gas turbine

Abstract

The objective is to provide a gas turbine that facilitates the maintenance of the condition of the windings wrapped around the stator. [Solution] The gas turbine comprises a generator including a rotor, a rotating shaft connected to rotate integrally with the rotor, a rotor connected to rotate integrally with the rotating shaft, and a stator, wherein the stator is located around the rotor and includes a stator core made of a magnetic material, and includes a plurality of teeth that protrude radially inward from the rotational axis of the rotor and are spaced apart from each other in the circumferential direction of the rotational axis, a conductive winding wound around the plurality of teeth, and a projection that protrudes from the stator core in the direction of the rotational axis at a position radially inward from the winding.

Description

Technical Field

[0001] The present disclosure relates to a gas turbine.

Background Art

[0002] Patent Document 1 discloses a two-shaft gas turbine engine including a generator between a low-pressure compressor and a high-pressure compressor. The generator is driven by the rotational driving force of the rotating shaft of the gas turbine engine to generate electricity.

Prior Art Documents

Patent Documents

[0003]

Patent Document 1

Summary of the Invention

Problems to be Solved by the Invention

[0004] In Patent Document 1, since the generator is located near the high-pressure compressor, it is exposed to a high-temperature environment. Therefore, the conditions required for the member that holds the state of the electric wire wound around the stator are severe.

[0005] One aspect of the present disclosure aims to provide a gas turbine that facilitates maintaining the state of the winding wound around the stator.

Means for Solving the Problems

[0006] A gas turbine according to one aspect of the present disclosure includes a generator comprising a rotor, a rotating shaft connected to rotate integrally with the rotor, a rotor connected to rotate integrally with the rotating shaft, and a stator, wherein the stator is located around the rotor and comprises a stator core made of a magnetic material, and includes a plurality of teeth that project inward in the radial direction of the rotational axis of the rotor and are spaced apart from each other in the circumferential direction of the rotational axis, a conductive winding wound around the plurality of teeth, and a projection that projects from the stator core in the direction of the rotational axis at a position radially inward of the winding. [Effects of the Invention]

[0007] According to one aspect of this disclosure, the state of the windings wrapped around the stator can be easily maintained. [Brief explanation of the drawing]

[0008] [Figure 1] Figure 1 is a cross-sectional view showing an example of the configuration of a gas turbine according to an embodiment. [Figure 2] Figure 2 is an enlarged cross-sectional view showing the structure from the low-pressure side compressor to the high-pressure side compressor in Figure 1. [Figure 3] Figure 3 is a cross-sectional view showing an enlarged view of the generator in Figure 2. [Figure 4] Figure 4 is a view of the stator in Figure 3, seen in the axial direction. [Figure 5] Figure 5 is a perspective view showing an example of the configuration of the divided core shown in Figure 4. [Figure 6] Figure 6 shows the stator from Figure 3, viewed from a different position in the axial direction than in Figure 4. [Figure 7] Figure 7 shows an example of the binding points of the string material in Figure 6. [Figure 8] Figure 8 is a view of the generator housing shown in Figure 3, viewed in the axial direction. [Modes for carrying out the invention]

[0009] Illustrative embodiments of the present disclosure are described below with reference to the drawings. The embodiments described below are all comprehensive or specific examples. Components in the following embodiments that are not described in the independent claim representing the highest-level concept are described as optional components. The figures in the accompanying drawings are schematic and not necessarily strictly illustrative. In each figure, substantially identical components are denoted by the same reference numerals, and redundant descriptions may be omitted or simplified.

[0010] In the following explanation, axial direction X refers to the direction in which the axis L of the rotation shaft 2 of the gas turbine 1 extends. Furthermore, "front" refers to the side of the gas turbine 1 from which air is introduced from the outside in axial direction X, and "rear" refers to the side of the gas turbine 1 from which exhaust gas is discharged in axial direction X. Axial direction X is the front-to-back direction of the gas turbine 1.

[0011] Figure 1 is a cross-sectional view showing an example of the configuration of a gas turbine 1 according to an embodiment. As shown in Figure 1, in this embodiment, the gas turbine 1 is a twin-shaft gas turbine. The gas turbine 1 is used as an engine for aircraft such as unmanned aerial vehicles, but the application of the gas turbine 1 is not limited to aircraft. The gas turbine 1 can be used as a turbofan engine.

[0012] The gas turbine 1 comprises a rotating shaft 2, a fan 3, a compressor 4, a combustor 5, a turbine 6, a generator 7, and a casing 8. The fan 3 is connected to the front of the rotating shaft 2 and rotates together with the rotating shaft 2. The compressor 4, combustor 5, and turbine 6 are arranged in this order from front to rear along the rotating shaft 2. The casing 8 houses all or part of the rotating shaft 2, fan 3, compressor 4, combustor 5, turbine 6, and generator 7.

[0013] In this embodiment, the rotating shaft 2 includes a low-pressure shaft 2A and a high-pressure shaft 2B extending in the axial direction X. The high-pressure shaft 2B is arranged on the same axis as the low-pressure shaft 2A and is rotatable relative to the low-pressure shaft 2A. The high-pressure shaft 2B is a tubular hollow shaft. The low-pressure shaft 2A is inserted into the hollow space of the high-pressure shaft 2B and penetrates the hollow space. The low-pressure shaft 2A is longer in the front-rear direction than the high-pressure shaft 2B, and the front end 2Aa and rear end 2Ab of the low-pressure shaft 2A are exposed to the outside from the front end 2Ba and rear end 2Bb of the high-pressure shaft 2B, respectively. The front end 2Aa of the low-pressure shaft 2A is connected to the fan 3.

[0014] The compressor 4 includes a low-pressure side compressor 4A and a high-pressure side compressor 4B located behind the low-pressure side compressor 4A. The low-pressure side compressor 4A is an axial flow compressor and includes rotor blades connected to rotate integrally with the low-pressure shaft 2A. In this embodiment, the low-pressure side compressor 4A includes two rotor blades aligned in the axial direction X. The connection between the two rotor blades of the low-pressure side compressor 4A and the low-pressure shaft 2A is located between the front end 2Aa of the low-pressure shaft 2A and the front end 2Ba of the high-pressure shaft 2B. In this embodiment, the two rotor blades of the low-pressure side compressor 4A are connected to the front end 2Aa of the low-pressure shaft 2A together with the fan 3, although they may be connected to the low-pressure shaft 2A at a different position from the fan 3, further rearward from the front end 2Aa.

[0015] The high-pressure side compressor 4B is a centrifugal compressor and includes a rotor connected to the high-pressure shaft 2B so as to rotate integrally with it. In this embodiment, the high-pressure side compressor 4B includes one rotor. The connection between the rotor of the high-pressure side compressor 4B and the high-pressure shaft 2B is located in front of the combustor 5. The types of low-pressure side compressor 4A and high-pressure side compressor 4B are not limited to axial flow compressors and centrifugal compressors. A diffuser 12 is arranged on the outer circumference of the high-pressure side compressor 4B to send the air flowing out of the high-pressure side compressor 4B to the rear. Behind the diffuser 12 is the combustor 5. The combustor 5 is a back-flow type combustor.

[0016] The turbine 6 includes a high-pressure turbine 6B and a low-pressure turbine 6A disposed behind the high-pressure turbine 6B. The low-pressure shaft 2A mechanically connects the low-pressure compressor 4A to the low-pressure turbine 6A. The high-pressure shaft 2B mechanically connects the high-pressure compressor 4B to the high-pressure turbine 6B. The low-pressure turbine 6A includes rotating blades connected to rotate integrally with the low-pressure shaft 2A. In this embodiment, the low-pressure turbine 6A includes two rotating blades arranged in the axial direction X. The connection portion between the two rotating blades of the low-pressure turbine 6A and the low-pressure shaft 2A is located between the rear end portion 2Bb of the high-pressure shaft 2B and the rear end portion 2Ab of the low-pressure shaft 2A. The low-pressure turbine 6A can rotate the low-pressure compressor 4A and the fan 3 via the low-pressure shaft 2A.

[0017] The high-pressure turbine 6B includes rotating blades connected to rotate integrally with the high-pressure shaft 2B. In this embodiment, the high-pressure turbine 6B includes one rotating blade. The connection portion between the rotating blade of the high-pressure turbine 6B and the high-pressure shaft 2B is located between the high-pressure compressor 4B and the rear end portion 2Bb of the high-pressure shaft 2B. The high-pressure turbine 6B can rotate the high-pressure compressor 4B via the high-pressure shaft 2B.

[0018] The casing 8 includes a cylindrical outer shell 8A and an inner shell 8B arranged concentrically with each other. The inner shell 8B houses the compressor 4, the combustor 5, the turbine 6, and the generator 7. A cylindrical bypass flow path B is formed between the inner shell 8B and the outer shell 8A.

[0019] The gas turbine 1 includes a first cylinder 9 extending in the axial direction X from the fan 3 to the high-pressure compressor 4B inside the inner shell 8B. The outer diameter and the inner diameter of the first cylinder 9 decrease from the front to the rear. The first cylinder ⑨ defines a part of the compressed air flow path R from the low-pressure compressor 4A to the high-pressure compressor 4B between the first cylinder 9 and the inner shell 8B. The outer peripheral surface of the first cylinder 9 faces the compressed air flow path R. The generator 7 is disposed inside the first cylinder 9. The first cylinder 9 is connected to the inner shell 8B by a plurality of struts 9A and supported by the inner shell 8B. The rotating blades of the low-pressure compressor 4A and the rotating blades of the high-pressure compressor 4B are located in the compressed air flow path R.

[0020] The gas turbine 1 includes a second cylinder 10 that extends in the axial direction X from the high-pressure turbine 6B to the low-pressure turbine 6A inside the inner casing 8B. The second cylinder 10 defines at least a part of the gas flow path G extending rearward from the combustor 5 between the second cylinder 10 and the inner casing 8B inside the inner casing 8B. The outer peripheral surface of the second cylinder 10 faces the gas flow path G. The second cylinder 10 is connected to the inner casing 8B via a plurality of struts 10A etc. and is supported by the inner casing 8B. The gas flow path G merges with the bypass flow path B behind the low-pressure turbine 6A. The rotor blades of the low-pressure turbine 6A and the rotor blades of the high-pressure turbine 6B are located in the gas flow path G.

[0021] The gas turbine 1 includes a strut housing 11. Part or all of the strut housing 11 is housed in the outer casing 8A. The strut housing 11 is located in front of the high-pressure compressor 4B. In the present embodiment, the strut housing 11 is located between the generator 7 and the high-pressure compressor 4B in the axial direction X. The strut housing 11 extends in the axial diameter direction, which is the radial direction of the axis L, from the first cylinder 9 to the outer casing 8A. The strut housing 11 is connected to the outer casing 8A, the inner casing 8B, and the first cylinder 9, and connects the outer casing 8A, the inner casing 8B, and the first cylinder 9 to each other.

[0022] The strut housing 11 includes an outer casing portion 11a, an inner casing portion 11b, a cylinder portion 11c, and a plurality of struts 11d. The outer casing portion 11a has a cylindrical shape extending in the circumferential direction around the axis L, is connected to the outer casing 8A, and forms a part of the outer casing 8A. The inner casing portion 11b has a cylindrical shape extending in the circumferential direction, is connected to the inner casing 8B, and forms a part of the inner casing 8B. The cylinder portion 11c has a cylindrical shape extending in the circumferential direction, is connected to the first cylinder 9, and forms a part of the first cylinder 9. The plurality of struts 11d extend radially in the axial diameter direction from the cylinder portion 11c through the inner casing portion 11b to the outer casing portion 11a, and connect the outer casing portion 11a, the inner casing portion 11b, and the cylinder portion 11c to each other.

[0023] A portion of the air drawn in by fan 3 flows through bypass channel B and is discharged to the rear. The remaining air drawn in by fan 3 flows through compressed air channel R and enters the low-pressure compressor 4A. The air passes sequentially through the low-pressure compressor 4A and the high-pressure compressor 4B within the compressed air channel R and enters the combustor 5 via the diffuser 12. The combustion gas discharged from the outlet of the combustor 5 passes through the nozzle unit 13 and enters the gas channel G. The combustion gas passes sequentially through the high-pressure turbine 6B and the low-pressure turbine 6A within the gas channel G and is discharged to the rear. The combustion gas discharged from gas channel G merges with the air discharged from bypass channel B, is accelerated by the air, and is discharged to the outside of the casing 8.

[0024] The high-pressure side turbine 6B rotates under the influence of the high-temperature, high-pressure combustion gas flow immediately after it flows out of the combustor 5. The low-pressure side turbine 6A rotates under the influence of the combustion gas flow that has been cooled and depressurized as it passes through the high-pressure side turbine 6B. For this reason, the high-pressure side turbine 6B rotates at a higher rotational speed than the low-pressure side turbine 6A. Furthermore, the high-pressure side compressor 4B, which is rotated by the high-pressure side turbine 6B, rotates at a higher rotational speed than the low-pressure side compressor 4A, which is rotated by the low-pressure side turbine 6A. Rotational speed refers to the number of rotations per unit time. The air flowing through the compressed air passage R is pressurized by the low-pressure side compressor 4A, and then pressurized to an even higher pressure by the high-pressure side compressor 4B before flowing into the combustor 5. Because the high-pressure side compressor 4B is affected by the heat generated in the combustor 5, it is exposed to a higher temperature and pressure environment than the low-pressure side compressor 4A.

[0025] Figure 2 is an enlarged cross-sectional view showing the structure from the low-pressure side compressor 4A to the high-pressure side compressor 4B in Figure 1. As shown in Figure 2, the generator 7 generates electricity when the generator shaft 7A of the generator 7 is driven by the rotational driving force of the rotating shaft 2. In this embodiment, the generator shaft 7A is located coaxially with the low-pressure shaft 2A and the high-pressure shaft 2B. The generator 7 may also have a starter function that rotates the rotating shaft 2 when the gas turbine 1 is started. In this case, the generator 7 is a motor generator. The generator 7 is located inside the first cylinder 9 and in front of the high-pressure side compressor 4B. In this embodiment, the generator 7 is located between the low-pressure side compressor 4A and the high-pressure side compressor 4B.

[0026] The generator 7 includes a generator shaft 7A, a rotor 7B that rotates integrally with the generator shaft 7A, a stator 7C located around the rotor 7B, and a generator housing 7D. The generator shaft 7A and rotor 7B are located inside the stator 7C. The generator shaft 7A is a tubular hollow shaft extending in the axial direction X. The low-pressure shaft 2A is inserted into and penetrates the hollow space of the generator shaft 7A. The front end 2Ba of the high-pressure shaft 2B is inserted into the hollow space of the generator shaft 7A. The rear end 7Ab of the generator shaft 7A is connected to the front end 2Ba of the high-pressure shaft 2B to transmit rotational forces around axis L. The generator shaft 7A rotates together with the high-pressure shaft 2B around axis L.

[0027] In this embodiment, the rear end portion 7Ab of the generator shaft 7A and the front end portion 2Ba of the high-voltage shaft 2B are spline-connected. The inner circumferential surface of the rear end portion 7Ab of the generator shaft 7A includes a plurality of grooves spaced apart in the circumferential direction and extending in the axial direction X, which function as an internal spline. The outer circumferential surface of the front end portion 2Ba of the high-voltage shaft 2B includes a plurality of band-shaped projections spaced apart in the circumferential direction and extending in the axial direction X, which function as an external spline.

[0028] The rotor 7B is a cylindrical body having an internal space extending in the axial direction X. The generator shaft 7A is inserted into and passes through the internal space of the rotor 7B. The rotor 7B is coupled to the generator shaft 7A and rotates together with the generator shaft 7A around the axis L. The rotor 7B contains permanent magnets, and the stator 7C contains windings. The rotor 7B is surrounded by the stator 7C. Therefore, the generator 7 is of the permanent magnet type.

[0029] The generator housing 7D houses the rotor 7B and the stator 7C. The generator housing 7D covers the rotor 7B and the stator 7C from at least the outside in the radial direction. The generator housing 7D may also cover the rotor 7B and the stator 7C from both sides in the axial direction X.

[0030] As shown in Figure 1, the gas turbine 1 comprises a plurality of bearings 20 and a bearing housing 30 that supports the bearings 20. The bearings 20 include a low-pressure bearing 20A, a high-pressure bearing 20B, and a generator bearing 20C. The low-pressure bearing 20A rotatably supports the low-pressure shaft 2A, the high-pressure bearing 20B rotatably supports the high-pressure shaft 2B, and the generator bearing 20C rotatably supports the generator shaft 7A. In this embodiment, the low-pressure bearing 20A, the high-pressure bearing 20B, and the generator bearing 20C are radial bearings, for example, radial ball bearings or radial roller bearings.

[0031] As shown in Figure 2, the low-pressure bearing 20A includes a first low-pressure bearing 20Aa and a second low-pressure bearing 20Ab located at the front of the low-pressure shaft 2A, and a third low-pressure bearing 20Ac located at the rear of the low-pressure shaft 2A. The third low-pressure bearing 20Ac is shown in Figure 1. In this embodiment, the first low-pressure bearing 20Aa and the second low-pressure bearing 20Ab are located between the front end 2Aa of the low-pressure shaft 2A and the front end 7Aa of the generator shaft 7A. The second low-pressure bearing 20Ab is located behind the first low-pressure bearing 20Aa. The third low-pressure bearing 20Ac is located between the connection portion between the low-pressure shaft 2A and the low-pressure side turbine 6A and the rear end 2Bb of the high-pressure shaft 2B.

[0032] The high-pressure bearing 20B includes a first high-pressure bearing 20Ba located at the front of the high-pressure shaft 2B and a second high-pressure bearing 20Bb located at the rear of the high-pressure shaft 2B. The second high-pressure bearing 20Bb is shown in Figure 1. In this embodiment, the first high-pressure bearing 20Ba is located between the rear end 7Ab of the generator shaft 7A and the connection portion between the high-pressure side compressor 4B and the high-pressure shaft 2B. The second high-pressure bearing 20Bb is located between the connection portion between the high-pressure side turbine 6B and the high-pressure shaft 2B and the rear end 2Bb of the high-pressure shaft 2B.

[0033] The generator bearing 20C includes a first generator bearing 20Ca located at the front of the generator shaft 7A and a second generator bearing 20Cb located at the rear of the generator shaft 7A. The first generator bearing 20Ca is located in front of the rotor 7B, and the second generator bearing 20Cb is located behind the rotor 7B. In this embodiment, the first generator bearing 20Ca is located between the second low-pressure bearing 20Ab and the rotor 7B, and the second generator bearing 20Cb is located between the rotor 7B and the first high-pressure bearing 20Ba. The generator bearings 20Ca and 20Cb are fixed to the inner surface of the generator housing 7D and supported by the generator housing 7D from the radially outer side.

[0034] The bearing housing 30 includes a first bearing housing 30A and a second bearing housing 30B located aft of the first bearing housing 30A in the axial direction X. The second bearing housing 30B is shown in Figure 1. The first bearing housing 30A extends in the axial direction X from the first low-pressure bearing 20Aa to the first high-pressure bearing 20Ba. The first bearing housing 30A extends in the circumferential direction and surrounds the first low-pressure bearing 20Aa, the second low-pressure bearing 20Ab, the first high-pressure bearing 20Ba and the generator 7 from the radially outer side.

[0035] The first low-pressure bearing 20Aa, the second low-pressure bearing 20Ab, and the first high-pressure bearing 20Ba are fixed to the inner surface of the first bearing housing 30A and supported by the first bearing housing 30A from the radially outer side. The generator housing 7D is fixed to the first bearing housing 30A and supported by the first bearing housing 30A in the axial X direction and the radially outer direction. The first bearing housing 30A is connected to the first cylindrical body 9 by a plurality of struts 30Aa and is supported by the first cylindrical body 9. The rear of the first bearing housing 30A is connected to the cylindrical portion 11c of the strut housing 11.

[0036] As shown in Figure 1, the second bearing housing 30B extends axially X from the second high-pressure bearing 20Bb to the third low-pressure bearing 20Ac. The second bearing housing 30B extends circumferentially and surrounds the second high-pressure bearing 20Bb and the third low-pressure bearing 20Ac from the radially outer side. The second high-pressure bearing 20Bb and the third low-pressure bearing 20Ac are fixed to the inner surface of the second bearing housing 30B and supported by the second bearing housing 30B from the radially outer side. The second bearing housing 30B is connected to the second cylindrical body 10 by a plurality of struts and is supported by the second cylindrical body 10.

[0037] The gas turbine 1 includes a lubricant supply structure 100 that supplies lubricant to a plurality of bearings 20. In this embodiment, the lubricant is a liquid, specifically a mist-like liquid. For example, the lubricant supply structure 100 is a structure that supplies oil mist to a plurality of bearings 20. The lubricant supply structure 100 described in this embodiment is a structure that supplies oil mist to bearings 20 located in front of the high-pressure side compressor 4B.

[0038] As shown in Figure 2, the lubricant supply structure 100 includes a pump 101, a first lubricant supply passage 102, and a second lubricant supply passage 103. The pump 101 is located outside the outer shell 8A, specifically on the outer shell portion 11a of the strut housing 11. The pump 101 communicates with both the lubricant supply passages 102 and 103 and pumps mist-like lubricant into the lubricant supply passages 102 and 103, respectively.

[0039] The first lubricant supply passage 102 extends through the interior of the strut housing 11 to the rear of the first bearing housing 30A. The first lubricant supply passage 102 includes a lubricant space 102a formed between the rear of the first bearing housing 30A and the cylindrical portion 11c of the strut housing 11. The first lubricant supply passage 102 extends radially through the interior of the strut 11d from the outer shell portion 11a to the cylindrical portion 11c, reaching the lubricant space 102a. The first lubricant supply passage 102 includes lubricant holes 102b and 102c. The first lubricant hole 102b extends from the lubricant space 102a and opens forward toward the first high-pressure bearing 20Ba. The second lubricant hole 102c extends from the lubricant space 102a and opens forward toward the second generator bearing 20Cb. The lubricant supplied to the first lubricant supply passage 102 by the pump 101 is temporarily stored in the lubricant space 102a before being released to the first high-pressure bearing 20Ba and the second generator bearing 20Cb through the lubricant holes 102b and 102c. Since the lubricant holes 102b and 102c open toward the front, the lubricant released from the lubricant holes 102b and 102c is prevented from flowing into the rear high-pressure side compressor 4B.

[0040] The second lubricant supply passage 103 extends to the front of the low-pressure shaft 2A, passing through the interior of the strut housing 11 and the interior of the wall of the first bearing housing 30A. The second lubricant supply passage 103 extends radially through the interior of the strut 11d from the outer shell portion 11a to the cylindrical portion 11c, then extends into the interior of the wall of the first bearing housing 30A, and extends axially X inside the wall. The second lubricant supply passage 103 includes lubricant holes 103a, 103b, and 103c. The first lubricant hole 103a branches off from the second lubricant supply passage 103 and extends rearward, opening toward the first generator bearing 20Ca. The second lubricant hole 103b branches off from the second lubricant supply passage 103 and extends rearward, opening toward the second low-pressure bearing 20Ab. The third lubricant hole 103c branches off from the second lubricant supply passage 103, extends rearward, and opens toward the first low-pressure bearing 20Aa.

[0041] The lubricant supplied to the second lubricant supply passage 103 by the pump 101 is discharged to the first generator bearing 20Ca, the second low-pressure bearing 20Ab, and the first low-pressure bearing 20Aa through the lubricant holes 103a, 103b, and 103c. Since the lubricant holes 103a, 103b, and 103c open toward the rear, the lubricant discharged from the lubricant holes 103a, 103b, and 103c flows into the rear generator housing 7D, lubricating and cooling the components of the generator 7. In addition, the lubricant discharged from the lubricant holes 103a, 103b, and 103c is prevented from flowing into the low-pressure side compressor 4A and the fan 3.

[0042] The first high-pressure bearing 20Ba and the second generator bearing 20Cb are closer to the high-pressure side compressor 4B and combustor 5, and are therefore exposed to a higher temperature environment than the first generator bearing 20Ca, the second low-pressure bearing 20Ab, and the first low-pressure bearing 20Aa. However, since the flow rate of lubricant supplied through the first lubricant supply passage 102 can be greater than the flow rate of lubricant supplied through the second lubricant supply passage 103, the first high-pressure bearing 20Ba and the second generator bearing 20Cb can be effectively lubricated and cooled by receiving a high flow rate of lubricant.

[0043] The structure of the stator 7C of the generator 7 will be described. Figure 3 is an enlarged cross-sectional view of the generator 7 of Figure 2. Figure 4 is a view of the stator 7C of Figure 3 in the axial direction X. As shown in Figures 3 and 4, the stator 7C includes a stator core 7Ca that is located around the rotor 7B and contains a magnetic material. The stator core 7Ca includes a cylindrical yoke 7Cb and a plurality of teeth 7Cc. The plurality of teeth 7Cc project inward radially from the inner circumferential surface of the yoke 7Cb in the direction of the rotational axis of the rotor 7B. The plurality of teeth 7Cc are spaced apart from each other in the circumferential direction of the rotational axis of the rotor 7B and are arranged in an annular shape in the circumferential direction. In this embodiment, the direction of the rotational axis of the rotor 7B is the axial direction X, the radial direction of the rotational axis of the rotor 7B is the axial radial direction of the axis L, and the circumferential direction of the rotational axis of the rotor 7B is the axial circumferential direction of the axis L. Each of the multiple teeth 7Cc includes two flange portions 7Cca projecting in both directions in the circumferential direction at its inner end in the radial direction.

[0044] The stator 7C includes a conductive winding 7Cd wound around a plurality of teeth 7Cc. The stator 7C includes a first projection 7Ce projecting axially X from the stator core 7Ca at a position inside the axially radial direction of the winding 7Cd. Furthermore, the stator 7C includes a second projection 7Cf projecting axially X from the stator core 7Ca at a position outside the axially radial direction of the winding 7Cd. The first projection 7Ce projects more axially X and away from the stator core 7Ca than the second projection 7Cf.

[0045] In this embodiment, the first projection 7Ce is located adjacent to the flange portion 7Cca of the tooth 7Cc in the axial direction X. The second projection 7Cf is located adjacent to the yoke 7Cb in the axial direction X. The stator 7C includes the first projection 7Ce and the second projection 7Cf at positions corresponding to each of the multiple teeth 7Cc. Furthermore, the stator 7C includes the first projection 7Ce and the second projection 7Cf at positions corresponding to both ends of each tooth 7Cc in the axial direction X. At one end 7Ccb of each tooth 7Cc in the axial direction X, the first projection 7Ce protrudes further away from the stator core 7Ca than the second projection 7Cf. At the opposite end 7Ccc of each tooth 7Cc in the axial direction X, the first projection 7Ce protrudes further away from the stator core 7Ca than the second projection 7Cf.

[0046] The stator 7C includes end members 7Cg located adjacent to the axial ends of the teeth 7Cc in the axial direction X. In this embodiment, the stator 7C includes end members 7Cg at each of the ends 7Ccc and 7Ccd of the teeth 7Cc. Furthermore, the stator 7C includes end members 7Cg at each tooth 7Cc. The multiple end members 7Cg, like the multiple teeth 7Cc, are arranged in an annular manner in the axial direction at one end of the stator core 7Ca in the axial direction X, and in an annular manner in the axial direction at the opposite end of the stator core 7Ca in the axial direction X.

[0047] The end member 7Cg contains an electrical insulating material and has electrical insulating properties. For example, the end member 7Cg contains a resin material. In this embodiment, the end member 7Cg includes protrusions 7Ce and 7Cf. The end member 7Cg is integrated with the protrusions 7Ce and 7Cf by, for example, integral molding with the protrusions 7Ce and 7Cf using resin.

[0048] The conductor constituting the winding 7Cd is wound around each tooth 7Cc from the outside in the axial direction X, around the pair of two end members 7Cg at both ends of the tooth 7Cc and the tooth 7Cc, thereby forming the winding 7Cd on the tooth 7Cc. The conductor of the winding 7Cd is wound multiple times between the first projection 7Ce and the second projection 7Cf. The winding 7Cd does not protrude beyond the second projection 7Cf in the axial direction X.

[0049] The stator 7C includes an electrical insulating sheet 7Ch interposed between the winding 7Cd and the teeth 7Cc. The stator 7C includes an electrical insulating sheet 7Ch for each of the multiple teeth 7Cc. The stator 7C includes an electrical insulating sheet 7Ch on both sides of each tooth 7Cc in the circumferential direction of the tooth 7Cc. The electrical insulating sheet 7Ch contains an electrical insulating material and has electrical insulating properties. In this embodiment, the electrical insulating sheet 7Ch is insulating paper containing a multilayer laminate material.

[0050] In one tooth 7Cc, the electrical insulating sheet 7Ch extends from the side surface 7Ccd of the tooth 7Cc to the outer circumferential surface 7Cce of the flange portion 7Cca of the tooth 7Cc and the inner circumferential surface 7Cba of the yoke 7Cb. The side surface 7Ccd of the tooth 7Cc is the side surface facing the circumferential direction, located between the flange portion 7Cca and the yoke 7Cb. Furthermore, the electrical insulating sheet 7Ch extends along the inner circumferential surface 7Cba of the yoke 7Cb, and then extends inward in the axial radial direction from the inner circumferential surface 7Cba. The electrical insulating sheet 7Ch extends in the axial radial direction between the tooth 7Cc on which the electrical insulating sheet 7Ch is placed and between the tooth 7Cc adjacent to the tooth 7Cc in the axial radial direction. The electrical insulating sheet 7Ch may also extend outward in the axial radial direction from the end of the outer circumferential surface 7Cce of the flange portion 7Cca. Furthermore, the electrical insulation sheet 7Ch extends at least across the entire tooth 7Cc in the axial direction X. The electrical insulation sheet 7Ch may also extend to the two end members 7Cg.

[0051] The conductor constituting the winding 7Cd is wound around a single tooth 7Cc from the outside of an assembly in which two end members 7Cg at both ends of the tooth 7Cc in the axial direction X, two electrical insulating sheets 7Ch on both sides of the tooth 7Cc in the circumferential direction, and the tooth 7Cc are assembled together to form the winding 7Cd. The electrical insulating sheets 7Ch electrically insulate the tooth 7Cc and yoke 7Cb from the winding 7Cd in the circumferential and radial directions. The end members 7Cg electrically insulate the tooth 7Cc and yoke 7Cb from the winding 7Cd in the axial direction X.

[0052] The winding 7Cd is supported from the inside in the radial direction by the first projection 7Ce and from the outside in the radial direction by the second projection 7Cf. This prevents the winding 7Cd from becoming disordered and the conductor from moving in the radial direction. Furthermore, because the first projection 7Ce protrudes more in the axial direction X than the second projection 7Cf, the conductor of the winding 7Cd is prevented from moving inward in the radial direction and interfering with the rotor 7B.

[0053] The winding 7Cd may be impregnated with varnish after winding onto the stator core 7Ca and solidified by the varnish. However, in the stator 7C of this embodiment, the first projection 7Ce and the second projection 7Cf maintain the winding state of the winding 7Cd, so varnish impregnation of the winding 7Cd may be omitted. In this embodiment, varnish impregnation is omitted. This prevents, for example, solidified varnish from peeling off the winding 7Cd and entering the bearings 20, such as the generator bearings 20Ca and 20Cb. It also improves the cooling capacity of the winding 7Cd. For example, lubricant supplied to the first generator bearing 20Ca can pass through the first generator bearing 20Ca and be supplied to the stator core 7Ca. The lubricant can come into direct contact with the winding 7Cd and cool it. Also, air can flow into the generator housing 7D from the front. The air flowing into the generator housing 7D can come into direct contact with the winding 7Cd, thereby cooling the winding 7Cd.

[0054] In this embodiment, the stator core 7Ca is separable. The stator core 7Ca includes a plurality of separable cores 7E arranged in an annular shape in the circumferential direction. Figure 5 is a perspective view showing an example of the configuration of the separable cores 7E in Figure 4. As shown in Figure 5, the separable cores 7E include at least one tooth 7Cc, at least two first projections 7Ce located at both ends of the at least one tooth 7Cc in the axial direction X, and at least two second projections 7Cf located on both sides of the at least one tooth 7Cc in the axial direction X.

[0055] In this embodiment, the divided core 7E is divided at the yoke 7Cb. The divided core 7E includes one divided yoke 7Ea, one tooth 7Cc, and two end members 7Cg located at both ends of the tooth 7Cc in the axial direction X. The tooth 7Cc extends from the divided yoke 7Ea. The divided core 7E further includes two electrical insulating sheets 7Ch on both sides of the tooth 7Cc in the circumferential direction.

[0056] The segmented yoke 7Ea of a segmented core 7E is connected to the segmented yoke 7Ea of an adjacent segmented core 7E in the circumferential direction. The segmented yoke 7Ea includes an engaging portion 7Eb on one side in the circumferential direction and an engaging portion 7Ec on the opposite side in the circumferential direction. The engaging portion 7Eb of the segmented yoke 7Ea engages with the engaging portion 7Ec of an adjacent segmented core 7E in the circumferential direction. The engaging portions 7Eb and 7Ec that engage between the two segmented yokes 7Ea position the two segmented yokes 7Ea relative to each other and prevent the two segmented yokes 7Ea from becoming misaligned with each other.

[0057] In this embodiment, the engaging portion 7Eb is a projection that protrudes in the circumferential direction and extends in the axial direction X, and the engaging portion 7Ec is a groove that is recessed in the circumferential direction and extends in the axial direction X. The engaging portions 7Eb and 7Ec position the two divided yokes 7Ea in directions other than the axial direction X, and prevent the two divided yokes 7Ea from shifting relative to each other in directions other than the axial direction X. The structure of the engaging portions 7Eb and 7Ec may be any structure as long as it has the function of positioning or preventing misalignment.

[0058] A divided core 7E can have a winding 7Cd wound around it with two end members 7Cg and two electrical insulating sheets 7Ch attached. The divided core 7E can be assembled as an assembly with the two end members 7Cg, two electrical insulating sheets 7Ch and winding 7Cd attached, and a stator 7C can be assembled by connecting multiple assemblies of divided cores 7E in a ring shape.

[0059] As shown in Figure 3, the wires extending from the windings 7Cd of multiple teeth 7Cc are bundled in front of the stator 7C. Specifically, wires of the same phase are connected and bundled together. In this embodiment, the generator 7 is a three-phase AC generator. Therefore, the wires corresponding to the U phase, V phase, and W phase are bundled into three wire bundles 7Cda. The three wire bundles 7Cda extend circumferentially within the generator housing 7D and then are brought out to the outside of the generator housing 7D. The three wire bundles 7Cda are covered with an electrical insulating material.

[0060] Figure 6 is a view of the stator 7C of Figure 3 from a different position in the axial direction X than in Figure 4. As shown in Figures 3 and 6, inside the generator housing 7D, the three wire bundles 7Cda are bundled together by an electrically insulating string 7F. The string 7F is wrapped around the entire three wire bundles 7Cda, and the ends of the string 7F are tied together. The string 7F is wrapped in such a way that the number of ties is small, and the number of ties is less than the number of teeth 7Cc. In this embodiment, the number of ties Fa of the string 7F is one. By reducing the number of ties Fa of the string 7F, the risk of the string 7F coming undone is reduced.

[0061] As shown in Figure 7, in this embodiment, the free ends of the two strings 7F extending from the binding point Fa of the string 7F are fixed to each other by a crimping tool 7Fb. For example, the crimping tool 7Fb may be configured to crimp the two free ends together by crimping. Figure 7 shows an example of the binding point Fa of the string 7F in Figure 6.

[0062] Furthermore, as shown in Figure 3, the generator housing 7D includes a housing projection 7Db extending rearward from the end wall 7Da of the generator housing 7D, located in front of the stator 7C. The end wall 7Da is a wall extending radially in the axial direction in front of the stator 7C. The housing projection 7Db is adjacent to a projection 7Ce or 7Cf of the stator 7C in the axial direction X and extends circumferentially. Three wire bundles 7Cda are bundled together by a string 7F on the radially outside of the housing projection 7Db. In this embodiment, the housing projection 7Db is located radially inward of the first projection 7Ce, but it may be at the same position as the first projection 7Ce in the radial direction. The housing projection 7Db prevents the wire bundles 7Cda bundled by the string 7F from moving radially inward of the housing projection 7Db. This prevents the wire bundles 7Cda from coming into contact with the rotating parts inside the generator 7.

[0063] In this embodiment, as shown in Figure 8, the generator housing 7D includes a plurality of housing protrusions 7Db. Figure 8 is a view of the generator housing 7D of Figure 3 in the axial direction X. The plurality of housing protrusions 7Db are arranged in an annular shape, spaced apart from each other in the circumferential direction of the axis. As a result, the lubricant supplied to the first generator bearing 20Ca can pass through the first generator bearing 20Ca and through the gaps between the plurality of housing protrusions 7Db to be supplied to the stator core 7Ca. Thus, the stator core 7Ca can be cooled by the lubricant.

[0064] While exemplary embodiments of the present disclosure have been described above, the disclosure is not limited to these embodiments. That is, various modifications and improvements are possible within the scope of the disclosure. For example, embodiments that have been modified in various ways, and forms constructed by combining components from different embodiments, are also included within the scope of the disclosure.

[0065] For example, in the gas turbine 1 according to this embodiment, the stator 7C of the generator 7 includes a first projection 7Ce and a second projection 7Cf on the end member 7g, but the structure of the first projection 7Ce and the second projection 7Cf is not limited thereto. For example, the first projection 7Ce and the second projection 7Cf may be integrated with the teeth 7Cc and yoke 7Cb of the stator core 7Ca. The constituent material of the first projection 7Ce and the second projection 7Cf may be the same as that of the stator core 7Ca. The stator 7C may include an electrical insulating sheet 7Ch around the first projection 7Ce and the second projection 7Cf.

[0066] In the gas turbine 1 according to this embodiment, the wires extending from the multiple teeth 7Cc of the stator 7C of the generator 7 are bundled at the front end in the axial direction X of the stator 7C, but they may also be bundled at the rear end or both ends. At the rear end as well, the wire bundle 7Cda may be bundled with a string 7F in the same manner as in the embodiment.

[0067] In the gas turbine 1 according to this embodiment, the structure of the generator 7 is a permanent magnet type structure in which permanent magnets are included in the rotor 7B, but is not limited thereto. The rotor 7B does not have to include permanent magnets. For example, the structure of the generator 7 may be a reluctance type structure in which a magnetic material is included in the rotor 7B without including permanent magnets. For example, the rotor 7B may contain ferromagnetic iron as the magnetic material, and may be, for example, an iron core.

[0068] The gas turbine 1 according to this embodiment is a twin-shaft gas turbine in which the rotating shaft 2 includes two shafts, a low-pressure shaft 2A and a high-pressure shaft 2B. However, it may also be a single-shaft gas turbine in which the rotating shaft 2 includes only one shaft. In this case, the single-shaft gas turbine may have a structure in which a part or all of the inner circumferential surface of the generator shaft 7A engages with a part of the outer circumferential surface of the rotating shaft 2, or a structure in which a part or all of the outer circumferential surface of the generator shaft 7A engages with a part of the inner circumferential surface of the rotating shaft 2. Alternatively, the generator shaft 7A and the rotating shaft 2 may be a single continuous shaft.

[0069] The structure of the gas turbine 1 according to this embodiment is such that the front end 2Ba of the high-pressure shaft 2B is inserted into the internal space of the rear end 7Ab of the generator shaft 7A, but is not limited thereto. For example, the gas turbine 1 may have a structure in which the rear end 7Ab of the generator shaft 7A is inserted into the internal space of the front end 2Ba of the high-pressure shaft 2B. For example, the high-pressure shaft 2B and the generator shaft 7A may be a single continuous shaft. The components of the generator 7 may then be assembled to this shaft.

[0070] In the gas turbine 1 according to this embodiment, lubricant is supplied to the bearing 20 via lubricant supply passages 102 and 103 that pass through the strut housing 11 at a location between the generator 7 and the high-pressure side compressor 4B. However, the location of the lubricant supply passages 102 and 103 is not limited to this. For example, the gas turbine 1 may have a strut housing between the low-pressure side compressor 4A and the generator 7 instead of or in addition to the strut housing 11, and may include lubricant supply passages 102 and 103 that pass through the strut housing.

[0071] Examples of each aspect of the technology of the present disclosure are given below. A gas turbine according to a first aspect of the present disclosure comprises a generator including a rotor, a rotating shaft connected to rotate integrally with the rotor, a rotor connected to rotate integrally with the rotating shaft, and a stator, the stator being located around the rotor and comprising a stator core made of a magnetic material, comprising a plurality of teeth projecting radially inward from the rotational axis of the rotor and spaced apart from each other in the circumferential direction of the rotational axis, conductive windings wound around the plurality of teeth, and projections projecting from the stator core in the direction of the rotational axis at positions radially inward of the windings.

[0072] According to the first embodiment, the winding wrapped around the teeth is prevented from deforming radially inward by the projection. This prevents the winding from deforming radially inward and interfering with rotating parts such as the rotor. Therefore, no additional members are required to maintain the state of the winding wrapped around the teeth. In addition, the projection can extend the creepage distance between the winding and the conductive component around it. This can prevent corona discharge from occurring between the winding and the conductive component.

[0073] A gas turbine according to a second aspect of the present disclosure, in the first aspect, may be configured such that the stator includes a first projection as a projection and a second projection that protrudes from the stator core in the direction of the rotational axis at a position on the radially outer side of the winding, wherein the first projection protrudes more in the direction of the rotational axis than the second projection.

[0074] According to the second embodiment, the winding wrapped around the teeth is prevented from deforming radially outward by the second projection. Furthermore, since the first projection protrudes more than the second projection, the winding is reliably prevented from deforming radially inward and interfering with rotating parts such as the rotor. Therefore, no additional members are required to maintain the state of the winding wrapped around the teeth.

[0075] In a third aspect of the present disclosure, the gas turbine may be configured such that the plurality of first protrusions and the plurality of second protrusions are located on each of the plurality of teeth.

[0076] According to the third embodiment, the first projection and the second projection are arranged corresponding to each tooth. This prevents deformation of the windings wrapped around each tooth.

[0077] A gas turbine according to a fourth aspect of the present disclosure may be configured such that, in any one of the first to third aspects, the stator includes an end member located adjacent to the end of the teeth in the direction of the rotational axis and having electrical insulation, the end member includes the projection, and the winding is wound around the end member and the teeth.

[0078] According to the fourth embodiment, the protrusion is included in an electrically insulating end member separate from the stator core. The end member insulates the winding from the stator core and insulates the winding radially inward. This reduces noise generated in the current flowing through the winding.

[0079] A gas turbine according to a fifth aspect of the present disclosure may be configured such that, in any one of the second to fourth aspects, the stator core includes a cylindrical yoke, the plurality of teeth project radially inward from the inner circumferential surface of the yoke, each of the plurality of teeth includes a flange projecting circumferentially at its radially inward end, the first projection is located adjacent to the yoke, and the second projection is located adjacent to the flange.

[0080] According to the fifth embodiment, interference between the first and second projections and the windings when they are wound around the teeth is reduced.

[0081] A gas turbine according to a sixth aspect of the present disclosure may be configured such that, in any one of the first to fifth aspects, the stator includes a plurality of electrically insulating sheets interposed between the plurality of teeth and the windings, the plurality of electrically insulating sheets being located on both sides of each of the plurality of teeth in the circumferential direction, the stator core includes a cylindrical yoke, the plurality of teeth protruding radially inward from the inner circumferential surface of the yoke, each of the plurality of teeth includes a flange at its radially inward end that protrudes on both sides in the circumferential direction, the electrically insulating sheets extend from the teeth to the yoke and the flange, and further extend radially from the end at the yoke or the flange between adjacent teeth in the circumferential direction.

[0082] According to the sixth embodiment, the electrical insulating sheet insulates the winding from the teeth around which the winding is wound, the flange of the teeth, and the yoke from which the teeth extend, and further insulates the winding from adjacent windings in the circumferential direction. In addition, since the electrical insulating sheet is fixed to the teeth by the winding being wound around it, the electrical insulating sheet is easy to fix.

[0083] A gas turbine according to a seventh aspect of the present disclosure, in any one of the second to sixth aspects, the stator core may include a plurality of segmented cores arranged in an annular shape in the circumferential direction, wherein each segmented core includes at least one tooth, at least two first projections located on both sides of the at least one tooth in the direction of the rotational axis, and at least two second projections located on both sides of the at least one tooth in the direction of the rotational axis.

[0084] According to the seventh embodiment, a stator is assembled by first assembling a segmented core with windings wrapped around teeth, and then arranging these segmented cores in a ring shape. This simplifies the assembly of the stator.

[0085] A gas turbine according to an eighth aspect of the present disclosure, in a seventh aspect, may be configured such that each of the plurality of segmented cores includes an end member located adjacent to both ends of the teeth in the direction of the rotational axis and having electrical insulation, the end member includes the first projection and the second projection, and in the segmented core, the winding is wound around the end member and the teeth.

[0086] According to the eighth embodiment, a stator is assembled by combining divided cores, each with windings wrapped around teeth and end members, into an assembly, and then arranging these divided cores in a ring shape. This facilitates the assembly of the stator.

[0087] A gas turbine according to a ninth aspect of the present disclosure may be configured such that, in a seventh or eighth aspect, the segmented core includes a circumferentially extending yoke, the teeth of the segmented core project radially inward from the yoke, the teeth of the segmented core include a flange projecting circumferentially at the radially inward end, the first projection of the segmented core is located adjacent to the yoke, and the second projection of the segmented core is located adjacent to the flange.

[0088] According to the ninth aspect, interference between the first and second projections and the windings when they are wound around the teeth is reduced.

[0089] A gas turbine according to a tenth aspect of the present disclosure may be configured such that, in any one of the seventh to ninth aspects, the segmented core includes a circumferentially extending yoke and electrically insulating sheets located on both sides of the teeth in the circumferential direction, the teeth of the segmented core project radially inward from the yoke, the teeth of the segmented core include flanges at the radially inward ends projecting circumferentially on both sides, and the electrically insulating sheets extend from the teeth across the yoke and the flanges, and further extend radially from the ends at the yoke or the flanges.

[0090] According to the tenth embodiment, the electrical insulating sheet insulates the winding from the teeth around which the winding is wound, the flange of the teeth, and the yoke from which the teeth extend, and further insulates the winding in the direction opposite to the teeth. The teeth, end members, and divided cores with the winding wound around the electrical insulating sheet are assembled as an assembly, and the stator is assembled by arranging these divided cores in a ring shape. Thus, the assembly of the stator is made easier.

[0091] A gas turbine according to an eleventh aspect of the present disclosure may be configured such that, in any one of the first to tenth aspects, the generator includes an electrically insulating string that bundles a plurality of wires extending from the windings of the plurality of teeth at the end of the stator core in the direction of the rotational axis, wherein the number of binding points of the string is less than the number of teeth.

[0092] According to the 11th embodiment, by installing the string material in such a way that there are fewer points of binding, the risk of the binding coming undone can be reduced.

[0093] In the twelfth aspect of the present disclosure, the gas turbine may be configured such that, in the eleventh aspect, the generator includes a crimping device at the binding point of the string material for fixing the string materials together.

[0094] According to the 12th embodiment, the risk of the binding coming undone can be reduced by securing the binding point with a crimping tool.

[0095] A gas turbine according to a thirteenth aspect of the present disclosure may be configured such that, in any one of the first to twelfth aspects, the generator includes a housing that houses the rotor and the stator, the housing includes housing projections adjacent to the projections of the stator in the rotational axis direction and extending in the circumferential direction, and the plurality of wires extending from the windings of the plurality of teeth are bundled at the ends of the stator core on the projection side of the stator in the rotational axis direction.

[0096] According to the 13th embodiment, the housing projection can prevent the bundled wires from moving radially. This prevents the wires from interfering with rotating parts such as rotors.

[0097] A gas turbine according to a 14th aspect of the present disclosure may be configured such that, in any one of the first to 13th aspects, the generator includes a generator shaft that rotates integrally with the rotor, one end of the rotating shaft being connected to the other end of the generator shaft to transmit rotational forces, and the gas turbine includes a first bearing that rotatably supports a portion of the rotating shaft located opposite to the one end of the rotating shaft with respect to the rotor, and a second bearing that rotatably supports a portion of the generator shaft located opposite to the one end of the generator shaft with respect to the rotor.

[0098] According to the 14th embodiment, the gas turbine is equipped with bearings on the generator shaft and the rotating shaft, respectively. The gas turbine does not require additional members to maintain the state of the windings wrapped around the teeth, thereby preventing additional members from falling off and interfering with the bearings.

[0099] All ordinal numbers, quantities, and other figures used herein are illustrative to illustrate the technology of this disclosure, and this disclosure is not limited to such illustrative figures. The connections between components are illustrative to illustrate the technology of this disclosure, and the connections that realize the functions of this disclosure are not limited to these.

[0100] This disclosure can be implemented in various ways without departing from the scope of its essential features, and the scope of this disclosure is defined more by the appended claims than by the description in the specification; therefore, exemplary embodiments and modifications are illustrative and not limiting. All modifications within the claims and their scope, or equivalents within the claims and their scope, are intended to be encompassed by the claims. [Explanation of Symbols]

[0101] 1 Gas turbine, 2 Rotating shaft, 7 Generator, 7A Generator shaft, 7B Rotor, 7C Stator, 7Ca Stator core, 7Cb Yoke, 7Cc Teeth, 7Cca Flange, 7Cd Winding, 7Cda Wire bundle, 7Ce First projection, 7Cf Second projection, 7Cg End member, 7Ch Electrical insulation sheet, 7D Generator housing, 7Db Housing projection, 7E Split core, 7F String material, 7Fa Crimping tool, 7g End member, 20 Bearing.

Claims

1. Rotary blades and A rotating shaft connected to the aforementioned rotor blade so as to rotate integrally with it, The generator includes a rotor connected to rotate integrally with the rotating shaft, a stator, and a housing that accommodates the rotor and the stator. The stator is, A stator core located around the rotor and containing a magnetic material, comprising a plurality of teeth that protrude radially inward from the rotational axis of the rotor and are spaced apart from each other in the circumferential direction of the rotational axis, A winding that is wrapped around the plurality of teeth and is conductive, The winding includes a stator projection that protrudes from the stator core in the direction of the rotation center axis at an inner position in the radial direction of the winding, The aforementioned housing is An end wall located in the direction of the protrusion of the stator projection and extending in the radial direction, A housing projection adjacent to the stator projection in the rotational axis direction, including a housing projection that extends from the end wall toward the stator in the rotational axis direction and extends in the circumferential direction, The multiple wires extending from the windings of the multiple teeth are bundled together at the end of the stator core on the stator projection side in the rotational axis direction, and outside the housing projection in the radial direction. The housing projection is located in the radial direction at the same position as the stator projection or inward from the stator projection. Gas turbine.

2. Rotary blades and A rotating shaft connected to the aforementioned rotor blade so as to rotate integrally with it, A generator comprising a generator shaft connected to rotate integrally with the aforementioned rotating shaft, a rotor that rotates integrally with the generator shaft, a stator, and a housing that accommodates the rotor, the stator, and the generator shaft, A bearing that rotatably supports the generator shaft, It comprises a lubricant supply hole from which lubricant is released and which opens toward the bearing, The stator is, A stator core located around the rotor and containing a magnetic material, comprising a plurality of teeth that protrude radially inward from the rotational axis of the rotor and are spaced apart from each other in the circumferential direction of the rotational axis, A winding that is wrapped around the plurality of teeth and is conductive, The winding includes a stator projection that protrudes from the stator core in the direction of the rotation center axis at an inner position in the radial direction of the winding, The housing includes a plurality of housing protrusions adjacent to the stator protrusions in the rotational axis direction and extending in the circumferential direction, The multiple wires extending from the windings of the multiple teeth are bundled together at the end of the stator core on the stator projection side in the direction of the rotational axis axis. The plurality of housing protrusions are arranged in a ring shape with spacing between them in the circumferential direction. The bearing is positioned relative to the housing projection in a first direction toward the housing projection from the stator within the axis of rotation, The lubricant supply hole is located in the first direction relative to the bearing, Gas turbine.

3. Rotary blades and A rotating shaft connected to the aforementioned rotor blade so as to rotate integrally with it, The generator includes a rotor connected to rotate integrally with the rotating shaft, a stator, and a housing that accommodates the rotor and the stator. The stator is, A stator core located around the rotor and containing a magnetic material, comprising a plurality of teeth that protrude radially inward from the rotational axis of the rotor and are spaced apart from each other in the circumferential direction of the rotational axis, A winding that is wrapped around the plurality of teeth and is conductive, The winding includes a stator projection that protrudes from the stator core in the direction of the rotation center axis at an inner position in the radial direction of the winding, Multiple wires extend from the windings of the multiple teeth at a first end, which is one of the two ends of the stator core in the direction of the rotational axis, and are led out of the housing. The generator includes an electrically insulating string material for bundling the plurality of electric wires at the first end, The number of binding points of the string material is less than the number of teeth. The density of the string material used to bundle the multiple electric wires at the aforementioned binding point, and the density of the string material used to bundle the multiple electric wires in the portion proximal to the first end, is higher than the density of the string material used to bundle the multiple electric wires in the remaining portion. The location of the binding point is such that, in the region of the string material that bundles the multiple electric wires, it is further away from the proximal end from the first end towards the distal end. Gas turbine.

4. The stator is, The first stator projection, which is the stator projection, The winding includes a second stator projection that protrudes from the stator core in the direction of the rotation center axis at a position on the radially outer side of the winding, The first stator projection protrudes more than the second stator projection in the direction of the rotation center axis. A gas turbine according to any one of claims 1 to 3.

5. The plurality of first stator protrusions and the plurality of second stator protrusions are located on each of the plurality of teeth, The gas turbine according to claim 4.

6. The stator includes an end member that is located adjacent to the end of the teeth in the direction of the rotational center axis and is electrically insulating, The end member includes the stator projection, The winding is wrapped around the end member and the teeth. A gas turbine according to any one of claims 1 to 3.

7. The stator core includes a cylindrical yoke, The plurality of teeth protrude radially inward from the inner circumferential surface of the yoke, Each of the aforementioned multiple teeth includes a flange portion projecting in the circumferential direction at its radially inner end, The second stator projection is located adjacent to the yoke, The first stator projection is located adjacent to the flange portion, The gas turbine according to claim 4.

8. The stator includes a plurality of electrical insulating sheets interposed between the plurality of teeth and the windings, The plurality of electrical insulating sheets are positioned on both sides of each of the plurality of teeth in the circumferential direction. The stator core includes a cylindrical yoke, The plurality of teeth protrude radially inward from the inner circumferential surface of the yoke, Each of the plurality of teeth includes a flange portion at its radially inner end that protrudes on both sides in the circumferential direction. The electrical insulating sheet extends from the teeth to the yoke and the flange, and further extends radially from its end in the yoke or flange between adjacent teeth in the circumferential direction. A gas turbine according to any one of claims 1 to 3.

9. The stator core includes a plurality of segmented cores arranged in a ring shape in the circumferential direction, The divided core includes at least one tooth, at least two first stator protrusions located on both sides of the at least one tooth in the rotational axis direction, and at least two second stator protrusions located on both sides of the at least one tooth in the rotational axis direction. The gas turbine according to claim 4.

10. The stator includes, in each of the plurality of segmented cores, end members that are located adjacent to both ends of the teeth in the direction of the rotational center axis and are electrically insulating, The end member includes the first stator projection and the second stator projection, In the divided core, the winding is wound around the end member and the teeth. The gas turbine according to claim 9.

11. The divided core includes a yoke extending in the circumferential direction, The teeth of the divided core protrude radially inward from the yoke, The teeth of the divided core include a flange portion projecting in the circumferential direction at the radially inner end, The second stator projection of the divided core is located adjacent to the yoke, The first stator projection of the divided core is located adjacent to the flange portion. The gas turbine according to claim 9.

12. The aforementioned divided core is The aforementioned circumferentially extending yoke, The set includes an electrical insulating sheet located on both sides of the teeth in the circumferential direction, The teeth of the divided core protrude radially inward from the yoke, The teeth of the divided core include flanges at the inner radial end that protrude on both sides in the circumferential direction. The electrical insulating sheet extends from the teeth to the yoke and the flange, and further extends radially from the end at the yoke or the flange. The gas turbine according to claim 9.

13. The generator includes an electrically insulating string material that bundles together a plurality of wires extending from the windings of the plurality of teeth at the end of the stator core in the direction of the rotational center axis, The number of binding points in the aforementioned string material is less than the number of teeth. The gas turbine according to claim 1 or 2.

14. The generator includes a crimping device for securing the strings together at the binding points of the strings. The gas turbine according to claim 13.

15. The generator includes a generator shaft that rotates integrally with the rotor, One end of the rotating shaft is connected to one end of the generator shaft to transmit rotational force, The aforementioned gas turbine A first bearing rotatably supports the portion of the rotating shaft located on the opposite side of one end of the rotating shaft, with respect to the rotor blade, Includes a second bearing that rotatably supports the portion of the generator shaft located on the opposite side of the one end of the generator shaft with respect to the rotor, A gas turbine according to any one of claims 1 to 3.

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