Fuel supply structure for gas turbine combustors

Abstract

In a gas turbine, this design prevents fuel leakage between the combustor and the fuel supply pipe while allowing for a compact fuel supply structure. [Solution] A fuel supply structure for supplying fuel to a gas turbine combustor comprises a fuel supply pipe, a fuel nozzle including an inlet from which fuel is supplied from the fuel supply pipe, and an injection port for injecting fuel into the combustion chamber of the combustor, and a bolt for fastening the fuel supply pipe to the fuel nozzle. The bolt includes a fuel passage disposed inside the bolt that fluidly connects the fuel supply pipe to the fuel nozzle through the inlet.

Description

Technical Field

[0001] The present disclosure relates to a fuel supply structure for supplying fuel to a combustor for a gas turbine.

Background Art

[0002] Patent Document 1 discloses a structure in which fuel is injected into a combustion chamber of a combustor by a fuel injector in a gas turbine engine.

Prior Art Documents

Patent Documents

[0003]

Patent Document 1

Summary of the Invention

Problems to be Solved by the Invention

[0004] When arranging a fuel supply structure for supplying fuel to a combustor in a gas turbine, from the viewpoint of driving the combustor stably, it is required to prevent fuel leakage between the combustor and a fuel supply pipe for supplying fuel to the combustor. Further, even when the space in the gas turbine is restricted, it is required to arrange the fuel supply structure compactly.

[0005] Therefore, an object of the present disclosure is to enable the fuel supply structure to be arranged compactly while preventing fuel leakage between the combustor and the fuel supply pipe in a gas turbine.

Means for Solving the Problems

[0006] One aspect of the present disclosure is a fuel supply structure for supplying fuel to a combustor of a gas turbine, comprising: a fuel supply pipe; a fuel nozzle including an inlet from which fuel is supplied from the fuel supply pipe and an injection port for injecting fuel into the combustion chamber of the combustor; and a bolt for fastening the fuel supply pipe to the fuel nozzle, wherein the bolt includes a fuel passage disposed inside the bolt and fluidly connecting the fuel supply pipe to the fuel nozzle through the inlet. [Effects of the Invention]

[0007] According to one aspect of this disclosure, in a gas turbine, the fuel supply structure can be compactly arranged while preventing fuel leakage between the combustor and the fuel supply pipe. [Brief explanation of the drawing]

[0008] [Figure 1] Figure 1 is a partial cross-sectional view of a gas turbine according to an embodiment. [Figure 2] Figure 2 is a partial perspective view of the fuel supply structure shown in Figure 1. [Figure 3] Figure 3 is a partial cross-sectional view of the fuel supply structure shown in Figure 2. [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 axial direction X0 where the fan 3 is located. The rear side means the side in axial direction X0 opposite to the side where the fan 3 is located. Radial direction R means the radial direction of axis X, in other words, the direction perpendicular to axis X. Circumferential direction C means the direction around 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 rotating shaft 2, a fan 3, a compressor 4, a combustor 5, a turbine 6, a gas turbine casing 7, a combustor casing 19, and a fuel supply structure 20. As described below, the fuel supply structure 20 is configured to be compactly arranged while preventing fuel leakage between the combustor 5 and the fuel supply pipe 21, by including a fuel passage 23a in the bolts 23 that fasten the fuel supply pipe 21 to the fuel nozzle 22.

[0011] 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.

[0012] The gas turbine 1 is, for example, a twin-shaft gas turbine. The rotating shaft 2 includes 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.

[0013] The compressor 4 includes a low-pressure compressor 13 and a high-pressure compressor 14 positioned behind the low-pressure compressor 13. 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 positioned around 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 positioned behind the diffuser 8.

[0014] The turbine 6 includes a high-pressure turbine 15 and a low-pressure turbine 16 positioned 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.

[0015] 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 31 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 31 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 is introduced into the combustor 5 via the diffuser 8. The combustion gas discharged from the combustor 5 passes through the turbine nozzle 9 and is introduced into the high-pressure turbine 15.

[0016] The combustor 5 in this embodiment is, for example, a backflow type. Alternatively, the combustor 5 is an annular type having a ring 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 the combustion chamber S within the combustor 5. The axial direction of the combustor 5 coincides with the axial direction X0 of the rotation axis 2.

[0017] The inner liner 5a and outer liner 5b have a cylindrical shape extending in the axial direction X0. The outer liner 5b is positioned outside the inner liner 5a in the radial direction R. The end liner 5c connects one end of the inner liner 5a and outer liner 5b in the axial direction X0. The end liner 5c has a ring shape extending in the radial direction R. The tip of the fuel nozzle 22, which will be described later, is inserted into the end liner 5c.

[0018] 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 that is continuous with the combustion chamber S. The discharge port of the exhaust passage T is directed toward a turbine nozzle 9 including a plurality of nozzle guide vanes 9a.

[0019] The fuel supply structure 20 supplies fuel to the combustor 5. The fuel may be supplied to the fuel supply structure 20 through a pipe 30 extending in the axial direction X0. As an example, the gas turbine 1 of the present embodiment may include a plurality of fuel supply structures 20. In this case, the plurality of fuel supply structures 20 may be connected to each other by a predetermined pipe structure.

[0020] FIG. 2 is a partial perspective view of the fuel supply structure 20 of FIG. 1. In FIG. 2, the tip portion of the fuel nozzle 22 is shown by a dashed line. As shown in FIG. 2, the fuel supply structure 20 includes a fuel supply pipe 21, a fuel nozzle 22, and a bolt 23. A pipe 30 is connected to the fuel supply pipe 21. The fuel nozzle 22 may have a flange portion 22c fixed to the combustor casing 19. In this case, the flange portion 22c may be fixed to the combustor casing 19 by, for example, a plurality of fasteners B1 and B2. As an example, the bolt 23 has a head portion 23i exposed outside the combustor casing 19.

[0021] FIG. 3 is a partial cross-sectional view of the fuel supply structure 20 of FIG. 1. FIG. 3 shows a cross-section taken along the arrow III-III of the bolt 23 in FIG. 2 and a cross-section taken along the arrow III-III of a part of the fuel nozzle 22, omitting the combustor 5. As shown in FIG. 3, the fuel supply pipe 21 may include a hollow head portion 21a and a tube portion 21b. The hollow head portion 21a is sandwiched between the fuel nozzle 22 and the head portion 23i of the bolt 23. As an example, the outer peripheral surfaces of the head portion 23i and the hollow head portion 21a have a polygonal shape when viewed from the axial direction of the bolt 23 (see FIG. 2). Thereby, for example, with the outer peripheral surface of the hollow head portion 21a held by sandwiching it with a predetermined tool, the head portion 23i of the bolt 23 is attached to the fuel nozzle 22 by a tightening tool.

[0022] As an example, the tube portion 21b has an internal flow path 21e and extends from the hollow head portion 21a. The internal flow path 21e of the tube portion 21b is connected to the internal flow path 30a of the pipe 30. For example, the hollow head portion 21a has an internal space 21f, a first insertion hole 21c, and a second insertion hole 21d. The internal space 21f communicates with the internal flow path 21e. The internal space 21f surrounds the outer periphery of a shaft portion 23b of the bolt 23, which will be described later. The first insertion hole 21c is disposed in a wall portion of the hollow head portion 21a facing the head portion 23i of the bolt 23 and communicates with the internal space 21f. The second insertion hole 21d is disposed in a wall portion of the hollow head portion 21a facing the fuel nozzle 22 and communicates with the internal space 21f.

[0023] The bolt 23 includes a fuel flow path 23a disposed inside the bolt 23. The fuel flow path 23a fluidly connects the fuel supply pipe 21 to the fuel nozzle 22 through an inlet 22a. The bolt 23 may include a shaft portion 23b, at least one first opening 23c, and a second opening 23d. The head portion 23i of the bolt 23 is connected to one end side in the axial direction of the shaft portion 23b. The shaft portion 23b is inserted through the first insertion hole 21c, the internal space 21f, and the second insertion hole 21d of the fuel supply pipe 21. The fuel flow path 23a is disposed inside the shaft portion 23b.

[0024] As an example, the first opening 23c is located on the outer circumferential surface of the shaft portion 23b on one end in the axial direction. The first opening 23c communicates with the internal space 21f of the fuel supply pipe 21. The second opening 23d is located on the end face 23f of the other end of the shaft portion 23b in the axial direction.

[0025] The fuel passage 23a may have at least one first passage 23g and a second passage 23h. In this case, the first passage 23g may extend radially from the shaft portion 23b and communicate with a first opening 23c. The at least one first opening 23c may include a plurality of first openings 23c. In this case, the plurality of first openings 23c may be spaced apart from each other in the circumferential direction of the shaft portion 23b. The second passage 23h may extend axially from the shaft portion 23b and communicate with the first passage 23g and the second opening 23d.

[0026] The opening areas of the first opening 23c and the second opening 23d can be set as appropriate. For example, the opening area of ​​a single first opening 23c may be smaller than the opening area of ​​the second opening 23d. Also, the arrangement of the at least one first flow path 23g can be set as appropriate. The at least one first flow path 23g may have multiple first flow paths 23g that intersect and communicate with each other.

[0027] The fuel nozzle 22 includes an inlet 22a into which fuel is supplied from the fuel supply pipe 21, and an injection port 22b for injecting fuel into the combustion chamber S of the combustor 5. The fuel nozzle 22 may, for example, include a nozzle block 26 and a flow path block 27. The nozzle block 26 has an injection port 22b facing the combustion chamber S and may be attached to the combustor 5. The flow path block 27 is connected to the nozzle block 26 and may have a flange portion 22c. In this case, the flange portion 22c may be fixed to the combustor casing 19 facing the hollow head portion 21a of the fuel supply pipe 21.

[0028] As an example, the flow path block 27 has the inlet 22a. In the flow path block 27, the inlet 22a faces the second opening 23d of the bolt 23. The flow path block 27 may further have a flow passage 27a that fluidly connects the inlet 22a to the nozzle 22b, and a bolt housing hole 27b adjacent to the upstream side of the flow passage 27a and having a female thread 27c on its inner circumferential surface. As an example, a male thread 23e is arranged on the outer circumferential surface of the shaft portion 23b of the bolt 23. With the shaft portion 23b of the bolt 23 inserted into the bolt housing hole 27b, the male thread 23e of the bolt 23 is screwed into the female thread 27c of the flow path block 27. In this way, the bolt 23 is attached to the flow path block 27.

[0029] The fuel supply structure 20 may further include a first sealing member 24 and a second sealing member 25. For example, the first sealing member 24 is sandwiched between the head 23i of the bolt 23 and the hollow head portion 21a of the fuel supply pipe 21. The second sealing member 25 is sandwiched between the hollow head portion 21a of the fuel supply pipe 21 and the fuel nozzle 22. The sealing members 24 and 25 are arranged to surround the shaft portion 23b of the bolt 23 in the circumferential direction. The sealing members 24 and 25 seal the gap between the bolt 23 and the fuel supply pipe 21 by deforming, for example, in conjunction with the tightening of the bolt 23.

[0030] 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.

[0031] When the gas turbine 1 is driven, 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 22 of the fuel supply structure 20 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.

[0032] As described above, the bolt 23 of the fuel supply structure 20 includes a fuel passage 23a located inside the bolt 23 that fluidly connects the fuel supply pipe 21 to the fuel nozzle 22 through the inlet 22a.

[0033] This configuration allows the fuel passage 23a to be positioned inside the fastening structure between the fuel nozzle 22 and the fuel supply pipe 21 using bolts 23. Therefore, compared to the case where the fuel passage and the fastening structure are relatively far apart, fuel leakage from the gap between the fuel nozzle 22 and the fuel supply pipe 21 can be suppressed. Furthermore, by including the fuel passage 23a within the bolts 23, the fuel supply structure 20 can be made smaller, and the space required for the installation of the structure 20 can be reduced. Thus, in the gas turbine 1, the fuel supply structure 20 can be compactly arranged while preventing fuel leakage between the combustor 5 and the fuel supply pipe 21.

[0034] As another example, the bolt 23 of this embodiment includes a shaft portion 23b on which male threads 23e are arranged on the outer circumferential surface and a fuel passage 23a is arranged inside, at least one first opening 23c arranged on the outer circumferential surface of the shaft portion 23b on one end in the axial direction, and a second opening 23d arranged on the end face 23f on the other end in the axial direction of the shaft portion 23b. The fuel passage 23a has at least one first passage 23g extending radially in the shaft portion and communicating with the first opening 23c, and a second passage 23h extending axially and communicating with the first passage 23g and the second opening 23d.

[0035] In this configuration, fuel introduced from the fuel supply pipe 21 through the first opening 23c into the first flow path 23g flows through the second flow path 23h and is then supplied from the bolt 23 to the fuel nozzle 22 through the second opening 23d. Therefore, a fuel flow path 23a can be easily formed in the bolt 23.

[0036] As another example, the at least one first opening 23c may include multiple first openings 23c. This allows fuel to be stably introduced into the fuel passage 23a of the bolt 23 through the multiple first openings 23c. Furthermore, by adjusting the number of first openings 23c, the total cross-sectional area of ​​the first openings 23c can be adjusted. This allows the amount of fuel supplied to the fuel nozzle 22 per unit time to be adjusted.

[0037] Furthermore, the multiple first openings 23c are arranged at intervals from each other in the circumferential direction of the shaft portion 23b. With this configuration, fuel can be stably introduced into the fuel passage 23a of the bolt 23 from multiple positions in the circumferential direction of the bolt 23 through the multiple first openings 23c.

[0038] Furthermore, the at least one first channel 23g has a plurality of first channels 23g that intersect and communicate with each other. With this configuration, for example, the plurality of first channels 23g and the plurality of first openings 23c can be formed by drilling, for example, drilling a hole in the shaft portion 23b radially from the outside. Therefore, the plurality of first channels 23g and the plurality of first openings 23c can be formed relatively easily.

[0039] As another example, the opening area of ​​the first opening 23c is smaller than the opening area of ​​the second opening 23d. This configuration makes it easier to maintain the axial rigidity of the shaft portion 23b at one end and to ensure the strength of the bolt 23.

[0040] As another example, the fuel supply pipe 21 includes a hollow head portion 21a and a tube portion 21b. The hollow head portion 21a also includes an internal space 21f, a first insertion hole 21c, and a second insertion hole 21d. The shaft portion 23b of the bolt 23 is inserted through the first insertion hole 21c, the internal space 21f, and the second insertion hole 21d, and the first opening 23c of the bolt 23 is in communication with the internal space 21f.

[0041] With this configuration, the shaft portion 23b of the bolt 23 can be inserted through the first insertion hole 21c and the second insertion hole 21d of the hollow head portion 21a to connect the fuel supply pipe 21 to the fuel nozzle 22. Furthermore, by adjusting the layout of the tube portion 21b, the degree of freedom in arranging the fuel supply structure 20 within the space of the gas turbine 1 can be improved.

[0042] Furthermore, the fuel supply structure 20 may further include, as an example, a first sealing member 24 and a second sealing member 25. This configuration further prevents fuel leakage from the gap between the fuel nozzle 22 and the fuel supply pipe 21.

[0043] In this embodiment, the shaft portion 23b of the bolt 23 is inserted into the bolt housing hole 27b of the flow path block 27, and the male thread 23e of the bolt 23 is screwed into the female thread 27c of the flow path block 27. This allows the shaft portion 23b of the bolt 23 to be inserted into the bolt housing hole 27b of the flow path block 27 that is connected to the nozzle block 26. Thus, the fuel supply structure 20 can be made more compact.

[0044] 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 thereto 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. In addition, the components described in the attached drawings and detailed description include not only components that are essential for solving the problem, but also components that are not essential for solving the problem, in order to illustrate the technology. The bolt 23 may include multiple parts. For example, the bolt 23 may include a shaft portion 23b and a head portion 23i which is a separate piece from the shaft portion 23b.

[0045] [Pattern] The embodiments described above are specific examples of the following embodiments. [Aspect 1] A fuel supply structure that supplies fuel to the combustor of a gas turbine, Fuel supply pipe and A fuel nozzle including an inlet through which fuel is supplied from the fuel supply pipe and an injection port for injecting fuel into the combustion chamber of the combustor, The fuel supply pipe is fastened to the fuel nozzle with a bolt, A fuel supply structure for a gas turbine combustor, comprising a bolt disposed inside the bolt and including a fuel passage that fluidly connects the fuel supply pipe to the fuel nozzle through the inlet.

[0046] According to the above configuration, the fuel passage can be placed inside the bolted fastening structure between the fuel nozzle and the fuel supply pipe. Therefore, compared to the case where the fuel passage and the fastening structure are relatively far apart, fuel leakage from the gap between the fuel nozzle and the fuel supply pipe can be suppressed. In addition, because the bolt includes the fuel passage, the fuel supply structure can be made smaller and the space required for installation work can be reduced. Therefore, in a gas turbine, the fuel supply structure can be compactly arranged while preventing fuel leakage between the combustor and the fuel supply pipe.

[0047] [Aspect 2] The aforementioned bolt is A shaft portion having male threads arranged on its outer surface and the fuel passage arranged inside, At least one first opening is provided on the outer circumferential surface of the shaft portion at one end in the axial direction, It includes a second opening located on the end face of the other end of the shaft in the axial direction, The aforementioned fuel passage is The shaft portion comprises at least one first flow path extending radially and communicating with the first opening, The fuel supply structure according to embodiment 1, further comprising a second flow path extending in the axial direction and communicating with the first flow path and the second opening.

[0048] According to the above configuration, fuel introduced from the fuel supply pipe through the first opening into the first flow path flows through the second flow path and is then supplied from the bolt to the fuel nozzle through the second opening. Therefore, a fuel flow path can be easily formed in the bolt.

[0049] [Aspect 3] The fuel supply structure according to embodiment 2, wherein the at least one first opening includes a plurality of first openings.

[0050] According to the above configuration, fuel can be stably introduced into the fuel passage of the bolt through multiple first openings. Furthermore, by adjusting the number of first openings, the total cross-sectional area of ​​the flow path of the first openings can be adjusted. This allows for adjustment of the amount of fuel supplied to the fuel nozzle per unit time.

[0051] [Aspect 4] The fuel supply structure according to embodiment 3, wherein the plurality of first openings are arranged at intervals from each other in the circumferential direction of the shaft portion.

[0052] According to the above configuration, fuel can be stably introduced into the fuel passage of the bolt from multiple positions in the circumferential direction of the bolt through multiple first openings.

[0053] [Aspect 5] The fuel supply structure according to any one of embodiments 2 to 4, wherein the at least one first flow path has a plurality of first flow paths that intersect and communicate with each other.

[0054] According to the above configuration, for example, multiple first flow channels and multiple first openings can be formed by drilling the shaft portion radially from the outside. Therefore, multiple first flow channels and multiple first openings can be formed relatively easily.

[0055] [Aspect 6] The fuel supply structure according to any one of embodiments 2 to 5, wherein the opening area of ​​the first opening is smaller than the opening area of ​​the second opening.

[0056] According to the above configuration, by setting the opening area of ​​the first opening as described above, it is possible to maintain the rigidity of one end of the shaft in the axial direction and to easily ensure the strength of the bolt.

[0057] [Aspect 7] The bolt includes a head connected to one end of the shaft portion, The aforementioned fuel supply pipe is A hollow head portion sandwiched between the fuel nozzle and the head of the bolt, It includes a tube portion extending from the hollow head portion and having an internal flow path, The aforementioned hollow head portion is An internal space communicating with the aforementioned internal flow path, The hollow head portion includes a wall portion of the bolt facing the head, and a first through hole that communicates with the internal space, The hollow head portion includes a second insertion hole located in the wall portion facing the fuel nozzle and communicating with the internal space, The fuel supply structure according to any one of embodiments 2 to 6, wherein the shaft portion of the bolt is inserted through the first insertion hole, the internal space, and the second insertion hole, and the first opening of the bolt is in communication with the internal space.

[0058] With the above configuration, the fuel supply pipe can be connected to the fuel nozzle by inserting the shaft portion of the bolt through the first and second insertion holes in the hollow head portion. Furthermore, by adjusting the layout of the tube portion, the degree of freedom in arranging the fuel supply structure within the space of the gas turbine can be improved.

[0059] [Aspect 8] A first sealing member sandwiched between the head of the bolt and the hollow head portion of the fuel supply pipe, The fuel supply structure according to embodiment 7, further comprising a second sealing member sandwiched between the hollow head portion of the fuel supply pipe and the fuel nozzle.

[0060] With the above configuration, the first and second sealing members can further prevent fuel leakage from the gap between the fuel nozzle and the fuel supply pipe.

[0061] [Aspect 9] The aforementioned fuel nozzle is A nozzle block having the injection port facing the combustion chamber, The fuel supply pipe has a flange portion that is fixed to the combustor casing facing the hollow head portion, and includes a flow path block connected to the nozzle block, The aforementioned flow channel block is The inlet facing the second opening of the bolt, A flow passage that fluidly connects the inlet to the injection port, The flow passage has a bolt housing hole adjacent to the upstream side and having an internal thread on its inner surface, The fuel supply structure according to embodiment 7 or 8, wherein the shaft portion of the bolt is inserted into the bolt housing hole, and the male thread of the bolt is screwed into the female thread of the flow path block.

[0062] According to the above configuration, the shaft portion of the bolt can be inserted into the bolt housing hole of the flow path block connected to the nozzle block, making the fuel supply structure more compact.

[0063] [Aspect 10] A gas turbine comprising one of the fuel supply structures described in any of embodiments 1 to 9.

[0064] According to the above configuration, a gas turbine can be obtained that prevents fuel leakage between the combustor and the fuel supply pipe while allowing for a compact arrangement of the fuel supply structure.

[0065] [Aspect 11] An unmanned aerial vehicle equipped with a gas turbine according to embodiment 10.

[0066] According to the above configuration, an unmanned aerial vehicle equipped with a gas turbine can be obtained that prevents fuel leakage between the combustor and the fuel supply pipe while allowing for a compact arrangement of the fuel supply structure. [Explanation of Symbols]

[0067] 1 Gas Turbine 5 Combustor 19. Combustor casing 20 Fuel supply structure 21 Fuel supply pipe 21a Hollow head section 21b Tube section 21c First insertion hole 21d Second insertion hole 22 Fuel nozzles 22a Inlet 22b Nozzle 22c flange section 23 volts 23a Fuel passage 23b Shaft 23c 1st opening 23d 2nd opening 23e Male screw 23f End face of the shaft 23g First channel 23h Second channel 23i bolt head 24 First sealing member 25 Second sealing member 26 Nozzle Block 27 Flow channel block

Claims

1. A fuel supply structure that supplies fuel to the combustor of a gas turbine, Fuel supply pipe and A fuel nozzle including an inlet through which fuel is supplied from the fuel supply pipe and an injection port for injecting fuel into the combustion chamber of the combustor, The fuel supply pipe is fastened to the fuel nozzle with a bolt, The bolt includes a fuel passage located inside the bolt that fluidly connects the fuel supply pipe to the fuel nozzle through the inlet, A fuel supply structure for a gas turbine combustor, wherein fuel flows through the fuel passage from the fuel supply pipe toward the fuel nozzle.

2. The aforementioned bolt is A shaft portion having male threads arranged on its outer surface and the fuel passage arranged inside, At least one first opening is provided on the outer circumferential surface of the shaft portion at one end in the axial direction, It includes a second opening located on the other end face of the shaft portion in the axial direction, The aforementioned fuel passage is The shaft portion comprises at least one first flow path extending radially and communicating with the first opening, The fuel supply structure according to claim 1, further comprising a second flow path extending in the axial direction and communicating with the first flow path and the second opening.

3. The fuel supply structure according to claim 2, wherein the at least one first opening includes a plurality of first openings.

4. The fuel supply structure according to claim 3, wherein the plurality of first openings are arranged at intervals from each other in the circumferential direction of the shaft portion.

5. The fuel supply structure according to claim 4, wherein the at least one first flow path has a plurality of first flow paths that intersect and communicate with each other.

6. The fuel supply structure according to claim 2, wherein the opening area of ​​the first opening is smaller than the opening area of ​​the second opening.

7. The bolt includes a head connected to one end of the shaft portion, The aforementioned fuel supply pipe is A hollow head portion sandwiched between the fuel nozzle and the head of the bolt, It includes a tube portion extending from the hollow head portion and having an internal flow path, The aforementioned hollow head portion is An internal space communicating with the aforementioned internal flow path, The hollow head portion includes a wall portion of the bolt facing the head, and a first insertion hole that communicates with the internal space, The hollow head portion includes a second insertion hole located in the wall portion facing the fuel nozzle and communicating with the internal space, The fuel supply structure according to any one of claims 2 to 6, wherein the shaft portion of the bolt is inserted through the first insertion hole, the internal space, and the second insertion hole, and the first opening of the bolt is in communication with the internal space.

8. A first sealing member sandwiched between the head of the bolt and the hollow head portion of the fuel supply pipe, The fuel supply structure according to claim 7, further comprising a second sealing member sandwiched between the hollow head portion of the fuel supply pipe and the fuel nozzle.

9. The aforementioned fuel nozzle is A nozzle block having the injection port facing the combustion chamber, The fuel supply pipe has a flange portion that is fixed to the combustor casing facing the hollow head portion, and includes a flow path block connected to the nozzle block, The aforementioned flow channel block is The inlet facing the second opening of the bolt, A flow passage that fluidly connects the inlet to the injection port, The flow passage has a bolt housing hole adjacent to the upstream side and having an internal thread on its inner surface, The fuel supply structure according to claim 7, wherein the shaft portion of the bolt is inserted into the bolt housing hole, and the male thread of the bolt is screwed into the female thread of the flow path block.

10. A gas turbine comprising the fuel supply structure described in claim 1.

11. An unmanned aerial vehicle comprising the gas turbine according to claim 10.

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