of the first and second magnet holders 70a, 70b are held on the outer circumferential surface of the main body 44a. The first and second magnet holders 70a, 70b and the magnets 38 rotate together with the rotating shaft 39 as part of the rotor 34. Adjacent magnets 38 have opposite polarities facing outward. As the rotating shaft 39 rotates, the magnets 38 move on a predetermined circumference around the center of rotation of the rotating shaft 39. In the rotor 34, the boundaries between the main body 44a and the intermediate portion 44b including the magnets 38, the first and second magnet holders 70a, 70b, and the first and second holding plates 45a, 45b are formed in a stepped shape.

[0039] The expanded diameter portion 40 has a first wall surface 44c facing toward the left of the rotor 34. The first wall surface 44c is arranged on the pressing portion 712a of the first magnet holder 70a, which constitutes the left end of the expanded diameter portion 40. The first wall surface 44c is an annular end surface. The expanded diameter portion 40 has a second wall surface 44d facing toward the right of the rotor 34. The second wall surface 44d is arranged on the pressing portion 712b of the second magnet holder 70b, which constitutes the right end of the expanded diameter portion 40. The second wall surface 44d is an annular end surface.

[0040] The rotor 34 has a gas flow path 72 radially outward of the magnets 38. The gas flow path 72 is a clearance between the magnets 38 and the stator 36 (electromagnetic coil 110) which is disposed radially outward of the magnets 38. The gas flow path 72 is annular and extends along the rotational axis direction of the rotating shaft 39. The gas flow path 72 is disposed between the left and right ends of the magnets 38. Compressed air, which is a cooling gas, flows through the gas flow path 72. The compressed air is supplied from a gas turbine engine 200, which will be described later.

[0041] The cooling passage 41 is a flow path through which compressed air, which is a cooling gas, flows. The compressed air is supplied from a gas turbine engine 200, which will be described later. The gas turbine engine 200 is a gas supply mechanism that can supply compressed air to the cooling passage 41 and the gas flow path 72. The gas turbine engine 200 is provided separately from the rotor 34.

[0042] The cooling passage 41 is disposed inside the middle portion 44b of the rotating shaft 39 and the first and second magnet holders 70a, 70b. In a cross section perpendicular to the axis of the rotating shaft 39 shown in Figures 7 and 8, the cooling passage 41 is circular. The cooling passage 41 extends in the direction of the rotation axis of the outer shaft 44. The cooling passage 41 is an intra-rotor cooling passage disposed inside the rotor 34.

[0043] As shown in Figures 7 and 8, a plurality of cooling passages 41 are provided. The plurality of cooling passages 41 are arranged radially offset from the center of the rotation axis of the rotor 34 (outer shaft 44). The plurality of cooling passages 41 are equally spaced from one another in the circumferential direction around the rotation axis of the rotor 34. The plurality of cooling passages 41 are arranged on the same circle of the outer shaft 44 centered on the rotation axis of the rotating shaft 39. The number of cooling passages 41 is preferably, for example, four or more. Below, a case where eight cooling passages 41 are provided in the rotor 34 will be described.

[0044] 4, the cooling passage 41 opens to first and second wall surfaces 44c, 44d of the expanded diameter portion 40 in the rotor 34. The cooling passage 41 has first and second openings 411, 412 (see FIGS. 5 and 6).

[0045] As shown in Fig. 5, the first opening 411 is disposed at the upstream end of the cooling passage 41. That is, the first opening 411 is an inlet 413 through which compressed air is introduced. The first opening 411 is disposed in the first wall surface 44c of the expanded diameter section 40. The first opening 411, which is the upstream end of the cooling passage 41, opens into the outer surface of the rotor 34 (first magnet holder 70a). The first opening 411 is disposed in a first upstream hole 713a of the first magnet holder 70a.

[0046] 6, the second opening 412 is disposed at the downstream end of the cooling passage 41. That is, the second opening 412 is an outlet 414 through which the compressed air flows out after flowing through the cooling passage 41. The second opening 412 is disposed in the second wall surface 44d of the expanded diameter portion 40. . coldA second opening 412, which is the downstream end of the cooling passage 41, opens to the outer surface of the rotor 34 (second magnet holder 70b). The second opening 412 is disposed in the first downstream hole 713b of the second magnet holder 70b.

[0047] 5 and 6, the first and second openings 411, 412 are disposed to be offset in the radial direction from the center of the rotation axis of the rotor 34. In the radial direction of the rotor 34, the second opening 412 may be located between the inner periphery and the outer periphery of the magnet 38.

[0048] As shown in FIG. 4, the cooling passage 41 includes a parallel portion 455 and an inclined portion 456. The parallel portion 455 extends along the rotational axis direction of the outer shaft 44. The parallel portion 455 is arranged parallel to the rotational axis of the outer shaft 44. The parallel portion 455 is arranged in the intermediate portion 44b. The parallel portion 455 is arranged radially inward of the magnet 38. As shown in FIG. 5, the upstream end of the parallel portion 455 is the first opening 411 (inlet 413). The upstream end of the parallel portion 455 is connected to the first upstream hole 713a of the first magnet holder 70a and the second upstream hole 713a of the first holding plate 45a. above The cooling passage 41 may be formed in a spiral shape from the upstream end to the downstream end of the cooling passage 41.

[0049] As shown in Fig. 4, the upstream end of the inclined portion 456 is connected to the downstream end of the parallel portion 455. As shown in Fig. 6, the inclined portion 456 is inclined radially outward relative to the parallel portion 455 from the downstream end (right end) of the parallel portion 455 toward the second opening 412 (outlet 414). The downstream end of the inclined portion 456 is the second opening 412 (outlet 414). The inclined portion 456 is formed by the first downstream hole 713b of the second magnet holder 70b and the second downstream hole 451b of the second holding plate 45b.

[0050] The position of the inclined portion 456 is not limited to the case where it is disposed at the downstream end of the parallel portion 455. It is sufficient that the inclined portion 456 is disposed at a part of the cooling passage 41 in the extension direction. A plurality of inclined portions 456 may be disposed in the cooling passage 41. The cooling passage 41 may not include the parallel portion 455, and may be configured with the inclined portion 456 all along the extension direction of the cooling passage 41 from the upstream end to the downstream end.

[0051] As shown in FIG. 5 , the left end of the main body 44a of the rotating shaft 39 is rotatably supported by the first sub-housing 18 via a first bearing 74. The first bearing 74 is inserted between the outer shaft 44 and the first sub-housing 18. Specifically, the first sub-housing 18 has a cylindrical protrusion 76 that protrudes toward the main housing 16. A first insertion hole 78 is formed in the cylindrical protrusion 76. A first bearing holder 80 that holds the first bearing 74 is inserted into the first insertion hole 78. Therefore, the first bearing 74 is disposed in the first insertion hole 78.

[0052] The first insertion hole 78 extends in the left-right direction. The left end of the first insertion hole 78 is farther from the output shaft 204 than the right end of the first insertion hole 78. Hereinafter, the left end of the first insertion hole 78 will also be referred to as the "first distal end 781." On the other hand, the right end of the first insertion hole 78 is closer to the output shaft 204 than the left end of the first insertion hole 78 (first distal end 781). Hereinafter, the right end of the first insertion hole 78 will also be referred to as the "first proximal end 782."

[0053] A first outer stopper 81 located at a first distal end 781 and a first inner stopper 82 located at a first proximal end 782 are attached to the left end of the main body 44a of the outer shaft 44. The first bearing 74 is sandwiched between the first outer stopper 81 and the first inner stopper 82. The first bearing 74 is positioned and fixed by being sandwiched between the first outer stopper 81 and the first inner stopper 82. A clearance is formed between the first outer stopper 81 and the cylindrical protrusion 76.

[0054] The tip of the left end of the rotating shaft 39 is passed through the inner hole of the first bearing 74 and then passes through the first insertion hole 78. The tip of the left end of the rotating shaft 39 is further exposed outside the cylindrical protrusion 76 (hollow recess 118). Hereinafter, the portion of the rotating shaft 39 that protrudes from the left end of the first bearing 74 will be referred to as the "protruding tip 46." The protruding tip 46 includes the first externally threaded portion 48, the flange portion 50, the stopper portion 52, and the second externally threaded portion 54 of the left end 422 of the inner shaft 42.

[0055] As shown in Fig. 6, the right end of the rotating shaft 39 is rotatably supported by the second sub-housing 20 via a second bearing 84. As shown in Fig. 6, the second bearing 84 is inserted between the outer shaft 44 and the second sub-housing 20, which has a substantially circular plate shape.

[0056] 4, the rectifying structure 37 is housed inside the main housing 16. The rectifying structure 37 is capable of rectifying the flow of compressed air circulating inside the main housing 16. The rectifying structure 37 includes an inlet-side rectifying member 851 and an outlet-side rectifying member 852.

[0057] As shown in FIG. 5 , the inlet-side stratum member 851 stratums the compressed air flowing into the gas flow passage 72 and the cooling passage 41. The inlet-side stratum member 851 is disposed in a first space 853a. The first space 853a is a space surrounded by the first magnet holder 70a, the first bearing 74, the first sub-housing 18, and an insulating base material 112 (described later). The inlet-side stratum member 851 faces the inlet 413 (first opening 411) of the cooling passage 41. The inlet-side stratum member 851 faces the inlet of the gas flow passage 72. That is, the inlet-side stratum member 851 faces the upstream ends of the cooling passage 41 and the gas flow passage 72. The inlet-side stratum member 851 faces the cylindrical protrusion 76 of the first sub-housing 18. The inlet-side stratum member 851 is disposed between the magnet 38 and the first bearing 74. The inlet-side rectifying member 851 is disposed inside the insulating base material 112 .

[0058] As shown in FIG. 7, the inlet-side flow straightening member 851 has a cylindrical first body 854a and a plurality of inlet-side fins 855a.

[0059] 5, the outer peripheral surface of the first body 854a is held in contact with the insulating base material 112 (described later). The left end of the first body 854a is held in contact with the end face of the cylindrical protrusion 76. The right end of the first body 854a is held in contact with the left end of the electromagnetic coil 110 (described later). The first body 854a is disposed radially outward from the first magnet holder 70a. The first body 854a is disposed radially outward from the gas flow path 72.

[0060] As a result, inside the main housing 16, the inlet-side rectifying member 851 is held in the axial and radial directions by the insulating base material 112, the cylindrical protrusion 76, and the electromagnetic coil 110, which are non-rotating members.

[0061] The left end of the first body 854a has a plurality of communication holes 856. The communication holes 856 penetrate the first body 854a in the radial direction. The plurality of communication holes 856 are spaced apart from one another in the circumferential direction of the first body 854a (see FIG. 9). When the inlet-side rectifying member 851 is placed in the first space 853a, the communication holes 856 face the clearance between the insulating base material 112 and the first sub-housing 18 (see FIG. 5). The clearance and the communication holes 856 communicate with each other.

[0062] The multiple inlet-side fins 855a straighten the flow of compressed air supplied to the first space 853a in the circumferential direction (rotational direction) of the rotor .

[0063] As shown in FIG. 7, the multiple inlet side fins 855a are arranged on the inner circumferential surface of the first body 854a. Each inlet side fin 855a is arranged at a position closer to the magnet 38 than the communication hole 856. Each inlet side fin 855a protrudes radially inward from the inner circumferential surface of the first body 854a. The multiple inlet side fins 855a are arranged to surround the center of the rotation axis of the rotor 34 (main body portion 44a). The multiple inlet side fins 855a are equally spaced apart along the circumferential direction of the first body 854a. Each inlet side fin 855a is connected to the expanded diameter portion 40 (first wall surface 44c) of the rotor 34, the pressing portion 71 of the first magnet holder 70a, and the like. 2a (See Figure 5).

[0064] The inlet fins 855a and a first imaginary circle D1 connecting the centers of the first openings 411 of the cooling passage 41 face each other in the axial direction. The left end of the gas flow path 72 and the inlet fins 855a face each other in the axial direction (see FIG. 5).

[0065] As shown in FIG. 9 , each inlet-side fin 855a has a direction changer 857a, a first fin end 858a, and a second fin end 859a. The direction changer 857a curves from one axial end of the first body 854a to the other axial end, changing its direction from the axial direction to the circumferential direction of the first body 854a. The first fin end 858a is located at one end of the direction changer 857a in the axial direction of the first body 854a. The first fin end 858a is the upstream end of the inlet-side fin 855a. The first fin end 858a faces the axial direction of the first body 854a. The second fin end 859a is located at the other end of the direction changer 857a in the axial direction of the first body 854a. The second fin end 859a is the downstream end of the inlet-side fin 855a. Second fin end 859a extends in the circumferential direction of first body 854a toward first fin end 858a.

[0066] 5 is disposed in the first space 853a, the first fin end 858a faces the first bearing 74 and the cylindrical protrusion 76. The second fin end 859a faces the first wall surface 44c of the expanded diameter portion 40. The second fin end 859a faces the gas flow path 72 and the first opening 411 (inlet 413) of the cooling passage 41.

[0067] The direction changer 857a curves from the first fin end 858a to the second fin end 859a in the rotation direction R of the rotary shaft 39. Below, a case will be described where the rotation direction R of the rotor 34 is counterclockwise when viewed from the left end of the rotary shaft 39 shown in Fig. 7. When compressed air is supplied to the inlet-side rectifying member 851, the direction of the compressed air is changed downstream (to the right) by the direction changer 857a of the multiple inlet-side fins 855a in the rotation direction R of the rotor 34.

[0068] As shown in FIG. 6 , the outlet-side stratum member 852 stratums the compressed air flowing out of the gas flow path 72 and the cooling passage 41. The outlet-side stratum member 852 is disposed in the second space 853b. The second space 853b is a space surrounded by the second magnet holder 70b, the second sub-housing 20, and an insulating base material 112 (described later). The outlet-side stratum member 852 faces the outlet 414 (second opening 412) of the cooling passage 41 of the expanded diameter portion 40. The outlet-side stratum member 852 faces the outlet of the gas flow path 72. In other words, the outlet-side stratum member 852 faces the downstream ends of the cooling passage 41 and the gas flow path 72. The outlet-side stratum member 852 faces the cylindrical portion 87 of the second sub-housing 20. The outlet-side stratum member 852 is disposed between the magnet 38 and the second bearing 84. The outlet-side rectifying member 852 is disposed inside the insulating base material 112 .

[0069] As shown in Fig. 8, the outlet-side rectifying member 852 has a cylindrical second body 854b and a plurality of outlet-side fins 855b. As shown in Fig. 6, the outer peripheral surface of the second body 854b is held in contact with an insulating base material 112, which will be described later. The right end of the second body 854b is held in contact with an end face of the cylindrical portion 87 of the second sub-housing 20. The left end of the second body 854b is held in contact with a right end of the electromagnetic coil 110, which will be described later. The second body 854b is disposed radially outward from the second magnet holder 70b. The second body 854b is disposed radially outward from the gas flow path 72.

[0070] As a result, inside the main housing 16, the outlet-side rectifying member 852 is held in the axial and radial directions by the insulating base material 112, which is a non-rotating member, the cylindrical portion 87, and the electromagnetic coil 110. The multiple outlet-side fins 855b rectify the flow of compressed air flowing out from the cooling passage 41 and the gas flow path 72 toward the axial direction of the rotor 34.

[0071] As shown in FIG. 8, the outlet side fins 855b are arranged on the inner circumferential surface of the second body 854b. Each outlet side fin 855b protrudes radially inward from the inner circumferential surface of the second body 854b. The outlet side fins 855b are arranged to surround the center of the rotation axis of the rotor 34. The outlet side fins 855b are equally spaced apart along the circumferential direction of the second body 854b. Each outlet side fin 855b is connected to the expanded diameter portion 40 (second wall surface 44d) of the rotor 34, the pressing portion 71 of the second magnet holder 70b, and the like. 2 Facing b.

[0072] 8, a second imaginary circle D2 connecting the centers of the second openings 412 of the cooling passage 41 faces the outlet-side fins 855b in the axial direction. The right end of the gas flow path 72 faces the outlet-side fins 855b in the axial direction (see FIG. 6).

[0073] As shown in FIG. 10 , each outlet-side fin 855b has a direction changer 857b, a first fin end 858b, and a second fin end 859b. The direction changer 857b curves from one axial end of the second body 854b to the other axial end, changing its direction from the axial direction to the circumferential direction of the second body 854b. The first fin end 858b is located at one end of the direction changer 857b in the axial direction of the second body 854b. The first fin end 858b is the upstream end of the outlet-side fin 855b. The first fin end 858b faces the axial direction of the second body 854b. The second fin end 859b is located at the other end of the direction changer 857b in the axial direction of the second body 854b. The second fin end 859b is the downstream end of the outlet-side fin 855b. The second fin end 859b extends in the circumferential direction of the second body 854b toward the first fin end 858b.

[0074] 6 is disposed in the second space 853b, the second fin end 859b faces the second magnet holder 70b and the second wall surface 44d of the expanded diameter portion 40. The second fin end 859b faces the right end of the gas flow path 72 and the second opening 412 (outlet 414) of the cooling passage 41. The first fin end 858b faces the cylindrical portion 87 of the second sub-housing 20.

[0075] The direction changer 857b curves from the second fin end 859b to the first fin end 858a in the rotation direction of the rotary shaft 39. When compressed air flows out from the cooling passage 41 and the gas flow path 72 into the second space 853b, the compressed air that has swirled in the rotation direction of the rotor 34 is redirected downstream in the axial direction of the rotor 34 by the direction changer 857b of the multiple outlet-side fins 855b.

[0076] Note that the arrangement is not limited to the case where the inlet-side straightening member 851 and the outlet-side straightening member 852 are disposed at the first and second openings 411, 412 of the cooling passage 41. Only one of the inlet-side straightening member 851 and the outlet-side straightening member 852 may be disposed to face the cooling passage 41.

[0077] As shown in FIG. 3, the second sub-housing 20 is connected to the main housing 16 via bolts (not shown). The center of the second sub-housing 20 has a cylindrical portion 87. As shown in FIG. 6, a second insertion hole 86 is formed in the cylindrical portion 87. The second insertion hole 86 extends in the left-right direction. The left end of the second insertion hole 86 is farther from the output shaft 204 than the right end of the second insertion hole 86. Hereinafter, the left end of the second insertion hole 86 will also be referred to as the "second distal end 861." On the other hand, the right end of the second insertion hole 86 is closer to the output shaft 204 than the left end (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."

[0078] A second bearing holder 88 holding a second bearing 84 is inserted into the second insertion hole 86. Thus, the second bearing 84 is disposed in the second insertion hole 86. The second bearing 84 is sandwiched between a second inner stopper 90 located at the second distal end 861 and a second outer stopper 92 located at the second proximal end 862. Based on this sandwiching, the second bearing 84 is positioned and fixed.

[0079] At the second distal end 861, a clearance is formed between the second inner stopper 90 and the second bearing holder 88. This clearance is a third sub-branch path 941.

[0080] As shown in FIG. 2 , a guide member 96 is connected to the end surface of the second sub-housing 20 facing the gas turbine engine 200. The guide member 96 has a bottom portion 98, a reduced-diameter portion 100, and a top portion 102. The bottom portion 98 facing the second sub-housing 20 is in the shape of a large-diameter, thin-walled cylindrical plate. The top portion 102 facing the gas turbine engine 200 is in the shape of a small-diameter, relatively long cylindrical plate. The reduced-diameter portion 100 between the bottom portion 98 and the top portion 102 has a gradually decreasing diameter. Therefore, the guide member 96 has a mountain-like shape or a bottomless cup-like shape. The outer surface of the reduced-diameter portion 100 is smooth and has low surface roughness.

[0081] An inlet 104 is formed in the end surface of the hem portion 98 facing the second sub-housing 20. The reduced diameter portion 100 is hollow. That is, a relay chamber 106 is formed inside the reduced diameter portion 100. The inlet 104 is an input port for compressed air to enter the relay chamber 106.

[0082] An insertion hole 108 is formed in the top portion 102 along the left-right direction. The diameter (opening diameter) of the insertion hole 108 is larger than the outer diameter of the portion of the second outer stopper 92 that extends along the rotation shaft 39. Therefore, the portion of the second outer stopper 92 that has entered the insertion hole 108 and the outer peripheral wall are spaced apart from the inner wall of the insertion hole 108. In other words, a clearance is formed between the outer peripheral wall of the second outer stopper 92 and the inner wall of the insertion hole 108. This clearance is the fourth sub-branch passage 942. The width of the relay chamber 106 increases as it approaches the insertion hole 108 and the fourth sub-branch passage 942.

[0083] Furthermore, the diameter (opening diameter) of the insertion hole 108 is larger than the outer diameter of the left end (small diameter cylindrical portion 242), which has a relatively small diameter, of the compressor wheel 222. Therefore, the small diameter cylindrical portion 242 that has entered the insertion hole 108 also moves away from the inner wall of the insertion hole 108. In other words, a clearance is formed between the outer peripheral wall of the small diameter cylindrical portion 242 and the inner wall of the insertion hole 108. This clearance is the outlet path 943.

[0084] 3, the first insertion hole 78 and the third sub-branch passage 941 communicate with the accommodation chamber 22. Therefore, the first bearing 74 and the second bearing 84 are exposed to the accommodation chamber 22.

[0085] The stator 36, together with the rotor 34, constitutes the rotating electric machine 12. The stator 36 has an electromagnetic coil 110 and a plurality of insulating substrates 112. The electromagnetic coils 110 include three types of coils: a U-phase coil, a V-phase coil, and a W-phase coil, which are wound around the insulating substrates 112. When the rotating electric machine 12 is a generator, the rotating electric machine 12 is a so-called three-phase power supply. The plurality of insulating substrates 112 are arranged in an annular shape. This arrangement forms an inner hole in the stator 36. The inlet-side rectifying member 851 is held radially by the inner circumferential surface of the insulating substrate 112 arranged at the left end of the stator 36. The outlet-side rectifying member 852 is held radially by the inner circumferential surface of the insulating substrate 112 arranged at the right end of the stator 36.

[0086] The stator 36 is accommodated in the accommodation chamber 22. The second sub-housing 20 serves as a stator holder. That is, an annular recess 114 is formed in the second sub-housing 20. An insulating base material 112 included in the stator 36 is engaged with the annular recess 114. This engagement positions and fixes the stator 36. Furthermore, the columnar protrusion 76 enters the left opening of the inner hole of the stator 36.

[0087] The inner wall of the accommodating chamber 22 and the electromagnetic coil 110 are spaced apart from each other by a small distance, which electrically insulates the main housing 16 from the electromagnetic coil 110.

[0088] 5, a first space 853a is formed between the outer peripheral wall of the cylindrical protrusion 76 and the insulating substrate 112. A gas flow path 72 is provided between the outer wall of the magnet 38 and the inner wall of the electromagnetic coil 110. Compressed air flows through the first space 853a and the gas flow path 72. In other words, the first space 853a and the gas flow path 72 are part of the compressed air flow path.

[0089] The first sub-housing 18 has an annular protrusion 116 that protrudes in an annular shape. The inside of the annular protrusion 116 forms a hollow recess 118. The protruding tip 46, which is part of the left end 422 of the inner shaft 42, extends into the hollow recess 118.

[0090] The resolver holder 30 is provided on the annular protrusion 116. The resolver holder 30 has a flange-shaped stopper 120 that protrudes radially outward. The flange-shaped stopper 120 has a diameter larger than the inner diameter of the annular protrusion 116. Therefore, the flange-shaped stopper 120 abuts against the annular protrusion 116. This abutment positions the resolver holder 30. In this state, the resolver holder 30 is connected to the first sub-housing 18 via, for example, a mounting bolt (not shown) or the like.

[0091] A small cylindrical portion 122 is provided to the left of the flange-shaped stopper 120 of the resolver holder 30. A large cylindrical portion 124 is provided to the right of the flange-shaped stopper 120. The large cylindrical portion 124 has a larger diameter than the small cylindrical portion 122. A retaining hole 126 is formed in the resolver holder 30. Most of the resolver stator 130 is fitted into the retaining hole 126. The resolver stator 130 is held in the resolver holder 30 by this fitting.

[0092] When the large cylindrical portion 124 enters the hollow recess 118 and the flange-shaped stopper 120 abuts against the annular protrusion 116, the resolver rotor 56 is positioned in the inner hole of the resolver stator 130. The resolver stator 130 and the resolver rotor 56 form a resolver 132. The resolver 132 is a rotation parameter detector. In this embodiment, the resolver 132 detects the rotation angle of the inner shaft 42. As described above, the resolver rotor 56 is held by the flange 50 on the left end 422 of the inner shaft 42.

[0093] An engagement hole 134 is formed in the flange-shaped stopper 120. A transmitting connector 136 is engaged with the engagement hole 134. The resolver stator 130 and the transmitting connector 136 are electrically connected via a signal line 138. A receiving connector of a receiver (not shown) is inserted into the transmitting connector 136. The resolver 132 and the receiver are electrically connected via the transmitting connector 136 and the receiving connector. The receiver receives a signal emitted by the resolver 132.

[0094] The small cylindrical portion 122 is provided with a plurality of tab portions 140 (omitted in FIG. 1). One tab portion 140 is shown in FIG. 3. Furthermore, a cap cover 32 is placed over the small cylindrical portion 122. The cap cover 32 closes the left opening of the small cylindrical portion 122 and shields the left end portion 422 of the inner shaft 42. The cap cover 32 is connected to the tab portions 140 via a connecting bolt 142.

[0095] As described above, the first casing 26 and the second casing 28 are integrally provided on the side wall near the left end of the main housing 16. The first casing 26 accommodates the U-phase terminal 1441, the V-phase terminal 1442, and the W-phase terminal 1443. The U-phase terminal 1441 is electrically connected to the U-phase coil of the electromagnetic coil 110. The V-phase terminal 1442 is electrically connected to the V-phase coil of the electromagnetic coil 110. The W-phase terminal 1443 is electrically connected to the W-phase coil of the electromagnetic coil 110. The U-phase terminal 1441, the V-phase terminal 1442, and the W-phase terminal 1443 are electrical terminals to which an external device (external load or external power source) is electrically connected. Electric power generated by the rotating electric machine 12 is supplied to the external device. An example of the external load is a motor (not shown). An example of the external device is a battery 146 shown in FIG. 11 .

[0096] The second casing 28 is adjacent to the first casing 26. The second casing 28 houses a thermistor 148, which is a temperature measuring device. Although not specifically shown, the measurement terminal of the thermistor 148 is drawn out from the second casing 28 and then connected to the electromagnetic coil 110. A harness 149 connected to the thermistor 148 is drawn out from the second casing 28 to the outside.

[0097] The internal space of the second casing 28 and the internal space of the first casing 26 are in communication with each other via a communication hole (not shown). The internal space of the first casing 26 is in communication with the storage chamber 22.

[0098] 1 and 2, a current converter 150 is provided on the outer peripheral wall of the main housing 16. The current converter 150 is closer to the gas turbine engine 200 than the first casing 26. As shown in FIG. 11, the current converter 150 has a conversion circuit 152, a capacitor 154, and a control circuit 156. The conversion circuit 152, the capacitor 154, and the control circuit 156 are housed in an equipment case 158. The equipment case 158 is disposed, for example, on the outer peripheral wall of the main housing 16 at a location that does not interfere with the first hollow pipe portion 1601, the second hollow pipe portion 1602, and the third hollow pipe portion 1603 (see FIG. 1).

[0099] 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 passages through which compressed air flows. That is, in this embodiment, three relay communication passages are formed in the rotating electrical machine housing 14.

[0100] The conversion circuit 152 includes a power module 161. The conversion circuit 152 converts the AC current generated in the electromagnetic coil 110 into a DC current. At this time, the capacitor 154 temporarily stores the DC current converted by the conversion circuit 152 as an electric charge. The conversion circuit 152 also has the function of converting the DC current sent from the battery 146 into an AC current. In this case, the capacitor 154 temporarily stores the DC current sent from the battery 146 to the electromagnetic coil 110 as an electric charge.

[0101] The control circuit 156 controls the current density of the DC current flowing from the capacitor 154 to the battery 146 or the DC current flowing in the opposite direction. The DC current from the battery 146 is supplied to a motor (neither of which is shown) via an AC-DC converter, for example.

[0102] Next, a compressed air flow path provided in the rotating electrical machine system 10 will be described.

[0103] As shown in Fig. 12, an annular collecting passage 162 made up of an annular recess is formed on the end surface of the second sub-housing 20 facing the gas turbine engine 200. As will be described later, part of the compressed air generated by the gas turbine engine 200 flows through the collecting passage 162. Three upstream communication holes 164 are formed in the bottom wall of the collecting passage 162 (annular recess). The upstream communication holes 164 are inlets for compressed air.

[0104] Air relay paths 166 are provided inside the second sub-housing 20. The air relay paths 166 extend radially along the diameter direction of the second sub-housing 20. The air relay paths 166 communicate with the collecting flow path 162 on the outer side in the diameter direction via upstream communication holes 164. Furthermore, three first downstream communication holes 1681 to 1683 are formed on the end face of the second sub-housing 20 facing the rotating electric machine 12. The first downstream communication holes 1681 to 1683 are first output ports of the air relay path 166. The collecting flow path 162 and the air relay path 166 form a distribution path.

[0105] Three second downstream communicating holes 1701-1703 are formed on the end face of the second sub-housing 20 facing the gas turbine engine 200. The second downstream communicating holes 1701-1703 are second output ports of the air relay path 166. The second downstream communicating holes 1701-1703 are located radially inward of the first downstream communicating holes 1681-1683. Therefore, the compressed air that has flowed through the air relay path 166 is divided into compressed air that enters the first downstream communicating holes 1681-1683 and compressed air that enters the second downstream communicating holes 1701-1703.

[0106] As shown in Fig. 2, a first hollow pipe 1601 to a third hollow pipe 1603 are provided on the outer surface of the side wall of the main housing 16. The first downstream communication holes 1681 to 1683 open individually into the first hollow pipe 1601 to the third hollow pipe 1603, respectively. As can be seen from this, the air relay path 166 communicates between the collecting flow path 162 and the hollow interiors of the first hollow pipe 1601 to the third hollow pipe 1603. As shown in Fig. 3, the first hollow pipe 1601 to the third hollow pipe 1603 are located diametrically outward of the cooling jacket 24 formed inside the side wall of the main housing 16.

[0107] The first to third hollow pipes 1601 to 1603 extend along the axial direction of the main housing 16. The hollow interior of the first hollow pipe 1601 communicates with the internal space of the second casing 28. The hollow interiors of the second hollow pipe 1602 and the third hollow pipe 1603 communicate with the internal space of the first casing 26. As will be described later, the diverted air that has flowed through the hollow interior of the first hollow pipe 1601 flows into the internal space of the second casing 28. The diverted air that has flowed through the hollow interiors of the second hollow pipe 1602 and the third hollow pipe 1603 flows into the internal space of the first casing 26. As can be seen from this, the first casing 26 and the second casing 28 are disposed downstream of the portions of the first to third hollow pipes 1601 to 1603 that are located outside the cooling jacket 24.

[0108] As described above, the internal space of the first casing 26 and the internal space of the second casing 28 are in communication with each other via the interconnecting hole. In addition, the internal space of the first casing 26 is in communication with the accommodation chamber 22. Therefore, the compressed air that has flowed through the first hollow pipe portion 1601 to the third hollow pipe portion 1603 flows into the accommodation chamber 22 via the first casing 26.

[0109] In this embodiment, the case where first hollow tube portion 1601 to third hollow tube portion 1603 are provided is illustrated, but the number of hollow tube portions is determined appropriately depending on the flow rate or flow speed required for the curtain air formed from compressed air. That is, the number of hollow tube portions is not limited to three. Similarly, the cross-sectional area of ​​the hollow tube portions is also determined appropriately depending on the flow rate or flow speed required for the curtain air.

[0110] As shown in FIG. 5, 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, the compressed air flows through a first space 853a between the first sub-housing 18 and the rotor 34, and is introduced into the interior of the inlet-side flow straightening member 851 through a plurality of communication holes 856. In this manner, the first space 853a is the first branch path L (see FIG. 3). Part of the compressed air flows from the left end of the inlet-side flow straightening member 851 toward the first insertion hole 78. The compressed air that flows toward the first insertion hole 78 forms an air curtain that seals in the lubricating oil supplied to the first bearing 74.

[0111] Meanwhile, the remaining part of the compressed air is rectified by passing through the multiple inlet-side fins 855a of the inlet-side rectifying member 851, and then flows through the gas flow path 72 and the cooling passage 41 toward the second insertion hole 86. The gas flow path 72 is a second branch path M branching off from the first branch path L.

[0112] Specifically, a portion of the remaining compressed air passes through the inside of the first body 854a from the left end of the inlet-side flow straightening member 851. As the compressed air flows from the left end to the right end of the first body 854a, the direction change portions 857a of the multiple inlet-side fins 855a change the compressed air flow from an axial direction to a circumferential direction. At this time, when the compressed air flows out to the downstream side of the inlet-side flow straightening member 851, the compressed air becomes a swirling flow. The swirling direction of the compressed air is the rotation direction R of the rotor 34 (counterclockwise in FIG. 7). The swirling compressed air is introduced into the cooling passage 41 through the multiple first openings 411 (inlets 413). At the same time, the swirling compressed air is introduced into the annular gas flow passage 72 from the left end of the gas flow passage 72.

[0113] After flowing along the cooling passage 41 and the gas flow path 72, the compressed air flows from the cooling passage 41 through the second opening 412 (the outlet 414) into the second space 853b. The compressed air flows out from the right end of the gas flow path 72 into the second space 853b. In the second space 853b, the compressed air passes between the outlet-side fins 855b of the outlet-side flow straightening member 852. The direction change portions 857b of the outlet-side fins 855b change the flow of the compressed air from a swirling state to a flow along the axial direction. The compressed air flowing in the axial direction reaches the third sub-branch passage 941 (the second distal end 861 of the second insertion hole 86) from the cooling passage 41 and the gas flow path 72, forming an air curtain that seals in the lubricating oil supplied to the second bearing 84. In this way, the compressed air that flows into the accommodation chamber 22 functions as an air curtain.

[0114] As shown in Fig. 6, three inlets 104 are formed in the bottom portion 98 of the guide member 96. Fig. 6 shows only one of them. One inlet 104 communicates with a second downstream communication hole 1701 (not shown). Another inlet 104 communicates with a second downstream communication hole 1702 (shown). Another inlet 104 communicates with a second downstream communication hole 1703 (not shown). Therefore, 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 guide member 96 via the inlets 104.

[0115] The relay chamber 106 is connected to the insertion hole 108 formed in the top portion 102. The width of the relay chamber 106 increases as it approaches the insertion hole 108 and the fourth sub-branch passage 942. Therefore, as the compressed air flows through the relay chamber 106, the pressure of the diverted air decreases.

[0116] The outlet 414 of the relay chamber 106 faces the small diameter cylindrical portion 242 of the compressor wheel 222. Therefore, the compressed air that enters the relay chamber 106 comes into contact with the small diameter cylindrical portion 242 of the compressor wheel 222. The compressed air is then divided into compressed air that flows toward the fourth sub-branch path 942 and compressed air that flows toward the outlet path 943. As a result, the pressure of the compressed air that flows along the fourth sub-branch path 942 toward the second proximal end 862 of the second insertion hole 86 decreases.

[0117] The compressed air that reaches the second proximal end 862 of the second insertion hole 86 from the fourth sub-branch passage 942 forms an air curtain that seals the lubricating oil supplied to the second bearing 84. In addition, the compressed air that flows into the outlet passage 943 is guided toward the inside of the first end (open end) of the shroud case 220. This compressed air is sucked back into the compressor wheel 222.

[0118] An exhaust path 172 (first exhaust path) is formed in the main housing 16. The compressed air that has reached the first branch path L and the compressed air that has reached the second branch path M are exhausted to the outside of the main housing 16 via the exhaust path 172.

[0119] The rotating electric machine system 10 is cooled by circulating lubricating oil to the first and second bearings 74, 84 through a lubricating oil flow path (not shown). The lubricating oil used to lubricate and cool the first and second bearings 74, 84 is discharged to the outside of the main housing 16. The compressed air and lubricating oil supplied to the inside of the rotating electric machine housing 14 are recovered in a gas-liquid separator (not shown). The gas-liquid mixture is separated into lubricating oil and air. The lubricating oil is discharged from the gas-liquid separator (not shown) by a circulation pump (not shown) and resupplied to the lubricating oil flow path. Meanwhile, the compressed air is released into the atmosphere through an outlet (not shown).

[0120] Next, the gas turbine engine 200 will be described. As shown in Fig. 13, the gas turbine engine 200 includes an engine housing 202 and an output shaft 204 that rotates within the engine housing 202. The engine housing 202 includes an inner housing 2021 and an outer housing 2022. The inner housing 2021 is connected to the second sub-housing 20 of the rotating electrical machine system 10. The outer housing 2022 is connected to the inner housing 2021. The outer housing 2022 is a housing main body.

[0121] 1 and 12 , the inner housing 2021 has a first annular portion 206, a second annular portion 208, and a plurality of leg portions 210. The first annular portion 206 is connected to the second sub-housing 20. The diameter of the second annular portion 208 is larger than the diameter of the first annular portion 206. The leg portions 210 connect the first annular portion 206 and the second annular portion 208. In the illustrated example, the number of legs 210 is six. However, the number of legs 210 is determined depending on the connection strength required between the gas turbine engine 200 and the rotating electrical machine system 10. That is, the number of legs 210 is not limited to six as in the illustrated example.

[0122] A cylindrical cover portion 212 protrudes from a central opening of the second annular portion 208 toward the rotating electrical machine system 10. The right ends of the leg portions 210 are connected to both cylindrical cover portions 212. An intake space 214 is formed between the leg portions 210.

[0123] As shown in Figures 12 and 13, bleed passages 216 are individually formed inside the six leg portions 210. An inlet 413 of the bleed passage 216 is individually formed at a connection point of the leg portion 210 with the cylindrical cover portion 212. An outlet 414 of the bleed passage 216 is individually formed on the end surface of the first annular portion 206 facing the second sub-housing 20. All of the outlets 414 of the bleed passages 216 are located on the circumference of an imaginary circle. Therefore, all of the outlets 414 of the bleed passages 216 overlap with the collecting passage 162, which is formed in an annular shape. In other words, all of the multiple bleed passages 216 are communicated with the collecting passage 162. In this way, compressed air from the multiple bleed passages 216 flows into and collects in the collecting passage 162.

[0124] An air vent hole 217 is formed in the leg portion 210. The air vent hole 217 extends linearly from the inner wall to the outer wall of the cylindrical cover portion 212. The air vent hole 217 can also extend from the inner wall of the cylindrical cover portion 212 to the outer wall of the leg portion 210. There may be one or more air vent holes 217. Furthermore, it is not essential to form the air vent hole 217.

[0125] 13, an annular engaging recess 218 is formed on the right end surface of the second annular portion 208. The engaging recess 218 positions and fixes the shroud case 220 and the diffuser 226.

[0126] The gas turbine engine 200 further includes a shroud case 220 , a compressor wheel 222 , a turbine wheel 224 , a diffuser 226 , a combustor 228 , and a nozzle 230 .

[0127] The shroud case 220 is hollow and larger than the guide member 96. The small-diameter left end of the shroud case 220 faces the guide member 96. The large-diameter right end of the shroud case 220 is inserted into the cylindrical cover portion 212 of the inner housing 2021. The diameter of the shroud case 220 gradually decreases from the right end to the left end, but the tip of the left end is curved so as to expand outward in the diameter direction.

[0128] The left end of the shroud case 220 is exposed to the intake space 214. The top portion 102 of the guide member 96 extends into the interior of the left end of the shroud case 220. An annular closing flange portion 232 is provided on the curved peripheral side wall of the shroud case 220. The outer edge of the closing flange portion 232 abuts against the inner walls of the cylindrical cover portion 212 and the leg portion 210.

[0129] An air bleed port 234 is formed in the side wall of the shroud case 220 between the blocking flange portion 232 and the first engaging protrusion 238. The air bleed port 234 extends from the inner surface to the outer surface of the side wall of the shroud case 220. The air bleed port 234 is an inlet 413 to the chamber 236 through which compressed air enters the chamber 236.

[0130] The chamber 236 is interposed between the bleed port 234 and the bleed passage 216. That is, the chamber 236 connects the bleed port 234 and the bleed passage 216. The chamber 236 is also open to the atmosphere via an air vent hole 217.

[0131] A first engagement protrusion 238 protrudes from the right end of the shroud case 220 toward the second annular portion 208. The first engagement protrusion 238 engages with the engagement recess 218 of the second annular portion 208. This engagement, together with the outer edge of the closing flange portion 232 abutting against the inner walls of the cylindrical cover portion 212 and the leg portion 210, positions and fixes the shroud case 220 to the inner housing 2021. At the same time, a chamber 236 is formed that is surrounded by the leg portion 210, the cylindrical cover portion 212, the second annular portion 208, the closing flange portion 232 of the shroud case 220, the side peripheral wall, and the first engagement protrusion 238. The chamber 236 forms an annular shape surrounding the shroud case 220.

[0132] The compressor wheel 222 and the turbine wheel 224 can rotate integrally with the rotary shaft 39 and the output shaft 204. That is, as shown in FIG. 6 , the compressor wheel 222 has a small-diameter cylindrical portion 242 at its left end. The small-diameter cylindrical portion 242 enters an insertion hole 108 formed in the guide member 96. A first external spline 239 is formed on the inner wall of the small-diameter cylindrical portion 242. The first external spline 239 meshes with a first internal spline 66 formed on a right open end 442 of the outer shaft 44.

[0133] The right open end 442 of the outer shaft 44 is press-fitted into the hollow interior of the small diameter cylindrical portion 242. Therefore, the inner peripheral wall of the left opening of the small diameter cylindrical portion 242 presses the outer peripheral wall of the right open end 442 of the outer shaft 44 radially inward. The compressor wheel 222 is connected to the outer shaft 44 (rotating shaft 39) by the above-mentioned meshing and press-fitting.

[0134] A through hole 240 extending in the left-right direction is formed at the diametric center of the compressor wheel 222. A second external spline 246 is engraved on the inner wall of the through hole 240 at the left end. The diameter of the through hole 240 at a portion that communicates with the hollow interior of the small-diameter cylindrical portion 242 is slightly smaller than other portions. For this reason, an inner flange portion 248 is provided on the compressor wheel 222 near the opening of the through hole 240 on the small-diameter cylindrical portion 242 side. The diameter of the through hole 240 is smallest at the portion where the inner flange portion 248 is provided.

[0135] The output shaft 204 provided on the turbine wheel 224 is inserted into the through hole 240. The left end of the output shaft 204 extends to approximately the same position as the left end of the small-diameter cylindrical portion 242 of the compressor wheel 222. As described above, the outer peripheral wall of the right open end 442 of the outer shaft 44 is inserted into the hollow interior of the small-diameter cylindrical portion 242. Therefore, the left end of the output shaft 204 protruding from the through hole 240 enters the connecting hole 62 of the rotating shaft 39. A male thread portion 252 is formed on the left end of the output shaft 204. The male thread portion 252 is threadedly engaged with a female thread portion 64 formed on the inner wall of the connecting hole 62. This threaded engagement connects the rotating shaft 39 and the output shaft 204.

[0136] A second internal spline 254 is formed near the left end of the output shaft 204. The second internal spline 254 meshes with a second external spline 246 formed on the inner circumferential wall of the through hole 240. In addition, the left end of the output shaft 204 is press-fitted into the inner flange portion 248.

[0137] 13, a ring member 256 is interposed between the compressor wheel 222 and the turbine wheel 224. The ring member 256 is made of a heat-resistant metal material such as a nickel-based alloy.

[0138] 14, a fitting hole 258 extending from the compressor wheel 222 toward the turbine wheel 224 is formed in the ring member 256. Furthermore, a plurality of (e.g., three) labyrinth-forming protrusions 264 are formed on the outer peripheral wall of the ring member 256. The labyrinth-forming protrusions 264 protrude outward in the diameter direction of the ring member 256 and extend along the circumferential direction of the outer peripheral wall. As will be described later, the labyrinth-forming protrusions 264 prevent burned fuel (exhaust gas) generated in the combustor 228 from flowing back into the compressor wheel 222.

[0139] An annular protrusion 268 protrudes from the right end surface of the compressor wheel 222 facing the turbine wheel 224. When the left end surface of the ring member 256 seats on the right end surface of the compressor wheel 222, the annular protrusion 268 fits into the fitting hole 258. Meanwhile, the output shaft 204 extends from the left end surface of the turbine wheel 224 facing the compressor wheel 222. A fitting protrusion 270 surrounding the output shaft 204 protrudes from the left end surface. When the right end surface of the ring member 256 seats on the left end surface of the turbine wheel 224, the top surface of the fitting protrusion 270 fits into the fitting hole 258. In this state, a portion of each of the compressor wheel 222 and the turbine wheel 224 is fitted into the fitting hole 258. In this state, the ring member 256 is sandwiched between the compressor wheel 222 and the turbine wheel 224.

[0140] The labyrinth-forming protrusion 264 is surrounded by an intermediate plate 266 within the hollow interior of the outer housing 2022 (see FIG. 13 ). The labyrinth-forming protrusion 264 is inserted into a hole 272 formed in the intermediate plate 266. A labyrinth flow path is formed by the inner wall of the hole 272 and the labyrinth-forming protrusion 264 abutting against this inner wall. Compressed air generated by the compressor wheel 222 reaches the labyrinth-forming protrusion 264 via the back surface of the compressor wheel 222. Meanwhile, combustion gas from the turbine wheel 224 reaches the labyrinth-forming protrusion 264. Because the pressure of the compressed air is higher than the pressure of the combustion gas, it is possible to prevent the combustion gas from passing through the labyrinth-forming protrusion 264 and flowing into the space surrounding the compressor wheel 222.

[0141] 13 , within the hollow interior of the outer housing 2022, portions of the shroud case 220 and the compressor wheel 222, and the intermediate plate 266 are surrounded by the diffuser 226. A second engagement protrusion 273 is formed on the left end of the diffuser 226. The second engagement protrusion 273, together with the first engagement protrusion 238 of the shroud case 220, is engaged with the engagement recess 218. This engagement positions and fixes the diffuser 226 to the inner housing 2021.

[0142] Within the hollow interior of the outer housing 2022, the turbine wheel 224 is surrounded by a nozzle 230, which is in turn surrounded by a combustor 228. An annular combustion air flow path 274 is formed between the combustor 228 and the outer housing 2022. The combustion air flow path 274 is a passage through which combustion air flows. A fuel supply nozzle 275 is positioned and fixed to the right end face of the outer housing 2022. The fuel supply nozzle 275 supplies fuel to the combustor 228.

[0143] The combustor 228 is formed with relay holes 276 that connect the combustion air flow path 274 with the interior of the combustor 228. As will be described later, combustion air compressed by the compressor wheel 222 passes through the diffuser 226, the combustion air flow path 274, and the relay holes 276 and reaches the interior of the combustor 228. The combustor 228 is also formed with fine holes (not shown). The air discharged from the fine holes forms an air curtain that cools the interior of the combustor 228.

[0144] The nozzle 230 has a portion surrounding the largest diameter portion of the turbine wheel 224. This portion is formed with a delivery hole (not shown) for supplying combusted fuel together with combustion air to the turbine wheel 224. Note that, hereinafter, combusted fuel will also be referred to as "burned fuel." "Burned fuel" is synonymous with "combustion gas" or "exhaust gas after combustion."

[0145] An exhaust port 280 opens at the right ends of the outer housing 2022 and the nozzle 230. The burned fuel passes through the delivery holes and enters the nozzle 230, and is then blown out of the outer housing 2022 through the exhaust port 280 by the rotating turbine wheel 224. Although not specifically shown, the exhaust port 280 is provided with a discharge pipe for discharging the burned fuel.

[0146] The combined power system 400 according to this embodiment is basically configured as described above. Next, the effects of the combined power system 400 will be described. Below, a case will be described in which the rotor 34 of the rotating electrical machine system 10 rotates counterclockwise (rotation direction R) as viewed from the left end of the rotor 34 shown in FIG.

[0147] First, a direct current is supplied from the battery 146. The conversion circuit 152 of the current converter 150 shown in FIGS. 2 and 11 converts this direct current into an alternating current. The alternating current is supplied to the electromagnetic coils 110 (the U-phase coil, the V-phase coil, and the W-phase coil) via the U-phase terminal 1441, the V-phase terminal 1442, and the W-phase terminal 1443. When the alternating current flows through the electromagnetic coils 110, an alternating magnetic field is generated in the stator 36. Therefore, an attractive force and a repulsive force act alternately between the electromagnetic coil 110 and the magnet 38 of the rotor 34. As a result, the rotating shaft 39 starts to rotate in the rotation direction R. Alternatively, the rotating shaft 39 may be rotated by a known starter (not shown).

[0148] As shown in FIG. 6 , a first internal spline 66 is formed on the outer peripheral wall of the right open end 442 of the outer shaft 44, and a first external spline 239 is formed on the inner wall of the small-diameter cylindrical portion 242 of the compressor wheel 222. The first internal spline 66 and the first external spline 239 mesh with each other. Furthermore, a second internal spline 254 is formed on the output shaft 204, and a second external spline 246 is formed on the inner wall of the through hole 240 of the compressor wheel 222. The second internal spline 254 and the second external spline 246 mesh with each other. Therefore, the rotational torque of the rotating shaft 39 is quickly transmitted to the output shaft 204 via the compressor wheel 222.

[0149] That is, when the rotating shaft 39 starts to rotate in the rotation direction R, the output shaft 204 also starts to rotate integrally with the rotating shaft 39. Accordingly, the compressor wheel 222 and the turbine wheel 224 supported on the output shaft 204 rotate integrally with the output shaft 204. As described above, by meshing the first internal spline 66 with the first external spline 239 and meshing the second internal spline 254 with the second external spline 246, the rotational torque of the rotating shaft 39 can be sufficiently transmitted to the output shaft 204.

[0150] Moreover, the right end of the rotating shaft 39 is press-fitted into the hollow interior of the small-diameter cylindrical portion 242 of the compressor wheel 222. In addition, the left end of the output shaft 204 is press-fitted into the inner flange portion 248 of the compressor wheel 222. Therefore, the axis of the rotating shaft 39 and the axis of the output shaft 204 are precisely aligned. This sufficiently prevents the output shaft 204 from rotating eccentrically or vibrating.

[0151] In addition, as shown in FIG. 14, a ring member 256 is interposed between the compressor wheel 222 and the turbine wheel 224. An annular protrusion 268 on the right end surface of the compressor wheel 222 and a mating protrusion 270 on the left end surface of the turbine wheel 224 are fitted into a fitting hole 258 of the ring member 256. This fitting also contributes to suppressing eccentric rotation (vibration) of the output shaft 204. Therefore, there is no need to provide a mechanism for suppressing vibration. There is also no need to increase the diameter of the output shaft 204. This allows the combined power system 400 to be made more compact.

[0152] Furthermore, a frictional force is generated between the right end surface of the compressor wheel 222 and the left end surface of the ring member 256. A frictional force is also generated between the right end surface of the ring member 256 and the left end surface of the turbine wheel 224. This frictional force causes the compressor wheel 222, the ring member 256, and the turbine wheel 224 to adhere to one another. Therefore, rotational misalignment between the two wheels 222, 224 is prevented.

[0153] Furthermore, when assembling the compound power system 400, the above-described fitting allows the compressor wheel 222 and the turbine wheel 224 to be aligned (centered) with respect to the output shaft 204. In this manner, it is preferable to provide a ring member 256 between the two wheels 222, 224, and to individually fit portions of the two wheels 222, 224 into fitting holes 258 of the ring member 256. This makes it easy to center the compressor wheel 222 and the turbine wheel 224 with respect to the output shaft 204.

[0154] As a result of the rotation, as shown in FIG. 13 , air is drawn into the shroud case 220 through the air intake space 214 between the legs 210 of the inner housing 2021. Here, the guide member 96 is located at the diametric center of the inner housing 2021. As described above, the guide member 96 has a mountain-like shape that narrows in diameter toward the shroud case 220. Furthermore, the surface of the narrowed-diameter portion 100 is smooth. Therefore, the guide member 96 straightens the drawn air toward the shroud case 220. Because the right end of the guide member 96 enters the left-end opening of the shroud case 220, the air is efficiently guided into the shroud case 220. In this way, by shaping the guide member 96 as described above and by having the top portion 102 enter the shroud case 220, the air can be efficiently collected by the shroud case 220.

[0155] The air drawn into the shroud case 220 flows between the compressor wheel 222 and the shroud case 220. Because the space between the compressor wheel 222 and the shroud case 220 is sufficiently narrow compared to the left opening of the shroud case 220, the air is compressed during this flow. In other words, compressed air is generated.

[0156] An air bleed port 234 is formed in the shroud case 220. As a result, a portion of the compressed air is diverted from the air bleed port 234 and flows into a chamber 236. The chamber 236 is annular and has a volume larger than the volume of the air bleed port 234. As a result, the diverted air that has flowed into the chamber 236 is temporarily stored in the chamber 236.

[0157] Since a plurality of bleed passages 216 are formed, compressed air is distributed from the chamber 236 to each bleed passage 216. In this case, the pressure of the distributed diverted air may differ. However, in this embodiment, the compressed air that has passed through the bleed port 234 flows into the single annular chamber 236. This makes the pressure of the diverted air in the chamber 236 uniform. In other words, the pressure of the diverted air is made uniform. In this way, the chamber 236 is a pressure adjustment chamber that adjusts the pressure of the diverted air to a substantially constant value.

[0158] As described above, the diverted air flowing in from the bleed port 234 is part of the compressed air and is under high pressure. Here, because the volume of the chamber 236 is larger than the volume of the bleed port 234, the diverted air diffuses as it flows into the chamber 236. This reduces the pressure of the diverted air. As can be seen from this, the chamber 236 also serves as a buffer chamber that reduces the pressure of the compressed air.

[0159] In addition to the bleed passage 216, the inner housing 2021 is also formed with an air vent hole 217. Excess compressed air is released to the outside of the gas turbine engine 200 (to the atmosphere) through the air vent hole 217. This prevents the pressure of the diverted air in the chamber 236 from increasing excessively. In other words, the air vent hole 217 makes it possible to easily adjust the pressure in the chamber 236.

[0160] In the chamber 236, the inlets 413 of the bleed passages 216 individually formed in each of the six legs 210 open. Therefore, the diverted air in the chamber 236 then flows individually through the six bleed passages 216, and thereby proceeds toward the second sub-housing 20. As described above, the pressure of the diverted air is approximately constant at this point.

[0161] 12, the outlets 414 of the six bleed passages 216 all overlap with the collecting passage 162. Therefore, the diverted air that has flowed through the six bleed passages 216 flows into and collects in the collecting passage 162, and then diffuses in an annular shape along the collecting passage 162. In this process, the pressure of the diverted air is further equalized.

[0162] The diverted air then flows from the collecting passage 162 into the three upstream communication holes 164 individually, and circulates along the three air relay passages 166 individually. A portion of the diverted air is then discharged from the first downstream communication holes 1681-1683. The remainder of the diverted air is discharged from the second downstream communication holes 1701-1703. Hereinafter, the diverted air discharged from the first downstream communication holes 1681-1683 will be referred to as "first diverted air." The diverted air discharged from the second downstream communication holes 1701-1703 will be referred to as "second diverted air."

[0163] The path of the first diverted air will be described. The first downstream communicating hole 1681 is connected to the hollow interior of the first hollow pipe portion 1601. The first downstream communicating hole 1682 is connected to the hollow interior of the second hollow pipe portion 1602. The first downstream communicating hole 1683 is connected to the hollow interior of the third hollow pipe portion 1603. Therefore, the first diverted air flows through the hollow interiors of the first hollow pipe portion 1601 to the third hollow pipe portion 1603 shown in FIG. 1 etc., and flows from the second end to the first end of the rotating electric machine housing 14.

[0164] The first hollow pipe portion 1601 to the third hollow pipe portion 1603 are located on the outer periphery of the cooling jacket 24. A cooling medium is already circulated through the cooling jacket 24. Therefore, as the first diverted air flows along the first hollow pipe portion 1601 to the third hollow pipe portion 1603, heat of the first diverted air is sufficiently conducted to the cooling medium. This reduces the temperature of the first diverted air to a relatively low temperature. That is, in this embodiment, the cooling jacket 24, which cools the rotating electric machine 12, the current converter 150, and the like, can lower the temperature of the first diverted air. Therefore, there is no need to provide separate cooling equipment for cooling the curtain air in the gas turbine engine 200 or the rotating electric machine system 10. This eliminates the need to provide separate cooling equipment for cooling the curtain air in the gas turbine engine 200 or the rotating electric machine system 10. This allows the combined power system 400 to be made more compact.

[0165] The first diverted air that has flowed through the first hollow pipe portion 1601 flows into the internal space of the second casing 28, as shown in FIG. 2. This forms an air curtain inside the second casing 28. The excess first diverted air flows into the hollow interior (internal space) of the first casing 26 through the interconnecting holes. Meanwhile, the first diverted air that has flowed through each of the second hollow pipe portion 1602 and the third hollow pipe portion 1603 flows into the internal space of the first casing 26. Therefore, inside the first casing 26, an air curtain is formed by the first diverted air that has flowed through the first hollow pipe portion 1601 to the third hollow pipe portion 1603.

[0166] As shown in Fig. 3, the excess first diverted air in the first casing 26 flows into the storage chamber 22 formed in the main housing 16. As can be understood from this, the internal spaces of the first casing 26 and the second casing 28 are upstream in the flow path of the first diverted air. The storage chamber 22 of the main housing 16 is downstream in the flow path of the first diverted air.

[0167] The first casing 26 and the second casing 28 are disposed at the first end (left end) of the main housing 16. Therefore, the first diverted air flows into the left end of the accommodation chamber 22. The first diverted air then enters the clearance between the outer peripheral wall of the cylindrical protrusion 76 and the insulating base material 112. This clearance is the inner hole of the stator 36.

[0168] The first diverted air flow is then introduced into the inlet-side rectifying member 851 arranged in the first branch path L (first space 853a) through the communication hole 856. A portion of the first diverted air flow flows from the left end of the first body 854a of the inlet-side rectifying member 851 toward the first insertion hole 78. A portion of the first diverted air flow that has flowed toward the first insertion hole 78 reaches the first proximal end 782 of the first insertion hole 78. At this first proximal end 782, a portion of the first diverted air becomes an air curtain of the first bearing 74. A portion of the first diverted air flow is not rectified by the inlet-side rectifying member 851.

[0169] The remainder of the first diverted air flows through the first body 854a from the left end to the right end of the inlet-side flow straightening member 851. The first diverted air flows axially into the inlet-side flow straightening member 851. The first diverted air flows from the first fin ends 858a of the inlet-side fins 855a along the direction change portions 857a toward the second fin ends 859a. As a result, the first diverted air becomes a swirling flow that gradually swirls counterclockwise as viewed from the left end of the rotary shaft 39 shown in FIGS. 7 and 9. The first diverted air flows downstream from the second fin ends 859a of the inlet-side fins 855a while swirling. That is, as the first diverted air passes through the inlet-side flow straightening member 851, the first diverted air swirls in the same direction as the rotation direction R of the rotor 34. The remainder of the swirling first diverted air is supplied to the gas flow path 72, which is the second branch path M, and is also supplied to the cooling passages 41 of the rotary shaft 39. The remainder of the first diverted air flows along the annular gas flow path 72 toward the right end of the rotary shaft 39. The remainder of the first diverted air is introduced into the interiors of the cooling passages 41 through the first openings 411 (inlets 413) and flows along the cooling passages 41 toward the right end of the rotary shaft 39. Because the first diverted air swirls in the same direction as the rotational direction of the rotor 34, the first diverted air flows smoothly into the cooling passages 41 and the gas flow path 72.

[0170] The remainder of the first diverted air flows in the axial direction toward the right end of the gas flow path 72. The remainder of the first diverted air flows in the axial direction from the first openings 411 (inlets 413) of the multiple cooling passages 41 along the parallel portion 455. At this time, centrifugal force generated by the rotation of the rotor 34 generates negative pressure from the inclined portion 456 toward the second openings 412 (outlet 414). This negative pressure promotes the flow of the compressed air from the parallel portion 455 toward the inclined portion 456, allowing the compressed air to flow smoothly toward the outlet 414.

[0171] The first diverted air flows out from the right end of the gas flow path 72 and the second opening 412 of the cooling passage 41 into the inside of the outlet-side flow straightening member 852 in the second space 853b. As a result, the rotor 34 and magnets 38 are effectively cooled by the first diverted air flowing through the multiple cooling passages 41. The rotor 34 including the magnets 38 and the stator 36 are effectively cooled by the first diverted air flowing through the gas flow path 72.

[0172] In the second space 853b, the remainder of the first diverted air flows from the second fin end 859b of the outlet-side fin 855b of the outlet-side rectifying member 852 along the direction change portion 857b toward the first fin end 858b. The remainder of the first diverted air is rectified by the multiple outlet-side fins 855b, and the swirling force of the compressed air flowing in the same direction as the rotational direction R of the rotor 34 gradually decreases. The remainder of the first diverted air changes to a linear flow that flows along the axial direction and circulates downstream. After being rectified by the outlet-side rectifying member 852, the first diverted air passes through the third sub-branch channel 941 and reaches the second distal end 861 of the second insertion hole 86. At the second distal end 861, the remainder of the first diverted air becomes an air curtain for the second bearing 84.

[0173] In this way, the first diverted air flow branches into compressed air flowing toward the first insertion hole 78 at the left end (first end) and compressed air flowing toward the second insertion hole 86 at the right end (second end). The first diverted air flow then reaches the exhaust path 172 of the main housing 16 together with second diverted air flow, which will be described later.

[0174] The path of the second diverted air will now be described. The second downstream communication holes 1701-1703 overlap with three inlets 104 formed in the bottom portion 98 of the guide member 96. Therefore, the second diverted air flows into the relay chamber 106 (the hollow interior of the guide member 96) through the inlets 104.

[0175] As described above, the outlet 414 of the relay chamber 106 opens at a position facing the small diameter cylindrical portion 242 of the compressor wheel 222. Therefore, the second diverted air that flows into the relay chamber 106 comes into contact with the small diameter cylindrical portion 242. A portion of the second diverted air then flows toward the fourth sub-branch path 942. The remainder of the second diverted air flows toward the outlet path 943.

[0176] A portion of the second diverted air reaches the second proximal end 862 of the second insertion hole 86 via the fourth sub-branch passage 942. At the second proximal end 862, the portion of the second diverted air forms an air curtain around the second bearing 84. In this manner, the second bearing 84 is sandwiched between the remainder of the second diverted air that has reached the second proximal end 862 and the portion of the first diverted air that has reached the second distal end 861.

[0177] The remainder of the second diverted air is discharged through the outlet passage 943 to the inside of the left end of the shroud case 220. As described above, air is being drawn into the opening at the left end of the shroud case 220. Therefore, the remainder of the second diverted air is compressed by the compressor wheel 222 together with the drawn-in atmospheric air.

[0178] The excess first diverted air passes through the accommodation chamber 22 and reaches the exhaust path 172. The excess second diverted air flows from the second end to the first end of the main housing 16, for example, via a clearance between the inner wall of the accommodation chamber 22 and the electromagnetic coil 110. Thereafter, the excess second diverted air reaches the exhaust path 172. The first diverted air and second diverted air that have reached the exhaust path 172 are collected in a gas-liquid separator (not shown).

[0179] As described above, the pressure of the curtain air is made uniform by the chamber 236 provided between the inner housing 2021 and the shroud case 220. Therefore, the occurrence of pressure distribution in the curtain air is avoided. Furthermore, the occurrence of surging in the curtain air is also avoided. Therefore, it is possible to supply the curtain air to the periphery of the first bearing 74 and the second bearing 84 while maintaining the pressure of the curtain air substantially constant.

[0180] As described above, the width of the relay chamber 106 increases as it approaches the fourth sub-branch path 942. Moreover, the second diverted air flowing out of the relay chamber 106 is divided into a portion that flows toward the fourth sub-branch path 942 and a remainder that flows toward the outlet path 943. Therefore, the pressure of the second diverted air that has reached the second proximal end 862 is lower than the pressure of the second diverted air before it flows into the relay chamber 106. As a result, the pressure of the first diverted air that has reached the second distal end 861 and the pressure of the second diverted air that has reached the second proximal end 862 are balanced.

[0181] Compressed air that passes between the shroud case 220 and the compressor wheel 222 without entering the bleed port 234 becomes combustion air. As shown in FIG. 13 , the combustion air flows into the diffuser 226. The combustion air flows from an outlet hole formed in the wall of the diffuser 226 into a combustion air flow path 274 between the combustor 228 and the outer housing 2022. The combustion air further flows into the combustion chamber (the hollow interior of the combustor 228) through a relay hole 276 and fine holes formed in the combustor 228, a clearance between the combustor 228 and the fuel supply nozzle 275, and the like.

[0182] The combustor 228 is preheated. Therefore, the combustion chamber is also at a high temperature. Fuel is supplied to the high-temperature combustion chamber from the fuel supply nozzle 275. The fuel burns with combustion air, producing high-temperature burned fuel. When this burned fuel is supplied into the nozzle 230 from the delivery holes, it expands within the nozzle 230. This causes the turbine wheel 224 to begin rotating at a high speed.

[0183] The output shaft 204 holds a turbine wheel 224. A compressor wheel 222 is also provided on the output shaft 204. Therefore, as the turbine wheel 224 rotates at high speed, the output shaft 204 and the compressor wheel 222 rotate integrally at high speed. At the same time, the rotating shaft 39 also rotates at high speed. The burned fuel is discharged to the outside of the outer housing 2022 through a discharge pipe (not shown) provided at the discharge port 280.

[0184] The ring member 256 interposed between the compressor wheel 222 and the turbine wheel 224 serves as a sealing member that seals the gap between the two wheels 222, 224. Furthermore, as shown in FIG. 14 , a plurality of labyrinth-forming protrusions 264 are formed on the outer peripheral wall of the ring member 256. The labyrinth-forming protrusions 264 abut against the inner walls of holes 272 formed in the intermediate plate 266. Compressed air generated by the compressor wheel 222 reaches the labyrinth-forming protrusions 264 via the back surface of the compressor wheel 222. Furthermore, combustion gas from the turbine wheel 224 reaches the labyrinth-forming protrusions 264. As described above, the pressure of the compressed air is higher than the pressure of the combustion gas. Therefore, the combustion gas is prevented from passing through the labyrinth-forming protrusions 264 and flowing into the compressor wheel 222. For these reasons, the intrusion of burned fuel into the through-hole 240 from between the two wheels 222, 224 is prevented.

[0185] 13, when output shaft 204 starts to rotate at high speed, the supply of current from battery 146 (see FIG. 11) to electromagnetic coil 110 is stopped. However, because turbine wheel 224 is already rotating at high speed as described above, rotating shaft 39 rotates at high speed integrally with turbine wheel 224 and output shaft 204. Even at this time, for the same reason as described above, sufficient rotational torque is transmitted from output shaft 204 to rotating shaft 39.

[0186] 3, the rotation direction of the output shaft 204 and the rotating shaft 39 is preferably opposite to the rotation direction when the small cap nut 58, the large cap nut 60, and the male threaded portion 252 are screwed together. In this case, the small cap nut 58, the large cap nut 60, and the male threaded portion 252 are prevented from loosening during rotation of the rotating shaft 39. Note that the small cap nut 58, the large cap nut 60, or the male threaded portion 252 may be provided with a mechanism to prevent loosening.

[0187] Because the rotating shaft 39 holds the magnet 38, an AC current is generated in the electromagnetic coil 110 surrounding the magnet 38. The AC current is sent to the current converter 150 shown in FIGS. 2 and 11 via a U-phase terminal 1441, a V-phase terminal 1442, and a W-phase terminal 1443. A conversion circuit 152 of the current converter 150 converts this AC current into a DC current. When a control circuit 156 of the current converter 150 determines that the output of an external load (e.g., a motor) electrically connected to the battery 146 has decreased, the control circuit 156 supplies a DC current to the battery 146 (see FIG. 11) via a capacitor 154. This charges the battery 146.

[0188] During this process, the current converter 150, particularly the conversion circuit 152 and the capacitor 154, become heated. However, in this embodiment, the conversion circuit 152 and the capacitor 154 in the device case 158 are located close to the cooling jacket 24. Therefore, the heat of the conversion circuit 152 and the capacitor 154 is quickly conducted to the cooling medium in the cooling jacket 24. This prevents the conversion circuit 152 and the capacitor 154 from becoming excessively hot.

[0189] The electromagnetic coil 110 generates heat as current flows through it. Here, a portion of the first diverted air flowing through the first space 853a contacts the left end of the stator 36. The remaining portion of the first diverted air flowing through the gas flow path 72 of the accommodation chamber 22 and toward the second space 853b (second insertion hole 86) contacts the inner wall of the stator 36 and the outer periphery of the rotor 34. The remaining portion of the first diverted air flowing toward the second space 853b through the multiple cooling passages 41 contacts the inside of the rotor 34. Therefore, the stator 36 and the rotor 34 (magnets 38) are cooled by the first diverted air. In addition, a cooling medium flows through the cooling jacket 24 provided in the main housing 16. The rotating electric machine 12 is quickly cooled by this cooling medium.

[0190] In this embodiment, the rotating electric machine housing 14 (main housing 16) that houses the rotating electric machine 12 and the first casing 26 that houses the U-phase terminal 1441, the V-phase terminal 1442, and the W-phase terminal 1443 are provided separately. Therefore, the heat generated in the stator 36 in the main housing 16 is unlikely to affect the U-phase terminal 1441, the V-phase terminal 1442, and the W-phase terminal 1443 in the first casing 26. Note that the U-phase terminal 1441, the V-phase terminal 1442, and the W-phase terminal 1443 also generate heat when current is applied. However, the U-phase terminal 1441, the V-phase terminal 1442, and the W-phase terminal 1443 are quickly cooled by the first diverted air flow supplied to the first casing 26.

[0191] In this way, the first diverted air also serves to cool heat-generating locations in the rotating electric machine system 10. Because the electrical terminals (U-phase terminal 1441, V-phase terminal 1442, and W-phase terminal 1443), the electromagnetic coil 110, the magnet 38, etc. are cooled, the influence of heat on the output control, etc. of the rotating electric machine system 10 is avoided. In addition, a decrease in the excitation of the electromagnetic coil 110, the magnet 38, etc. due to heat is also avoided. As a result, the reliability of the rotating electric machine system 10 is improved.

[0192] Furthermore, because the main housing 16 that houses the rotating electric machine 12 and the first casing 26 that houses the U-phase terminal 1441, the V-phase terminal 1442, and the W-phase terminal 1443 are provided separately, the rotating electric machine 12 and the electrical terminals are spaced apart from each other. Therefore, the U-phase terminal 1441, the V-phase terminal 1442, and the W-phase terminal 1443 are less susceptible to the effects of vibrations that occur as the rotor 34 rotates. In other words, the U-phase terminal 1441, the V-phase terminal 1442, and the W-phase terminal 1443 are protected from vibrations. Furthermore, as described above, the lubricating oil in the first bearing 74 and the second bearing 84 prevents seizure. Therefore, the rotating electric machine system 10 has excellent durability.

[0193] While the rotating shaft 39 is rotating, the rotation angle (rotation parameter) of the rotating shaft 39 is detected by the resolver 132. Specifically, the resolver rotor 56 fitted onto the left end portion 422 of the inner shaft 42 rotates integrally with the rotating shaft 39. As a result, an electrical signal generated in the resolver stator 130 is transmitted to the receiver via the transmitting connector 136. The receiver reads the electrical signal and calculates the rotation angle of the rotating shaft 39 based on the electrical signal. The receiver sends the calculation result to a control device or the like (not shown). The control device or the like calculates the rotation speed based on this rotation angle.

[0194] The resolver 132 is disposed at the protruding tip 46 of the rotating shaft 39 that is exposed from the rotating electric machine housing 14. Therefore, the resolver 132 is less likely to be affected by heat generated in the electromagnetic coil 110 of the stator 36 inside the rotating electric machine housing 14. The resolver 132 is also less likely to be affected by vibrations that occur with the rotation of the rotor 34. In addition, the first bearing 74 and the second bearing 84 that support the rotating shaft 39 are provided inside the rotating electric machine housing 14. Therefore, the rotating electric machine housing 14 suppresses vibration of the first bearing 74 and the second bearing 84. This also makes it less likely that the resolver 132 will be affected by vibrations.

[0195] For example, in this embodiment, a third sub-branch channel 941 and a fourth sub-branch channel 942 are provided. Alternatively, the first branch channel L may be branched into a first sub-branch channel and a second sub-branch channel. In this case, a portion of the first diverted air flow is supplied from the first sub-branch channel to the first distal end 781, and a portion of the first diverted air flow is supplied from the second sub-branch channel to the first proximal end 782. Alternatively, the first branch channel L may be branched into a first sub-branch channel and a second sub-branch channel, and a third sub-branch channel 941 and a fourth sub-branch channel 942 may be provided.

[0196] In the gas turbine engine 200, the compressor wheel 222 and the turbine wheel 224 may be arranged in the opposite direction to that shown in Figure 13. In this case, a through hole 240 may be formed in the turbine wheel 224, and the compressor wheel 222 may be provided with the output shaft 204. Alternatively, the compressor wheel 222 and the turbine wheel 224 may be of a centrifugal type or an axial flow type. As long as the compressor wheel 222 and the turbine wheel 224 are arranged on the same axis, a combination of a centrifugal type and an axial type multi-stage compressor wheel and a multi-stage turbine wheel may be used.

[0197] 3, the rotating electric machine 12 constituting the rotating electric machine system 10 may be a motor in which the rotating shaft 39 rotates when current is applied to the electromagnetic coil 110. In this case, the U-phase terminal 1441, the V-phase terminal 1442, and the W-phase terminal 1443 are electrical terminal portions that receive power from the battery 146.

[0198] In the above-described embodiment, a mode is exemplified in which a portion of the compressed air generated by the gas turbine engine 200 is supplied to the rotary electric machine housing 14. Alternatively, as shown in Fig. 15, it is also possible to use an externally provided compression pump 320 or the like as the gas supply source.

[0199] In this case, for example, a communication hole 322 is formed in the first casing 26. Compressed air sent from the compression pump 320 flows into this communication hole 322. Also, a communication hole 324 communicating with the upstream communication hole 164 is formed in the second sub-housing 20. The communication hole 324 is closed with a plug 326. In this state, the compression pump 320 compresses the atmosphere or the like to obtain compressed air. This compressed air is supplied to the first hollow tube portion 1601 to the third hollow tube portion 1603.

[0200] In this case, the entire amount of compressed air can be used as combustion air.

[0201] As described above, in this embodiment, the rotor 34 of the rotating electrical machine system 10 is provided with the cooling passage 41 through which compressed air for cooling flows, and the rectifying structure 37 has a plurality of inlet fins 855a and outlet fins 855b that can rectify the flow of the compressed air. The rectifying structure 37 is disposed facing the first and second openings 411, 412 of the cooling passage 41, and is fixed to a non-rotating portion within the main housing 16.

[0202] This makes it possible to prevent the rotor 34 from becoming too large in the radial direction, and to suppress vibration of the rotor 34 when it rotates, compared to a structure in which a suction fan is provided inside the rotor 34. The rectifying structure 37 rectifies the flow of compressed air, allowing the compressed air to smoothly flow through the cooling passage 41 and cool the rotor 34. 。

[0203] The first and second openings 411, 412 are disposed radially offset from the center of the rotation axis of the rotor 34, and the multiple inlet side fins 855a and outlet side fins 855b are disposed at intervals in the circumferential direction of the rotor 34. This allows the multiple inlet side fins 855a and outlet side fins 855b to effectively straighten the flow of compressed air.

[0204] The plurality of cooling passages 41 are arranged at equal intervals in the circumferential direction of the rotor 34, and the plurality of inlet-side fins 855a and outlet-side fins 855b face first and second imaginary circles D1 and D2 that connect the first and second openings 411 and 412 of each cooling passage 41. As a result, the plurality of inlet-side fins 855a and outlet-side fins 855b are arranged on the first and second imaginary circles D1 and D2 in accordance with the arrangement of the plurality of first and second openings 411 and 412, so that the rotor 34 can be effectively cooled by the compressed air flowing through the cooling passages 41.

[0205] The rotor 34 has an expanded diameter portion 40 whose diameter expands from the main body portion 44a. A first opening 411 opens to a first wall surface 44c of the expanded diameter portion 40. A second opening 412 opens to a second wall surface 44d of the expanded diameter portion 40. A plurality of inlet-side fins 855a and outlet-side fins 855b face the first and second wall surfaces 44c and 44d, respectively, in the axial direction. This allows the flow straightening structure 37, which has the inlet-side fins 855a and outlet-side fins 855b, to be disposed closer to the first and second openings 411 and 412 of the cooling passage 41. Therefore, the flow straightening structure 37 can more effectively straighten the compressed air.

[0206] Providing the outlet-side rectifying member 852 facing the outlet 414 (second opening 412) of the cooling passage 41 prevents the compressed air flowing out from the outlet 414 of the cooling passage 41 from accumulating in the second space 853b. This promotes the flow of compressed air in the cooling passage 41, thereby enabling the rotor 34 to be cooled efficiently.

[0207] The outlet-side rectifying member 852 has a plurality of outlet-side fins 855b that rectify the flow of compressed air flowing out from the outlet 414 of the cooling passage 41 in the axial direction of the rotor 34. This prevents the compressed air flowing out from the cooling passage 41 from swirling within the second space 853b. This effectively prevents the compressed air from stagnating.

[0208] Each of the multiple outlet-side fins 855b has a direction change portion 857b that curves downstream so as to change direction toward the axial direction of the rotor 34. This allows the direction change portion 857b to effectively straighten the flow of compressed air flowing out from the outlet 414 of the cooling passage 41 to the second space 853b toward the axial direction of the rotor 34.

[0209] By providing an inlet side straightening member 851 facing the inlet 413 (first opening 411) of the cooling passage 41, the flow of compressed air from the inlet 413 into the cooling passage 41 is promoted, thereby enabling the rotor 34 to be cooled efficiently.

[0210] The inlet-side rectifying member 851 has a plurality of inlet-side fins 855a that rectify the flow of compressed air in the circumferential direction of the rotor 34. This promotes the flow of compressed air into the cooling passage 41, thereby enabling the rotor 34 to be cooled efficiently.

[0211] Each of the multiple inlet-side fins 855a has a direction change portion 857a that curves downstream to change direction in the rotation direction of the rotor 34. This allows the direction change portion 857a to effectively straighten the flow of compressed air from the first space 853a to the inlet 413 of the cooling passage 41 in the circumferential direction of the rotor 34. When the rotor 34 is rotating, the compressed air can be efficiently introduced into the cooling passage 41 of the rotor 34.

[0212] By providing an inlet-side rectifying member 851 facing the inlet 413 of the cooling passage 41 and an outlet-side rectifying member 852 facing the outlet 414 of the cooling passage 41, it is possible to rectify both the flow of compressed air flowing into the cooling passage 41 and the flow of compressed air flowing out of the cooling passage 41. Therefore, the rotor 34 can be cooled more efficiently by the compressed air flowing through the cooling passage 41.

[0213] By arranging the flow straightening structure 37 facing the gas flow path 72 between the rotor 34 and the stator 36, it is possible to straighten the compressed air flowing through the gas flow path 72 in addition to the compressed air flowing through the cooling passage 41. Therefore, the rotor 34 can be efficiently cooled by the compressed air flowing through the cooling passage 41 and the gas flow path 72.

[0214] The above embodiment can be summarized as follows.

[0215] The above embodiment includes a rotor (34) having magnets (38); a stator (36) surrounding the rotor; a housing (14) that accommodates the rotor and the stator and rotatably supports the rotor; A rotating electrical machine system (10) comprising: a cooling passage (41, 72) through which a cooling gas supplied from a gas supply mechanism provided separately from the rotor flows is provided in at least one of the inside and the outer periphery of the rotor; the rotating electric machine system includes a rectifying structure (37) having a plurality of fins (855a, 855b) capable of rectifying the flow of the gas; The flow straightening structure is fixed to a non-rotating portion within the housing so as to face the cooling passage.

[0216] The cooling passage includes an intra-rotor cooling passage (41) disposed inside the rotor, The rotor cooling passage has openings (411, 412) that open to the outer surface of the rotor, the opening faces the opening and opens on the outer surface of the rotor at a position offset in the radial direction from the center of the rotation axis of the rotor; The fins are arranged at intervals in the circumferential direction of the rotor so as to surround the center of the rotation axis of the rotor.

[0217] a plurality of the rotor internal cooling passages are arranged in the rotor so as to be equally spaced apart in the circumferential direction of the rotor; The plurality of fins face an imaginary circle (D1, D2) that connects the openings of the plurality of in-rotor cooling passages in the axial direction of the rotor.

[0218] The rotor includes a main body portion (44a) supported by the housing; an expanded diameter portion (40) that is disposed in an intermediate portion between one end and the other end of the main body portion in the axial direction of the rotor and expands in diameter radially outward from the main body portion; and The openings are open to end faces (44c, 44d) of the enlarged diameter portion in the axial direction, The fins and the expanded diameter portion face each other in the axial direction.

[0219] the openings include an inlet (413) and an outlet (414) of the rotor cooling passage; The flow straightening structure has an outlet side flow straightening member (852) facing the outlet.

[0220] The outlet-side rectifying member has a plurality of outlet-side fins (855b) that rectify the flow of the gas flowing out from the outlet in the axial direction of the rotor.

[0221] Each of the outlet fins has a direction change portion (857b) that curves toward the downstream side so as to change direction toward the axial direction of the rotor.

[0222] the opening includes an inlet and an outlet of the rotor cooling passage; The flow straightening structure has an inlet side flow straightening member (851) facing the inlet.

[0223] The inlet-side straightening member has a plurality of inlet-side fins (855a) that straighten the flow of the gas in the circumferential direction of the rotor.

[0224] Each of the plurality of inlet fins has a direction change portion (857a) that curves downstream to change direction in the rotation direction of the rotor.

[0225] the opening includes an inlet and an outlet of the rotor cooling passage; The flow straightening structure has an inlet side flow straightening member facing the inlet and an outlet side flow straightening member facing the outlet.

[0226] the cooling passage has a gas flow path (72) that is disposed between the rotor and the stator and through which the gas flows; The flow straightening structure faces at least one of the upstream and downstream sides of the gas flow path.

[0227] The present invention is not limited to the above disclosure, and various configurations can be adopted without departing from the gist of the present invention. [Explanation of symbols]

[0228] 10... Rotating electric machine system 12... Rotating electric machine 14... Rotating electric machine housing 34... Rotor 36... Stator 37... Rectification structure 38...Magnet 39...Rotating shaft 40... Expanded diameter part 41... Cooling passage 44...Outer shaft 72...Gas flow path 851... Inlet side straightening member 852... Outlet side straightening member 855a...Inlet side fin 855b...Outlet side fin

Claims

1. a rotor having a magnet; a stator surrounding the rotor; a housing that accommodates the rotor and the stator and rotatably supports the rotor; A rotating electrical machine system comprising: a cooling passage through which a cooling gas supplied from a gas supply mechanism provided separately from the rotor flows is provided in at least one of the inside and the outer periphery of the rotor; the rotating electrical machine system includes a rectifying structure having a plurality of fins capable of rectifying the flow of the gas, the flow straightening structure is fixed to a non-rotating portion within the housing so as to face the cooling passage; The cooling passage is an internal rotor cooling passage disposed within the rotor; a gas flow path disposed between the rotor and the stator through which the gas flows; and a rotor cooling passage and a gas flow passage, the rotor cooling passage and the gas flow passage being directly opposite each other in the axial direction of the rotor;

2. 2. The rotating electrical machine system according to claim 1, the rotor internal cooling passage has an opening that opens to an outer surface of the rotor, the opening opens to the outer surface of the rotor at a position offset in the radial direction from the center of the rotation axis of the rotor; The rotating electric machine system, wherein the plurality of fins are arranged at intervals in the circumferential direction of the rotor so as to surround the center of the rotation axis of the rotor.

3. 3. The rotating electrical machine system according to claim 2, a plurality of the rotor internal cooling passages are arranged in the rotor so as to be equally spaced apart in the circumferential direction of the rotor; a rotating electric machine system in which the plurality of fins face an imaginary circle formed by connecting the openings of the plurality of cooling passages within the rotor in the axial direction of the rotor;

4. 4. The rotating electrical machine system according to claim 2, The rotor includes a main body supported by the housing; an expanded diameter portion that is disposed in an intermediate portion between one end and the other end of the main body portion in the axial direction of the rotor and that expands radially outward from the main body portion; and the opening opens at an end surface of the expanded diameter portion in the axial direction, The rotating electric machine system, wherein the plurality of fins and the expanded diameter portion face each other in the axial direction.

5. 3. The rotating electrical machine system according to claim 2, the opening includes an inlet and an outlet of the rotor cooling passage; The rectifying structure has an outlet-side rectifying member facing the outlet.

6. 6. The rotating electrical machine system according to claim 5, The outlet-side straightening member has a plurality of outlet-side fins that straighten the flow of the gas flowing out from the outlet in the axial direction of the rotor.

7. 7. The rotating electrical machine system according to claim 6, A rotating electric machine system, wherein each of the plurality of outlet-side fins has a direction change portion that curves toward the downstream side so as to change direction toward the axial direction of the rotor.

8. 3. The rotating electrical machine system according to claim 2, the opening includes an inlet and an outlet of the rotor cooling passage; The rectifying structure has an inlet-side rectifying member facing the inlet.

9. 9. The rotating electrical machine system according to claim 8, The inlet-side straightening member has a plurality of inlet-side fins that straighten the flow of the gas in the circumferential direction of the rotor.

10. 10. The rotating electrical machine system according to claim 9, A rotating electric machine system, wherein each of the plurality of inlet fins has a direction change portion that curves toward the downstream side so as to change direction toward the rotation direction of the rotor.

11. 3. The rotating electrical machine system according to claim 2, the opening includes an inlet and an outlet of the rotor cooling passage; The flow straightening structure includes an inlet side flow straightening member facing the inlet, an outlet-side flow straightening member facing the outlet; A rotating electric machine system having:

12. 3. The rotating electrical machine system according to claim 1, a rotating electrical machine system, wherein the fins of the flow straightening structure face at least one of the upstream and downstream sides of the gas flow path;

13. In the rotating electrical machine system according to claim 1 or 2, a first space provided upstream of the gas flow path and the rotor internal cooling passage, the first space communicating with the gas flow path and the rotor internal cooling passage; a second space provided downstream of the gas flow path and the rotor internal cooling passage, the second space communicating with the gas flow path and the rotor internal cooling passage; and the gas supplied to the first space is divided into the gas flow path and the rotor internal cooling passage, the gas flowing through the gas flow path and the gas flowing through the rotor internal cooling passage join together in the second space; a rotating electric machine system, wherein each of the plurality of fins is disposed in the first space and the second space;

14. In the rotating electrical machine system according to claim 1, Each of the plurality of fins is a plurality of inlet fins that rectify the flow of the gas supplied to the cooling passage from the axial direction to the circumferential direction of the rotor; a plurality of outlet-side fins that rectify the flow of the gas flowing out from the outlet of the cooling passage in the axial direction; and each of the plurality of inlet-side fins has a first upstream end provided upstream in the axial direction, a first downstream end provided downstream in the axial direction, and an inlet-side direction change portion that curves in the axial direction from the first upstream end to the first downstream end so as to face a rotation direction of the rotor, a rotating electric system, wherein each of the plurality of outlet side fins has a second upstream end provided upstream in the axial direction, a second downstream end provided downstream in the axial direction, and an outlet side direction change portion that curves in the axial direction from the second downstream end to the second upstream end so as to face in a direction opposite to the rotation direction of the rotor.

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