Gas turbine combustor

Abstract

A gas turbine combustor according to an aspect of the present disclosure comprises: an outer wall surrounding a combustion chamber; a liner located inside the outer wall and facing the combustion chamber; and a fixture for attaching the liner to the outer wall with a gap between the outer wall and the liner. The fixture includes: a shaft that penetrates through the outer wall; a head that supports the liner; and a head groove that is located on the outer peripheral surface of the head and has one end connected to the gap and the other end connected to the combustion chamber.

Description

[Technical field]

[0001] The present disclosure relates to combustors for gas turbines. [Background technology]

[0002] In recent years, the combustion temperature in gas turbines has been increasing in order to improve fuel efficiency. To meet this demand, combustors have been devised that have liners attached to the inside of the outer wall (shell) that surrounds the combustion chamber. As a fixture for attaching the liner, a fixture has been proposed that has a head that supports the liner and has a cooling air flow path formed inside the head (see Patent Document 1). [Prior art documents] [Patent documents]

[0003] [Patent Document 1] US Patent Application Publication No. 2003 / 0123953 Summary of the Invention [Problem to be solved by the invention]

[0004] As described above, a fitting for attaching a liner has been proposed that has an air passage for cooling. However, the fitting is not heated evenly throughout, and the head exposed to the combustion chamber is particularly prone to becoming hot. Therefore, the present disclosure has an object to provide a combustor for a gas turbine that uses a fitting for attaching a liner to an outer wall, and that suppresses the temperature rise of the head in particular. [Means for solving the problem]

[0005] A combustor of a gas turbine according to one aspect of the present disclosure comprises an outer wall surrounding a combustion chamber, a liner located inside the outer wall and facing the combustion chamber, and a mounting fixture for attaching the liner to the outer wall with a gap between the outer wall and the liner, the mounting fixture including a shaft portion penetrating the outer wall, a head supporting the liner, and a head groove located on an outer circumferential surface of the head, one end of which connects to the gap and the other end of which connects to the combustion chamber. Effect of the Invention

[0006] According to the above configuration, it is possible to provide a combustor for a gas turbine that can suppress an increase in temperature of the fitting for attaching the liner to the outer wall, particularly the head. [Brief description of the drawings]

[0007] [Figure 1] FIG. 1 is a cross-sectional view of a combustor according to a first embodiment. [Diagram 2] FIG. 2 is an enlarged view of the vicinity of the mounting fixture shown in FIG. [Diagram 3] FIG. 3 is a cross-sectional view of the fixture shown in FIG. [Figure 4] FIG. 4 is an enlarged view of the vicinity of the mounting fixture in a modified example of the first embodiment. [Diagram 5] FIG. 5 is a cross-sectional view of a mounting fixture for a combustor according to the second embodiment. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0008] (First embodiment) First, a combustor 100 according to the first embodiment will be described. The combustor 100 according to the present embodiment is for a gas turbine and is a so-called annular type. However, the combustor 100 may be of a type other than the annular type, such as a can type. FIG. 1 is a cross-sectional view of the combustor 100 at a certain circumferential position. A central axis (not shown) of the combustor 100 is located at the bottom of the plane of FIG. 1, the left-right direction of the plane of FIG. 1 is the axial direction of the combustor 100, and the up-down direction of the plane of FIG. 1 is the radial direction of the combustor 100 (hereinafter simply referred to as the "radial direction").

[0009] 1, a combustor 100 according to this embodiment includes an outer wall 10, a liner 20, and a mounting fixture 30. These components will be described in order below.

[0010] <Outer wall> The outer wall 10 is a member that surrounds the combustion chamber 11. The outer wall 10 is made of, for example, metal, but may be made of a material other than metal. The combustion chamber 11 in this embodiment is annular, and a portion of the outer wall 10 located radially outward from the combustion chamber 11 is a so-called outer shell 12, and a portion located radially inward from the combustion chamber 11 is a so-called inner shell 13. The outer wall 10 is surrounded by an annular housing 14, and the outer wall 10 and the combustion chamber 11 are located in an internal space 15 of the housing 14.

[0011] A fuel injection unit 16 is provided in the combustion chamber 11, and fuel is injected from the fuel injection unit 16 into the combustion chamber 11. Air is supplied to the internal space 15 of the housing 14, and a portion of the supplied air is supplied to the fuel injection unit 16. Also, as shown by the white arrow in Fig. 1, a remaining portion of the air supplied to the internal space 15 flows between the outer wall 10 and the housing 14.

[0012] <liner> The liner 20 is a member located inside the outer wall 10 and facing the combustion chamber 11. The liner 20 in this embodiment is attached to the outer wall 10. Although the liner 20 in this embodiment is plate-shaped, the shape of the liner 20 is not limited thereto. The material of the liner 20 is also not limited. The material of the liner 20 is a ceramic material, a metal material, or the like. For example, it is a ceramic matrix composite material (CMC). The liner 20 is attached to the outer wall 10 using a mounting fixture 30 described later. The liner 20 may be an assembly of a plurality of panels arranged in the circumferential direction to form a cylindrical shape. The liner 20 may be integrally molded into a cylindrical shape without being divided into a plurality of panels arranged in the circumferential direction.

[0013] FIG. 2 is an enlarged view of the vicinity of the mounting fixture 30. The lower side of the paper in FIG. 2 is the direction toward the combustion chamber 11 (hereinafter referred to as "inward"), and the upper side of the paper is the direction away from the combustion chamber 11 (hereinafter referred to as "outward"). This also applies to FIGS. 3 to 5 described later. As shown in FIG. 2, a gap is formed between the outer wall 10 and the liner 20. For example, the positions of the outer wall 10 and the liner 20 can be determined by inserting a spacer 21 or a spring between the outer wall 10 and the liner 20. Also, the positions of the outer wall 10 and the liner 20 may be determined by, for example, the mounting fixture 30 without using these means.

[0014] The outer wall 10 has an outer wall hole 17, and as shown by the white arrow in Fig. 2, air flows into the gap between the outer wall 10 and the liner 20 through this outer wall hole 17. Note that a part of the air supplied to the fuel injection unit 16 may also flow into the gap between the outer wall 10 and the liner 20. The air that flows in cools the liner 20. Note that the shape of the means (e.g., spacer 21 or spring) for forming a gap between the outer wall 10 and the liner 20 is not limited, but is formed to allow air to pass through.

[0015] <Mounting fixture> The mounting fixture 30 is a member that mounts the liner 20 to the outer wall 10. The mounting fixture 30 is made of, for example, metal, but may be made of a material other than metal. FIG. 3 is a cross-sectional view of the mounting fixture 30. Strictly speaking, FIG. 3 shows not only the cross-section of the mounting fixture 30, but also the vicinity of the mounting fixture 30. As shown in FIGS. 2 and 3, the mounting fixture 30 includes a shaft portion 31, a head 32, an air flow passage 33, an air intake port 39, a shaft groove 35, and a head groove 36. Note that, although the mounting fixture 30 includes the shaft groove 35 in this embodiment, the mounting fixture 30 does not necessarily need to include the shaft groove 35.

[0016] The shaft portion 31 is a portion that penetrates the outer wall 10. The shaft portion 31 has a columnar outer portion 37 located on the outer side of the shaft portion 31, and a columnar inner portion 38 located on the inner side of the shaft portion 31. For example, the outer portion 37 and the inner portion 38 are cylindrical. The boundary between the outer portion 37 and the inner portion 38 can be arbitrarily determined. The inner portion 38 may have a larger outer diameter than the outer portion 37. A fixing member is fastened to the portion of the inner portion 38 that is outward from the outer wall 10. For example, a male thread is formed on the portion of the inner portion 38 that is outward from the outer wall 10, and a nut 41 is fastened to the male thread. Other fastening methods may be used. In addition, a spring 42, a spacer, or the like may be inserted between the nut 41 and the outer wall 10, or nothing may be inserted. The spring 42 in this embodiment is a coil spring, but the type of spring is not limited, and may be, for example, a leaf spring. Spring 42 exerts an outward force on fitting 30 through nut 41 .

[0017] The head 32 is a portion that supports the liner 20. The head 32 is located on the inner side of the shaft portion 31. In this embodiment, the outer diameter of the portion of the head 32 on the combustion chamber 11 side is larger than the outer diameter of the portion on the shaft portion 31 side. The head 32 has a shape including, for example, a truncated cone shape or a truncated pyramid shape. When the spring 42 is attached between the nut 41 and the outer wall 10, the spring 42 applies an outward force to the mounting fixture 30, so that the head 32 is more likely to maintain a state in which it is in close contact with the liner 20. In addition, as shown in FIG. 2, the head 32 is exposed to the combustion chamber 11, and therefore is more likely to become hotter than other portions of the mounting fixture 30.

[0018] The air flow passage 33 is a flow passage through which cooling air passes. As shown in FIG. 3, the air flow passage 33 is located inside the mounting fixture 30 from the shaft portion 31 to the head 32, and extends along the central axis direction of the mounting fixture 30. The air flow passage 33 is also open to the combustion chamber 11. That is, the air flow passage 33 is connected to the combustion chamber 11. The air flow passage 33 of this embodiment includes a shape corresponding to the shape of the head 32. For example, the head 32 and the part of the air flow passage 33 corresponding to the head 32 are both shaped to include a truncated cone shape or a truncated pyramid shape. Compared to the case where the entire air flow passage 33 is cylindrical, this embodiment can reduce the thickness (volume) of the head 32, and heat is less likely to accumulate in the head 32. In addition, the part of the air flow passage 33 corresponding to the head 32 can have a large contact area with the cooling air, and the head 32 is less likely to become hot.

[0019] In addition, the angle α of the outer peripheral surface 49 of the head 32 of the air flow path 33 with respect to the central axis 101 of the mounting fixture 30 may be 30 degrees or more and 45 degrees or less. By making the angle α of the outer peripheral surface 49 of the head 32 with respect to the central axis 101 of the mounting fixture 30 30 degrees or more, the head 32 can reliably support the liner 20. In addition, by making the angle α of the outer peripheral surface 49 of the head 32 with respect to the central axis 101 of the mounting fixture 30 45 degrees or less, the area of ​​the end face 43 (the surface facing the combustion chamber 11) of the head 32 is reduced, and the head 32 can be prevented from becoming too hot. Note that the angle of the inner peripheral surface 40 of the head 32 with respect to the central axis 101 of the mounting fixture 30 may be the same angle as the angle α of the outer peripheral surface 49 of the head 32 with respect to the central axis 101 of the mounting fixture 30, or may be a different angle.

[0020] Furthermore, the inner peripheral surface 40 and the end face 43 (the surface facing the combustion chamber 11) of the head 32 may have a thermal barrier coating (TBC) layer on the surface. The TBC layer may be, for example, a layer including a top coat such as a ceramic coating for a thermal barrier effect, and a bond coat such as an aluminum diffusion coating for oxidation resistance. By having the TBC layer on the surface of the inner peripheral surface 40 and the end face 43 of the head 32, heat is less likely to be transferred from the combustion chamber 11 to the inner peripheral surface 40 and the end face 43 of the head 32, and the head 32 can be prevented from becoming too hot.

[0021] The air intake 39 is an intake port for air into the air flow path 33. The air intake 39 can be the swirl generating section 34 that swirls the air passing through the air flow path 33. A plurality of air intakes 39 are formed on the side surface of the outer section 37 of the shaft section 31. However, the number and positions of the air intakes 39 are not limited. The air intake 39 is a section that takes in air from the outside of the mounting fixture 30 into the air flow path 33. In this embodiment, the taken-in air functions as cooling air that cools the mounting fixture 30.

[0022] When the supply direction of air supplied from air inlet 39 to air flow passage 33 is inclined relative to the radial direction of air flow passage 33, the air taken in from air inlet 39 passes through air flow passage 33 while swirling along the wall surface that forms air flow passage 33, as shown by the dashed arrow in Fig. 3. Note that air inlet 39 extends perpendicular to the central axis direction of mounting fixture 30 (parallel to outer wall 10). Air inlet 39 may be inclined relative to the central axis direction of mounting fixture 30 so that air can easily flow toward combustion chamber 11.

[0023] When the air passes through the air flow passage 33 while swirling, the cooling air stays in the air flow passage 33 for a long time and comes into close contact with the wall surface that forms the air flow passage 33, so that the mounting fixture 30 can be effectively cooled. Also, the air can be sent at an angle that makes it easy for the air to come into contact with the end surface of the head 32 (the surface facing the combustion chamber 11), so that the end surface of the head 32 can be effectively cooled. Note that a spiral groove may be formed in the wall surface that forms the air flow passage 33, and this groove may be used as the swirl generating portion 34.

[0024] The shaft groove 35 is a groove located on the outer circumferential surface 48 of the shaft portion 31. In this embodiment, the mounting tool 30 includes the shaft groove 35, but may not include it. When the mounting tool 30 includes the shaft groove 35, as shown in FIG. 2, the shaft grooves 35 in this embodiment are formed on the outer circumferential surface 48 of the shaft portion 31 at equal intervals in the circumferential direction, and the shaft grooves 35 extend linearly along the central axis direction of the shaft portion 31. However, the shaft grooves 35 do not have to be linear, such as extending spirally, and the number of the shaft grooves is not limited. The inner end (one end) of the shaft groove 35 is connected to the head groove 36 described later. The outer end (the other end) may be located between the outer wall 10 and the liner 20, or may be located outward from the outer wall 10. When the outer end of the shaft groove 35 is located between the outer wall 10 and the liner 20, the shaft groove 35 can be shortened, and the mounting tool 30 can be easily processed. When the outer end of the shaft groove 35 is located outward of the outer wall 10, the contact area between the mounting fixture 30 and the cooling air becomes large, so that the mounting fixture 30 can be cooled effectively.

[0025] The head groove 36 is a groove located on the outer peripheral surface 49 of the head 32. In this embodiment, a plurality of head grooves 36 are formed on the outer peripheral surface 49 of the head 32 in correspondence with the shaft groove 35. The head groove 36 has an outer end (one end) connected to the gap between the outer wall 10 and the liner 20. The inner end (the other end) connected to the combustion chamber 11. The head groove 36 may have an outer end (one end) connected to the shaft groove 35. When the head groove 36 is connected to the shaft groove 35 (i.e., when the mounting fixture 30 includes the shaft groove 35), the contact area between the mounting fixture 30 and the cooling air can be increased, so that the mounting fixture 30 can be effectively cooled. The air that flows into the gap between the outer wall 10 and the liner 20 passes through the head groove 36 or passes through both the shaft groove 35 and the head groove 36, and is released into the combustion chamber 11. At this time, the head 32 is cooled by the air passing through the outer peripheral surface 49.

[0026] When the head groove 36 is formed in the head 32 described above (e.g., in a truncated cone shape), the head groove 36 becomes longer, the contact area between the head 32 and the air becomes larger, and the head 32 can be cooled more effectively. The head groove 36 may be located at different circumferential positions on the outer side and the inner side as viewed from the central axial direction of the head 32. The head groove 36 may also be curved. In this case, the same effect can be obtained.

[0027] When both the air intake port 39 and the head groove 36 are used, the inside, end face, and outside of the head 32 can be cooled simultaneously, so that the head 32 can be cooled effectively. Furthermore, when the direction of the air passing through the air intake port 39 is the same as the direction of the air passing through the head groove 36, the air passing through each of them is less likely to stagnate near the air flow path 33, so that cooling air can be stably sent to the head 32. For example, the air passing through the air intake port 39 and the head groove 36 may each be swirled.

[0028] In the above embodiment, the outer end and the inner end of the head groove 36 are located at different circumferential positions and are curved, but the shape of the head groove 36 is not limited to the above. For example, as shown in Fig. 4, the outer end and the inner end of the head groove 36 may be located at the same circumferential position as viewed from the central axis direction of the head 32, or may be linear. The number of the head grooves is also not limited.

[0029] Second embodiment Next, a combustor 200 according to a second embodiment will be described. Fig. 5 is a cross-sectional view of the combustor 200 according to the second embodiment, and corresponds to Fig. 3 of the first embodiment. The combustor 200 according to this embodiment differs from the combustor 100 according to the first embodiment in the configuration of the air flow path 33 of the mounting fixture 30. Other points are basically the same as those of the combustor 100 according to the first embodiment. Hereinafter, the air flow path 33 of the combustor 200 according to this embodiment will be described.

[0030] As shown in FIG. 5, the air flow path 33 of this embodiment has a double structure and includes an inner flow path 51 and an outer flow path 52.

[0031] The inner flow passage 51 is a flow passage extending along the central axis direction of the mounting fixture 30. Here, the air intake 39 in this embodiment includes an inner air intake 53 connected to the inner flow passage 51, and an outer air intake 54 connected to the outer flow passage 52. A plurality of inner air intakes 53 connected to the inner flow passage 51 are formed on the side surface of the outer part 37 of the shaft part 31, but the number is not limited. When the central axis of each inner air intake 53 is inclined relative to the radial direction of the inner flow passage 51, the air taken in from the inner air intake 53 passes through the inner flow passage 51 while swirling.

[0032] The outer flow passage 52 is a flow passage surrounding all or part of the inner flow passage 51. The inner flow passage 51 and the outer flow passage 52 are separated by a cylindrical internal wall 55. The outer flow passage 52 may be formed corresponding to a part of the inner flow passage 51. A plurality of outer air intakes 54 connected to the outer flow passage 52 are formed on the side surface of the inner part 38 of the shaft part 31, but the number is not limited. When the central axis of the outer air intake 54 is inclined with respect to the radial direction of the outer flow passage 52, the air taken in from the outer air intake 54 passes through the outer flow passage 52 while swirling.

[0033] In the above embodiment, the air flow passage 33 has a double structure. However, the air flow passage 33 may have only the outer flow passage 52.

[0034] In this manner, the outer flow passage 52 of the air flow passage 33 in this embodiment allows the mounting fixture 30 to be cooled by air passing through the outer flow passage 52, so that the entire mounting fixture 30 can be cooled effectively.

[0035] The flow path area of ​​the outer flow path 52 at the end on the combustion chamber 11 side may be smaller than the flow path area of ​​the inner flow path 51 at the end on the combustion chamber 11 side. Also, the flow path area of ​​the outer flow path 52 at the end on the combustion chamber 11 side may be smaller than the flow path area of ​​the air intake 39 (outer air intake 54) of the outer flow path 52. Since the air flow rate is maintained at the end on the combustion chamber 11 side of the outer flow path 52, the air can flow close to the wall surface that forms the air flow path 33 in the portion of the air flow path 33 that corresponds to the head 32. As a result, the head 32 can be effectively cooled.

[0036] In the above-described embodiment, the angle α of the outer circumferential surface 49 of the head 32 of the inner flow passage 51 and the outer circumferential surface 50 of the head 32 of the outer flow passage 52 with respect to the central axis 101 of the mounting fixture 30 may be 30 degrees or more and 45 degrees or less. In addition, the inner circumferential surface 44 and the end face 46 (the faces facing the combustion chamber 11) of the head 32 of the inner flow passage 51, and the inner circumferential surface 45 and the end face 47 (the faces facing the combustion chamber 11) of the head 32 of the outer flow passage 52 may have a thermal barrier coating (TBC) layer on their surfaces.

[0037] (summary) A first item disclosed in this specification is a combustor for a gas turbine, comprising: an outer wall surrounding a combustion chamber; a liner located inside the outer wall and facing the combustion chamber; and a mounting fixture for attaching the liner to the outer wall with a gap between the outer wall and the liner, the mounting fixture including a shaft portion penetrating the outer wall, a head supporting the liner, and a head groove located on the outer peripheral surface of the head, one end of which connects to the gap and the other end of which connects to the combustion chamber.

[0038] According to this configuration, the head can be cooled by the air flowing through the head groove, which makes it possible to prevent the head from becoming too hot.

[0039] A second item disclosed herein is a combustor for a gas turbine according to the first item, wherein the liner includes a ceramic matrix composite material.

[0040] According to this configuration, the heat resistance of the combustor can be improved.

[0041] A third item disclosed in this specification is a combustor of a gas turbine according to the first or second item, wherein the mounting fixture further includes a shaft groove located on an outer circumferential surface of the shaft portion, and one end of the shaft groove is connected to the head groove.

[0042] According to this configuration, cooling air can be circulated not only through the head groove but also through the shaft groove, increasing the contact area of ​​the air, thereby enabling the fixture to be cooled effectively.

[0043] A fourth item disclosed in this specification is a combustor for a gas turbine according to any one of the first to third items, wherein the head includes a truncated cone shape.

[0044] According to this configuration, in a fixture having a head including a truncated cone shape, the head groove becomes longer, and the head can be cooled effectively.

[0045] A fifth item disclosed in this specification is a combustor of a gas turbine according to any one of the first to fourth items, wherein one end and the other end of the head groove are located at different circumferential positions as viewed from a central axial direction of the head.

[0046] According to this configuration, the contact area between the head and the cooling air is increased, so that the head can be cooled effectively.

[0047] A sixth item disclosed in this specification is a combustor for a gas turbine according to any one of the first to fifth items, wherein the head groove is curved.

[0048] According to this configuration, the contact area between the head and the cooling air is increased, so that the head can be cooled effectively.

[0049] A seventh item disclosed in this specification is a combustor of a gas turbine according to any one of the first to sixth items, wherein the mounting fixture includes an air flow passage located inside the mounting fixture and connected to the combustion chamber, and an air intake that takes in air into the air flow passage, and a direction of air passing through the head groove is along the direction of air passing through the air flow passage.

[0050] According to this configuration, the air passing through the head groove and the air flow path is less likely to stagnate near the air flow path, so that cooling air can be stably sent to the head.

[0051] An eighth item disclosed in this specification is a combustor of a gas turbine according to any one of the first to sixth items, wherein the mounting fixture includes an air flow passage located inside the mounting fixture and connected to the combustion chamber, and a swirl generating unit that swirls air passing through the air flow passage, and both of the direction of air passing through the head groove and the direction of air passing through the air flow passage are swirl directions.

[0052] According to this configuration, the air passing through the head groove and the air flow path is less likely to stagnate near the air flow path, so that cooling air can be stably sent to the head. [Explanation of symbols]

[0053] 10 Outer wall 11 Combustion chamber 20 Liner 30 Mounting fixture 31 Shaft 32 Head 33 Air passage 34 Swirling part 35 Shaft groove 36 Head groove 39 Air Intake 51 Inner flow passage 52 Outer channel 100 Combustor 200 Combustor

Claims

1. An outer wall surrounding the combustion chamber; a liner located inside the outer wall and facing the combustion chamber; a fitting for attaching the liner to the outer wall with a gap between the outer wall and the liner; The mounting fixture includes: A shaft portion passing through the outer wall; A head supporting the liner; a plurality of head grooves located on an outer peripheral surface of the head, the grooves having one end connected to the gap and the other end connected to the combustion chamber; a combustor for a gas turbine, the head grooves being arranged at intervals around a central axis of the head, and each of the head grooves guides air taken in through a gap between the outer wall and the liner outward as viewed from the central axis of the head, and releases it into the combustion chamber.

2. The gas turbine combustor of claim 1 , wherein the liner comprises a ceramic matrix composite material.

3. The mounting tool further includes a plurality of shaft grooves located on an outer peripheral surface of the shaft portion, 3. The combustor of a gas turbine according to claim 1, wherein one ends of the plurality of shaft grooves are connected to one of the plurality of head grooves.

4. The combustor of claim 1 or 2, wherein the head includes a frusto-conical shape.

5. 3. The combustor of a gas turbine according to claim 1, wherein one end and another end of each of the plurality of head grooves are located at different circumferential positions as viewed from a central axial direction of the head.

6. The combustor of a gas turbine according to claim 1 or 2, wherein each of the plurality of head grooves is curved.

7. An outer wall surrounding a combustion chamber; a liner located inside the outer wall and facing the combustion chamber; a fitting for attaching the liner to the outer wall with a gap between the outer wall and the liner; The mounting fixture includes: A shaft portion passing through the outer wall; A head supporting the liner; a head groove located on an outer peripheral surface of the head, one end of the head groove being connected to the gap and the other end of the head groove being connected to the combustion chamber; The fitting includes an air flow passage located inside the fitting and connected to the combustion chamber, and an air intake that draws air into the air flow passage, A combustor for a gas turbine, wherein a direction of air passing through the head groove is aligned with a direction of air passing through the air passage.

8. An outer wall surrounding a combustion chamber; a liner located inside the outer wall and facing the combustion chamber; a fitting for attaching the liner to the outer wall with a gap between the outer wall and the liner; The mounting fixture includes: A shaft portion passing through the outer wall; A head supporting the liner; a head groove located on an outer peripheral surface of the head, one end of the head groove being connected to the gap and the other end of the head groove being connected to the combustion chamber; The mounting fixture includes an air flow path located inside the mounting fixture and connected to the combustion chamber, and a swirl generating unit that swirls air passing through the air flow path, A combustor for a gas turbine, wherein a direction of air passing through said head groove and a direction of air passing through said air flow passage are both swirling directions.

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