Combustor for gas turbines
The combustor design stabilizes the evaporator tube by integrating it with the outer or inner liner, addressing vibration issues and enhancing fuel diffusion and ignition performance.
Patent Information
- Authority / Receiving Office
- JP · JP
- Patent Type
- Applications
- Current Assignee / Owner
- KAWASAKI JUKOGYO KK
- Filing Date
- 2024-12-18
- Publication Date
- 2026-06-30
Smart Images
Figure 2026106473000001_ABST
Abstract
Description
Technical Field
[0001] The present disclosure relates to a combustor for a gas turbine.
Background Art
[0002] Patent Document 1 discloses a reverse flow combustor for a gas turbine. Compressed air is supplied from a compressor to the internal space of the combustor, and fuel is supplied from a fuel injector. The fuel from the fuel injector is evaporated through an evaporation pipe disposed in the internal space and supplied to the internal space of the combustor. 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.
Prior Art Documents
Patent Documents
[0003]
Patent Document 1
Summary of the Invention
Problems to be Solved by the Invention
[0004] When the evaporation pipe vibrates in the internal space of the combustor, the position of the evaporation pipe in the internal space becomes unstable.
[0005] Therefore, an object of the present disclosure is to stably arrange an evaporation pipe that supplies fuel from a fuel injector to the internal space of a reverse flow combustor for a gas turbine.
Means for Solving the Problems
[0006] One aspect of the present disclosure is a backflow combustor for a gas turbine having a rotating shaft having an axis extending in the axial direction, comprising: an outer liner having an annular shape extending around the axis and including an opening into which a fuel injector is inserted; an inner liner having an annular shape extending around the axis and facing the outer liner from the radially inward side of the axis; an end liner having an annular shape, positioned on one side in the axial direction with respect to the outer liner and the inner liner, connecting the outer liner to the inner liner; a combustion chamber defined by the outer liner, the inner liner and the end liner; and an evaporator tube connected to the outer liner and positioned in the combustion chamber, including an internal passage communicating with the opening of the outer liner, and evaporating fuel in the internal passage, wherein the tip of the evaporator tube, located on the side of the internal passage opposite to the opening of the outer liner, is connected to a specific liner which is at least one of the outer liner, the inner liner and the end liner. [Effects of the Invention]
[0007] According to one aspect of this disclosure, in a reverse-flow combustor for a gas turbine, the evaporator tube that supplies fuel from a fuel injector into the internal space of the combustor can be stably arranged. [Brief explanation of the drawing]
[0008] [Figure 1] Figure 1 is a cross-sectional view of a gas turbine according to the first embodiment. [Figure 2] Figure 2 is a partial cross-sectional view of the combustor in Figure 1. [Figure 3] Figure 3 is a partial view of the evaporator tube in Figure 2, seen from one side along its axial direction. [Figure 4] Figure 4 is a partial cross-sectional view of a combustor according to the second embodiment. [Modes for carrying out the invention]
[0009] (First Embodiment) The first embodiment will be described below with reference to the drawings. In the following description, the direction in which the axis X of the rotating shaft 2 of the gas turbine 1 extends will be referred to as the axial direction X. The axis X of the rotating shaft 2 coincides with the axis X of the combustor 5. Front and front side mean the upstream side in the direction in which air flows in the compressor 4 and turbine 6 of the gas turbine 1. Rear and rear side mean the downstream side in the direction in which air flows in the compressor 4 and turbine 6 of the gas turbine 1. That is, front and front side mean the side on which the fan 3 is located in the axial direction X of the gas turbine 1. Rear and rear side mean the side opposite to the side on which the fan 3 is located in the axial direction X of the gas turbine 1. Radial direction R means the direction perpendicular to the axis X. Circumferential direction C means the direction around the axis X. Since the combustor 5 is a backflow type, the upstream side of the combustor 5 means the downstream side of the compressor 4 and turbine 6, and the downstream side of the combustor 5 means the upstream side of the compressor 4 and turbine 6.
[0010] Figure 1 is a cross-sectional view of a gas turbine 1 according to a first 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 5, a turbine 6, and a casing 7. As shown below, in the gas turbine 1, both one end and the other end of the evaporator tube 26 of the combustor 5 are supported by the liner of the combustor 5 (see Figure 2). This configuration allows the combustor 5 to be driven stably.
[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 together with it. The compressor 4, combustor 5, and turbine 6 are arranged in this order from front to rear along the rotating shaft 2. The casing 7 is a cylindrical object with an axis that coincides with the axis X of the rotating shaft 2. The casing 7 houses the rotating shaft 2, fan 3, compressor 4, combustor 5, and turbine 6.
[0012] 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.
[0013] The compressor 4 includes a low-pressure compressor 13 and a high-pressure compressor 14 positioned 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 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. Behind the diffuser 8 is an annular combustor 5 having a ring shape extending in the circumferential direction C around the axis X.
[0014] The combustor 5 will be described in detail later, so Figure 1 shows a schematic representation of the combustor 5. As shown in Figure 1, one side of the combustor 5 in the axial direction X is the upstream side of the combustor 5 and the rear side of the gas turbine 1. The other side of the combustor 5 in the axial direction X is the downstream side of the combustor 5 and the front side of the gas turbine 1. The combustor 5 may be a processed product made from a metal plate, or it may be an additively manufactured product made by additive manufacturing of metal materials.
[0015] 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.
[0016] The casing 7 includes a cylindrical inner shell 17 and an outer shell 18 arranged concentrically with respect to each other. The inner shell 17 houses the compressor 4, the combustor 5, and the turbine 6. A cylindrical bypass passage B is formed 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 flows into the combustor 5 via the diffuser 8. The combustion gas discharged from the outlet of the combustor 5 flows through the nozzle unit 9 and into the high-pressure turbine 15.
[0017] Figure 2 is a partial cross-sectional view of the combustor 5 in Figure 1. Figure 2 partially shows a cross-section of the combustor 5 viewed from the radial direction R. As shown in Figure 2, the combustor 5 comprises an outer liner 21, an inner liner 22, an end liner 23, an outer turn guide 24, an inner turn guide 25, and an evaporator tube 26. In the combustor 5 of this embodiment, at least the outer liner 21, the inner liner 22, the end liner 23, and the evaporator tube 26 are integrally continuous with each other. In this embodiment, the liners 21-23, the turn guides 24 and 25, and the evaporator tube 26 are monolithic parts integrally formed based on additive manufacturing. The combustor 5 does not necessarily have to include monolithic parts and may include multiple parts. For example, the combustor 5 may also include metal processed parts.
[0018] The outer liner 21 has an annular shape extending in the circumferential direction C around the axis X. The inner liner 22 has an annular shape with a smaller diameter than the outer liner 21. The inner liner 22 is arranged concentrically with the outer liner 21 and faces the outer liner 21 from the inside in the radial direction R perpendicular to the axis X. The outer liner 21 and the inner liner 22 each have a cylindrical shape extending in the axial direction X.
[0019] The end liner 23 is disposed on one side of the axial direction X with respect to the outer liner 21 and the inner liner 22. The end liner 23 connects the outer liner 21 to the inner liner 22. The end liner 23 has an annular shape extending in the radial direction R. The end liner 23 has a dome-shaped cross-sectional shape that is convex toward one side of the axial direction X in a cross-sectional view seen from the radial direction R. The combustor 5 of the present embodiment further includes a liner component 20. The liner component 20 includes an outer liner 21, an inner liner 22, and an end liner 23 that are integrally connected to each other.
[0020] The outer liner 21, the inner liner 22, and the end liner 23 define a combustion chamber S. That is, the combustion chamber S has an annular shape extending in the circumferential direction C around the axis X. The outer liner 21 and the inner liner 22 extend from the end liner 23 to the other side of the axial direction X. The outer turn guide 24 curves so as to change the direction by 180° from the tip of the outer liner 21 on the other side of the axial direction X and extends to one side of the axial direction X. The inner turn guide 25 curves so as to change the direction by 180° from the tip of the inner liner 22 on the other side of the axial direction X and extends to one side of the axial direction X.
[0021] The outer turn guide 24 and the inner turn guide 25 define an exhaust passage T that is continuous with the combustion chamber S. The combustion gas generated in the combustor 5 flows from the combustion chamber S into the exhaust passage T. An exhaust port Ta of the exhaust passage T is disposed at the tips of the outer turn guide 24 and the inner turn guide 25 on one side of the axial direction X. The exhaust port Ta faces a nozzle unit 9 (see FIG. 1) including a plurality of nozzle guide vanes. The combustion gas discharged from the exhaust port Ta is guided by the nozzle guide vanes of the nozzle unit 9 and flows into the high-pressure turbine 15.
[0022] The outer liner 21 includes an opening 21b into which the fuel injector 10 is inserted. One end of an evaporation pipe 26 disposed in the combustion chamber S is connected to the outer liner 21. The evaporation pipe 26 is disposed in the combustion chamber S which is the internal space of the combustor 5. The evaporation pipe 26 extends from the outer liner 21 toward the inner side in the radial direction R and one side in the axial direction X. The evaporation pipe 26 includes an internal flow path 31 that communicates with the opening 21b of the outer liner 21, and evaporates fuel in this internal flow path 31. A tip portion 26c of the evaporation pipe 26 located on the side opposite to the opening 21b side of the outer liner 21 in the internal flow path 31 is connected to a specific liner which is at least any one of the outer liner 21, the inner liner 22, and the end liner 23. The specific liner of the present embodiment includes the inner liner 22. Thus, both ends of the evaporation pipe 26 are supported by the liner of the combustor 5.
[0023] Here, the tip portion 26c of the evaporation pipe 26 refers to a portion from the edge located on the most one side in the axial direction X of the evaporation pipe 26 to the central position in the length dimension in the axial direction X of the evaporation pipe 26. The tip portion 26c may be directly connected to the specific liner, or may be indirectly connected to the specific liner via another member such as a support member.
[0024] The tip portion 26c of the evaporation pipe 26 may include an opening end 26e in which the peripheral edge of the opening 31a is inclined so as to have a downward gradient approaching the inner liner 22 toward the end liner 23. Further, the evaporation pipe 26 may include an outer peripheral surface 26a exposed to the combustion chamber S and an inner peripheral surface 26b that defines the internal flow path 31 which is the main flow path. The direction in which the flow path axis Y of the internal flow path 31 of the evaporation pipe 26 extends is referred to as the flow path axial direction Y. The internal flow path 31 of the evaporation pipe 26 communicates with the opening 21b of the outer liner 21. That is, one end of the evaporation pipe 26 is connected to the peripheral edge of the opening 21b of the outer liner 21.
[0025] The fuel injector 10 is inserted into the internal flow path 31 of the evaporator tube 26 through the opening 21b of the outer liner 21. The fuel injector 10 is positioned on the flow path axis Y of the evaporator tube 26. A gap exists between the outer surface of the fuel injector 10 and the inner surface 26b of the evaporator tube 26. The length of the portion of the fuel injector 10 positioned in the internal flow path 31 of the evaporator tube 26 in the direction of the flow path axis Y is shorter than the length of the evaporator tube 26 in the direction of the flow path axis Y. That is, the tip of the fuel injector 10 that ejects fuel is located in the middle of the internal flow path 31 of the evaporator tube 26 in the direction of the flow path axis Y.
[0026] The evaporator tube 26 includes, for example, an expanded section 26d in which the flow path cross-sectional area expands from the opening 21b of the outer liner 21 toward the tip 26c. The expanded section 26d has a length dimension that is longer than half the length dimension of the evaporator tube 26, for example in the axial direction X. The expanded section 26d may extend, for example, from a position in the middle of the evaporator tube 26 to the furthest point of the opening end 26e, in the axial direction X. The expanded section 26d may also be positioned to overlap with the fuel injector 10 in the radial direction R.
[0027] The evaporator tube 26 also includes, as an example, a first tube section 26f extending radially inward in the direction R from one end connected to the periphery of the opening 21b of the outer liner 21, and a second tube section 26g extending from one end of the first tube section 26f in the axial direction X to that side. The second tube section 26g extends with a gentler slope than the first tube section 26f, and the slope becomes downward as it approaches the end liner 23, getting closer to the inner liner 22. The second tube section 26g is located on one side in the axial direction X from the tip of the fuel injector 10. In other words, the tip of the fuel injector 10 is located inside the first tube section 26f. The evaporator tube 26 is connected to a specific liner at the second tube section 26g. The tip of the fuel injector 10 may also be located inside the second tube section 26g.
[0028] Here, Figure 3 is a partial view of the evaporator tube 26 in Figure 2, viewed from one side in the axial direction X. As shown in Figure 3, the tip portion 26c of the evaporator tube 26 in this embodiment has an opening periphery 26h that widens towards the end liner 23 in the circumferential direction of the inner liner 22. The opening periphery 26h defines the outer circumferential shape of the opening end 26e. The opening periphery 26h has a periphery top portion 26i located closest to the outer liner 21 of the evaporator tube 26. The opening periphery 26h has a periphery portion that widens circumferentially from the periphery top portion 26i towards the inner liner 22. Note that the circumferential direction of the inner liner 22 in this embodiment coincides with the circumferential direction C around the axis X.
[0029] As shown in Figure 2, the combustor 5 comprises a casing component 40 that covers the liner component 20 from the outside, and an air passage 52 through which air supplied from the diffuser 8 flows. The casing component 40 includes an outer wall 41, an inner wall 42, and an end wall 43. The outer wall 41 is located outside the outer liner 21 in the radial direction R, with a gap between it and the outer liner 21. The gap between the outer liner 21 and the outer wall 41 is the air passage 51 through which air supplied from the diffuser 8 flows. The inner wall 42 is located inside the inner liner 22 in the radial direction R, with a gap between it and the inner liner 22. The air passage 52 is the gap between the inner liner 22 and the inner wall 42.
[0030] The end wall 43 is positioned on one side of the end liner 23 in the axial direction X, with a gap between it and the end liner 23. The end liner 23 is connected to the end wall 43 by a connecting wall 44. The connecting wall 44 has a connecting passage 45 that connects the air passage 51 to the air passage 52. The outer wall 41, inner wall 42, and end wall 43 constitute the casing component 40. The outer wall 41 forms part of the inner shell 17 of the casing 7.
[0031] Air supplied from the high-pressure compressor 14 (see Figure 1) via the diffuser 8 flows into the internal passage 31 of the evaporator tube 26 through the opening 21b. The fuel injector 10 injects liquid fuel into the internal passage 31 of the evaporator tube 26. For example, in the internal passage 31 of the evaporator tube 26, the liquid fuel injected from the fuel injector 10 adheres to the high-temperature evaporator tube 26 and evaporates, generating evaporated fuel. The evaporator tube 26 includes an opening 31a located at its tip 26c that discharges the evaporated fuel from the internal passage 31 into the combustion chamber S. The evaporated fuel is mixed with air.
[0032] The opening 31a of the evaporator tube 26 is spaced apart from the end liner 23 on the other side in the axial direction X, and faces the end liner 23. The opening 31a of the evaporator tube 26 is closer to the inner liner 22 than to the outer liner 21. However, the opening 31a of the evaporator tube 26 does not have to be closer to the inner liner 22 than to the outer liner 21.
[0033] The outer liner 21 includes a plurality of combustion air inlet holes 21a. The arrangement of the plurality of combustion air inlet holes 21a may include positions on one side of the opening 21b of the outer liner 21 in the axial direction X, and positions on the other side of the opening 21b of the outer liner 21 in the axial direction X. The inner liner 22 also includes a plurality of combustion air inlet holes 22a. Air supplied from the diffuser 8 flows into the combustion chamber S through the combustion air inlet holes 21a and 22a. The air that flows into the combustion chamber S from the combustion air inlet holes 21a and 22a is used for the combustion of evaporated fuel.
[0034] When the evaporated fuel discharged from the opening 31a of the evaporator tube 26 toward the end liner 23 burns, combustion gas is generated toward the end liner 23. This combustion gas flows radially outward along the end liner 23 in the direction R, and then flows toward the other side in the axial direction X along the inner circumferential surface of the outer liner 21.
[0035] The evaporator tube 26 may include, for example, at least one cooling air passage 32 positioned between the outer circumferential surface 26a and the inner circumferential surface 26b of the evaporator tube 26. The cooling air passage 32 communicates with an air passage 51 located outside the outer liner 21. The outer liner 21 includes, for example, a plurality of cooling air inlet holes 21c. The plurality of cooling air inlet holes 21c may be arranged along the opening 21b of the outer liner 21. The cooling air passage 32 of the evaporator tube 26 communicates with the cooling air inlet holes 21c of the outer liner 21. The outer liner 21 may not have cooling air inlet holes 21c, and the inlet of the cooling air passage 32 may be formed to communicate with the opening 21b of the outer liner 21.
[0036] The cooling air passage 32 is arranged along the outer circumferential surface 26a of the evaporator tube 26 and extends from the cooling air inlet hole 21c of the outer liner 21 in the direction Y of the flow path axis of the evaporator tube 26. The evaporator tube 26 includes a plurality of cooling air outlets 32a located inside its radial direction R. The cooling air outlets 32a open the ends of the cooling air passage 32 inside the radial direction R to the combustion chamber S.
[0037] Air supplied from the high-pressure compressor 14 via the diffuser 8 flows into the cooling air passage 32 of the evaporator tube 26 through the cooling air inlet 21c of the outer liner 21. This cools the evaporator tube 26 and prevents it from burning out. The air that has cooled the evaporator tube 26 is discharged into the combustion chamber S from the cooling air outlet 32a. This discharged air is effectively used for the combustion of unburned fuel in the combustion chamber S.
[0038] The cooling air passage 32 is located distal to the end liner 23 in the evaporator tube 26. That is, the cooling air passage 32 is located on the other side of the axial direction X relative to the internal passage 31. The cooling air passage 32 is not located proximal to the end liner 23 in the evaporator tube 26.
[0039] As described above, according to this embodiment, the tip 26c of the evaporator tube 26 can be stably supported by a specific liner. Therefore, vibration of the evaporator tube 26 is suppressed in the combustion chamber S, which is the internal space of the combustor 5, and the evaporator tube 26 can be stably positioned. Thus, the fuel can be stably burned inside the combustor 5. As a result, the combustor 5 can be driven stably.
[0040] Furthermore, if the specific liner includes an inner liner 22, the tip 26c of the evaporator tube 26 can be stably supported by the inner liner 22. Also, for example, since it is not necessary to provide a support structure for the tip 26c of the evaporator tube 26 on the outer liner 21, the design flexibility of the outer liner 21 can be improved.
[0041] Furthermore, the evaporator tube 26 of this embodiment includes, as an example, an expanded tube section 26d in which the flow path cross-sectional area expands from the opening 21b of the outer liner 21 toward the tip 26c. Therefore, a region in the evaporator tube 26 in which the flow path cross-sectional area increases from the opening 21b of the outer liner 21 toward the tip 26c of the evaporator tube 26 can be arranged. This allows, for example, the outer surface of the expanded tube section 26d to be enlarged, and the evaporator tube 26 to be stably supported by a specific liner on that outer surface. In addition, by diffusing the evaporated fuel in the internal flow path 31 and supplying an abundant amount of fuel to a predetermined area of the combustion chamber S, ignition performance can be improved.
[0042] Furthermore, the tip portion 26c of the evaporator tube 26 in this embodiment includes an open end 26e having a periphery of an opening 31a that widens towards the end liner 23 in the circumferential direction of the inner liner 22. With this configuration, the tip portion 26c of the evaporator tube 26 can be stably supported by, for example, the outer liner 21 or the inner liner 22 using the periphery of the widening opening 31a. In addition, by using the open end 26e having the periphery of the widening opening 31a, the evaporated fuel flowing through the internal passage 31 can be widely diffused towards the tip portion 26c of the evaporator tube 26, thereby improving ignition performance.
[0043] As another example, the tip 26c of the evaporator tube 26 includes an open end 26e whose periphery of the opening 31a is inclined such that it slopes downwards towards the end liner 23, getting closer to the inner liner 22. This allows fuel to be supplied to a relatively wide area of the combustion chamber S through the open end 26e of the evaporator tube 26, thereby improving ignition performance.
[0044] Furthermore, in the combustor 5 of this embodiment, at least the outer liner 21, inner liner 22, end liner 23, and evaporator tube 26 are integrally continuous with each other. With this configuration, at least the outer liner 21, inner liner 22, end liner 23, and evaporator tube 26 can be integrally constructed, thereby strengthening the connection between these components, improving the strength of the combustor 5, and allowing the tip portion 26c of the evaporator tube 26 to be supported more stably by a specific liner.
[0045] (Second Embodiment) The second embodiment will now be described, focusing on the differences from the first embodiment. Figure 4 is a partial cross-sectional view of the combustor 105 according to the second embodiment. Figure 4 partially shows a cross-section of the combustor 105 viewed from the radial direction R. The specific liner of the combustor 105 includes an end liner 23. In other words, the tip 26c of the evaporator tube 26 in this embodiment is connected to the end liner 23. The tip 26c of the evaporator tube 26 is supported by the end liner 23 by being connected to the end liner 23 via at least one support member 27 extending in the axial direction X. Since the support member 27 does not completely partition the combustion chamber S in either the circumferential direction C or the radial direction R, the flow of air and combustion gas in the combustion chamber S in this embodiment is maintained substantially the same as the flow of air and combustion gas in the combustion chamber S in the first embodiment.
[0046] Furthermore, in the example shown in Figure 4, the inner liner 22 is not included in the specific liner, but the inner liner 22 may be included in the specific liner. That is, the tip 26c of the evaporator tube 26 may be connected to the inner liner 22 and the end liner 23. The tip 26c of the evaporator tube 26 only needs to be connected to at least one of the outer liner 21, the inner liner 22, and the end liner 23.
[0047] 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. Furthermore, it is 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.
[0048] [Pattern] The embodiments described above are specific examples of the following embodiments. [Aspect 1] A reverse-flow combustor for a gas turbine having a rotating shaft with an axis extending in the axial direction, An outer liner having an annular shape extending around the aforementioned axis and including an opening into which a fuel injector is inserted, An inner liner having an annular shape extending around the aforementioned axis and facing the outer liner from the radially inward side of the axis, An end liner is positioned on one side in the axial direction relative to the outer liner and the inner liner, connecting the outer liner to the inner liner and having a ring shape. The combustion chamber defined by the outer liner, the inner liner, and the end liner, The combustion chamber is connected to the outer liner and includes an evaporator tube that has an internal passage communicating with the opening of the outer liner and evaporates fuel in the internal passage, A combustor for a gas turbine, wherein the tip of the evaporator tube located on the opposite side of the opening of the outer liner of the internal flow path is connected to a specific liner which is at least one of the outer liner, the inner liner, and the end liner.
[0049] With the above configuration, the tip of the evaporator tube can be stably supported by a specific liner. Therefore, vibrations of the evaporator tube are suppressed within the combustion chamber, which is the internal space of the combustor, and the evaporator tube can be stably positioned. Consequently, the fuel can be stably burned within the combustor. As a result, the combustor can be driven stably.
[0050] [Aspect 2] The combustion device according to embodiment 1, wherein the specified liner includes the inner liner.
[0051] With the above configuration, the tip of the evaporator tube can be stably supported by the inner liner. Furthermore, since it is not necessary to provide a support structure for the tip of the evaporator tube on the outer liner, the design flexibility of the outer liner can be improved.
[0052] [Aspect 3] The combustor according to embodiment 1 or 2, wherein the evaporator tube includes an enlarged tube portion in which the flow path cross-sectional area of the outer liner expands from the opening to the tip.
[0053] According to the above configuration, by using an expanded section of the evaporator tube, a region can be arranged in the evaporator tube in which the flow path cross-sectional area increases from the opening of the outer liner to the tip. This allows, for example, the outer surface of the expanded section to be enlarged, and the evaporator tube to be stably supported by a specific liner on that outer surface. Furthermore, by diffusing the evaporated fuel in the internal flow path and supplying an abundant amount of fuel to a predetermined area of the combustion chamber, ignition performance can be improved.
[0054] [Aspect 4] The combustor according to any one of embodiments 1 to 3, wherein the tip of the evaporator tube has an open end having an open periphery that widens towards the end liner in the circumferential direction of the inner liner.
[0055] With the above configuration, the tip of the evaporator tube can be stably supported by, for example, an outer liner or an inner liner using the flared opening periphery. Furthermore, by using an open end with the flared opening periphery, the evaporated fuel flowing through the internal passage can be diffused more widely towards the tip of the evaporator tube, thereby improving ignition performance.
[0056] [Aspect 5] The combustor according to any one of embodiments 1 to 4, wherein the tip of the evaporator tube includes an open end whose opening edge is inclined such that it slopes downward towards the inner liner as it approaches the end liner.
[0057] With the above configuration, fuel can be supplied to a relatively wide area of the combustion chamber through the open end of the evaporator tube, whose opening edge is inclined to create a downward slope, thereby improving ignition performance.
[0058] [Aspect 6] A combustor according to any one of embodiments 1 to 5, wherein at least the outer liner, the inner liner, the end liner, and the evaporator tube are integrally continuous with respect to each other.
[0059] According to the above configuration, at least the outer liner, inner liner, end liner, and evaporator tube can be integrally constructed, thereby strengthening the connections between these components, improving the strength of the combustor, and allowing the tip of the evaporator tube to be supported more stably by a specific liner.
[0060] [Aspect 7] A reverse-flow combustor for a gas turbine having a rotating shaft with an axis extending in the axial direction, An outer liner having an annular shape extending around the aforementioned axis and including an opening into which a fuel injector is inserted, An inner liner having an annular shape extending around the aforementioned axis and facing the outer liner from the radially inward side of the axis, An end liner is positioned on one side in the axial direction relative to the outer liner and the inner liner, connecting the outer liner to the inner liner and having a ring shape. The combustion chamber defined by the outer liner, the inner liner, and the end liner, The combustion chamber is connected to the outer liner and includes an evaporator tube that has an internal passage communicating with the opening of the outer liner and evaporates fuel in the internal passage, The combustor includes an evaporator tube, the evaporator tube having an expanded tube section in which the cross-sectional area of the flow path expands from the opening of the outer liner toward the tip of the evaporator tube located opposite the opening of the outer liner in the internal flow path.
[0061] According to the above configuration, by using an expanded section of the evaporator tube, a region can be arranged in the evaporator tube where the flow path cross-sectional area increases from the opening of the outer liner to the tip. This allows, for example, the outer surface of the expanded section to be enlarged, and the evaporator tube to be stably supported on that outer surface by the outer liner, inner liner, or end liner. Thus, the position of the evaporator tube can be stabilized. Furthermore, by diffusing the evaporated fuel in the internal flow path and supplying an abundant amount of fuel to a predetermined area of the combustion chamber, ignition performance can be improved. [Explanation of Symbols]
[0062] 1 Gas Turbine 2 rotation axes 5, 105 Combustor 10 Fuel Injectors 21 Outer Liner 21b Opening of the outer liner 22 Inner Liner 23 Endliner 26 Evaporator tubes 26c Tip of the evaporator tube 26d Expanded section of the evaporator tube 26h Periphery of the evaporator tube opening 26e Open end of the evaporator tube 31 Internal flow path of the evaporator tube 31a Evaporator tube opening R radial direction S Combustion Chamber X-axis direction
Claims
1. A reverse-flow combustor for a gas turbine having a rotating shaft with an axis extending in the axial direction, An outer liner having an annular shape extending around the aforementioned axis and including an opening into which a fuel injector is inserted, An inner liner having an annular shape extending around the aforementioned axis and facing the outer liner from the radially inward side of the axis, An end liner is positioned on one side in the axial direction relative to the outer liner and the inner liner, connecting the outer liner to the inner liner and having a ring shape. The combustion chamber defined by the outer liner, the inner liner, and the end liner, The combustion chamber is connected to the outer liner and includes an evaporator tube that has an internal passage communicating with the opening of the outer liner and evaporates fuel in the internal passage, A combustor for a gas turbine, wherein the tip of the evaporator tube located on the opposite side of the opening of the outer liner of the internal flow path is connected to a specific liner which is at least one of the outer liner, the inner liner, and the end liner.
2. The combustion apparatus according to claim 1, wherein the specified liner includes the inner liner.
3. The combustor according to claim 1, wherein the evaporator tube includes an enlarged tube portion in which the flow path cross-sectional area of the outer liner expands from the opening to the tip.
4. The combustor according to any one of claims 1 to 3, wherein the tip of the evaporator tube includes an open end having an open periphery that widens towards the end liner in the circumferential direction of the inner liner.
5. The combustor according to any one of claims 1 to 3, wherein the tip of the evaporator tube includes an open end whose opening edge is inclined such that it slopes downward towards the inner liner as it approaches the end liner.
6. The combustor according to any one of claims 1 to 3, wherein at least the outer liner, the inner liner, the end liner, and the evaporator tube are integrally continuous with respect to each other.
7. A reverse-flow combustor for a gas turbine having a rotating shaft with an axis extending in the axial direction, An outer liner having an annular shape extending around the aforementioned axis and including an opening into which a fuel injector is inserted, An inner liner having an annular shape extending around the aforementioned axis and facing the outer liner from the radially inward side of the axis, An end liner is positioned on one side in the axial direction relative to the outer liner and the inner liner, connecting the outer liner to the inner liner and having a ring shape. The combustion chamber defined by the outer liner, the inner liner, and the end liner, The combustion chamber is connected to the outer liner and includes an evaporator tube that has an internal passage communicating with the opening of the outer liner and evaporates fuel in the internal passage, The combustor includes an evaporator tube, the evaporator tube having an expanded tube section in which the cross-sectional area of the flow path expands from the opening of the outer liner toward the tip of the evaporator tube located opposite the opening of the outer liner in the internal flow path.