Combustor system for gas turbines

Abstract

In gas turbine combustors, the combustor can be efficiently cooled by air. [Solution] A combustor device for a gas turbine comprises a combustor, a combustor casing that covers the combustor via an air passage, and a plurality of fins disposed between the combustor and the combustor casing. The combustor includes an annular inner liner surrounding an axis extending in a predetermined axial direction, an annular outer liner disposed outside the inner liner in the radial direction of the axis and surrounding the inner liner, and an end liner connecting one axial end of the inner liner and the outer liner. The plurality of fins are connected to the end liner.

Description

Technical Field

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

Background Art

[0002] Patent Document 1 discloses a reverse flow combustor for a gas turbine. In this combustor, compressed air is supplied from a compressor and fuel is also supplied. In the combustor, the fuel is mixed with the compressed air and burned. The combustion gas generated by the combustion of the fuel is supplied to the turbine to drive the turbine. The combustor is cooled by air.

Prior Art Documents

Patent Documents

[0003]

Patent Document 1

Summary of the Invention

Problems to be Solved by the Invention

[0004] In the combustor having the above-described structure, it is required to efficiently cool the combustor with air.

[0005] Therefore, an object of the present disclosure is to enable the combustor of a gas turbine to be efficiently cooled by air.

Means for Solving the Problems

[0006] One aspect of the present disclosure is a combustor device for a gas turbine, comprising: a combustor; a combustor casing covering the combustor via an air passage; and a plurality of fins disposed between the combustor and the combustor casing, wherein the combustor includes: an annular inner liner surrounding an axis extending in a predetermined axial direction; an annular outer liner disposed outside the inner liner and surrounding the inner liner in the radial direction of the axis; and an end liner connecting one end of the inner liner and the outer liner in the axial direction, the plurality of fins being connected to the end liner. [Effects of the Invention]

[0007] According to one aspect of this disclosure, a combustor for a gas turbine can be efficiently cooled by air. [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 a partial cross-sectional view of the combustor apparatus shown in Figure 1, viewed from the circumferential direction along the axis. [Figure 3] Figure 3 is a partially enlarged cross-sectional view of the combustor apparatus shown in Figure 2. [Figure 4] Figure 4 is a cross-sectional view taken along the line IV-IV in Figure 3. [Figure 5] Figure 5 is a cross-sectional view taken along the VV line in Figure 3. [Modes for carrying out the invention]

[0009] [Embodiment] Embodiments will be described below with reference to the drawings. In the following description, unless otherwise specified, axial direction X0 means the direction in which the axis X of the rotating shaft 2 extends. Forward and front side mean the upstream side in the direction in which air flows in the compressor 4 and turbine 6.

[0010] Furthermore, "rear" and "backside" refer to the downstream side in the direction of airflow in the compressor 4 and turbine 6. That is, "front" and "front side" refer to the side where the fan 3 is located in the axial direction X0. "Rear" and "backside" refer to the side opposite to where the fan 3 is located in the axial direction X0.

[0011] Furthermore, the radial direction R refers to the radial direction of axis X, or in other words, the direction perpendicular to axis X. The circumferential direction C refers to the direction around axis X. In this embodiment, since the combustor 20 of the combustor device 5 is of the reverse flow type, the upstream side of the combustor device 5 refers to the downstream side of the compressor 4 and turbine 6, and the downstream side of the combustor device 5 refers to the upstream side of the compressor 4 and turbine 6.

[0012] 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. As shown in Figure 1, the gas turbine 1 comprises a rotating shaft 2, a fan 3, a compressor 4, a combustor device 5, a turbine 6, and a gas turbine casing 7. The rotating shaft 2 extends in the front-rear direction of the gas turbine 1. The fan 3 is connected to the front of the rotating shaft 2 and rotates together with the rotating shaft 2. The compressor 4, combustor device 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 device 5, and turbine 6.

[0013] The gas turbine 1 is, for example, a two-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.

[0014] The compressor 4 includes a low-pressure compressor 13 and a high-pressure compressor 14 disposed behind the low-pressure compressor 13. The low-pressure compressor 13 is an axial-flow compressor. The high-pressure compressor 14 is a centrifugal compressor. A diffuser 8 for sending the air flowing out from the high-pressure compressor 14 backward is disposed on the outer periphery of the high-pressure compressor 14. A combustor device 5 is disposed behind the diffuser 8.

[0015] The combustor device 5 burns fuel in a combustor 20 described later and cools the combustor 20 with the air supplied from the diffuser 8. Since the details of the combustor device 5 will be described later, the combustor device 5 is schematically illustrated in FIG. 1. As shown in FIG. 1, one side in the axial direction X0 of the combustor device 5 is the upstream side of the combustor device 5 and the rear side of the gas turbine 1. The other side in the axial direction X0 of the combustor device 5 is the downstream side of the combustor device 5 and the front side of the gas turbine 1.

[0016] The turbine 6 includes a high-pressure turbine 15 and a low-pressure turbine 16 disposed 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.

[0017] The gas turbine casing 7 includes an inner casing 17 and an outer casing 18. The inner casing 17 and the outer casing 18 have a cylindrical shape and are arranged concentrically with each other. The inner casing 17 houses the compressor 4, the combustor device 5, and the turbine 6. A cylindrical bypass passage B is disposed between the inner casing 17 and the outer casing 18. A part of the air sucked by the fan 3 flows through the bypass passage B and is discharged backward. The remaining part of the air sucked 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 flows into the combustor device 5 through the diffuser 8. The combustion gas discharged from the outlet of the combustor device 5 flows into the high-pressure turbine 15 through the nozzle unit 9.

[0018] The combustor device 5 includes an annular combustor 20 extending in the circumferential direction C. FIG. 2 is a partial cross-sectional view of the combustor device 5 in FIG. 1 as viewed from the circumferential direction C. As shown in FIG. 2, the combustor 20 includes an inner liner 21, an outer liner 22, an end liner 23, an outer turn guide 24, an inner turn guide 25, and an evaporation tube 26. The liners 21 to 23 define a combustion chamber S which is the internal space of the combustor 20. The combustion chamber S has an annular shape surrounding the axis X. The axial direction of the combustor 20 coincides with the axial direction X0 of the rotation axis 2.

[0019] The inner liner 21 and the outer liner 22 have a cylindrical shape extending in the axial direction X0. In the present embodiment, the circumferential direction of the inner liner 21 and the outer liner 22 coincides with the circumferential direction C. The inner liner 21 has an annular shape surrounding the axis extending in a predetermined axial direction. As an example, the "axis extending in a predetermined axial direction" mentioned here coincides with the "axis X extending in the axial direction X0". The inner liner 21 includes a plurality of combustion air introduction holes 21a.

[0020] The outer liner 22 is disposed outside the inner liner 21 in the radial direction R. The outer liner 22 has an annular shape surrounding the inner liner 21. As an example, the outer liner 22 surrounds the outer circumference of the inner liner 21. That is, the outer liner 22 has a larger diameter than the inner liner 21. The outer liner 22 is arranged concentrically with the inner liner 21 and faces the inner liner 21 from the outside in the radial direction R.

[0021] The outer liner 22 includes a plurality of combustion air introduction holes 22a and a plurality of cooling air introduction holes 22c. The arrangement positions of the plurality of combustion air introduction holes 22a may include a plurality of positions spaced apart in the axial direction X0. For example, the arrangement positions include a position on one side of the axial direction X0 with respect to an opening 22b of the outer liner 22 to be described later and a position on the other side of the axial direction X0 with respect to the opening 22b. The plurality of cooling air introduction holes 22c may be arranged, for example, along the opening 22b.

[0022] The end liner 23 connects one end of the inner liner 21 and the outer liner 22 in the axial direction X0. The end liner 23 has an annular shape extending in the radial direction R. When viewed from the circumferential direction C, the end liner 23 has a dome-shaped cross-section that is convex toward one side in the axial direction X0. The outer liner 22 and the inner liner 21 extend from the end liner 23 toward the other side in the axial direction X0.

[0023] The outer turn guide 24 curves 180° from the tip of the outer liner 22 on the other side of the axial direction X0 and extends to one side of the axial direction X0. The inner turn guide 25 curves 180° from the tip of the inner liner 21 on the other side of the axial direction X0 and extends to one side of the axial direction X0.

[0024] The outer turn guide 24 and the inner turn guide 25 define an exhaust passage T that is continuous with the combustion chamber S. Combustion gas generated in the combustor 20 flows through the exhaust passage T. The exhaust passage T includes an exhaust port Ta located at the ends of the outer turn guide 24 and the inner turn guide 25 on one side in the axial direction X0. The exhaust port Ta is directed toward a nozzle unit 9 which includes a plurality of nozzle guide vanes.

[0025] The outer liner 22 includes an opening 22b into which a fuel injector 10 is inserted. The evaporator tube 26 is positioned in the combustion chamber S, into which the fuel injector 10 is inserted, and is connected to the periphery of the opening 22b of the outer liner 22. The evaporator tube 26 includes an internal passage 27 that communicates with the opening 22b and evaporates the fuel. The evaporator tube 26 also includes an outer circumferential surface 26a exposed to the combustion chamber S and an inner circumferential surface 26b defining the internal passage 27. The end of the evaporator tube 26 opposite to the outer liner 22 is connected to the inner liner 21, for example.

[0026] The evaporator tube 26 includes an opening 27a that discharges evaporated fuel from the internal passage 27 into the combustion chamber S. The opening 27a is spaced apart from the end liner 23 on the other side in the axial direction X0 and directed toward the end liner 23. The evaporator tube 26 includes at least one cooling air passage 28. The cooling air passage 28 is located between the outer circumferential surface 26a and the inner circumferential surface 26b and communicates with a cooling air inlet hole 22c.

[0027] The evaporator tube 26 includes a plurality of cooling air outlets 28a that open the end of the cooling air passage 28 inward in the radial direction R to the combustion chamber S. A gap is provided between the outer circumferential surface of the fuel injector 10 and the inner circumferential surface 26b of the evaporator tube 26. The fuel injection side tip of the fuel injector 10 is located in the middle of the internal passage 27.

[0028] The combustor device 5 further comprises a combustor casing 40 that covers the combustor 20 via an air passage 50, and a plurality of fins 30 positioned between the combustor 20 and the combustor casing 40. The combustor casing 40 in this embodiment houses the entire combustor 20. The combustor casing 40 includes an outer wall 41, an inner wall 42, and an end wall 43.

[0029] The outer wall 41, inner wall 42, and end wall 43 are connected to each other. In the radial direction R, the outer wall 41 is located outside the outer liner 22. The outer wall 41 forms part of the inner shell 17 of the gas turbine casing 7. In the radial direction R, the inner wall 42 is located inside the inner liner 21. The outer wall 41 and inner wall 42 extend in the axial direction X0. The end wall 43 is located on one side of the end liner 23 in the axial direction X0 and extends in the radial direction R.

[0030] The multiple fins 30 have, for example, an elongated shape extending in one direction. In this embodiment, the multiple fins 30 have an elongated shape with the circumferential direction C as the thickness direction and the radial direction R as the longitudinal direction. The multiple fins 30 are arranged in the circumferential direction C and connected to the end liner 23. Adjacent fins 30 are arranged with a gap 31 between them. In this embodiment, the multiple fins 30 are also connected to the combustor casing 40. As a result, the end liner 23 is connected to the end wall 43 via the multiple fins 30.

[0031] The air passage 50 is located between the combustor 20 and the combustor casing 40 and allows air supplied via the diffuser 8 to circulate. The air passage 50 may include a plurality of passages. As an example, the air passage 50 in this embodiment includes a first passage 51, a second passage 52, and a third passage 53.

[0032] The first passage 51 is located between the outer liner 22 and the outer wall 41. The first passage 51 surrounds the outer circumferential surface of the outer liner 22 in the circumferential direction C. The second passage 52 is located between the end liner 23 and the end wall 43 and includes a plurality of gaps 31. The second passage 52 is in contact with the outer surface of the end liner 23 from one side in the axial direction X0 of the end liner 23. The third passage 53 is located between the inner liner 21 and the inner wall 42. The third passage 53 surrounds the outer circumferential surface of the inner liner 21 in the circumferential direction C. The passages 51 to 53 are in communication with each other.

[0033] Figure 3 is a partially enlarged cross-sectional view of the combustor device 5 of Figure 2. As shown in Figure 3, the maximum length L in the radial R of the fin 30 and the maximum length H in the axial direction X0 of the portion of the fin 30 located between the end liner 23 and the combustor casing 40 may be different from each other. That is, for example, the maximum length L of the fin 30 may be greater than the maximum length H. Here, the length L of the fin 30 may refer to either the total length of the fin 30 in the radial R, or the length of a portion of the fin 30 in the radial R. Also, in the axial direction X0, at least a portion of one side of the fin 30 in the axial direction X0 may be connected to the end wall 43, and at least a portion of the other side in the axial direction X0 may be connected to the end liner 23. In this embodiment, the entire fin on one side in the axial direction X0 is connected to the end wall 43, and the entire fin on the other side in the axial direction X0 is connected to the end liner 23.

[0034] The fin 30 includes a first end 30a located on the inner wall 42 side and a second end 30b located on the outer wall 41 side. At least one of the first end 30a and the second end 30b may extend at an inclination with respect to the axial direction X0. For example, the first end 30a may be inclined to approach the end wall 43 from the end liner 23 as it moves from the outside to the inside of the radial direction R. The second end 30b may extend along the axial direction X0. The fin 30 may also include multiple portions with different extending directions. As an example, the fin 30 further includes a main body portion 30c extending in the radial direction R and a bent portion 30d that bends from the first end 30a side of the main body portion 30c toward the other side of the axial direction X0.

[0035] The fins 30 may have different thicknesses in the circumferential direction C at different positions in the axial direction X0. Figure 4 is a cross-sectional view taken along the line IV-IV in Figure 3. In Figure 4, as an example, a cross-section perpendicular to the longitudinal direction of some of the fins 30 provided in the combustor device 5. As shown in Figure 4, the fins 30 further include, for example, a first portion 30e and a second portion 30f.

[0036] The first portion 30e has a side surface 30i extending axially X0 from the end wall 43. The second portion 30f has an inclined surface 30h extending inclined with respect to the axial direction X0 from the end liner 23 side of the side surface 30i. The second portion 30f is connected to the end liner 23. In the circumferential direction C, the maximum thickness of the second portion 30f is greater than the maximum thickness of the first portion 30e. The second portion 30f may have a thickened portion 30g in which the thickness in the circumferential direction C increases towards the end liner 23.

[0037] In this embodiment, the two adjacent inclined surfaces 30h of an adjacent pair of fins 30 are inclined and extend toward each other as they approach the end liner 23. That is, the other end of the gap 31 in the axial direction X0 has a tapered shape that narrows toward the other end in the axial direction X0. The two inclined surfaces 30h are adjacent to each other on the end liner 23 side, separated by a ridge line 30j that extends radially R. The side surface 30i and the inclined surface 30h are in contact with the air flowing through the gap 31.

[0038] Figure 5 is a cross-sectional view taken along the line VV in Figure 3. In Figure 5, a cross-section perpendicular to the axial direction X0 is shown in the first portion 30e of some of the multiple fins 30 of the combustor device 5. As shown in Figure 5, in this embodiment, the multiple fins 30 and the multiple gaps 31 extend radially from the axis of axis X.

[0039] When viewed from the axial direction X0, each of the multiple fins 30 may include a portion where the thickness D in the circumferential direction C is constant, or it may include a portion where the thickness D in the circumferential direction C is different at different positions in the radial direction R. For example, the multiple fins 30 may include a portion where the thickness D in the circumferential direction C increases from one side to the other, either inward or outward in the radial direction R. That is, each of the multiple fins 30 may include a portion where the thickness D in the circumferential direction C increases from the inside to the outside in the radial direction R. As another example, the portion where the thickness D increases may include a first portion 30e.

[0040] Furthermore, when viewed from the axial direction X0, each of the multiple gaps 31 may include a portion where the width W in the circumferential direction C is constant, or it may include a portion where the width W in the circumferential direction C is different at different positions in the radial direction R. For example, the multiple gaps 31 may include a portion where the width W in the circumferential direction C increases from one side to the other, either inward or outward in the radial direction R. That is, the multiple gaps 31 may include a portion where the width W in the circumferential direction C increases from the inside to the outside in the radial direction R. Furthermore, when viewed from the axial direction X0, the maximum width W of the gap 31 at the outermost position max The minimum thickness D in the circumferential direction C of the fin 30 at its innermost position is... min It may be larger than this. Here, "outermost position" and "innermost position" refer to positions relative to the radial direction R.

[0041] The combustor device 5 may include a component in which multiple elements are integrally continuous. For example, in the combustor device 5 of this embodiment, the liners 21-23 and the multiple fins 30 are integrally continuous with each other. In this embodiment, the liners 21-23 and the multiple fins 30 are monolithic components formed integrally based on additive manufacturing. In this monolithic component, the liners 21-23, the multiple fins 30, and the combustor casing 40 may be integrally formed. Furthermore, the combustor device 5 does not have to include a monolithic component and may include multiple components. Also, for example, the combustor device 5 may include a metal processed product.

[0042] When the gas turbine 1 is driven, air supplied from the high-pressure compressor 14 via the diffuser 8 is introduced into the air passage 50. The air then flows into the internal passage 27 of the evaporator tube 26 through the opening 22b of the outer liner 22. The fuel injector 10 also injects liquid fuel into the internal passage 27. In the internal passage 27, the liquid fuel is mixed with air and evaporated. This generates evaporated fuel. The evaporated fuel is burned in the combustion chamber S.

[0043] Furthermore, the air introduced into the air passage 50 flows into the combustion chamber S through the combustion air inlet 22a of the outer liner 22 and the combustion air inlet 21a of the inner liner 21. The air that flows into the combustion chamber S is used for the combustion of evaporated fuel.

[0044] Furthermore, combustion gases are generated when the evaporated fuel is burned. The combustion gases move toward the end liner 23 and then flow radially outward along the end liner 23 in the direction R. Subsequently, the combustion gases flow toward the other side in the axial direction X0 along the inner circumferential surface of the outer liner 22. After that, the combustion gases are discharged from the outlet Ta of the combustor 20. The combustion gases discharged from the outlet Ta are guided by the nozzle guide vanes of the nozzle unit 9 and flow into the high-pressure turbine 15.

[0045] Furthermore, the air introduced into the air passage 50 flows into the cooling air passage 28 via the cooling air inlet 22c of the outer liner 22. The evaporator tube 26 is cooled by the air flowing into the cooling air passage 28, preventing burnout. The air that has cooled the evaporator tube 26 is discharged into the combustion chamber S from the cooling air outlet 28a. The air discharged into the combustion chamber S is used to burn the unburned fuel in the combustion chamber S.

[0046] Furthermore, the air introduced into the air passage 50 flows through passages 51 to 53, cooling the liners 21 to 23. At this time, the air that has flowed through the first passage 51 is introduced into the second passage 52 and flows through multiple gaps 31. As the air flows through the multiple gaps 31, it comes into contact with the surfaces of the multiple fins 30, end walls 43, and end liners 23. The air that has flowed through the multiple gaps 31 is introduced into the third passage 53.

[0047] As described here, in the combustor device 5, the multiple fins 30 are positioned between the combustor 20 and the combustor casing 40 and connected to the end liner 23. This allows the heat from the combustor 20 to be efficiently dissipated through the multiple fins 30 to the air flowing through the multiple gaps 31. Therefore, the combustor 20 can be efficiently cooled.

[0048] As another example, in the combustor device 5 of this embodiment, air passages 50 are arranged so as to surround each of the liners 21 to 23 in the circumferential direction C. Therefore, the entire liners 21 to 23 can be efficiently cooled by the air flowing through the air passages 50.

[0049] Furthermore, the combustor 20 in this embodiment is of the reverse flow type, and the fuel injection tip of the fuel injector 10 is directed toward the end liner 23. In a reverse flow type combustor, the fuel flame may easily be directed toward the end liner. According to this embodiment, even in such cases, since the multiple fins 30 are connected to the end liner 23, the heat transferred from the end liner 23 to the multiple fins 30 can be efficiently dissipated into the air flowing through the gap 31.

[0050] Furthermore, since the multiple fins 30 in this embodiment extend in the radial direction R, the multiple gaps 31 can be arranged to extend in the radial direction R. Therefore, by circulating air through the multiple gaps 31, the combustor 20 can be efficiently cooled.

[0051] Furthermore, the multiple fins 30 in this embodiment are arranged with gaps 31 in the circumferential direction C. Therefore, by arranging multiple gaps 31 in the circumferential direction C, the heat from the combustor 20 transmitted to the multiple fins 30 can be efficiently dissipated into the air flowing through the multiple gaps 31.

[0052] Furthermore, each of the multiple fins 30 in this embodiment includes a portion in which the thickness D increases from the inside to the outside in the radial direction R. This suppresses changes in the width W of the gaps 31 at multiple positions in the radial direction R. As a result, air can flow smoothly through each gap 31.

[0053] In this embodiment, the maximum width W of the gap 31 at the outermost position in the radial direction R is also specified. max The minimum thickness D of the fin 30 at its innermost position. min It is larger than this. Thus, the maximum width W max and minimum thickness D minBy setting this, a wider gap 31 can be secured. Therefore, air can be circulated more smoothly through each gap 31.

[0054] Furthermore, in this embodiment, the maximum length L in the radial direction R of the fin 30 is greater than the maximum length H in the axial direction X0 of the portion of the fin 30 located between the end liner 23 and the combustor casing 40 in the axial direction X0. Therefore, the dimensions of the combustor 20 in the axial direction X0 are not constrained by the multiple fins 30. In addition, the length of the combustor device 5 in the axial direction X0 can be set compactly. Also, the surface area of ​​the multiple fins 30 can be made sufficiently large in the radial direction R. As a result, the heat of the combustor 20 transmitted to the multiple fins 30 can be efficiently dissipated into the air flowing through the multiple gaps 31.

[0055] Furthermore, the multiple fins 30 in this embodiment are connected to the combustor casing 40. This allows the heat generated in the combustor 20 to be transferred to the combustor casing 40 via the multiple fins 30 for heat dissipation, and also allows for efficient dissipation into the air flowing through the multiple gaps 31. As a result, the cooling efficiency of the combustor 20 can be further improved. In addition, since the multiple fins 30 can be connected to both the end liner 23 and the combustor casing 40, the combustor 20 can be supported more stably by the combustor casing 40.

[0056] Furthermore, in the combustor device 5 of this embodiment, the inner liner 21, outer liner 22, end liner 23, and the multiple fins 30 are integrally continuous with each other. Therefore, the liners 21-23 and the multiple fins 30 can be constructed as a single integrated unit. As a result, the connection between the liners 21-23 and the multiple fins 30 can be strengthened, improving the strength of the combustor 20. In addition, the cooling effect of the combustor 20 by the multiple fins 30 can be stably obtained.

[0057] 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.

[0058] The end of the evaporator tube 26 opposite to the outer liner 22 may be separated from the inner liner 21. The outer liner 22 may also be configured such that the cooling air inlet hole 22c is omitted and the inlet of the cooling air passage 28 communicates with the opening 22b of the outer liner 22. Furthermore, if the fins 30 are arranged extending in the radial direction R, the fins 30 do not have to extend linearly along the radial direction R. In this case, for example, the fins 30 may include portions that extend in a direction inclined with respect to the radial direction R, or portions that extend while bending toward the radial direction R. In addition, the combustor 20 may be of a type other than the backflow type.

[0059] [Pattern] The embodiments described above are specific examples of the following embodiments. [Aspect 1] A combustor device for a gas turbine, Combustor and A combustor casing that covers the combustor via an air passage, The combustion chamber comprises a plurality of fins positioned between the combustion chamber and the combustion chamber casing, The aforementioned combustor is An annular inner liner surrounding an axis extending in a predetermined axial direction, In the radial direction of the aforementioned axis, an annular outer liner is disposed outside the inner liner and surrounds the inner liner, Includes an end liner that connects the inner liner and the outer liner at one end in the axial direction, The plurality of fins are connected to the end liner in a gas turbine combustor device.

[0060] With the above configuration, multiple fins connected to the end liner are positioned within the air passage, allowing the heat from the combustor to be efficiently dissipated into the air within the passage. Therefore, the combustor can be cooled efficiently.

[0061] [Aspect 2] The gas turbine combustor device according to embodiment 1, wherein the plurality of fins extend in the radial direction.

[0062] According to the above configuration, air can be circulated radially through the gaps between the multiple fins, and the combustor can be efficiently cooled by this air.

[0063] [Aspect 3] The gas turbine combustor device according to embodiment 1 or 2, wherein the plurality of fins are arranged with gaps between them in the circumferential direction of the axis.

[0064] According to the above configuration, multiple gaps can be arranged in the circumferential direction of the axis via multiple fins. Therefore, the heat transferred from the combustor to the multiple fins can be efficiently dissipated into the air flowing through each gap.

[0065] [Aspect 4] The gas turbine combustor device according to embodiment 3, wherein each of the plurality of fins includes a portion in which the circumferential thickness increases from the radially inward to the radially outward.

[0066] According to the above configuration, changes in the width of the gaps are suppressed at multiple positions in the radial direction of the axis. This allows air to flow smoothly through each gap.

[0067] [Aspect 5] The gas turbine combustor device according to embodiment 3 or 4, wherein the maximum width of the gap at the outermost position is greater than the minimum circumferential thickness of the fin at the innermost position.

[0068] According to the above configuration, the maximum width of the gap at the outermost position is greater than the minimum thickness of the fin at the innermost position, thus allowing for a wider gap. Consequently, air can flow more smoothly through each gap.

[0069] [Aspect 6] The gas turbine combustor device according to any one of embodiments 1 to 5, wherein the maximum value of the radial length of the fin is greater than the maximum value of the axial length of the fin between the end liner and the combustor casing.

[0070] According to the above configuration, the dimensions of the combustor in the axial direction of the axis can be suppressed from being constrained by the multiple fins. In addition, the axial length of the combustor device can be set to be compact. Furthermore, in the radial direction of the axis, a certain surface area of ​​the multiple fins can be secured, allowing the heat from the combustor transferred to the multiple fins to be efficiently dissipated into the air flowing through the gaps between the multiple fins.

[0071] [Aspect 7] The gas turbine combustor device according to any one of embodiments 1 to 6, wherein the plurality of fins are connected to the combustor casing.

[0072] With the above configuration, heat generated in the combustor can be transferred to the combustor casing via multiple fins for heat dissipation, and this heat can be efficiently dissipated into the air flowing through the gaps between the fins. Therefore, the cooling efficiency of the combustor can be further improved. In addition, since multiple fins can be connected to both the end liner and the combustor casing, the end liner can be stably supported by the combustor casing.

[0073] [Aspect 8] The gas turbine combustor device according to any one of embodiments 1 to 7, wherein the inner liner, the outer liner, the end liner, and the plurality of fins are integrally continuous with respect to one another.

[0074] According to the above configuration, the inner liner, outer liner, end liner, and multiple fins can be integrally formed. Therefore, the bonds between these components can be strengthened, improving the strength of the combustor.

[0075] [Aspect 9] A gas turbine comprising a combustor device in any one of embodiments 1 to 8.

[0076] According to the above configuration, in a gas turbine in operation, heat from the combustor can be efficiently dissipated to the air through multiple fins connected to the end liner between the combustor and the combustor casing. Therefore, the combustor can be efficiently cooled. [Explanation of symbols]

[0077] 5. Combustion device 20 Fuel device 21 Inner Liner 22 Outer Liner 23 Endliner 30 fins 31 Fin gaps 40 Combustor Casing 50 Air passage Circumferential direction of the C axis Fin thickness in the circumferential direction along the D axis D min Minimum fin thickness in the circumferential direction of the axis The length in the axial direction of the fin portion positioned between the axis of the H end liner and the combustor casing. Fin length in the radial direction along the L axis Radial direction of the R axis W max Maximum width of the gap in the circumferential direction of the axis X axis X0 Axial direction

Claims

1. A combustor device for a gas turbine, Combustor and A combustor casing that covers the combustor via an air passage, The combustion chamber comprises a plurality of fins positioned between the combustion chamber and the combustion chamber casing, The aforementioned combustor is An annular inner liner surrounding an axis extending in a predetermined axial direction, In the radial direction of the aforementioned axis, an annular outer liner is disposed outside the inner liner and surrounds the inner liner, Includes an end liner that connects the inner liner and the outer liner at one end in the axial direction, The plurality of fins are connected to the end liner in a gas turbine combustor device.

2. The gas turbine combustor device according to claim 1, wherein the plurality of fins extend in the radial direction.

3. The gas turbine combustor device according to claim 1, wherein the plurality of fins are arranged with gaps between them in the circumferential direction of the axis.

4. The gas turbine combustor device according to claim 3, wherein each of the plurality of fins includes a portion in which the circumferential thickness increases from the radially inward to the radially outward.

5. The gas turbine combustor device according to claim 3, wherein the maximum width of the gap at the outermost position is greater than the minimum circumferential thickness of the fin at the innermost position.

6. The gas turbine combustor device according to claim 3, wherein the maximum value of the radial length of the fin is greater than the maximum value of the axial length of the fin between the end liner and the combustor casing.

7. The gas turbine combustor device according to claim 1, wherein the plurality of fins are connected to the combustor casing.

8. The gas turbine combustor device according to any one of claims 1 to 7, wherein the inner liner, the outer liner, the end liner, and the plurality of fins are integrally continuous with respect to each other.

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