Bearing support structure for gas turbines

Abstract

Even if the heat generated during the operation of the gas turbine reaches the bearings supporting the rotating shaft connected to the compressor and turbine, the bearings will be able to stably support the rotating shaft. [Solution] A bearing support structure for a gas turbine comprises a rotating shaft connected to a compressor and a turbine and rotating about a predetermined axis, at least one bearing supporting the rotating shaft, and a bearing housing through which the rotating shaft is inserted and which supports the at least one bearing. The bearing housing includes a housing body and at least one fluid passage disposed in the housing body. The at least one fluid passage has an air passage that extends in the circumferential direction of the rotating shaft and circulates air supplied to the at least one bearing.

Description

Technical Field

[0001] The present disclosure relates to a bearing support structure for a gas turbine.

Background Art

[0002] Patent Document 1 discloses a structure for guiding an oil mist to a bearing of a rotating shaft in a gas turbine engine including a rotating shaft connected to a compressor and a turbine.

Prior Art Documents

Patent Documents

[0003]

Patent Document 1

Summary of the Invention

Problems to be Solved by the Invention

[0004] Even when heat generated during the operation of the gas turbine reaches the bearing of the rotating shaft, it is required to stably support the rotating shaft by the bearing.

[0005] Therefore, an object of the present disclosure is to enable the bearing to stably support the rotating shaft even when heat generated during the operation of the gas turbine reaches the bearing that supports the rotating shaft connected to the compressor and the turbine.

Means for Solving the Problems

[0006] A bearing support structure for a gas turbine according to an aspect of the present disclosure includes a rotating shaft connected to a compressor and a turbine and rotating about a predetermined axis, at least one bearing that supports the rotating shaft, and a bearing housing through which the rotating shaft is inserted and that supports the at least one bearing. The bearing housing includes a housing body and at least one fluid flow path disposed in the housing body, and the at least one fluid flow path has an air flow path that extends in the circumferential direction of the rotating shaft and allows air supplied to the at least one bearing to flow therethrough. [Effects of the Invention]

[0007] According to one aspect of this disclosure, even if the heat generated when the gas turbine is driven reaches the bearing supporting the rotating shaft connected to the compressor and the turbine, the bearing can stably support the rotating shaft. [Brief explanation of the drawing]

[0008] [Figure 1] Figure 1 is a cross-sectional view of a gas turbine according to an embodiment. [Figure 2] Figure 2 is an enlarged cross-sectional view of the bearing support structure in Figure 1. [Figure 3] Figure 3 is a partial cross-sectional view of the bearing support structure in Figure 1, viewed from the axial direction. [Figure 4] Figure 4 is a schematic diagram of the unmanned aerial vehicle equipped with the gas turbine shown in Figure 1. [Modes for carrying out the invention]

[0009] [Embodiment] Embodiments will be described below with reference to the drawings. In the following description, axial direction X0 means the direction in which the axis X of the rotating shaft 2 extends. The front side means the upstream side in the direction in which air flows in the compressor 4 and turbine 6. The rear side means the downstream side in the direction in which air flows in the compressor 4 and turbine 6. That is, the front side means the side in the axial direction X0 where the fan 3 is located. The rear side means the side in the axial direction X0 opposite to the side where the fan 3 is located. Also, the first side of the axial direction X0 of the rotating shaft 2 refers to the front side of the axial direction X0. The second side of the axial direction X0 of the rotating shaft 2 refers to the rear side of the axial direction X0. Radial direction R means the radial direction of the axis X, in other words, the direction perpendicular to the axis X. Circumferential direction C means the direction around the axis X.

[0010] Figure 1 is a cross-sectional view of a gas turbine 1 according to an embodiment. The gas turbine 1 is used, for example, as an engine for an aircraft such as an unmanned aerial vehicle, but the applications of the gas turbine 1 are not limited. As shown in Figure 1, the gas turbine 1 comprises a bearing support structure 20 with a rotating shaft 2, a fan 3, a compressor 4, a combustor 5, a turbine 6, a gas turbine casing 7, and a combustor casing 19.

[0011] As shown below, in the gas turbine 1, in the bearing support structure 20 that supports at least one bearing BR supporting the rotating shaft 2, the bearing housing 21 is configured to have an air passage 22b that extends in the circumferential direction C of the rotating shaft 2 and allows air supplied to the bearing BR to flow through it. As a result, even if the bearing BR is exposed to heat, the bearing BR can be cooled and the rotating shaft 2 can be stably supported by the bearing BR.

[0012] The rotating shaft 2 extends in the front-to-back direction of the gas turbine 1. The fan 3 is connected to the front of the rotating shaft 2 and rotates 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 gas turbine casing 7 is a cylindrical object whose axis coincides with axis X. The gas turbine casing 7 houses the rotating shaft 2, fan 3, compressor 4, combustor casing 19, and turbine 6. The combustor casing 19 is located inside the gas turbine casing 7 and houses the combustor 5.

[0013] The gas turbine 1 is, for example, a twin-shaft gas turbine. The rotating shafts 2 include a low-pressure shaft 11 and a high-pressure shaft 12 which is arranged on the same axis as the low-pressure shaft 11 and is rotatable relative to the low-pressure shaft 11. The high-pressure shaft 12 is a tubular hollow shaft. The low-pressure shaft 11 is inserted through the hollow space of the high-pressure shaft 12. The low-pressure shaft 11 is longer than the high-pressure shaft 12 in the front-rear direction. The front and rear ends of the low-pressure shaft 11 are exposed to the outside of the high-pressure shaft 12. The low-pressure shaft 11 is connected to a fan 3.

[0014] The compressor 4 includes a low-pressure compressor 13 and a high-pressure compressor 14. The low-pressure compressor 13 is located on the first side of the axial direction X0 relative to the high-pressure compressor 14. For example, the low-pressure compressor 13 is an axial-flow compressor, and the high-pressure compressor 14 is a centrifugal compressor. A diffuser 8 is located on the outer circumference of the high-pressure compressor 14 to send the air flowing out of the high-pressure compressor 14 to the rear. A combustor 5 is located behind the diffuser 8.

[0015] The turbine 6 includes a high-pressure turbine 15 and a low-pressure turbine 16 located behind the high-pressure turbine 15. The low-pressure shaft 11 mechanically connects the low-pressure compressor 13 to the low-pressure turbine 16. The high-pressure shaft 12 mechanically connects the high-pressure compressor 14 to the high-pressure turbine 15.

[0016] The gas turbine casing 7 includes an inner shell 17 and an outer shell 18. The inner shell 17 and outer shell 18 are cylindrical in shape and are arranged concentrically with respect to each other. The inner shell 17 houses the compressor 4, the combustor 5, and the turbine 6. A cylindrical bypass passage B is located between the inner shell 17 and the outer shell 18. A portion of the air drawn in by the fan 3 flows through the bypass passage B and is discharged to the rear. The remaining air drawn in by the fan 3 flows into the low-pressure compressor 13. The air that has passed through the low-pressure compressor 13 and the high-pressure compressor 14 enters the combustor casing 19 via the diffuser 8 and is introduced into the combustor 5. The combustion gas discharged from the combustor 5 passes through the turbine nozzle 9 and is introduced into the high-pressure turbine 15.

[0017] The outer shell 18 is fitted with a lubricant pump LP and an air pump AP. A first pipe 30 extending in the axial direction X0 is connected to the lubricant pump LP. A second pipe 31 extending in the axial direction X0 is connected to the air pump AP. The first pipe 30 is connected to the bearing support structure 20 via a lubricant pipe LT. The second pipe 31 is connected to the bearing support structure 20 via an air pipe AT. The lubricant pipe LT and the air pipe AT extend in the radial direction R at a position that overlaps with the bearing support structure 20 in the radial direction R.

[0018] The combustor 5 of this embodiment is, as an example, a reverse flow type. Further, the combustor 5 is, for example, an annular type having an annular shape extending in the circumferential direction C. The combustor 5 includes an inner liner 5a, an outer liner 5b, an end liner 5c, a first turn guide 5d, and a second turn guide 5e. The liners 5a to 5c define a combustion chamber S in the combustor 5. The axial direction of the combustor 5 coincides with the axial direction X0 of the rotating shaft 2.

[0019] The inner liner 5a and the outer liner 5b have a cylindrical shape extending in the axial direction X0. The outer liner 5b is disposed outside the inner liner 5a in the radial direction R. The end liner 5c connects one end portion in the axial direction X0 of the inner liner 5a and the outer liner 5b. The end liner 5c has an annular shape extending in the radial direction R. A fuel nozzle N of the combustor 5 is attached to the end liner 5c.

[0020] The first turn guide 5d is curved so as to change the direction by 180° from the tip of the outer liner 5b on the front side in the axial direction X0 and extends to the rear side in the axial direction X0. The second turn guide 5e is curved so as to change the direction by 180° from the tip of the inner liner 5a on the front side in the axial direction X0 and extends to the rear side in the axial direction X0. The turn guides 5d and 5e define an exhaust passage T continuous with the combustion chamber S. The exhaust port of the exhaust passage T is directed toward a turbine nozzle 9 including a plurality of nozzle guide vanes 9a.

[0021] [[ID=??]]The bearing support structure 20 includes, in addition to the rotating shaft 2 described above, at least one bearing BR and a bearing housing 21. The bearing housing 21 has the rotating shaft 2 inserted therethrough and supports the at least one bearing BR. The bearing support structure 20 may be disposed behind the exhaust port of the exhaust passage T. When viewed from the axial direction X0, all or a part of the bearing support structure 20 may be disposed at a position overlapping the combustor 5.

[0022] It seems there is a typo in your original text where "[[ID=??]]" should be something else. I've translated it as best as possible with the given content.Figure 2 is an enlarged cross-sectional view of the bearing support structure 20 of FIG. 1. In FIG. 2, a cross-section of the bearing support structure 20 along the axial direction X0 is shown. As shown in FIG. 2, the rotating shaft 2 is supported by a plurality of bearings. The at least one bearing BR includes, among the plurality of bearings, a first bearing BR1 that supports the high-pressure shaft 12 and is disposed on the most second side with respect to the high-pressure shaft 12, and a second bearing BR2 that supports the low-pressure shaft 11 and is disposed on the most second side with respect to the low-pressure shaft 11.

[0023] The bearing housing 21 includes a housing body 22 and at least one fluid flow path 22a disposed in the housing body 22. The fluid flow path 22a has an air flow path 22b that extends in the circumferential direction C and allows air supplied to the at least one bearing BR to flow therethrough. The circumferential length of the air flow path 22b in the circumferential direction C can be set as appropriate. For example, the circumferential length of the air flow path 22b may be any value of 1 / 4 or more, 1 / 2 or more, 3 / 4 or more of the circumferential length of the rotating shaft 2 in the circumferential direction C, or may be the same value as the circumferential length of the rotating shaft 2.

[0024] The fluid flow path 22a further has a lubricant flow path 22c that allows lubricant supplied to the at least one bearing BR to flow therethrough. The lubricant flow path 22c is connected to a lubricant pipe LT. The air flow path 22b is connected to an air pipe AT. The air flow path 22b has an introduction path 22f into which air is introduced and a buffer flow path 22g that is connected to the introduction path 22f and extends in the circumferential direction C. The buffer flow path 22g suppresses pressure fluctuations of the air flowing through the air flow path 22b.

[0025] The bearing housing 21 may include a first block 23 and a second block 24 arranged side by side in the axial direction X0. In this case, a specific flow path that is at least one of the air flow path 22b and the lubricant flow path 22c may be defined by the first block 23 and the second block 24. The specific flow path in the present embodiment is, as an example, both the air flow path 22b and the lubricant flow path 22c. The configuration of the specific flow path is not limited thereto.

[0026] The first block 23 may be located in front of the second block 24. The lubricant passage 22c may have a first lubricant passage 22d and a second lubricant passage 22e. The first lubricant passage 22d supplies lubricant to a specific bearing among the at least one bearing BR from one side in the axial direction X0 of the rotating shaft 2. The second lubricant passage 22e supplies lubricant to the specific bearing from the other side in the axial direction X0. For example, one side here refers to the front side, and the other side refers to the rear side. The specific bearing is, for example, the first bearing BR1. As an example, the first lubricant passage 22d may be located in the first block 23. The second lubricant passage 22e may be located in the second block 24.

[0027] Thus, in the bearing housing 21, multiple lubricant passages 22d and 22e may be arranged to spray lubricant onto a specific bearing. In this case, the bearing housing 21 may include a front outlet 22m located in front of the specific bearing and communicating with the first lubricant passage 22d, which sprays lubricant backward toward the specific bearing, and a rear outlet 22n located behind the specific bearing and communicating with the second lubricant passage 22e, which sprays lubricant forward toward the specific bearing.

[0028] As another example, the lubricant passage 22c may have at least one third lubricant passage 22h that supplies lubricant to the remaining bearings of the at least one bearing BR excluding a specific bearing. In this embodiment, the third lubricant passage 22h supplies lubricant to, for example, the second bearing BR2. In this case, the third lubricant passage 22h may branch off from a portion of the second lubricant passage 22e. Figure 2 shows, as an example, a configuration in which the bearing housing 21 is positioned in front of the second bearing BR2, communicates with the third lubricant passage 22h, and includes a front outlet 22o that sprays lubricant backward toward the second bearing BR2. In this case, the bearing housing 21 may further include a rear outlet that is positioned behind the second bearing BR2, communicates with the third lubricant passage 22h, and sprays lubricant forward toward the second bearing BR2.

[0029] The bearing housing 21 may include a bearing support block 25 in which a first bearing BR1 and a second bearing BR2 are integrally and continuously arranged inside. This bearing support block 25 is, for example, a second block 24. The configuration of the bearing support block 25 is not limited thereto. The first bearing BR1 may be supported by the bearing support block 25 via a first spacer 35 having an annular shape extending in the circumferential direction C. The second bearing BR2 may be supported by the bearing support block 25 via a second spacer 36 having an annular shape extending in the circumferential direction C.

[0030] The bearing housing 21 may include a through hole 21a through which a rotating shaft 2 and at least one bearing BR are inserted. The air passage 22b may further have at least one connecting passage 22i and at least one air nozzle 22j. If the air passage 22b has multiple connecting passages 22i and multiple air nozzles 22j, the multiple connecting passages 22i may extend from the buffer passage 22g and be spaced apart in the circumferential direction C. Alternatively, as an example, the multiple connecting passages 22i may extend in the axial direction X0. In this case, both the multiple connecting passages 22i and the buffer passage 22g may extend continuously in the axial direction X0.

[0031] Multiple air nozzles 22j communicate with the communication passage 22i and inject air into the insertion hole 21a. The multiple air nozzles 22j may be spaced apart in the circumferential direction C. The air nozzles 22j may be inclined from front to rear in a direction approaching the axis X. Air from the air nozzles 22j is supplied to a seal air supply space 27 located between the outer circumferential surface of a rotating shaft 2, such as a high-pressure shaft 12, and the inner circumferential surface of the bearing housing 21. This prevents high-temperature gases such as combustion gases from entering the seal air supply space 27.

[0032] Figure 3 is a partial cross-sectional view of the bearing support structure 20 of Figure 1, viewed from the axial direction X0. Figure 3 shows a part of the radial R cross-section of the buffer channel 22g of Figure 2. The buffer channel 22g has a plurality of first buffer channels 22k and a second buffer channel 22l. The plurality of first buffer channels 22k are spaced apart in the circumferential direction C. The second buffer channel 22l may connect any two of the plurality of first buffer channels 22k. As an example, the second buffer channel 22l may connect adjacent first buffer channels 22k.

[0033] Here, the housing body 22 has a hollow structure 26 extending in the axial direction X0. The hollow structure 26 is, for example, a structure that defines a part of the lubricant flow path 22c. The configuration of the hollow structure 26 is not limited to this. The second buffer flow path 22l may bypass the hollow structure 26 and connect adjacent first buffer flow paths 22k among a plurality of first buffer flow paths 22k.

[0034] Figure 4 is a schematic diagram of an unmanned aerial vehicle 40 equipped with the gas turbine 1 shown in Figure 1. As shown in Figure 4, the gas turbine 1 is located, for example, inside a through-hole 41a that extends in the longitudinal direction and is positioned in the fuselage 41 of the unmanned aerial vehicle 40. The configuration of the unmanned aerial vehicle 40 and the arrangement of the gas turbine 1 in the unmanned aerial vehicle 40 are not limited to this.

[0035] When the gas turbine 1 is running, air supplied from the high-pressure compressor 14 via the diffuser 8 is introduced into the combustion chamber S of the combustor 5. The fuel nozzle N also injects liquid fuel into the combustion chamber S. In the combustion chamber S, the fuel mixed with air is burned to produce combustion gas. After being discharged from the combustor 5, the combustion gas is guided by the nozzle guide vane 9a of the turbine nozzle 9 and flows into the high-pressure turbine 15.

[0036] The combustion gas that has passed through the high-pressure turbine 15 then flows to the low-pressure turbine 16. When the rotational driving force of the turbine 6 is transmitted to the rotating shaft 2, the rotating shaft 2 is rotated in the circumferential direction C while being supported by the plurality of bearings, including the first bearing BR1 and the second bearing BR2.

[0037] As described above, the bearing housing 21 of the bearing support structure 20 of this embodiment comprises a rotating shaft 2, at least one bearing BR supporting the rotating shaft 2, and the bearing housing 21. The bearing housing 21 includes a housing body 22 and at least one fluid passage 22a disposed in the housing body 22. The at least one fluid passage 22a has an air passage 22b.

[0038] With this configuration, air is circulated through the air passage 22b of the fluid passage 22a, allowing at least one bearing BR to be cooled over a wide area in the circumferential direction C. As a result, even if the heat generated when the gas turbine 1 is driven reaches the bearing BR that supports the rotating shaft 2 connected to the compressor 4 and the turbine 6, the bearing BR can stably support the rotating shaft 2. In addition, by cooling the bearing housing 21 with the air circulating in the air passage 22b, thermal expansion of the bearing housing 21 can be suppressed.

[0039] As another example, the air passage 22b in this embodiment has an introduction passage 22f into which air is introduced, and a buffer passage 22g connected to the introduction passage 22f and extending in the circumferential direction C. With this configuration, the buffer passage 22g connected to the introduction passage 22f can stabilize the injection pressure when air is injected from the air passage 22b to at least one bearing BR. In addition, the abundant air flowing through the buffer passage 22g can adequately cool the bearing housing 21.

[0040] As another example, the housing body 22 has a hollow structure 26 extending in the axial direction of the rotation axis, and the buffer flow path 22g has a plurality of first buffer flow paths 22k arranged spaced apart in the circumferential direction C, and a second buffer flow path 22l that bypasses the hollow structure 26 and connects adjacent first buffer flow paths 22k. With this configuration, interference between the hollow structure 26 of the housing body 22 and the buffer flow path 22g can be suppressed by the second buffer flow path 22l, while the buffer flow path 22g can be arranged in the housing body 22. Thus, the design freedom of the bearing support structure 20 can be improved.

[0041] Furthermore, the bearing housing 21 includes a through hole 21a through which the rotating shaft 2 and at least one bearing BR are inserted, and the air passage 22b has a plurality of connecting passages 22i extending from the buffer passage 22g and arranged spaced apart in the circumferential direction C, and a plurality of air nozzles 22j communicating with the connecting passages 22i and injecting air into the through hole 21a. With this configuration, air can be injected into the through hole 21a through the plurality of connecting passages 22i and the plurality of air nozzles 22j, which are spaced apart in the circumferential direction C, so that at least one bearing BR and the bearing housing 21 can be efficiently cooled. In addition, the cross-sectional area of ​​each connecting passage 22i can be reduced, making the bearing housing 21 smaller.

[0042] Furthermore, multiple connecting passages 22i extend in the axial direction X0. With this configuration, air that has flowed through the connecting passages 22i of the air passage 22b can be injected from the air nozzle 22j to a predetermined position in the axial direction X0 of the bearing housing 21, making it easier to cool the bearing housing 21.

[0043] As another example, at least one fluid passage 22a further includes a lubricant passage 22c through which lubricant supplied to at least one bearing BR flows. With this configuration, at least one bearing BR can be cooled by the air flowing through the air passage 22b while being lubricated by the lubricant. Therefore, the rotating shaft 2 can be supported more stably by the bearing BR.

[0044] As another example, the bearing housing 21 includes a first block 23 and a second block 24 arranged side by side in the axial direction X0, and a specific passage, which is at least one of an air passage 22b and a lubricant passage 22c, is defined by the first block 23 and the second block 24.

[0045] With this configuration, a specific flow path can be defined by the first block 23 and the second block 24, making it easier to form the specific flow path by combining each block 23 and 24. Therefore, the workload for manufacturing the bearing housing 21 can be reduced. In addition, the design freedom of the bearing support structure 20 can be improved.

[0046] As another example, the lubricant passage 22c of this embodiment has a first lubricant passage 22d that supplies lubricant to a specific bearing among at least one bearing BR from one side in the axial direction X0, and a second lubricant passage 22e that supplies lubricant to the specific bearing from the other side in the axial direction X0. As a result, the first lubricant passage 22d and the second lubricant passage 22e can supply lubricant to the specific bearing from both one side and the other side in the axial direction X0. Therefore, the lubrication effect of the specific bearing can be further improved.

[0047] As another example, in this embodiment, the first lubricant passage 22d is located in the first block 23, and the second lubricant passage 22e is located in the second block 24. This allows the first lubricant passage 22d and the second lubricant passage 22e to be formed separately in the first block 23 and the second block 24, respectively. Thus, the workload for manufacturing the bearing housing 21 can be reduced. Furthermore, the design flexibility of the bearing support structure 20 can be improved.

[0048] As another example, the rotating shaft 2 in this embodiment is supported by the plurality of bearings. At least one bearing BR includes, among the plurality of bearings, a first bearing BR1 that supports the high-pressure shaft 12 and is positioned furthest to the second side relative to the high-pressure shaft 12, and a second bearing BR2 that supports the low-pressure shaft 11 and is positioned furthest to the second side relative to the low-pressure shaft 11.

[0049] With the above configuration, even when the first bearing BR1 and the second bearing BR2 are placed in an environment that becomes relatively hot when the gas turbine 1 is in operation, air can be circulated through the air passage 22b to cool both the first bearing BR1 and the second bearing BR2. Therefore, the first bearing BR1 and the second bearing BR2 can stably support the rotating shaft 2.

[0050] As another example, the bearing housing 21 of this embodiment includes a bearing support block 25 in which a first bearing BR1 and a second bearing BR2 are integrally and continuously arranged inside. By arranging the first bearing BR1 and the second bearing BR2 inside the integrally and continuously arranged bearing support block 25, the first bearing BR1 and the second bearing BR2 can be stably supported by the high rigidity of the bearing support block 25.

[0051] As described above, the embodiments have been explained as examples of the technology disclosed in this application. However, the technology in this disclosure is not limited to these embodiments and can be applied to embodiments that have been modified, replaced, added, or omitted as appropriate. It is also possible to combine the components described in the embodiments to create new embodiments. For example, some components or methods in one embodiment may be applied to other embodiments, and some components in an embodiment can be separated from other components in that embodiment and extracted as appropriate. Furthermore, the components described in the attached drawings and detailed description include not only components essential for solving the problem, but also components that are not essential for solving the problem, in order to illustrate the technology.

[0052] [Aspect] The embodiments described above are specific examples of the following embodiments. [Aspect 1] A rotating shaft connected to the compressor and turbine, which rotates around a predetermined axis, At least one bearing supporting the aforementioned rotating shaft, The rotating shaft is inserted through a bearing housing that supports at least one bearing, The bearing housing is The housing body and The housing body includes at least one fluid passage, A bearing support structure for a gas turbine, wherein the at least one fluid passage has an air passage that extends in the circumferential direction of the rotating shaft and circulates air supplied to the at least one bearing.

[0053] According to the above configuration, air can be circulated through the air passage of the fluid passage to cool at least one bearing over a wide area in the circumferential direction. As a result, even if the heat generated when the gas turbine is driven reaches the bearing supporting the rotating shaft connected to the compressor and the turbine, the bearing can stably support the rotating shaft. In addition, by cooling the bearing housing with air circulating through the air passage, thermal expansion of the bearing housing can be suppressed.

[0054] [Aspect 2] The aforementioned air passage is An intake passage through which air is introduced, A bearing support structure for a gas turbine according to embodiment 1, comprising a buffer channel connected to the introduction channel and extending in the circumferential direction.

[0055] According to the above configuration, the buffer channel connected to the introduction path stabilizes the injection pressure when air is injected from the air channel to at least one bearing. In addition, the abundant air flowing through the buffer channel allows for proper cooling of the bearing housing.

[0056] [Aspect 3] The housing body has a hollow structure that extends in the axial direction of the rotation shaft, The buffer channel is The plurality of first buffer channels arranged spaced apart in the circumferential direction, A bearing support structure for a gas turbine according to embodiment 2, comprising a second buffer channel that bypasses the hollow structure and connects adjacent first buffer channels among the plurality of first buffer channels.

[0057] With the above configuration, interference between the hollow structure of the housing body and the buffer flow path can be suppressed by the second buffer flow path, while the buffer flow path can be positioned within the housing body. Therefore, the design flexibility of the bearing support structure can be improved.

[0058] [Aspect 4] The bearing housing includes an insertion hole through which the rotating shaft and the at least one bearing are inserted. The aforementioned air passage is A plurality of connecting passages extending from the buffer flow path and arranged spaced apart in the circumferential direction, A bearing support structure for a gas turbine according to embodiment 2 or 3, comprising a plurality of air nozzles that communicate with the communication passage and inject air into the insertion hole.

[0059] According to the above configuration, air can be injected into the insertion hole through the multiple connecting passages and multiple air nozzles that are spaced apart in the circumferential direction, thereby efficiently cooling the at least one bearing and the bearing housing. Furthermore, the cross-sectional area of ​​the flow path of each connecting passage can be reduced, allowing for a smaller bearing housing.

[0060] [Aspect 5] The bearing support structure for a gas turbine according to embodiment 4, wherein the plurality of connecting passages extend in the axial direction of the rotating shaft.

[0061] According to the above configuration, air flowing through the air passage can be injected from the air nozzle to a predetermined axial position of the bearing housing, making it easier to cool the bearing housing.

[0062] [Aspect 6] The bearing support structure for a gas turbine according to any one of embodiments 1 to 5, wherein the at least one fluid passage further comprises a lubricant passage for circulating a lubricant to be supplied to the at least one bearing.

[0063] According to the above configuration, at least one bearing can be cooled by the air flowing through the air passage while the bearing is lubricated by a lubricant. Therefore, the rotating shaft can be supported more stably by the bearing.

[0064] [Aspect 7] The bearing housing includes a first block and a second block arranged side by side in the axial direction of the rotating shaft, The bearing support structure for a gas turbine according to embodiment 6, wherein a specific flow path, which is at least one of the air flow path and the lubricant flow path, is defined by the first block and the second block.

[0065] With the above configuration, a specific flow path can be defined by the first and second blocks, making it easier to form the specific flow path by combining the blocks. Therefore, the workload for manufacturing the bearing housing can be reduced. In addition, the design flexibility of the bearing support structure can be improved.

[0066] [Aspect 8] The aforementioned lubricant flow path is A first lubricant channel is provided for supplying the lubricant to a specific bearing among the at least one bearings from one side in the axial direction of the rotating shaft, A bearing support structure for a gas turbine according to embodiment 6 or 7, comprising a second lubricant channel for supplying the lubricant to the specified bearing from the other side in the axial direction.

[0067] According to the above configuration, the first and second lubricant passages allow lubricant to be supplied to the specific bearing from both one and the other side in the axial direction. Therefore, the lubrication effect of the specific bearing can be further improved.

[0068] [Aspect 9] The bearing housing includes a first block and a second block arranged side by side in the axial direction, The bearing support structure for a gas turbine according to embodiment 8, wherein the first lubricant passage is located in the first block and the second lubricant passage is located in the second block.

[0069] According to the above configuration, the first and second lubricant passages can be formed separately in the first and second blocks, respectively. Therefore, the workload for manufacturing the bearing housing can be reduced. In addition, the design flexibility of the bearing support structure can be improved.

[0070] [Aspect 10] The compressor includes a high-pressure compressor and a low-pressure compressor positioned on the first axial side of the rotating shaft relative to the high-pressure compressor. The turbine includes a high-pressure turbine and a low-pressure turbine positioned on the second side in the axial direction relative to the high-pressure turbine. The rotating shaft includes a hollow high-pressure shaft connecting the high-pressure compressor and the high-pressure turbine, and a low-pressure shaft inserted through the high-pressure shaft and connecting the low-pressure compressor and the low-pressure turbine. The aforementioned rotating shaft is supported by multiple bearings, The bearing support structure for a gas turbine according to any one of embodiments 1 to 9, wherein the at least one bearing includes, among the plurality of bearings, a first bearing that supports the high-pressure shaft and is positioned furthest to the second side with respect to the high-pressure shaft, and a second bearing that supports the low-pressure shaft and is positioned furthest to the second side with respect to the low-pressure shaft.

[0071] With the above configuration, even when the first and second bearings are located in an environment that becomes relatively hot when the gas turbine is in operation, air can be circulated through the air passage to cool both the first and second bearings. Therefore, the rotating shaft can be stably supported by the first and second bearings.

[0072] [Aspect 11] The bearing support structure for a gas turbine according to embodiment 10, wherein the bearing housing includes a bearing support block in which the first bearing and the second bearing are integrally and continuously disposed inside.

[0073] According to the above configuration, by arranging the first and second bearings inside a continuous, integral bearing support block, the first and second bearings can be stably supported due to the high rigidity of the bearing support block.

[0074] [Aspect 12] A gas turbine comprising one of the bearing support structures described in embodiments 1 to 11.

[0075] According to the above configuration, even if the heat generated during the operation of the gas turbine reaches the bearing supporting the rotating shaft connected to the compressor and the turbine, a gas turbine can be obtained in which the rotating shaft can be stably supported by the bearing.

[0076] [Aspect 13] An unmanned aerial vehicle equipped with a gas turbine according to embodiment 12.

[0077] According to the above configuration, even if the heat generated when the gas turbine is driven reaches the bearing supporting the rotating shaft connected to the compressor and the turbine, an unmanned aerial vehicle can be obtained in which the rotating shaft can be stably supported by the bearing. [Explanation of Symbols]

[0078] BR bearing BR1 First bearing BR2 Second bearing C Circumferential direction of the axis of rotation S Combustion chamber X axis X0 Axial direction 1 Gas Turbine 2 rotation axes 4. Compressor 5 Combustor 6 Turbines 11 Low-voltage shaft 12 High-voltage shaft 13 Low-pressure compressor 14. High-pressure compressor 15 High-pressure turbine 16 Low-pressure turbine 20 Bearing support structure 21 Bearing housing 21a Through hole 22 Housing body 22a Fluid flow path 22b Airflow channel 22c Lubricant flow path 22d First lubricant flow path 22e Second lubricant flow path 22f introduction road 22g buffer channel 22i communication path 22j air nozzle 22k First Buffer Channel 22l Second buffer channel 23 Block 1 24 Block 2 25 Bearing support block 26 Hollow structure

Claims

1. A rotating shaft connected to the compressor and turbine, which rotates around a predetermined axis, At least one bearing supporting the aforementioned rotating shaft, A bearing housing through which the rotating shaft is inserted and which supports the at least one bearing, The bearing housing is provided with an air pipe for introducing air from the outside, The bearing housing is The housing body and The housing body includes at least one fluid passage, The at least one fluid passage extends in the circumferential direction of the rotating shaft at a position separated from the rotating shaft and has an air passage for introducing and circulating air supplied to the at least one bearing from the air piping. A bearing support structure for a gas turbine, wherein contact of the rotating shaft with the air introduced from the air piping before it flows through the air passage is avoided.

2. The aforementioned air passage is An intake passage through which air is introduced, The bearing support structure for a gas turbine according to claim 1, comprising a buffer channel connected to the introduction channel and extending in the circumferential direction.

3. A rotating shaft connected to a compressor and a turbine and rotating around a predetermined axis, At least one bearing supporting the aforementioned rotating shaft, The rotating shaft is inserted through a bearing housing that supports at least one bearing, The bearing housing is The housing body and The housing body includes at least one fluid passage, The at least one fluid passage has an air passage that extends in the circumferential direction of the rotating shaft and circulates air supplied to the at least one bearing, The aforementioned air passage is An intake passage through which air is introduced, It has a buffer channel connected to the introduction path and extending in the circumferential direction, The housing body has a hollow structure that extends in the axial direction of the rotation shaft, The buffer channel is The plurality of first buffer channels arranged spaced apart in the circumferential direction, A bearing support structure for a gas turbine, comprising: a second buffer channel that bypasses the aforementioned hollow structure and connects adjacent first buffer channels among the plurality of first buffer channels.

4. The bearing housing includes an insertion hole through which the rotating shaft and the at least one bearing are inserted. The aforementioned air passage is A plurality of connecting passages extending from the buffer flow path and arranged spaced apart in the circumferential direction, The bearing support structure for a gas turbine according to claim 2, further comprising a plurality of air nozzles that communicate with the aforementioned communication passage and inject air into the insertion hole.

5. The bearing support structure for a gas turbine according to claim 4, wherein the plurality of connecting passages extend in the axial direction of the rotating shaft.

6. The bearing support structure for a gas turbine according to claim 1, wherein the at least one fluid passage further comprises a lubricant passage for circulating a lubricant to be supplied to the at least one bearing.

7. The bearing housing includes a first block and a second block arranged side by side in the axial direction of the rotating shaft, The bearing support structure for a gas turbine according to claim 6, wherein a specific passage, which is at least one of the air passage and the lubricant passage, is defined by the first block and the second block.

8. The aforementioned lubricant flow path is A first lubricant channel is provided for supplying the lubricant to a specific bearing among the at least one bearings from one side in the axial direction of the rotating shaft, The bearing support structure for a gas turbine according to claim 6, further comprising a second lubricant channel for supplying the lubricant to the specified bearing from the other side in the axial direction.

9. A rotating shaft connected to a compressor and a turbine and rotating around a predetermined axis, At least one bearing supporting the aforementioned rotating shaft, The rotating shaft is inserted through a bearing housing that supports at least one bearing, The bearing housing is The housing body and The housing body comprises at least one fluid channel, It includes a first block and a second block arranged side by side in the axial direction of the rotation axis, The at least one fluid channel is, An air passage extending in the circumferential direction of the rotating shaft and for circulating air supplied to the at least one bearing, It has a lubricant passage through which a lubricant supplied to at least one bearing flows, The aforementioned lubricant flow path is A first lubricant channel that supplies the lubricant to a specific bearing among the at least one bearing from one side in the axial direction, The bearing has a second lubricant channel that supplies the lubricant from the other side in the axial direction to the specified bearing, A bearing support structure for a gas turbine, wherein the first lubricant passage is located in the first block, and the second lubricant passage is located in the second block.

10. The compressor includes a high-pressure compressor and a low-pressure compressor positioned on the first axial side of the rotation shaft relative to the high-pressure compressor. The turbine includes a high-pressure turbine and a low-pressure turbine positioned on the second side in the axial direction relative to the high-pressure turbine. The rotating shaft includes a hollow high-pressure shaft connecting the high-pressure compressor and the high-pressure turbine, and a low-pressure shaft inserted through the high-pressure shaft and connecting the low-pressure compressor and the low-pressure turbine. The aforementioned rotating shaft is supported by multiple bearings, The bearing support structure for a gas turbine according to any one of claims 1 to 9, wherein the at least one bearing includes, among the plurality of bearings, a first bearing that supports the high-pressure shaft and is positioned furthest to the second side with respect to the high-pressure shaft, and a second bearing that supports the low-pressure shaft and is positioned furthest to the second side with respect to the low-pressure shaft.

11. The bearing housing includes a bearing support block in which the first bearing and the second bearing are integrally and continuously arranged inside, the bearing support structure for a gas turbine according to claim 10.

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