Gas turbine combustor
The gas turbine combustor design addresses thermal stress issues by allowing the shell and liner to move relative to each other, enhancing liner durability through a fitting system with a shaft, head, and flange configuration, and incorporating spacers and washers for easy attachment.
Patent Information
- Authority / Receiving Office
- JP · JP
- Patent Type
- Applications
- Current Assignee / Owner
- KAWASAKI JUKOGYO KK
- Filing Date
- 2024-12-23
- Publication Date
- 2026-07-03
AI Technical Summary
The temperature difference between the shell and the liner, along with differences in thermal expansion coefficients, leads to thermal stress and reduced durability of the liner in gas turbine combustors.
A gas turbine combustor design that includes a shell and a liner with a fitting system allowing for play in the central axis direction, utilizing a shaft portion, head portion, and flange portion to accommodate thermal expansion differences, with a spacer and washer configuration for easy attachment and stress reduction.
The design improves the durability of the liner by allowing it to move relative to the shell, reducing thermal stress and facilitating easy installation and removal.
Smart Images
Figure 2026111036000001_ABST
Abstract
Description
Technical Field
[0001] The present disclosure relates to a gas turbine combustor.
Background Art
[0002] In recent years, for the purpose of improving fuel efficiency, the combustion temperature in gas turbines has been increasing. Patent Document 1 discloses a combustor in which a liner is disposed inside a shell surrounding a combustion chamber and the liner is fastened to the shell by nuts or screws.
Prior Art Documents
Patent Documents
[0003]
Patent Document 1
Summary of the Invention
Problems to be Solved by the Invention
[0004] During operation of a gas turbine, a temperature difference occurs between the shell and the liner. Also, there is a difference in the coefficient of thermal expansion between the shell material and the liner material. Therefore, during operation of the gas turbine, a difference occurs between the amount of thermal expansion of the shell and the amount of thermal expansion of the liner. Further, a temperature difference occurs between the outer surface and the inner surface of the liner. Accordingly, thermal stress due to displacement restraint by the fasteners is generated, and the life of the liner may be shortened.
[0005] One aspect of the present disclosure aims to enhance the durability of a liner in a gas turbine combustor.
Means for Solving the Problems
[0006] A gas turbine combustor according to one aspect of the present disclosure comprises a shell including a through hole, a liner disposed along the shell and defining a combustion chamber, and including a through hole, and a fitting for attaching the liner to the shell. The fitting includes a shaft portion inserted through the through hole of the shell and the through hole of the liner, a head portion connected to the shaft portion and disposed inside the shell and facing the liner from the combustion chamber, and a flange portion connected to the shaft portion and disposed outside the shell and facing the outer surface of the shell. The head portion and the flange portion are positioned on the shaft portion in the direction of the central axis of the shaft portion. The shell is disposed with play in the direction of the central axis in the space between the liner and the flange portion of the fitting. [Effects of the Invention]
[0007] According to one aspect of this disclosure, the durability of the liner in a gas turbine combustor can be improved. [Brief explanation of the drawing]
[0008] [Figure 1] Figure 1 is a schematic cross-sectional view of a gas turbine according to the first embodiment. [Figure 2] Figure 2 is a rear view of the combustor of the gas turbine shown in Figure 1. [Figure 3] Figure 3 is a cross-sectional view of the combustor shown in Figure 2, taken along line III-III. [Figure 4] Figure 4 is a partial cross-sectional view of the combustor in Figure 3. [Figure 5] Figure 5 is a perspective view of the liner panel and mounting fixtures of the combustor shown in Figure 2. [Figure 6] Figure 6 is a partial cross-sectional view of the combustor according to the second embodiment, corresponding to Figure 4. [Modes for carrying out the invention]
[0009] (First Embodiment) The embodiments will be described below with reference to the drawings. Note that the axis X of the gas turbine 1 is the same as the axis of the combustor 3. The direction in which axis X extends is referred to as the axial direction X. The direction perpendicular to the axis X of the combustor 3 is referred to as the radial direction R of the combustor 3, and the direction around axis X is referred to as the circumferential direction C of the combustor 3. In the compressed air flow direction F of the combustion chamber 16, the side toward the fuel injector 17 is referred to as the upstream side, and the side toward the combustion chamber outlet 16a is referred to as the downstream side.
[0010] Figure 1 is a schematic cross-sectional view of a gas turbine 1 according to the first embodiment. As shown in Figure 1, the gas turbine 1 comprises a compressor 2, a combustor 3, a turbine 4, a rotating shaft 5, a casing 10, and a fan 7. In the gas turbine 1, air introduced into the casing 10 from the outside is compressed by the compressor 2, the compressed air compressed by the compressor 2 is led to the combustor 3, and the energy of the high-temperature, high-pressure combustion gas obtained by burning fuel together with the compressed air in the combustor 3 is extracted as rotational power in the turbine 4.
[0011] The turbine 4 is connected to the compressor 2 via a rotating shaft 5. The axis X of the rotating shaft 5 is the axis of the gas turbine 1. A fan 7 is connected to the front end of the rotating shaft 5. The rotational power generated by the turbine 4 drives the compressor 2 and the fan 7. Various types of gas turbines exist. Turbofan engines primarily use rotational power generated by the turbine to drive the fan and are used as aircraft engines. Figure 1 illustrates a turbofan engine, which is one form of gas turbine, but the forms of gas turbines are not limited to this.
[0012] Figure 2 is a rear view of the combustor 3 of the gas turbine 1 shown in Figure 1. As shown in Figure 2, the combustor 3 is, for example, an annular combustor formed in an annular shape surrounding the axis X of the gas turbine 1. Note that the combustor 3 may be of a type other than an annular shape. In the combustor 3, the casing 10 has a cylindrical outer casing 11 and a cylindrical inner casing 12 arranged concentrically on the inner diameter side of the outer casing 11. The outer casing 11 and the inner casing 12 define an annular internal space.
[0013] A shell 13 is arranged concentrically with the casing 10 in the annular internal space of the casing 10. The shell 13 surrounds an annular combustion chamber 16. The shell 13 is made of, for example, metal. The shell 13 has a cylindrical outer shell 14 and a cylindrical inner shell 15 arranged concentrically on the inner diameter side of the outer shell 14. The inside of the shell 13 means the inside of the outer shell 14 in the radial direction R and the outside of the inner shell 15 in the radial direction R.
[0014] Upstream of the combustion chamber 16, a plurality of fuel injectors 17 are arranged in an annular pattern along the combustion chamber 16 for injecting fuel into the combustion chamber 16. The plurality of fuel injectors 17 are arranged in the circumferential direction C on a virtual circle concentric with the shell 13. The shell 13 is fitted with a spark plug 18 that generates a spark to ignite the fuel mixture in the combustion chamber 16 when the gas turbine 1 is started. Within the annular internal space of the shell 13, a liner 20 is arranged concentrically with the casing 10 and the shell 13.
[0015] The thermal expansion coefficient of the liner 20 is different from that of the shell 13. The liner 20 is made of, for example, a ceramic matrix composite (CMC). The liner 20 has a cylindrical outer liner 21 and a cylindrical inner liner 22 arranged concentrically on the inner diameter side of the outer liner 21. The liner 20 covers the surface of the shell 13 facing the combustion chamber 16. Specifically, the outer liner 21 covers the inner circumferential surface of the outer shell 14. The inner liner 22 covers the outer circumferential surface of the inner shell 15.
[0016] The outer liner 21 may be an assembly of multiple liner panels 31 arranged adjacent to each other in the circumferential direction to form a cylindrical shape. The inner liner 22 may also be an assembly of multiple liner panels 32 arranged adjacent to each other in the circumferential direction to form a cylindrical shape. One or both of the outer liner 21 and the inner liner 22 may be a cylindrical body integrally molded into a cylindrical shape without being divided into multiple liner panels arranged in the circumferential direction. The outer liner 21 and the inner liner 22 may be divided into multiple liner panels arranged in the axial direction X. Individual liner panels are not limited to arc-shaped plates but may be flat plates, and the liner composed of multiple liner panels is not limited to a cylindrical shape but may be a polygonal cylinder.
[0017] Figure 3 is a cross-sectional view of the combustor 3 in Figure 2, taken along line III-III. As shown in Figure 3, a diffuser 8 is provided on the upstream side of the casing 10 to draw compressed air generated by the compressor 2 into the casing 10. The fuel injector 17 is supported by a stem 9 fixed to the casing 10. A portion of the compressed air drawn into the compressed air space S1 within the casing 10 is supplied to the fuel injector 17 for combustion. The remaining compressed air drawn into the compressed air space S1 within the casing 10 cools the shell 13, and a portion of it is supplied as cooling air into the shell 13 through a cooling opening 14b formed in the outer shell 14, which will be described later. A cooling opening is also formed in the inner shell 15.
[0018] The outer liner 21 is arranged along the inner peripheral surface of the outer shell 14 and is spaced apart from the outer shell 14 by a distance inward in the radial direction R. The inner liner 22 is arranged along the outer peripheral surface of the inner shell 15 and is spaced apart from the inner shell 15 by a distance outward in the radial direction R. The outer liner 21 and the inner liner 22 are attached to the shell 13 in a state of being separated from the shell 13 by a plurality of fixtures 40 described later. The outer liner 21 and the inner liner 22 define the combustion chamber 16. The combustion gas in the combustion chamber 16 is discharged from the combustion chamber outlet 16a defined by the ends of the outer liner 21 and the inner liner 22 on the downstream side in the flow direction F of the compressed compressed air in the combustion chamber 16 toward the turbine 4 described above.
[0019] The attachment structure of the outer liner 21 to the outer shell 14 and the attachment structure of the inner liner 22 to the inner shell 15 are similar to each other. Therefore, as a representative of them, the attachment structure of the outer liner 21 to the outer shell 14 will be described below.
[0020] FIG. 4 is a partial cross-sectional view of the combustor 3 in FIG. 3. As shown in FIG. 4, the outer shell 14 has a through hole 14a for attachment and a cooling opening 14b. The liner panel 31 has a through hole 31a for attachment. The through hole 31a of the liner panel 31 is arranged to coincide with the through hole 14a of the outer shell 14 in the radial direction R. The inner peripheral surface of the through hole 31a has a shape corresponding to the fixture 40. For example, the inner peripheral surface of the through hole 31a has a tapered surface that expands toward the combustion chamber 16 in the radial direction R.
[0021] The fixture 40 attaches the liner panel 31 to the outer shell 14. The fixture 40 is, for example, made of metal, but may be formed of a material other than metal. The fixture 40 is an assembly including a support 41, a washer 42, a nut 43, and a spacer 44.
[0022] The support 41 is inserted through the through hole 31a of the liner panel 31 and the through hole 14a of the outer shell 14 from the inside in the radial direction R. The support 41 has a shaft portion 51 and a head portion 52. The support 41 is a one-piece. The shaft portion 51 extends in the radial direction R and is inserted through the through hole 14a of the outer shell 14. The central axis Y of the shaft portion 51 extends in the radial direction R. The direction in which the central axis Y of the shaft portion 51 extends is referred to as the central axis direction Y. Male threads are formed on the outer circumferential surface of the shaft portion 51 in the portion that is radially R outside the outer shell 14.
[0023] The shaft portion 51 includes a first portion 51a positioned in the cooling space S2 between the outer shell 14 and the liner panel 31, and a second portion 51b that protrudes from the first portion 51a into the compressed air space S1 from the outer shell 14 in the central axis direction Y and is thinner than the first portion 51a. The outer circumferential surface of the second portion 51b has male threads. The shaft portion 51 has a step between the first portion 51a and the second portion 51b. The first portion 51a has an end face 51c facing the compressed air space S1 in the central axis direction Y. The end face 51c of the first portion 51a is an annular surface positioned around the second portion 51b.
[0024] The head 52 is connected to the end of the shaft 51 facing the combustion chamber 16 in the central axis direction Y. That is, the head 52 is connected to the end of the first portion 51a of the shaft 51 opposite to the second portion 51b. Since the support 41 is a one-piece, the head 52 is positioned on the shaft 51 in the central axis direction Y. The head 52 is located inside the shell 13. The outer diameter of the head 52 is larger than the outer diameter of the shaft 51. The outer circumferential surface of the head 52 has a tapered surface that widens towards the combustion chamber 16 in the radial direction R. The head 52 is located in the through hole 31a of the liner panel 31.
[0025] The tapered surface of the outer circumferential surface of the head 52 abuts against the tapered surface of the inner circumferential surface of the through hole 31a. That is, the head 52 supports the liner panel 31 from the side where the combustion chamber 16 is located in the central axis direction Y. Alternatively, the head 52 of the support 41 may abut against the surface of the liner panel 31 facing the combustion chamber 16, without providing tapered surfaces on the outer circumferential surface of the head 52 and the inner circumferential surface of the through hole 31a.
[0026] The support 41 has an air passage 53 that connects the compressed air space S1 to the combustion chamber 16. The air passage 53 extends along the central axis Y of the support 41 from the shaft portion 51 to the head portion 52. The end region of the air passage 53 facing the combustion chamber 16 has a frustoconical shape that widens toward the combustion chamber 16. Note that the support 41 does not necessarily have to have an air passage 53.
[0027] The compressed air that flows from the aforementioned compressor 2 into the compressed air space S1 via the diffuser 8 flows as cooling air into the cooling space S2 between the outer shell 14 and the liner panel 31 through the opening 14b of the outer shell 14. If an air passage 53 is provided in the support 41, the compressed air in the compressed air space S1 flows through the air passage 53 as cooling air and is discharged into the combustion chamber 16 along the inner surface of the liner panel 31.
[0028] The washer 42 is positioned in the compressed air space S1 and is inserted through the second portion 51b of the shaft portion 51 of the support 41. The washer 42 abuts against the outer surface of the outer shell 14 facing the compressed air space S1 and also abuts against the end face 51c of the first portion 51a of the shaft portion 51. The washer 42 covers the through hole 14a of the outer shell 14 from the compressed air space S1. Note that the washer 42 may not completely close the through hole 14a of the outer shell 14 but may partially open it.
[0029] The nut 43 is screwed onto the male thread of the second portion 51b of the shaft portion 51 of the support 41. The nut 43 presses the washer 42 toward the end face 51c of the first portion 51a of the shaft portion 51. The washer 42 is positioned between the outer shell 14 and the nut 43.
[0030] The washer 42 and nut 43 are examples of fasteners 60 positioned on the shaft portion 51 of the support 41 in the central axis direction Y. The washer 42 is an example of a flange portion 61 positioned on the outside of the shell 13, facing the outer surface of the shell 13 and positioned on the shaft portion 51 in the central axis direction Y.
[0031] The spacer 44 is interposed between the outer shell 14 and the liner panel 31 and is located in the cooling space S2. The spacer 44 is positioned in the cooling space S2 with play in the direction of the central axis Y. The spacer 44 has, but is not limited to, an annular shape around the central axis Y. The spacer 44 is fitted onto the first portion 51a of the shaft portion 51 of the support 41 with play.
[0032] The spacer 44 has a ring plate portion 44a and a cylindrical portion 44b. The ring plate portion 44a is positioned between the outer shell 14 and the liner panel 31. The outer diameter of the ring plate portion 44a is larger than the inner diameter of the through hole 14a of the outer shell 14 when viewed from the central axis direction Y. There are no springs adjacent to the spacer 44 between the outer shell 14 and the liner panel 31. However, springs may be present between the outer shell 14 and the liner panel 31.
[0033] The cylindrical portion 44b protrudes from the inner circumference of the ring plate portion 44a toward the washer 42 along the central axis direction Y and is inserted into the through hole 14a of the outer shell 14. A gap G1 is formed between the inner circumference of the through hole 14a of the outer shell 14 and the cylindrical portion 44b of the spacer 44 of the mounting fixture 40. That is, the spacer 44 is displaceable relative to the outer shell 14 in a direction perpendicular to the central axis Y.
[0034] The washer 42 is pressed by the nut 43 so as to contact the end face 51c of the first portion 51a of the shaft 51, thereby positioning the washer 42 on the shaft 51 in the direction of the central axis Y. Since the head 52 and the shaft 51 form a one-piece structure, the head 52 is also positioned on the shaft 51 in the direction of the central axis Y. That is, the distance between the washer 42 and the head 52 is constant in the direction of the central axis Y.
[0035] A gap G2 is formed between the ring plate portion 44a of the spacer 44 and the outer shell 14. The spacer 44 is positioned with play in the central axis direction Y within the cooling space S2 between the outer shell 14 and the liner panel 31. The spacer 44 is displaceable relative to the outer shell 14 and the liner panel 31 in the central axis direction Y. A gap G3 is formed between the cylindrical portion 44b of the spacer 44 and the washer 42. The outer shell 14 is positioned with play in the central axis direction Y within the space between the liner panel 31 and the washer 42. The outer shell 14 is displaceable relative to the liner panel 31 and the washer 42 in the central axis direction Y.
[0036] Figure 5 is a perspective view of the liner panel 31 and mounting fixtures 40 of the combustor 3 shown in Figure 2. In Figure 5, the support 41 of the mounting fixture 40 is shown, but the washer 42, nut 43, spacer 44 and outer shell 14 of the mounting fixture 40 are not shown. As shown in Figure 5, the liner panel 31 is supported at three points by three mounting fixtures 40. The liner panel 31 extends along the axial direction X of the combustor 3. Two mounting fixtures 40 are located on one longitudinal side of the liner panel 31, and one mounting fixture 40 is located on the other longitudinal side of the liner panel 31.
[0037] The three mounting brackets 40 are positioned at the vertices of an isosceles triangle. The three mounting brackets 40 are positioned to avoid the center of the liner panel 31. Therefore, the support 41 can change its orientation to tilt relative to the outer shell 14 by utilizing the aforementioned gap G1. Note that the arrangement of the mounting brackets 40 is not limited to this and can be arranged in any way.
[0038] According to the configuration described above, the outer shell 14 is positioned with play in the central axis direction Y in the space between the liner panel 31 and the washer 42 of the mounting fixture 40. Therefore, even if a difference occurs between the thermal expansion of the outer shell 14 and the thermal expansion of the liner panel 31 during the operation of the gas turbine 1, the outer shell 14 and the liner panel 31 can be displaced relative to each other, reducing the stress caused by displacement constraints on the liner panel 31. Thus, the durability of the liner panel 31 in the combustor 3 can be improved.
[0039] Since the flange portion 61 connected to the shaft portion 51 of the support 41 is formed by a washer 42 separate from the support 41, the liner panel 31 can be easily attached and detached by attaching and detaching the nut 43 and washer 42.
[0040] The spacer 44 interposed between the outer shell 14 and the liner panel 31 is positioned with some play in the central axis direction Y within the cooling space S2 between the outer shell 14 and the liner panel 31, so that the washer 42 can stably contact the end face 51c of the first portion 51a of the shaft portion 51.
[0041] Because there is a gap G1 between the inner periphery of the through hole 14a of the outer shell 14 and the shaft portion 51 of the mounting fixture 40, even if a difference occurs between the amount of thermal expansion of the outer shell 14 and the amount of thermal expansion of the liner panel 31 during the operation of the gas turbine 1, the difference in thermal expansion can be absorbed by the gap G1.
[0042] (Second Embodiment) Figure 6 is a partial cross-sectional view of the combustor 103 according to the second embodiment, corresponding to Figure 4. Components common to the first embodiment are denoted by the same reference numerals and their descriptions are omitted. As shown in Figure 6, the mounting fixture 140 of the combustor 103 in the second embodiment is an assembly comprising a support 141, a washer 42, a nut 43, and a spacer 144. In the mounting fixture 140 of the second embodiment, the support 141 and spacer 144 are different from those of the mounting fixture 40 in the first embodiment.
[0043] The support 141 has a shaft portion 151 and a head portion 152. The support 141 is a one-piece. The shaft portion 151 has a constant outer diameter along the central axis direction Y. The shaft portion 151 extends radially R and passes through the through hole 14a of the outer shell 14. Male threads are formed on the outer circumferential surface of the shaft portion 151 on the portion radially R outward from the outer shell 14. The head portion 152 is connected to the end of the shaft portion 151 facing the combustion chamber 16 in the central axis direction Y. The head portion 152 is located inside the shell 13. The outer diameter of the head portion 152 is larger than the outer diameter of the shaft portion 151. The support 141 has an air passage 153 that connects the compressed air space S1 to the combustion chamber 16, but it may not have an air passage 153. The washer 42 and nut 43 are the same as those of the first embodiment.
[0044] The spacer 144 is interposed between the outer shell 14 and the liner panel 31 and is located in the cooling space S2. The spacer 144 has a ring-shaped plate portion 144a and a cylindrical portion 144b. The ring-shaped plate portion 144a is located between the outer shell 14 and the liner panel 31. The outer diameter of the ring-shaped plate portion 144a is larger than the inner diameter of the through-hole 14a of the outer shell 14 when viewed from the direction of the central axis Y. The ring-shaped plate portion 144a may or may not come into contact with the liner panel 31.
[0045] The cylindrical portion 144b protrudes from the inner circumference of the ring plate portion 144a along the central axis direction Y toward the washer 42 and is inserted into the through hole 14a of the outer shell 14. The tip of the cylindrical portion 144b in the central axis direction Y abuts against the washer 42. The spacer 144 and the liner panel 31 are sandwiched between the head 152 of the support 141 and the washer 42. As a result, the washer 42 is positioned on the shaft portion 151 of the support 141 in the central axis direction Y. That is, the distance between the washer 42 and the head 152 of the support 141 is constant in the central axis direction Y.
[0046] A gap G2 is formed between the ring plate portion 144a of the spacer 144 and the outer shell 14. The outer shell 14 is positioned with play in the central axis direction Y in the space between the liner panel 31 and the washer 42. The outer shell 14 is displaceable relative to the liner panel 31 and the washer 42 in the central axis direction Y.
[0047] With the above configuration, the outer shell 14 is positioned with play in the central axis direction Y in the space between the liner panel 31 and the washer 42 of the mounting fixture 140. Therefore, even if a difference occurs between the thermal expansion of the outer shell 14 and the thermal expansion of the liner panel 31 during gas turbine operation, the outer shell 14 and the liner panel 31 can be displaced relative to each other, and the stress caused by displacement constraint that may occur in the liner panel 31 can be reduced.
[0048] Furthermore, since the spacer 144 and the liner panel 31 are sandwiched between the head 152 of the support 141 and the washer 42, the washer 42 is positioned on the shaft portion 151 in the central axis direction Y. This allows the liner panel 31 to be easily attached and detached by attaching and detaching the nut 43 and the washer 42, and also stabilizes the spacer 144 and the liner panel 31 in the assembled state. Note that the other configurations are the same as those of the first embodiment described above, so their description will be omitted.
[0049] It should be noted that the technology of this disclosure is not limited to the embodiments described above. For example, the fastener 60 positioned on the shaft portion 51 of the support 41 in the central axis direction Y may be a C-ring that engages with an annular groove on the outer circumferential surface of the shaft portion 51, instead of a washer 42 and a nut 43. The flange portion 61, which is located outside the shell 13, facing the outer surface of the shell 13 and positioned on the shaft portion 51 in the central axis direction Y, may be a C-ring that engages with an annular groove on the outer circumferential surface of the shaft portion 51, instead of a washer 42 and a nut 43, or it may be integrated with the shaft portion 51. The washer 42 is in direct contact with the outer surface of the outer shell 14, but other parts may be interposed between the washer 42 and the outer shell 14. These modifications are not limited to the first embodiment but can also be applied to the second embodiment.
[0050] 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.
[0051] [Pattern] The embodiments described above are specific examples of the following embodiments.
[0052] (Aspect 1) A shell including a through hole, A liner positioned along the aforementioned shell, defining the combustion chamber and including through holes, The shell comprises a mounting fixture for attaching the liner, The aforementioned mounting fixture is A shaft portion inserted through the through hole of the shell and the through hole of the liner, The shaft portion is connected to the head portion, which is positioned inside the shell and faces the liner from the combustion chamber, It includes a flange portion connected to the shaft portion and positioned outside the shell, facing the outer surface of the shell, The head portion and the flange portion are positioned on the shaft portion in the direction of the central axis of the shaft portion, A gas turbine combustor in which the shell is positioned with play in the central axis direction in the space between the liner and the flange portion of the mounting fixture.
[0053] With this configuration, even if a difference arises between the thermal expansion of the shell and the thermal expansion of the liner during gas turbine operation, the shell and liner can be displaced relative to each other, reducing stress on the liner. Therefore, the durability of the liner in the gas turbine combustor can be improved.
[0054] (Aspect 2) The aforementioned mounting fixture includes a support, washer, and nut. The support is a one-piece having the shaft portion and the head portion, The washer constitutes the flange portion, The outer circumferential surface of the shaft portion has male threads on the outside of the shell, The nut is screwed onto the male thread of the shaft portion. The washer is located between the shell and the nut with the shaft portion inserted through it. The shaft portion has a first portion positioned in the space between the shell and the liner, and a second portion that protrudes from the first portion outward from the shell in the direction of the central axis and is thinner than the first portion. The gas turbine combustor according to embodiment 1, wherein the washer is pressed by the nut so that the washer contacts the end face of the first portion of the shaft, thereby positioning the washer on the shaft in the direction of the central axis.
[0055] With this configuration, the liner can be easily attached and removed by attaching and detaching nuts and washers.
[0056] (Aspect 3) The mounting fixture further includes a spacer interposed between the shell and the liner, The gas turbine combustor according to embodiment 2, wherein the spacer is arranged with play in the central axis direction in the space between the shell and the liner.
[0057] With this configuration, the spacers are positioned with some play in the direction of the central axis, allowing the washers to stably contact the end face of the first portion of the shaft.
[0058] (Aspect 4) The aforementioned mounting fixture includes a support, washer, nut and spacer, The support is a one-piece having the shaft portion and the head portion, The washer constitutes the flange portion, The outer circumferential surface of the shaft portion has male threads on the outside of the shell, The nut is screwed onto the male thread of the shaft portion. The washer is located between the shell and the nut with the shaft portion inserted through it. The spacer is interposed between the shell and the liner, The gas turbine combustor according to embodiment 1, wherein the spacer and the liner are sandwiched between the head and the flange so that the washer is positioned on the shaft in the direction of the central axis.
[0059] This configuration allows for easy installation and removal of the liner by attaching and detaching nuts and washers, and also allows for stability of the spacer and liner in the assembled state.
[0060] (Aspect 5) A gas turbine combustor according to any one of embodiments 1 to 4, wherein there is a gap between the inner periphery of the through hole in the shell and the mounting fixture.
[0061] With this configuration, even if a difference arises between the thermal expansion of the shell and the thermal expansion of the liner during gas turbine operation, the difference in thermal expansion can be absorbed by the gap. [Explanation of Symbols]
[0062] 1 Gas Turbine 3 Combustor 13 Shells 14 Outer Shell 14a Through hole 16 Combustion chamber 20 Liners 21 Outer Liner 31 Liner Panel 31a Support hole 40,140 Mounting hardware 41,141 support 42 washers 43 nuts 44,144 Spacers 44a, 144a Ring plate section 44b,144b Cylinder part 51,151 shaft 51a Part 1 51b Part 2 51c end face 52,152 head 53,153 Airflow channels 60 Fixtures 61 Guard section S1 Compressed air space S2 cooling space X-axis direction Y center axis direction
Claims
1. A shell including a through hole, A liner positioned along the aforementioned shell, defining the combustion chamber and including through holes, The shell comprises a mounting fixture for attaching the liner, The aforementioned mounting fixture is A shaft portion inserted through the through hole of the shell and the through hole of the liner, The shaft portion is connected to the head portion, which is positioned inside the shell and faces the liner from the combustion chamber, It includes a flange portion connected to the shaft portion and positioned outside the shell, facing the outer surface of the shell, The head portion and the flange portion are positioned on the shaft portion in the direction of the central axis of the shaft portion, A gas turbine combustor in which the shell is positioned with play in the central axis direction in the space between the liner and the flange portion of the mounting fixture.
2. The aforementioned mounting fixture includes a support, washer, and nut. The support is a one-piece having the shaft portion and the head portion, The washer constitutes the flange portion, The outer circumferential surface of the shaft portion has male threads on the outside of the shell, The nut is screwed onto the male thread of the shaft portion. The washer is located between the shell and the nut with the shaft portion inserted through it. The shaft portion has a first portion positioned in the space between the shell and the liner, and a second portion that protrudes from the first portion outward from the shell in the direction of the central axis and is thinner than the first portion. The gas turbine combustor according to claim 1, wherein the washer is pressed by the nut so that the washer contacts the end face of the first portion of the shaft, thereby positioning the washer on the shaft in the direction of the central axis.
3. The mounting fixture further includes a spacer interposed between the shell and the liner, The gas turbine combustor according to claim 2, wherein the spacer is arranged with play in the central axis direction in the space between the shell and the liner.
4. The aforementioned mounting fixture includes a support, washer, nut and spacer, The support is a one-piece having the shaft portion and the head portion, The washer constitutes the flange portion, The outer circumferential surface of the shaft portion has male threads on the outside of the shell, The nut is screwed onto the male thread of the shaft portion. The washer is located between the shell and the nut with the shaft portion inserted through it. The spacer is interposed between the shell and the liner, The gas turbine combustor according to claim 1, wherein the spacer and the liner are sandwiched between the head and the flange so that the washer is positioned on the shaft in the direction of the central axis.
5. A gas turbine combustor according to any one of claims 1 to 4, wherein there is a gap between the inner periphery of the through hole of the shell and the mounting fixture.