Combustor panel and gas turbine combustor equipped with same

Abstract

To decrease thermal stress arising in a CMC panel of a gas turbine combustor, resulting from heat of a combustion chamber.SOLUTION: The combustor panel comprises an outer surface facing an inner circumferential surface of a shell with a gap therebetween, and an inner surface defining a combustion chamber extending in the flow direction from upstream to downstream of the combustor. At least a part of a neutral surface disposed between the outer surface and the inner surface is of a planar shape or of a curved surface shape curving along the circumferential direction with a smaller curvature than an imaginary arc concentric to the circumferential surface of the shell.SELECTED DRAWING: Figure 5

Description

[Technical Field]

[0001] The present disclosure relates to a combustor panel made of a ceramic matrix composite material and a gas turbine combustor including the same. [Background technology]

[0002] In gas turbine combustors, there is a demand for components with improved heat resistance temperature in order to achieve high-temperature, high-pressure combustion for improved fuel efficiency. Conventionally, panels that define the combustion chamber of a combustor are made of metal and are cooled by air during gas turbine operation.

[0003] Patent Document 1 discloses a configuration in which combustor panels are made of ceramic matrix composite material (CMC). CMC is lighter than metal. Because CMC has a high heat resistance temperature, it is possible to reduce the amount of cooling air required while achieving high-temperature, high-pressure combustion. Therefore, using CMC panels can improve the fuel efficiency of gas turbines. [Prior art documents] [Patent documents]

[0004] [Patent Document 1] International Publication No. 2018 / 087878 Summary of the Invention [Problem to be solved by the invention]

[0005] CMC panels have a high heat resistance and are used in a position facing the combustion chamber, so high-temperature heat is input from the combustion chamber to their inner peripheral surface. A thermal gradient occurs from the inner peripheral surface to the outer peripheral surface of the CMC panel, and thermal stress is generated in the CMC panel due to the heat from the combustion chamber. Therefore, it is necessary to reduce the thermal stress in the CMC panel.

[0006] Therefore, one aspect of the present disclosure aims to reduce thermal stress generated in a CMC panel of a gas turbine combustor due to heat in the combustion chamber. [Means for solving the problem]

[0007] A combustor panel according to one aspect of the present disclosure is a panel made of a ceramic matrix composite material, which is one of a plurality of panels arranged circumferentially inside a cylindrical shell of a gas turbine combustor, the panel including: an outer surface facing an inner circumferential surface of the shell with a gap therebetween; and an inner surface defining a combustion chamber extending in a flow direction from upstream to downstream of the combustor. At least a portion of a midplane between the outer surface and the inner surface has a planar shape or a curved shape along the circumferential direction with a curvature smaller than an imaginary arc concentric with the circumferential surface of the shell.

[0008] A combustor for a gas turbine according to one aspect of the present disclosure includes a cylindrical shell and a panel made of a ceramic matrix composite material that is circumferentially arranged inside the shell. [Effects of the Invention]

[0009] According to one aspect of the present disclosure, at least a portion of the panel made of ceramic matrix composite material has a flat or nearly flat shape, thereby reducing constraints imposed by the shape of the panel and reducing thermal stresses generated in the panel due to the heat of the combustion chamber. [Brief explanation of the drawings]

[0010] [Figure 1] FIG. 1 is a cross-sectional view of a combustor of a gas turbine according to a first embodiment, viewed from the downstream side in the flow direction. [Figure 2] FIG. 2 is a cross-sectional view of the combustor of FIG. 1 taken along line II-II. [Figure 3] FIG. 3 is a partial cross-sectional view of the combustor of FIG. 2 as seen from the flow direction. [Figure 4] FIG. 4 is a partial cross-sectional view of the combustor of FIG. 3 as viewed in the circumferential direction. [Figure 5] FIG. 5 is a perspective view of the panel of FIG. [Figure 6A]FIG. 6A is a view of the panel of FIG. 5 as seen from the VIA direction (downstream side). [Figure 6B] FIG. 6B is a view of the panel of FIG. 5 as seen from the VIB direction (circumferential direction). [Figure 7] 4 is a diagram showing a modified example of the panel of FIG. 3. [Figure 8] FIG. 8 is a perspective view of a panel of a combustor according to the second embodiment. [Figure 9A] FIG. 9A is a view of the panel of FIG. 8 as seen from the direction IXA (downstream side). [Figure 9B] FIG. 9B is a view of the panel of FIG. 8 as seen from the IXB direction (circumferential direction). [Figure 10A] FIG. 10A is a view corresponding to FIG. 9A, showing a modification of the panel of FIG. 9A. [Figure 10B] FIG. 10B is a view equivalent to FIG. 9B showing the panel of FIG. 10A. [Figure 11] FIG. 11 is a perspective view of a panel of a combustor according to a third embodiment. [Figure 12A] FIG. 12A is a view of the panel of FIG. 11 as seen from the direction XIIA (downstream side). [Figure 12B] FIG. 12B is a view of the panel of FIG. 11 as seen from direction XIIB (circumferential direction). [Figure 13A] FIG. 13A is a view corresponding to FIG. 12A, showing a modification of the panel of FIG. 12A. [Figure 13B] FIG. 13B is a view equivalent to FIG. 12B showing the panel of FIG. 13A. DETAILED DESCRIPTION OF THE INVENTION

[0011] Hereinafter, an embodiment will be described with reference to the drawings. In the following description, a direction perpendicular to an axial line X of the gas turbine 1 will be referred to as a radial direction R, a direction extending around the axial line X will be referred to as a circumferential direction C, and in a flow direction F of the combustion chamber 9, the side of the fuel injection device 10 will be referred to as the upstream side and the side of the exhaust port 9a will be referred to as the downstream side.

[0012] (First embodiment) FIG. 1 is a schematic diagram of a combustor 2 of a gas turbine 1 according to a first embodiment, viewed from the downstream side in the flow direction. The combustor 2 is a combustor of the gas turbine 1 used as an aircraft engine. The combustor 2 mixes compressed air supplied from a compressor with fuel to generate an air-fuel mixture, and combusts the air-fuel mixture to generate high-temperature, high-pressure combustion gas. The generated combustion gas is supplied to a turbine to drive the turbine.

[0013] The combustor 2 is, for example, an annular type combustor formed in an annular shape surrounding the axial line X of the gas turbine 1. However, the combustor 2 may be of a type other than the annular type. The combustor 2 includes a casing 3. The casing 3 has an annular outer casing 4 and an annular inner casing 5 concentrically disposed inside the outer casing 4. The outer casing 4 and the inner casing 5 form an annular internal space. A shell 6, which is a combustion tube, is disposed concentrically with the casing 3 in the annular internal space of the casing 3. The shell 6 has an annular outer shell 7 and an annular inner shell 8 concentrically disposed inside the outer shell 7. The annular space surrounded by the outer shell 7 and the inner shell 8 is used as a combustion chamber 9. The outer shell 7 and the inner shell 8 extend linearly from the upstream side to the downstream side in a cross section viewed from the circumferential direction C.

[0014] A plurality of fuel injectors 10 that inject fuel into the combustion chamber 9 are arranged in an annular pattern along the upstream side of the combustion chamber 9. The plurality of fuel injectors 10 are arranged at equal intervals in the circumferential direction C on an imaginary circle concentric with the shell 6. The shell 6 is provided with an ignition plug 11 that generates a spark to ignite the air-fuel mixture in the combustion chamber 9 when the gas turbine 1 starts.

[0015] Fig. 2 is a cross-sectional view of the combustor 2 taken along line II-II in Fig. 1. In Fig. 2, the spark plug 11 side is the outer side in the radial direction R of the gas turbine 1, the axial line X side is the inner side in the radial direction R of the gas turbine 1, the diffuser 12 side is the upstream side, and the exhaust port 9a side of the combustion chamber 9 is the downstream side. Note that the inside of the shell 6 means the radially inner side of the outer shell 7 and the radially outer side of the inner shell 8.

[0016] As shown in Figure 2, a diffuser 12 is provided in the upstream portion of the casing 3, which takes in compressed air generated by the compressor into the casing 3. The fuel injection device 10 is supported by a stem 13 fixed to the casing 3. A portion of the compressed air taken into the casing 3 is supplied to the fuel injection device 10 for combustion. The remainder of the compressed air taken into the casing 3 cools the outer surface of the shell 6, and a portion of it is supplied into the shell 6 from openings 7b (see Figure 4) formed in the shell 6 as cooling air.

[0017] A substantially cylindrical outer panel group 14 is arranged as a liner on the inside of the cylindrical outer shell 7 in the radial direction R. A substantially cylindrical outer panel group 14 is arranged as a liner on the outside of the cylindrical inner shell 8 in the radial direction R. The outer panel group 14 and the inner panel group 15 define a combustion chamber 9. Gas combusted in the combustion chamber 9 is discharged toward the turbine from an outlet 9a defined by the downstream ends of the outer shell 7 and the inner shell 8.

[0018] Fig. 3 is a partial cross-sectional view of the combustor 2 of Fig. 2 as seen from the flow direction F. Fig. 4 is a partial cross-sectional view of the combustor of Fig. 3 as seen from the circumferential direction. As shown in Fig. 3, the outer panel group 14 is an assembly of a plurality of panels 20 arranged adjacent to one another to form a substantially cylindrical shape. Note that the inner panel group 15 (see Fig. 2) is also an assembly of a plurality of panels arranged adjacent to one another to form a substantially cylindrical shape, but the outer panel group 14 will be described below as a representative example.

[0019] The panels 20 are made of ceramic matrix composite (CMC). The panels 20 are arranged inside the shell 6 in the circumferential direction C. As shown in FIG. 4 , the panels 20 are attached to the outer shell 7 by fasteners 16 with a gap therebetween. The fasteners 16 include, for example, bolts and nuts, but the configuration of the fasteners 16 is not particularly limited. The panels 20 have an outer surface 20a that faces the inner circumferential surface 7a of the outer shell 7 with a gap therebetween, and an inner surface 20b that defines the combustion chamber 9 extending in the flow direction F from upstream to downstream of the combustor 2. The space between the outer shell 7 and the panels 20 is used as a cooling air chamber S.

[0020] FIG. 5 is a perspective view of the panel 20 of FIG. 5. FIG. 6A is a view of the panel 20 of FIG. 5 as seen from the VIA direction (downstream side). FIG. 6B is a view of the panel of FIG. 5 as seen from the VIB direction (circumferential direction). As shown in FIGS. 5, 6A, and 6B, the length L of the panel 20 in the flow direction F is longer than the width W of the panel 20 in the circumferential direction C. For example, the panel 20 may extend from the upstream end to the downstream end of the combustion chamber 9 in the flow direction F. The panel 20 may extend from the upstream end to the downstream end of the inner circumferential surface of the shell 6 in the flow direction F.

[0021] A midplane 20N between the outer surface 20a and the inner surface 20b of the panel 20 has a planar shape. In this embodiment, the panel 20 has a flat plate shape. That is, the outer surface 20a and the inner surface 20b each have a planar shape. However, the panel 20 may have a midplane 20N that has a planar shape and the outer surface 20a and the inner surface 20b that have a non-planar shape.

[0022] The panel 20 has a plurality of mounting holes 20c into which the mounting fixtures 16 are inserted. The panel 20 has a plurality of cooling holes 20d. The plurality of cooling holes 20d are arranged at intervals in the circumferential direction C of the panel 20. Note that there may be only one cooling hole 20d rather than multiple cooling holes. The plurality of cooling holes 20d may be arranged in the flow direction F, or may be arranged in both the circumferential direction C and the flow direction F. The cooling hole 20d is arranged between the upstream mounting hole 20c and the downstream mounting hole 20c in the flow direction F. The panel 20 has a notch 20e at an end in the circumferential direction C. The notches 20e of a pair of adjacent panels 20 match with each other to form a cooling hole.

[0023] Returning to FIG. 4, the outer shell 7 has an opening 7b. A portion of the compressed air in the casing 3 (see FIG. 2) is supplied from the opening 7b to the cooling air chamber S as cooling air. The pressure in the cooling air chamber S becomes higher than the pressure in the combustion chamber 9. Therefore, the cooling air in the cooling air chamber S flows out from the cooling holes 20d in the panel 20 into the combustion chamber 9. The cooling air flowing out from the cooling holes 20d covers the inner surface 20b of the panel 20 and reduces the temperature rise of the inner surface 20b of the panel 20 due to the combustion gas in the combustion chamber 9.

[0024] FIG. 7 is a diagram showing a modification of the panel 20 of FIG. 3. As shown in FIG. 7, the midplane 120N of the modified panel 120 may not be completely flat, but may have a shape close to a flat shape. For example, when viewed from the flow direction F, imagine an imaginary arc V that passes through both ends of the midplane 120N of the panel 120 in the circumferential direction C and is concentric with the inner circumferential surface 7a of the outer shell 7. The midplane 120N of the panel 120 may have a curved shape along the circumferential direction C with a curvature smaller than that of the imaginary arc V. In other words, the panel 120 may have a curved shape in which the radius of curvature R1 of the midplane 120N is smaller than the radius of curvature R2 of the imaginary arc V.

[0025] According to the configuration described above, the panel 20 made of ceramic matrix composite material has a flat plate shape or a shape close to a plane, which reduces constraints due to the shape of the panel 20 and makes it possible to reduce stress on the panel 20 caused by the heat of the combustion chamber 9. Because the entire neutral plane 20N of the panel 20 has a planar shape, stress on the panel 20 can be reduced by using a simple shape. Because the length L of the panel 20 in the flow direction F is longer than the width W of the panel 20 in the circumferential direction C, the shape of the panel 20 can be simplified, improving manufacturability while preventing the number of panels 20 from becoming too large.

[0026] (Second embodiment) FIG. 8 is a perspective view of a panel 220 of a combustor according to the second embodiment. FIG. 9A is a view of the panel 220 of FIG. 7 as seen from the IXA direction (downstream side). FIG. 9B is a view of the panel 220 of FIG. 7 as seen from the IXB direction (circumferential direction). Note that components common to the first embodiment are denoted by the same reference numerals, and descriptions thereof will be omitted. As shown in FIGS. 7, 8A, and 8B, the panel 220 includes a plurality of sections 221 and 222 arranged in the flow direction F. Specifically, the panel 220 includes a first section 221 and a second section 222. The panel 220 is integrally molded from a ceramic matrix composite material. The length of the panel 220 in the flow direction F is longer than the width of the panel 220 in the circumferential direction C. For example, the panel 220 may extend from the upstream end to the downstream end of the combustion chamber 9 in the flow direction F.

[0027] The first section 221 is adjacent to the downstream side of the second section 222. The first section 221 is continuous with the second section 222. A neutral plane 221N between the outer surface 221a and the inner surface 221b of the first section 221 has an arc-shaped curved surface shape along the circumferential direction C. In this embodiment, the first section 221 has a bow plate shape.

[0028] A neutral surface 222N between the outer surface 222a and the inner surface 222b of the second section 222 has a planar shape. In this embodiment, the second section 222 has a flat plate shape. That is, the outer surface 222a and the inner surface 222b of the second section 222 each have a planar shape. Note that the second section 222 may have a neutral surface 222N that has a planar shape and the outer surface 222a and the inner surface 222b that have a non-planar shape.

[0029] The second section 222 may have a curved surface shape along the circumferential direction C with a curvature smaller than the average curvature of the neutral plane 221N of the first section 221. The thickness of the second section 222 is the same as, but may be different from, the thickness of the first section 221. The thicknesses of the first section 221 and the second section 222 are constant, but may be varied.

[0030] The curvature of the midplane 221N of the first section 221 decreases as it approaches the second section 222 in the flow direction F. Conversely, the curvature of the midplane 221N of the first section 221 increases as it moves away from the second section 222 in the flow direction F. The rate of change of the curvature of the first section 221 is constant along the flow direction F, but may be varied.

[0031] 9A, the first section 221 is disposed such that, when viewed from the flow direction F, the circumferential center portion of the first section 221 protrudes outward in the radial direction R relative to the second section 222. The amount by which the first section 221 protrudes outward in the radial direction R relative to the second section 222 increases with increasing distance from the second section 222.

[0032] The total area of ​​the flat plate-shaped parts of the panel 220 is larger than the total area of ​​the arched plate-shaped parts of the panel 220. The length in the flow direction F of the total flat plate-shaped parts of the panel 220 is longer than the length in the flow direction F of the total arched plate-shaped parts of the panel 220. In this embodiment, the second section 222 is larger than the first section 221. The length in the flow direction F of the second section 222 is longer than the length in the flow direction F of the first section 221.

[0033] According to the above configuration, a simple combination of shapes can achieve both curved surface and stress reduction in the panel 220. Furthermore, the curvature of the neutral surface 221N of the first section 221 decreases as it approaches the second section 222 in the flow direction F, which prevents the panel 220 from becoming distorted, contributing to stress reduction in the panel 220. Note that other configurations are the same as those in the first embodiment described above, and therefore a description thereof will be omitted.

[0034] FIG. 10A is a view corresponding to FIG. 9A, illustrating a modified example of the panel 220 of FIG. 9A. FIG. 10B is a view corresponding to FIG. 9B, illustrating the panel 220 of FIG. 10A. As shown in FIGS. 10A and 10B, the first section 221 may be disposed such that both circumferential ends of the first section 221 protrude inward in the radial direction R relative to the second section 222, as viewed from the flow direction F. The amount of inward protrusion of the first section 221 in the radial direction R relative to the second section 222 increases with increasing distance from the second section 222. This configuration makes it easier to form a uniform gap between the panel 220 and the shell 6 (see FIG. 2).

[0035] (Third embodiment) FIG. 11 is a perspective view of a panel 320 of a combustor according to the third embodiment. FIG. 12A is a view of the panel of FIG. 11 as seen from the XIIA direction (downstream side). FIG. 12B is a view of the panel of FIG. 11 as seen from the XIIB direction (circumferential direction). Note that components common to the first embodiment are denoted by the same reference numerals, and description thereof will be omitted. As shown in FIGS. 11, 12A, and 12B, the panel 320 includes a plurality of sections 321 to 323 arranged in the flow direction F. Specifically, the panel 320 includes a first section 321, a second section 322, and a third section 323. The panel 320 is integrally molded from a ceramic matrix composite material. The length of the panel 320 in the flow direction F is longer than the width of the panel 320 in the circumferential direction C. For example, the panel 320 may extend from the upstream end to the downstream end of the combustion chamber 9 in the flow direction F.

[0036] The first section 321 is adjacent to the downstream side of the second section 322. The third section 323 is adjacent to the upstream side of the second section 322. The first section 321 and the third section 323 are continuous with the second section 322. The neutral surfaces 321N, 323N of the first section 321 and the third section 323 have arc-shaped curved surfaces along the circumferential direction C. In this embodiment, the first section 321 and the third section 323 have a bow plate shape.

[0037] The neutral surface 322N between the outer surface 322a and the inner surface 322b of the second section 322 has a planar shape. In this embodiment, the second section 322 has a flat plate shape. Note that the neutral surface 322N of the second section 322 may have a planar shape, and the outer surface 322a and the inner surface 322b may have non-planar shapes. The second section 322 may also have a curved shape along the circumferential direction C with a curvature smaller than the average curvature of the neutral surface 321N of the first section 321. The thicknesses of the first section 321 and the third section 323 are the same as the thickness of the second section 322, but may be different. The thicknesses of the first to third sections 321 to 323 are constant, but may be varied.

[0038] The midplane 321N between the outer surface 321a and the inner surface 321b of the first section 321 and the midplane 323N between the outer surface 323a and the inner surface 323b of the third section 323 may have shapes symmetrical to each other with respect to the second section 322. The length of the first section 321 in the flow direction F may be the same as or different from the length of the third section 323 in the flow direction F. The curvatures of the midplanes 321N, 323N of the first section 321 and the third section 323 decrease in the flow direction F as they approach the second section 322. The rate of change of the curvature of the first section 321 and the third section 323 is constant along the flow direction F, but may be varied.

[0039] 12A , the first section 321 and the third section 323 may be arranged such that, when viewed from the flow direction F, circumferential central portions of the first section 321 and the third section 323 protrude outward in the radial direction R relative to the second section 322. Alternatively, the first section 321 and the third section 323 may be arranged such that, when viewed from the flow direction F, both circumferential end portions of the first section 321 and the third section 323 protrude inward in the radial direction R relative to the second section 322.

[0040] The total area of ​​the flat plate-shaped parts of panel 320 is smaller than the total area of ​​the arched plate-shaped parts of panel 320. The length in the flow direction F of the total flat plate-shaped parts of panel 220 is shorter than the length in the flow direction F of the total arched plate-shaped parts of panel 220. In this embodiment, second section 322 is larger than the sum of the lengths in the flow direction F of first section 321 and third section 323. The length in the flow direction F of second section 322 is longer than the total length in the flow direction F of first section 321 and third section 323.

[0041] According to the above configuration, a simple combination of shapes can achieve both curved surface and stress reduction in the panel 320. Furthermore, the curvatures of the neutral surfaces 321N, 323N of the first section 321 and the third section 323 decrease as they approach the second section 322 in the flow direction F, which prevents the panel 320 from becoming distorted, contributing to stress reduction in the panel 320. Note that other configurations are the same as those in the first embodiment described above, and therefore a description thereof will be omitted.

[0042] FIG. 13A is a view corresponding to FIG. 12A, illustrating a modification of the panel 320 of FIG. 12A. FIG. 13B is a view corresponding to FIG. 12B, illustrating the panel 320 of FIG. 13A. As shown in FIGS. 13A and 13B, the first section 321 may be disposed such that both circumferential ends of the first section 321 protrude inward in the radial direction R relative to the second section 322, as viewed from the flow direction F. Similarly, the third section 323 may be disposed such that both circumferential ends of the first section 323 protrude inward in the radial direction R relative to the second section 322, as viewed from the flow direction F. The amount of inward protrusion of the first section 321 and the third section 323 in the radial direction R relative to the second section 322 increases with increasing distance from the second section 322. This configuration facilitates the formation of a uniform gap between the panel 320 and the shell 6 (see FIG. 2).

[0043] As described above, the above-described embodiments have been described as examples of the technology disclosed in this application. However, the technology of the present disclosure is not limited to these embodiments and can be applied to embodiments in which modifications, substitutions, additions, omissions, etc. are made as appropriate. Furthermore, the components described in the above-described embodiments can be combined to create new embodiments. For example, some configurations or methods in one embodiment may be applied to other embodiments, and some configurations in one embodiment may be separated from other configurations in that embodiment and extracted as desired. Furthermore, the components described in the accompanying drawings and detailed description include not only components essential for solving the problem, but also components that are not essential for solving the problem, and are used to illustrate the technology. [Explanation of symbols]

[0044] 1. Gas turbine 2. Combustor 6 shells 7 Outer Shell 8 Inner shell 9 Combustion chamber 14 Outer panels 15 Inner panels 16 Mounting fixture 20,120,220,320 panels 20a,221a,222a,321a,322a,323a External surface 20b, 221b, 222b, 321b, 322b, 323b inner surface 20d cooling hole 20N, 120N, 221N, 222N, 321N, 322N, 323N neutral plane 221,321 Section 1 222,322 Section 2 323 Section 3 C circumferential direction F Flow direction R Radial direction S Cooling air chamber X-axis center line

Claims

1. A ceramic matrix composite panel, which is one of a plurality of panels arranged circumferentially inside a cylindrical shell disposed in an annular interior space formed in a casing of a combustor of a gas turbine, an outer surface facing the inner circumferential surface of the shell with a gap therebetween; an inner surface defining a combustion chamber extending in a flow direction from upstream to downstream of the combustor; a plurality of sections aligned in the flow direction, the plurality of sections including a first section and a second section; a midplane between the outer surface and the inner surface of the first section has a curved shape along the circumferential direction with a curvature smaller than an imaginary arc concentric with the circumferential surface of the shell, The neutral surface of the second section is have a planar shape, or The first section has a curved surface shape along the circumferential direction with a curvature smaller than the average curvature of the neutral surface, the virtual arc is an arc whose radius is the distance between an end of the midplane of the panel in the circumferential direction and a turbine shaft center of the gas turbine, The combustor panel, wherein the first section and the second section both extend in a flow direction.

2. The combustor panel of claim 1 , wherein the first section has a bow shape and the second section has a flat plate shape.

3. the plurality of sections further includes a third section; The plurality of sections are adjacent to one another along the flow direction in the order of the first section, the second section, and the third section, the first section and the third section have a bow shape; the second section has a flat plate shape; The combustor panel of claim 1 or 2, wherein the third section extends in a flow direction.

4. the first section is adjacent to the second section in the flow direction and is continuous with the second section; The combustor panel of claim 1 , wherein the curvature of the midplane of the first section decreases as the midplane approaches the second section in the flow direction.

5. The combustor panel according to claim 1 , wherein the second section is disposed upstream of the first section in the flow direction.

6. The combustor panel according to claim 1 , wherein a length of the panel in the flow direction is longer than a width of the panel in the circumferential direction.

7. A cylindrical shell; a plurality of panels made of ceramic matrix composite material arranged circumferentially inside the shell, at least one of the plurality of panels being the panel according to any one of claims 1 to 6.

8. The gas turbine combustion chamber of claim 7 , wherein the plurality of panels extend from an upstream end to a downstream end of the combustion chamber in the flow direction.

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