Fuel nozzle for gas turbine combustor

Abstract

In a gas turbine, the fuel flowing through the fuel nozzle is maintained at an appropriate temperature, making it possible to inject it into the combustion chamber of the combustor. [Solution] A fuel nozzle for injecting fuel into the combustion chamber of a gas turbine combustor, comprising: an air passage for circulating air supplied to the combustion chamber; a fuel passage for circulating fuel supplied to the combustion chamber; and an insulating structure disposed between the air passage and the fuel passage.

Description

Technical Field

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[0001] The present disclosure relates to a fuel nozzle that injects fuel into a combustion chamber of 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 Document

Patent Document

[0003]

Patent Document 1

Summary of the Invention

Problems to be Solved by the Invention

[0004] In a gas turbine, from the viewpoint of stably driving the combustor, it is required to maintain the fuel flowing through a fuel nozzle such as a fuel injector at an appropriate temperature.

[0005] Therefore, an object of the present disclosure is to enable the fuel flowing through the fuel nozzle in a gas turbine to be maintained at an appropriate temperature and injected into the combustion chamber of the combustor.

Means for Solving the Problems

[0006] One aspect of the present disclosure is a fuel nozzle that injects fuel into a combustion chamber of a combustor of a gas turbine, including an air flow path through which air supplied to the combustion chamber flows, a fuel flow path through which fuel supplied to the combustion chamber flows, and a heat insulation structure disposed between the air flow path and the fuel flow path.

Effects of the Invention

[0007] According to one aspect of the present disclosure, in a gas turbine, the fuel flowing through the fuel nozzle can be maintained at an appropriate temperature and injected into the combustion chamber of the combustor. [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 schematic partial cross-sectional view of the fuel nozzle shown in Figure 1. [Figure 3] Figure 3 is a cross-sectional view of the fuel nozzle in Figure 2, taken along the line III-III. [Figure 4] Figure 4 is a cross-sectional view of the fuel nozzle in Figure 2, taken along the line IV-IV. [Figure 5] Figure 5 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 gas turbine 1 is configured such that the fuel nozzle 22 has a predetermined heat insulating structure 22c, which insulates the fuel flowing through the fuel passage 22b of the fuel nozzle 22 from the air flowing through the air passage 22a, and allows the fuel to be injected into the combustion chamber S of the combustor 5 while maintaining it at an appropriate temperature.

[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 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 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 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 of the inner liner 5a and the outer liner 5b in the axial direction X0. The end liner 5c has an annular shape extending in the radial direction R.

[0018] The first turn guide 5d curves 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 curves 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.

[0019] The fuel supply structure 20 supplies fuel to the combustor 5. The fuel supply structure 20 includes a fuel nozzle 22 that injects fuel into the combustion chamber S of the combustor 5. The tip of the fuel nozzle 22 is inserted into the end liner 5c of the combustor 5. Fuel may be supplied through a pipe 10 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.

[0020] FIG. 2 is a schematic partial cross-sectional view of the fuel nozzle 22 of FIG. 1. FIG. 2 shows a schematic cross-section along the nozzle axial direction P of the fuel nozzle 22. As shown in FIG. 2, the fuel nozzle 22 includes an air flow path 22a, a fuel flow path 22b, a heat insulation structure 22c, and an injection port 22d. As an example, each of the air flow path 22a, the fuel flow path 22b, and the heat insulation structure 22c is arranged to extend in the nozzle axial direction P.

[0021] The air flow path 22a allows the air supplied to the combustion chamber S to flow through. The fuel flow path 22b allows the fuel supplied to the combustion chamber S to flow through. The fuel nozzle 22 includes an opening 22e that opens the fuel flow path 22b toward the injection port 22d. The heat insulation structure 22c is disposed between the air flow path 22a and the fuel flow path 22b. As an example, the heat insulation structure 22c is disposed between the air flow path 22a and the fuel flow path 22b in the nozzle diameter direction Q.

[0022] The heat insulation structure 22c may include a plurality of heat insulation structures. For example, the heat insulation structure 22c may include a first heat insulation structure 22f and a second heat insulation structure 22g that are spaced apart from each other in the nozzle diameter direction Q. In this case, the fuel flow path 22b may be disposed between the first heat insulation structure 22f and the second heat insulation structure 22g in the nozzle diameter direction Q.

[0023] The air flow path 22a may include a plurality of flow paths. For example, the air flow path 22a of the present embodiment includes a first air flow path 22h and a second air flow path 22i. In this case, the first air flow path 22h may be disposed inside the fuel flow path 22b in the nozzle diameter direction Q. Also, the second air flow path 22i may be disposed outside the fuel flow path 22b in the nozzle diameter direction Q.

[0024] In this configuration, the first heat insulation structure 22f is disposed between the first air flow path 22h and the fuel flow path 22b in the nozzle diameter direction Q. The second heat insulation structure 22g is disposed between the second air flow path 22i and the fuel flow path 22b in the nozzle diameter direction Q. The fuel nozzle 22 may include an opening 22j that opens the first air flow path 22h toward the injection port 22d and an opening 22k that opens the second air flow path 22i toward the injection port 22d. As an example, when viewed from the nozzle axis direction P, the opening 22j has a circular shape. Also, when viewed from the nozzle axis direction P, the opening 22k has an annular shape.

[0025] The fuel nozzle 22 may also include a nozzle block 26 that houses an air passage 22a, a fuel passage 22b, and a heat insulating structure 22c. The nozzle block 26 includes an injection port 22d and is attached to the combustor 5. The nozzle block 26 may further include a first communication passage 26d that communicates with the fuel passage 22b. The first communication passage 26d is located on the side of the nozzle block 26 opposite to the injection port 22d. The first communication passage 26d may extend, for example, in the direction of the nozzle axis P. Fuel is supplied to the first communication passage 26d from outside the fuel nozzle 22.

[0026] The nozzle block 26 may also include a second communication passage 26e that communicates with the first air passage 22h. The second communication passage 26e is positioned, for example, to overlap with the first communication passage 26d in the nozzle radial direction Q. The second communication passage 26e may extend, for example, in the nozzle radial direction Q.

[0027] The nozzle block 26 may also have a first air inlet 26b and a second air inlet 26c. The air inlets 26b and 26c are arranged on the outer circumferential surface of the nozzle block 26 and are connected to the air passage 22a. The air inlets 26b and 26c may be spaced apart in the direction of the nozzle axis P. Here, the nozzle block 26 may have a plurality of first air inlets 26b. In this case, the plurality of first air inlets 26b may be spaced apart in the circumferential direction of the nozzle axis Y. The nozzle block 26 may also have a plurality of second air inlets 26c. In this case, the plurality of second air inlets 26c may be spaced further away from the injection port 22d than the plurality of first air inlets 26b, and spaced apart in the circumferential direction of the nozzle axis Y.

[0028] As shown in Figure 2, the fuel nozzle 22 may further include at least one swirler 34. In this case, the fuel passage 22b and the heat insulating structure 22c may be positioned to overlap with the at least one swirler 34 in the nozzle radial direction Q. As an example, the at least one swirler 34 may include a first swirler 35 located inside the first air passage 22h and a second swirler 36 located inside the second air passage 22i. At least one of the swirlers 35 and 36 may include a helical stator vane that rotates in the circumferential direction of the nozzle axis Y and extends in the nozzle axial direction P. At least one of the swirlers 35 and 36 may also be omitted.

[0029] The first air passage 22h may have a passage opening 22q that communicates with the second communication passage 26e. The first air passage 22h may also be positioned to coincide with the nozzle axis Y. The second air passage 22i may communicate with the first air inlet 26b. The second air passage 22i may also include a portion that approaches the nozzle axis Y as it moves from the direction of the nozzle axis Y of the nozzle block 26 toward the injection port 22d.

[0030] Furthermore, the insulating structure 22c may include a hollow structure. A fluid such as a gas may be placed in this hollow structure. As shown in Figure 2, in this case, the insulating structure 22c may include an air layer 22l. The air layer 22l may be arranged extending in the direction P of the nozzle axis.

[0031] The heat insulating structure 22c may also include a dead-end portion 22m that isolates at least one end of the air layer 22l in the nozzle axial direction P from the outside of the fuel nozzle 22. This end is, for example, the injection port 22d side of the air layer 22l in the nozzle axial direction P.

[0032] The thermal insulation structure 22c may include a dead-end portion 22o, which is positioned in correspondence with the first thermal insulation structure 22f, and a dead-end portion 22p, which is positioned in correspondence with the second thermal insulation structure 22g, as dead-end portions 22m. In the fuel nozzle 22, the thermal insulation structure 22c includes dead-end portions 22m, thereby suppressing the flow of outside air through the air layer 22l in the direction of the nozzle axis P. The air layer 22l does not need to be completely isolated from the outside.

[0033] Figure 3 is a cross-sectional view of the fuel nozzle 22 in Figure 2, taken along the line III-III. As shown in Figure 3, the second communication passage 26e may extend from the outer circumferential surface of the nozzle block 26 toward the nozzle axis Y, while being separated from the first communication passage 26d in the nozzle radial direction Q.

[0034] Figure 4 is a cross-sectional view of the fuel nozzle 22 in Figure 2, taken along the line IV-IV. In Figure 4, the swirl 35, which will be described later, is not shown. As shown in Figure 4, the fuel nozzle 22 of this embodiment includes, as an example, a portion in which the first air passage 22h, the first heat insulating structure 22f, the fuel passage 22b, the second heat insulating structure 22g, and the second air passage 22i are arranged in this order from the inside to the outside in the nozzle radial direction Q. At least one of the first heat insulating structure 22f, the fuel passage 22b, the second heat insulating structure 22g, and the second air passage 22i may have a cylindrical shape extending in the circumferential direction of the nozzle axis Y. If the first heat insulating structure 22f, the fuel passage 22b, the second heat insulating structure 22g, and the second air passage 22i all have the cylindrical shape, they may be arranged concentrically when viewed from the nozzle axial direction P.

[0035] Figure 5 is a schematic diagram of an unmanned aerial vehicle 40 equipped with the gas turbine 1 shown in Figure 1. As shown in Figure 5, 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.

[0036] When the gas turbine 1 is running, a portion of the air supplied from the high-pressure compressor 14 via the diffuser 8 is introduced into the combustion chamber S of the combustor 5. The remaining portion of this air is introduced into the fuel nozzle 22. At this time, the air introduced into the fuel nozzle 22 from the second air inlet 26c enters the first air passage 22h of the air passage 22a and is rectified by the swirler 35. Subsequently, the air in the first air passage 22h passes through the opening 22j and is injected into the combustion chamber S from the injection port 22d.

[0037] Furthermore, the air introduced into the fuel nozzle 22 from the multiple first air inlets 26b enters the second air passage 22i of the air passage 22a and is rectified by the swirl 36. Subsequently, the air in the second air passage 22i passes through the opening 22k and is injected into the combustion chamber S from the injection port 22d.

[0038] Furthermore, the fuel that has passed through the first communication passage 26d flows through the fuel passage 22b. Subsequently, the fuel passes through the opening 22e and is injected into the combustion chamber S from the injection port 22d. As a result, fuel and air are supplied to the combustion chamber S from the injection port 22d of the fuel nozzle 22. In the combustion chamber S, the fuel mixed with air is burned to generate 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.

[0039] As described above, the fuel nozzle 22 of this embodiment includes an air passage 22a for circulating air supplied to the combustion chamber S, a fuel passage 22b for circulating fuel supplied to the combustion chamber S, and a heat insulating structure 22c disposed between the air passage 22a and the fuel passage 22b. With this configuration, even when high-temperature air flows through the air passage 22a, the fuel flowing through the fuel passage 22b can be insulated from the air flowing through the air passage 22a by the heat insulating structure 22c. Therefore, the fuel flowing through the fuel nozzle 22 can be maintained at an appropriate temperature and injected into the combustion chamber S of the combustor 5.

[0040] As another example, the heat insulating structure 22c of this embodiment includes a first heat insulating structure 22f and a second heat insulating structure 22g, which are spaced apart from each other in the nozzle radial direction Q. The fuel passage 22b is located between the first heat insulating structure 22f and the second heat insulating structure 22g in the nozzle radial direction Q. With this configuration, the fuel flowing through the fuel passage 22b can be efficiently insulated from both sides of the fuel passage 22b in the nozzle radial direction Q from the air flowing through the air passage 22a.

[0041] As another example, the air passage 22a includes a first air passage 22h located inside the nozzle radial direction Q of the fuel passage 22b, and a second air passage 22i located outside the nozzle radial direction Q of the fuel passage 22b. The first insulating structure 22f is located between the first air passage 22h and the fuel passage 22b in the nozzle radial direction Q, and the second insulating structure 22g is located between the second air passage 22i and the fuel passage 22b in the nozzle radial direction Q. With this configuration, the first insulating structure 22f and the second insulating structure 22g can adequately insulate the fuel flowing through the fuel passage 22b from the air flowing through the first air passage 22h and the second air passage 22i.

[0042] Furthermore, the air passage 22a, fuel passage 22b, and heat insulating structure 22c are each arranged to extend in the direction of the nozzle axis P, for example. With this configuration, in a wide area of ​​the fuel nozzle 22 extending in the direction of the nozzle axis P, the fuel flowing through the fuel passage 22b can be efficiently insulated from the air flowing through the air passage 22a by the heat insulating structure 22c.

[0043] Furthermore, each of the air passage 22a, fuel passage 22b, and heat insulating structure 22c has a cylindrical shape extending in the circumferential direction of the nozzle axis Y. With this configuration, even in a fuel nozzle 22 equipped with both cylindrical fuel passage 22b and air passage 22a, the fuel flowing through the fuel passage 22b can be properly insulated from the air flowing through the air passage 22a by the heat insulating structure 22c around the entire circumference of the nozzle axis Y.

[0044] As another example, the insulating structure 22c includes an air layer 22l. With this configuration, for example, by using an insulating structure 22c with an air layer 22l placed inside, the fuel flowing through the fuel passage 22b can be properly insulated from the air flowing through the air passage 22a.

[0045] As another example, the heat insulating structure 22c includes a dead-end portion 22m that isolates at least one end of the air layer 22l, which is arranged to extend in the nozzle axial direction P, from the outside of the fuel nozzle 22.

[0046] With this configuration, for example, the high-temperature air in the air passage 22a can be prevented from flowing into the air layer 22l of the insulating structure 22c in the direction P of the nozzle axis by the dead-end portion 22m of the insulating structure 22c. This retains the air placed in the air layer 22l of the insulating structure 22c, and a stable insulating effect can be obtained from the insulating structure 22c.

[0047] As another example, the fuel nozzle 22 of this embodiment further includes at least one swirler 34 positioned in the air passage 22a, extending in the direction of the nozzle axis P, and causing the air flowing through the air passage 22a to swirl around the nozzle axis Y. The fuel passage 22b and the heat insulating structure 22c are positioned to overlap with the at least one swirler 34 in the nozzle radial direction Q. With this configuration, in the nozzle radial direction Q, the fuel flowing through the fuel passage 22b can be insulated by the heat insulating structure 22c from the air flowing through the air passage 22a, which is swirled by the swirler 34.

[0048] 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. Furthermore, 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 nozzle block 26 may be composed of multiple parts that have been machined, for example, by cutting or drilling. The heat insulating structure 22c may also include a heat insulating material other than a fluid, such as a gas.

[0049] [Aspect] The embodiments described above are specific examples of the following embodiments. [Aspect 1] A fuel nozzle for injecting fuel into the combustion chamber of a gas turbine combustor, An air passage for circulating air supplied to the combustion chamber, A fuel passage for circulating fuel to be supplied to the combustion chamber, A fuel nozzle comprising a heat insulating structure disposed between the air passage and the fuel passage.

[0050] With the above configuration, even when high-temperature air flows through the air passage, the fuel flowing through the fuel passage can be insulated from the air flowing through the air passage by the insulating structure. Therefore, the fuel flowing through the fuel nozzle can be maintained at an appropriate temperature and injected into the combustion chamber of the combustor.

[0051] [Aspect 2] The aforementioned heat insulating structure includes a first heat insulating structure and a second heat insulating structure arranged apart from each other in the direction of the nozzle diameter. The fuel nozzle according to embodiment 1, wherein the fuel passage is located between the first insulating structure and the second insulating structure in the diameter direction of the nozzle.

[0052] According to the above configuration, the fuel flowing through the fuel passage can be efficiently insulated from the air flowing through the air passage from both sides in the nozzle diameter direction of the fuel passage.

[0053] [Aspect 3] The aforementioned air passage is A first air passage is located inside the nozzle radial direction relative to the fuel passage, It includes a second air passage located outside the fuel passage in the nozzle radial direction, The first heat insulating structure is positioned between the first air passage and the fuel passage in the radial direction of the nozzle. The fuel nozzle according to embodiment 2, wherein the second heat insulating structure is arranged between the second air passage and the fuel passage in the radial direction of the nozzle.

[0054] According to the above configuration, the first and second heat insulating structures can adequately insulate the fuel flowing through the fuel passage from the air flowing through the first and second air passages.

[0055] [Aspect 4] A fuel nozzle according to any one of embodiments 1 to 3, wherein each of the air passage, the fuel passage, and the heat insulating structure is arranged to extend in the direction of the nozzle axis.

[0056] According to the above configuration, in a wide area of ​​the fuel nozzle extending in the direction of the nozzle axis, the fuel flowing through the fuel passage can be efficiently insulated from the air flowing through the air passage by the insulating structure.

[0057] [Aspect 5] A fuel nozzle according to any one of embodiments 1 to 4, wherein each of the air passage, the fuel passage, and the heat insulating structure has a cylindrical shape extending in the circumferential direction of the nozzle axis.

[0058] According to the above configuration, even in a fuel nozzle that has both a cylindrical fuel passage and an air passage, the fuel flowing through the fuel passage can be properly insulated from the air flowing through the air passage by the insulating structure around the entire circumference of the nozzle axis.

[0059] [Aspect 6] The aforementioned heat insulating structure includes an air layer, as described in any one of embodiments 1 to 5 of the fuel nozzle.

[0060] According to the above configuration, for example, by using an insulating structure with an air layer inside, the fuel flowing through the fuel passage can be properly insulated from the air flowing through the air passage.

[0061] [Aspect 7] The air layer is arranged extending in the direction of the nozzle axis, The fuel nozzle according to embodiment 6, wherein the heat insulating structure includes a dead-end portion that isolates at least one end of the air layer in the nozzle axial direction from the outside of the fuel nozzle.

[0062] According to the above configuration, for example, the high-temperature air in the air passage can be prevented from flowing into the air layer of the insulating structure in the direction of the nozzle axis by the dead-end portion of the insulating structure. This retains the air placed in the air layer of the insulating structure, and a stable insulating effect can be obtained from the insulating structure.

[0063] [Aspect 8] The air passage is further provided with at least one swirl, which is positioned in the air passage and extends in the direction of the nozzle axis, causing the air flowing through the air passage to swirl around the nozzle axis. The fuel nozzle according to any one of embodiments 1 to 7, wherein the fuel passage and the heat insulating structure are positioned to overlap with at least one swirler in the nozzle radial direction.

[0064] According to the above configuration, in the diameter direction of the nozzle, the fuel flowing through the fuel passage can be insulated from the air flowing through the air passage, which is swirled by the swirler, by the insulating structure.

[0065] [Aspect 9] A gas turbine comprising one fuel nozzle from any one of embodiments 1 to 8.

[0066] According to the above configuration, a gas turbine can be obtained that can maintain the fuel flowing through the fuel nozzle at an appropriate temperature and inject it into the combustion chamber of the combustor.

[0067] [Aspect 10] An unmanned aerial vehicle equipped with a gas turbine according to embodiment 9.

[0068] According to the above configuration, an unmanned aerial vehicle can be obtained that is equipped with a gas turbine capable of maintaining the fuel flowing through the fuel nozzle at an appropriate temperature and injecting it into the combustion chamber of the combustor. [Explanation of symbols]

[0069] S Combustion Chamber P Nozzle axis direction Q Nozzle diameter direction Y Nozzle Axis 1 Gas Turbine 5 Combustor 22 Fuel nozzles 22a Airflow channel 22b Fuel passage 22c insulation structure 22L air layer 22m, 22o, 22p dead end 22f First Insulation Structure 22g Second insulation structure 22h First air channel 22i Second air passage 34 Swara 40 unmanned aerial vehicle

Claims

1. A fuel nozzle for injecting fuel into the combustion chamber of a gas turbine combustor, An air passage for circulating air supplied to the combustion chamber, A fuel passage for circulating fuel to be supplied to the combustion chamber, The system comprises a heat insulating structure disposed between the air passage and the fuel passage, Each of the air passage, fuel passage, and heat insulating structure has a cylindrical shape that extends around a nozzle axis that passes through the center in the diameter direction of the nozzle and extends perpendicular to the diameter direction of the nozzle. The aforementioned heat insulating structure includes a first heat insulating structure and a second heat insulating structure arranged apart from each other in the direction of the nozzle diameter, The fuel passage is located between the first and second insulating structures in the nozzle diameter direction, and is positioned at a distance from the nozzle axis in the nozzle diameter direction when viewed from the nozzle diameter direction.

2. The air passage is further comprising at least one swirl, which is disposed in the air passage and extends in the direction of the nozzle axis, causing the air flowing through the air passage to swirl around the nozzle axis, The fuel nozzle according to claim 1, wherein the fuel passage and the heat insulating structure are arranged to overlap with the at least one swirler in the diameter direction of the nozzle.

3. The aforementioned air passage is A first air passage is located inside the nozzle radial direction of the fuel passage, It includes a second air passage located outside the nozzle radial direction of the fuel passage, The first heat insulating structure is arranged between the first air passage and the fuel passage in the radial direction of the nozzle, The fuel nozzle according to claim 1, wherein the second heat insulating structure is disposed between the second air passage and the fuel passage in the diameter direction of the nozzle.

4. The fuel nozzle according to claim 1, wherein each of the air passage, the fuel passage, and the heat insulating structure is arranged to extend in the direction of the nozzle axis.

5. The fuel nozzle according to any one of claims 1 to 4, wherein the heat insulating structure includes an air layer.

6. The air layer is arranged extending in the direction of the nozzle axis, The fuel nozzle according to claim 5, wherein the heat insulating structure includes a dead-end portion that isolates at least one end of the air layer in the nozzle axial direction from the outside of the fuel nozzle.

7. A gas turbine comprising the fuel nozzle described in claim 1.

8. An unmanned aerial vehicle comprising the gas turbine described in claim 7.

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