Gas turbine stationary blade and gas turbine

Abstract

In a gas turbine stator blade, when a plane including a blade height direction and a thickness direction of a leading edge portion at a center of an inlet of a first film cooling hole is defined as a first plane, a center of an outlet of the first film cooling hole is positioned downstream of a position where the first plane intersects an outer surface of the leading edge portion in a flow of combustion gas. When a plane including the thickness direction of the leading edge portion and the blade height direction at the center of the inlet of the second film cooling hole is defined as a second plane, the outlet of the second film cooling hole is located at a position where the second plane intersects the outer surface of the leading edge portion. When a plane including the thickness direction and the blade height direction of the leading edge portion at the center of the inlet of the third film cooling hole is defined as a third plane, the center of the outlet of the third film cooling hole is located downstream of the flow of the combustion gas from the position where the third plane intersects the outer surface of the leading edge portion.

Description

Technical Field

[0001] The present disclosure relates to a gas turbine vane and a gas turbine.

[0002] This application claims priority based on Japanese Patent Application No. 2022-138919 filed with the Japan Patent Office on September 1, 2022, and the contents of which are incorporated herein by reference. Background Art

[0003] The leading edge of a gas turbine stator blade is exposed to the flow of high-temperature combustion gas. Patent Document 1 discloses that, in order to keep the metal temperature of the gas turbine stator blade below the allowable temperature of the blade material, a plurality of film cooling holes are provided at the leading edge of the gas turbine stator blade, and the surface of the gas turbine stator blade (blade surface) is film-cooled by the cooling air flowing out of the plurality of film cooling holes.

[0004] Prior art literature

[0005] Patent Literature

[0006] Patent Document 1: Japanese Patent Application Laid-Open No. 10-220203 Summary of the invention

[0007] Problems to be solved by the invention

[0008] The gas turbine vane described in Patent Document 1 has room for improvement in terms of efficiently performing film cooling on the surface of the gas turbine vane with a smaller amount of cooling air.

[0009] In view of the above circumstances, an object of at least one embodiment of the present disclosure is to provide a gas turbine stator blade and a gas turbine including the same, which can reduce the amount of cooling air and suppress a decrease in film efficiency of film cooling on the blade surface.

[0010] Means for solving problems

[0011] In order to achieve the above-mentioned object, a gas turbine stator blade according to at least one embodiment of the present disclosure includes a blade-shaped portion having a cavity formed therein.

[0012] The leading edge of the blade-shaped portion is formed with:

[0013] A first film cooling hole row, comprising a plurality of first film cooling holes arranged along a height direction of the blade;

[0014] A second film cooling hole array, comprising a plurality of second film cooling holes arranged along a height direction of the blade; and

[0015] A third film cooling hole row, which includes a plurality of third film cooling holes arranged along the height direction of the blade,

[0016] The second film cooling hole row is arranged between the first film cooling hole row and the third film cooling hole row,

[0017] The first film cooling hole extends in a direction inclined with respect to the wall thickness direction of the leading edge portion, and when a plane including the wall thickness direction of the leading edge portion and the blade height direction at the center of the inlet of the first film cooling hole is defined as a first plane, the center of the outlet of the first film cooling hole is located at a position downstream of a flow of the combustion gas along the leading edge portion relative to a position where the first plane intersects with an outer surface of the leading edge portion,

[0018] The second film cooling hole extends in a direction inclined relative to the wall thickness direction of the leading edge portion, and when a plane including the wall thickness direction of the leading edge portion and the blade height direction at the center of the inlet of the second film cooling hole is defined as a second plane, an outlet of the second film cooling hole is located at a position where the second plane intersects an outer surface of the leading edge portion,

[0019] The third film cooling hole extends in a direction inclined relative to the wall thickness direction of the leading edge portion, and when a plane including the wall thickness direction of the leading edge portion and the blade height direction at the center of the inlet of the third film cooling hole is defined as a third plane, the center of the outlet of the third film cooling hole is located on the downstream side of the flow of the combustion gas along the leading edge portion than a position where the third plane intersects with the outer surface of the leading edge portion.

[0020] Effects of the Invention

[0021] According to at least one embodiment of the present disclosure, there are provided a gas turbine stator blade capable of reducing the amount of cooling air and suppressing a decrease in film efficiency of film cooling on a blade surface, and a gas turbine including the same. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 This is a diagram showing a schematic configuration of a gas turbine 2 according to an embodiment of the present disclosure.

[0023] Figure 2 This is a diagram showing an example of a cross section of a turbine vane 12 according to an embodiment of the present disclosure, taken along the blade height direction.

[0024] Figure 3 Yes means Figure 2 FIG. 2 is a diagram showing an example of a cross section of a turbine vane 12 taken orthogonally to the blade height direction.

[0025] Figure 4 Yes Figure 3 An enlarged cross-sectional view of the leading edge portion 21 is shown.

[0026] Figure 5This is a diagram of the outer surface 25 of the leading edge portion 21 of the blade-shaped portion 20 as viewed from a direction perpendicular to the outer surface 25 .

[0027] Figure 6 1 is a diagram showing an example of a cross section along the blade height direction at the position of the first film-cooling hole row R71 in the leading edge portion 21 of the blade shape portion 20 .

[0028] Fig. 7A Yes Figure 6 FIG. 2 is an enlarged cross-sectional view of an outer first film cooling hole 711 serving as the first film cooling hole 71 in the vicinity of the outer shroud 22 .

[0029] Figure 7B Yes Figure 6 FIG. 2 is an enlarged cross-sectional view of an inner first film cooling hole 712 serving as the first film cooling hole 71 in the vicinity of the inner shroud 24 .

[0030] Fig. 8A Yes means Fig. 7A Diagram of the QG-QG cross section in.

[0031] Figure 8B Yes means Figure 7B Figure 2 shows the QH-QH cross section in Fig.

[0032] Fig. 9 1 is a diagram showing an example of a cross section along the blade height direction at the position of the second film-cooling hole row R72 in the leading edge portion 21 of the blade shape portion 20 .

[0033] Fig. 10A Yes Fig. 9 FIG. 2 is an enlarged cross-sectional view of an outer second film cooling hole 721 serving as the second film cooling hole 72 in the vicinity of the outer shroud 22 .

[0034] Fig. 10B Yes Fig. 9 FIG. 2 is an enlarged cross-sectional view of an inner second film-cooling hole 722 serving as the second film-cooling hole 72 in the vicinity of the inner shroud 24 .

[0035] Fig.11A Yes means Fig. 10A Figure 2 shows the QJ-QJ section in Figure 2.

[0036] Fig. 11B Yes means Fig. 10B Diagram of the QK-QK section in.

[0037] Fig.12 1 is a diagram showing an example of a cross section along the blade height direction at the position of the third film-cooling hole row R73 in the leading edge portion 21 of the blade shape portion 20 .

[0038] Fig.13A Yes Fig.12FIG. 2 is an enlarged cross-sectional view of an outer third film cooling hole 731 serving as the third film cooling hole 73 in the vicinity of the outer shroud 22 .

[0039] Fig. 13B Yes Fig.12 FIG. 2 is an enlarged cross-sectional view of an inner third film cooling hole 732 serving as the third film cooling hole 73 in the vicinity of the inner shroud 24 .

[0040] Fig.14A Yes means Fig.13A Figure 2. Diagram of the QL-QL section in FIG.

[0041] Fig. 14B Yes means Fig. 13B Diagram of the QM-QM section in.

[0042] Fig.15 1 is a diagram showing a cross section of the blade-shaped portion 020 according to the first comparative embodiment, which is perpendicular to the blade height direction.

[0043] Fig.16 It is a graph showing the relationship between the distance from the second film cooling hole row R72 of the turbine stator blade 12 of one embodiment and the average film efficiency in the blade span direction, and the relationship between the distance from the third film cooling hole row 07 (the film cooling hole row at a position corresponding to the second film cooling hole row R72) of the turbine stator blade 012 of the first comparison method and the average film efficiency in the blade span direction. DETAILED DESCRIPTION

[0044] Hereinafter, several embodiments of the present disclosure will be described with reference to the drawings. However, the dimensions, materials, shapes, and relative arrangements of the components described as embodiments or shown in the drawings are not intended to limit the scope of the invention and are merely illustrative examples.

[0045] For example, expressions such as "in a certain direction", "along a certain direction", "parallel", "orthogonal", "center", "concentric" or "coaxial" that indicate relative or absolute configurations not only strictly indicate such configurations, but also indicate a state of relative displacement at an angle or distance with a tolerance or a degree that can achieve the same function.

[0046] For example, expressions such as “same”, “equal”, and “homogeneous” indicating a state in which things are equal not only indicate a strictly equal state, but also indicate a state in which there is a tolerance or a difference to the extent that the same function can be obtained.

[0047] For example, expressions indicating shapes such as a quadrilateral and a cylindrical shape not only indicate shapes such as a quadrilateral and a cylindrical shape in a strict geometric sense, but also indicate shapes including concave and convex portions, chamfered portions, and the like within a range that can obtain the same effect.

[0048] On the other hand, expressions such as “including,” “comprising,” “having,” “containing,” or “having” a constituent element are not exclusive expressions excluding the presence of other constituent elements.

[0049] Figure 1 This is a diagram showing a schematic configuration of a gas turbine 2 according to an embodiment.

[0050] like Figure 1 As shown, the gas turbine 2 includes a compressor 4 , a combustor 6 for mixing compressed air generated by the compressor 4 with fuel and burning the mixture, and a turbine 8 for obtaining power from combustion gas generated by the combustor 6 .

[0051] like Figure 1 As shown, the turbine 8 includes a rotor 9 (turbine rotor), a turbine housing 10 accommodating the rotor 9, a plurality of turbine vanes 12 (gas turbine vanes) fixed to the inner surface of the turbine housing 10, and a plurality of turbine blades 16 implanted on the rotor 9 in a manner alternately arranged in the axial direction relative to the turbine vanes 12. Hereinafter, unless otherwise specified, "circumferential direction" means the circumferential direction of the gas turbine 2, i.e., the circumferential direction of the rotor 9, unless otherwise specified, "axial direction" means the axial direction of the gas turbine 2, i.e., the axial direction of the rotor 9, and unless otherwise specified, "radial direction" means the radial direction of the gas turbine 2, i.e., the radial direction of the rotor 9.

[0052] Figure 2 This is a diagram showing an example of a cross section of the turbine vane 12 along the blade height direction.

[0053] like Figure 2 As shown, the turbine vane 12 includes a blade-shaped portion 20, an outer shroud 22, and an inner shroud 24. Hereinafter, "the blade height direction" refers to the blade height direction of the turbine vane 12, that is, the blade height direction of the blade-shaped portion 20, which corresponds to the radial direction of the gas turbine 2, that is, the radial direction of the rotor 9. In addition, "the outer side in the blade height direction" refers to the outer side in the radial direction of the gas turbine 2, that is, the outer side in the radial direction of the rotor 9, and "the inner side in the blade height direction" refers to the inner side in the radial direction of the gas turbine 2, that is, the inner side in the radial direction of the rotor 9.

[0054] The blade-shaped portion 20 has a blade-shaped cross-sectional shape defined by a pressure surface and a negative pressure surface. A blade inner chamber described later is formed inside the blade-shaped portion 20. The blade inner chamber connects an outer chamber 32 formed outside the outer shroud 22 in the blade height direction with an inner chamber 34 formed inside the inner shroud 24 in the blade height direction. The outer chamber 32 is formed between the outer shroud 22 and the turbine housing 10 (see Figure 1 ), and the inner chamber 34 is a space formed between the inner shield 24 and an inner peripheral partition not shown.

[0055] like Figure 2As shown in FIG. 1 , a first film cooling hole row R71, a second film cooling hole row R72 and a third film cooling hole row R73 are formed in the leading edge portion 21 of the blade-shaped portion 20. It should be noted that in this specification, for example, Figure 3 As shown, the “front edge portion” refers to a portion of the blade-shaped portion 20 including the most upstream position E2 of the blade-shaped portion 20 in the axial direction, for example, a portion on the opposite side of the trailing edge TE of the blade-shaped portion 20 across the front edge portion partition wall 48 .

[0056] The first film cooling hole row R71 includes a plurality of first film cooling holes 71 arranged along the blade height direction. The second film cooling hole row R72 includes a plurality of second film cooling holes 72 arranged along the blade height direction. The third film cooling hole row R73 includes a plurality of third film cooling holes 73 arranged along the blade height direction. The second film cooling hole row R72 is arranged between the first film cooling hole row R71 and the third film cooling hole row R73.

[0057] The outer shroud 22 is connected to the outer end 20a of the blade-shaped portion 20 in the blade height direction, and is formed into a substantially plate-like shape along a surface intersecting the blade height direction. The outer shroud 22 forms an outer peripheral wall 33 of a flow path 31 of the combustion gas in the turbine 8 (a flow path of the mainstream of the combustion gas in the turbine 8). It should be noted that in this specification, "the upstream side in the axial direction" refers to the upstream side in the axial direction of the mainstream of the combustion gas of the turbine 8 (the flow of the combustion gas flowing in the flow path 31), and "the downstream side in the axial direction" refers to the downstream side in the axial direction of the mainstream of the combustion gas of the turbine 8.

[0058] The inner shroud 24 is connected to the inner end 20b of the blade-shaped portion 20 in the blade height direction and is formed in a substantially plate-like shape along a surface intersecting the blade height direction. The inner shroud 24 forms an inner peripheral wall 35 of a flow path 31 of the combustion gas in the turbine 8 (a flow path of the main flow of the combustion gas in the turbine 8).

[0059] Figure 3 Yes means Figure 2 1 is a diagram showing an example of a cross section perpendicular to the blade height direction of the turbine vane 12. The turbine vane 12 described below may be, for example, a first-stage turbine vane 12 used under the highest temperature condition in the turbine 8.

[0060] like Figure 3 As shown, the blade portion 20 of the turbine vane 12 includes a suction surface forming wall 38 forming a suction surface 36 and a pressure surface forming wall 44 forming a pressure surface 40 and forming a blade inner chamber 42 between the suction surface forming wall 38 .

[0061] The negative pressure surface forming wall 38 and the pressure surface forming wall 44 may each have a curved plate shape having a substantially constant thickness. The blade inner chamber 42 is formed inside the blade-shaped portion 20 from one end to the other end thereof along the blade height direction.

[0062] exist Figure 3 In the illustrated embodiment, a leading edge partition wall 48 is provided in the blade inner chamber 42 of the blade-shaped portion 20. The leading edge partition wall 48 is formed integrally with the blade-shaped portion 20 by casting, for example, and is configured to extend from the inner surface 39 of the negative pressure surface forming wall 38 to the inner surface 45 of the pressure surface forming wall 44 to divide the blade inner chamber 42 into a leading edge side inner chamber 46 and a trailing edge side inner chamber 49. The leading edge partition wall 48 may also have a plate shape having a substantially constant thickness.

[0063] exist Figure 3 In the illustrated embodiment, an insert 50 is provided in the leading edge side cavity 46 of the blade-shaped portion 20. The insert 50 is formed into a tubular shape, for example, from a metal plate, extending from one end to the other end of the blade-shaped portion 20 along the blade height direction, and is inserted into the leading edge side cavity 46. The internal space 51 of the insert 50 is connected to the outer cavity 32 (see Figure 2 ), and the compressed air supplied from the compressor 4 to the outer chamber 32 is supplied from the outer chamber 32 to the internal space 51 of the insert 50 as cooling air. The insert 50 is formed with a plurality of impingement cooling holes 52 for impingement cooling the wall surface (the inner surface 39 of the negative pressure surface forming wall 38 and the inner surface 45 of the pressure surface forming wall 44) forming the leading edge side chamber 46 in the blade-shaped portion 20. In the example shown in the figure, the plurality of impingement cooling holes 52 are formed in the portion of the insert 50 that faces the negative pressure surface forming wall 38 and the portion of the insert 50 that faces the pressure surface forming wall 44.

[0064] like Figure 3 As shown, the first film cooling hole row R71, the second film cooling hole row R72 and the third film cooling hole row R73 are formed in the leading edge portion 21 of the blade-shaped portion 20. As described above, the first film cooling hole row R71 includes a plurality of first film cooling holes 71 arranged along the blade height direction, the second film cooling hole row R72 includes a plurality of second film cooling holes 72 arranged along the blade height direction, and the third film cooling hole row R73 includes a plurality of third film cooling holes 73 arranged along the blade height direction. In addition, the second film cooling hole row R72 is arranged between the first film cooling hole row R71 and the third film cooling hole row R73.

[0065] like Figure 3As shown, the first film cooling hole 71, the second film cooling hole 72, and the third film cooling hole 73 are respectively located on the pressure surface 40 side of the camber line CL in the cross section of the blade-shaped portion 20 perpendicular to the blade height direction. That is, the first film cooling hole row R71, the second film cooling hole row R72, and the third film cooling hole row R73 are respectively formed in the pressure surface forming wall 44.

[0066] In the above-mentioned turbine stator blade 12, at least a portion of the cooling air supplied to the blade inner chamber 42 of the turbine stator blade 12 from the outside of the turbine stator blade 12 (for example, the above-mentioned compressor 4) flows out to the outside of the blade-shaped portion 20 through any one of the first film cooling holes 71, the second film cooling holes 72 and the third film cooling holes 73, and flows along the surface of the blade-shaped portion 20 to perform film cooling on the surface of the blade-shaped portion 20.

[0067] exist Figure 3 In the illustrated embodiment, a portion of the cooling air supplied from the outside of the turbine vane 12 (for example, the compressor 4) to the internal space 51 of the insert 50 is ejected from the plurality of impingement cooling holes 52 of the insert 50 to impinge and cool the wall surface forming the leading edge side cavity 46 in the blade-shaped portion 20. The cooling air ejected from the plurality of impingement cooling holes 52 of the insert 50 to impinge and cool the pressure surface forming wall 44 flows out to the outside of the leading edge portion 21 of the blade-shaped portion 20 through the first film cooling hole 71, the second film cooling hole 72, or the third film cooling hole 73, and flows along the surface of the blade-shaped portion 20 to perform film cooling on the surface of the blade-shaped portion 20.

[0068] Figure 4 Yes Figure 3 An enlarged cross-sectional view of the leading edge portion 21 is shown.

[0069] like Figure 4 As shown, the first film cooling holes 71 are respectively formed as through holes penetrating the leading edge portion 21, and extend from the inlet 71a to the outlet 71b of the first film cooling hole 71 along a direction inclined relative to the wall thickness direction of the leading edge portion 21 (directions respectively orthogonal to the outer surface 25 and the inner surface 26 of the leading edge portion 21).

[0070] exist Figure 4 In the illustrated embodiment, the first film cooling holes 71 are respectively formed from the inlet 71a to the outlet 71b of the first film cooling holes 71 along a plane ( Figure 4 The cross section of the blade-shaped portion 20 shown extends in an inclined direction.

[0071] In addition, if Figure 4As shown, when a plane including the wall thickness direction and the blade height direction of the leading edge portion 21 at the center C1a of the inlet 71a of the first film cooling hole 71 is defined as a first plane H1, the first film cooling hole 71 extends from the inlet 71a to the outlet 71b of the first film cooling hole 71 in a direction inclined with respect to the first plane H1. In addition, the center C1b of the outlet 71b of the first film cooling hole 71 is located at a position downstream of the flow F of the combustion gas along the leading edge portion 21 (the main flow of the combustion gas flowing in the above-mentioned flow path 31) than the position P1 where the first plane H1 intersects the outer surface 25 of the leading edge portion 21.

[0072] like Figure 4 As shown, the second film-cooling holes 72 are formed as through holes penetrating the leading edge portion 21 , and extend from an inlet 72 a to an outlet 72 b of the second film-cooling holes 72 in a direction inclined with respect to the wall thickness direction of the leading edge portion 21 .

[0073] exist Figure 4 In the illustrated example, the second film-cooling holes 72 extend from the inlet 72 a to the outlet 72 b of the second film-cooling holes 72 in a direction inclined with respect to a plane orthogonal to the blade height direction.

[0074] In addition, if Figure 4 As shown, when a plane including the wall thickness direction and the blade height direction of the leading edge portion 21 at the center C2a of the inlet 72a of the second film cooling hole 72 is defined as a second plane H2, the outlet 72b of the second film cooling hole 72 is located at a position P2 where the second plane H2 intersects the outer surface 25 of the leading edge portion 21.

[0075] like Figure 4 As shown, the third film-cooling holes 73 are formed as through holes penetrating the leading edge portion 21 , and extend from an inlet 73 a to an outlet 73 b of the third film-cooling holes 73 in a direction inclined with respect to the wall thickness direction of the leading edge portion 21 .

[0076] exist Figure 4 In the illustrated example, the third film-cooling holes 73 extend from the inlet 73 a to the outlet 73 b of the third film-cooling holes 73 in a direction inclined with respect to a plane orthogonal to the blade height direction.

[0077] In addition, if Figure 4 As shown, when a plane including the wall thickness direction and the blade height direction of the leading edge portion 21 at the center C3a of the inlet 73a of the third film cooling hole 73 is defined as a third plane H3, a center C3b of the outlet 73b of the third film cooling hole 73 is located on the downstream side of the flow F of the combustion gas along the leading edge portion 21 relative to a position P3 at which the third plane H3 intersects with the outer surface 25 of the leading edge portion 21.

[0078] like Figure 4As shown, in the cross section of the blade-shaped portion 20 orthogonal to the blade height direction, when the intersection of the camber line CL and the outer surface 25 of the leading edge portion 21 is set as E1 and the most upstream position of the blade-shaped portion 20 in the axial direction of the gas turbine 2 is set as E2, the center C1b of the outlet 71b of the first film-cooling hole 71 is located between the intersection E1 and the most upstream position E2 of the outer surface 25 of the blade-shaped portion 20, the center C2b of the outlet 72b of the second film-cooling hole 72 is located on the opposite side of the intersection E1 of the outer surface 25 of the blade-shaped portion 20 across the most upstream position E2 (on the leading edge portion partition wall 48 side), and the center C3b of the outlet 73b of the third film-cooling hole 73 is located on the opposite side of the intersection E1 of the outer surface 25 of the blade-shaped portion 20 across the most upstream position E2.

[0079] like Figure 4 As shown, in the cross section of the blade-shaped portion 20 orthogonal to the blade height direction, the first film cooling hole 71, the second film cooling hole 72 and the third film cooling hole 73 are each located upstream of the position G where the pressure surface forming wall 44 and the leading edge partition wall 48 are connected in the axial direction.

[0080] Figure 5 This is a diagram of the outer surface 25 of the leading edge portion 21 of the blade-shaped portion 20 as viewed from a direction perpendicular to the outer surface 25 . Figure 6 1 is a diagram showing an example of a cross section along the blade height direction at the position of the first film-cooling hole row R71 in the leading edge portion 21 of the blade shape portion 20 . Fig. 7A Yes Figure 6 FIG. 2 is an enlarged cross-sectional view of an outer first film cooling hole 711 serving as the first film cooling hole 71 in the vicinity of the outer shroud 22 . Figure 7B Yes Figure 6 FIG. 2 is an enlarged cross-sectional view of an inner first film cooling hole 712 serving as the first film cooling hole 71 in the vicinity of the inner shroud 24 . Fig. 8A Yes means Fig. 7A Diagram of the QG-QG cross section in. Figure 8B Yes means Figure 7B Figure 2 shows the QH-QH cross section in Fig.

[0081] Fig. 9 1 is a diagram showing an example of a cross section along the blade height direction at the position of the second film-cooling hole row R72 in the leading edge portion 21 of the blade shape portion 20 . Fig. 10A Yes Fig. 9 FIG. 2 is an enlarged cross-sectional view of an outer second film cooling hole 721 serving as the second film cooling hole 72 in the vicinity of the outer shroud 22 . Fig. 10B Yes Fig. 9 FIG. 2 is an enlarged cross-sectional view of an inner second film-cooling hole 722 serving as the second film-cooling hole 72 in the vicinity of the inner shroud 24 . Fig.11A Yes means Fig. 10A Figure 2 shows the QJ-QJ section in Figure 2. Fig. 11B Yes means Fig. 10B Diagram of the QK-QK section in.

[0082] Fig.12 1 is a diagram showing an example of a cross section along the blade height direction at the position of the third film-cooling hole row R73 in the leading edge portion 21 of the blade shape portion 20 . Fig.13A Yes Fig.12 FIG. 2 is an enlarged cross-sectional view of an outer third film cooling hole 731 serving as the third film cooling hole 73 in the vicinity of the outer shroud 22 . Fig. 13B Yes Fig.12 FIG. 2 is an enlarged cross-sectional view of an inner third film cooling hole 732 serving as the third film cooling hole 73 in the vicinity of the inner shroud 24 . Fig.14A Yes means Fig.13A Figure 2. Diagram of the QL-QL section in FIG. Fig. 14B Yes means Fig. 13B Diagram of the QM-QM section in.

[0083] For example, Figure 5 and Figure 6 As shown, the plurality of first film cooling holes 71 belonging to the first film cooling hole array R71 include a plurality of outer first film cooling holes 711 located at a position outside the first position K1 in the blade height direction and a plurality of inner first film cooling holes 712 located at a position inside the first position K1 in the blade height direction. It should be noted that, in the example shown in the figure, the first position K1 is a position closer to the inner shroud 24 than the center of the blade-shaped portion 20 in the blade height direction.

[0084] For example, Fig. 7A As shown, the outer first film-cooling hole 711 extends toward the inner side in the blade height direction as going from the inlet 71 a of the outer first film-cooling hole 711 toward the outlet 71 b of the outer first film-cooling hole 711 .

[0085] For example, Figure 7B As shown, the inner first film-cooling hole 712 extends toward the outer side in the blade height direction as it goes from the inlet 71 a of the inner first film-cooling hole 712 toward the outlet 71 b of the inner first film-cooling hole 712 .

[0086] For example, Figure 5 and Fig. 9 As shown, the plurality of second film cooling holes 72 belonging to the second film cooling hole row R72 include a plurality of outer second film cooling holes 721 located outside the first position K1 in the blade height direction and a plurality of inner second film cooling holes 722 located inside the first position K1 in the blade height direction.

[0087] For example, Fig. 10AAs shown, the outer second film-cooling hole 721 extends toward the inner side in the blade height direction as going from the inlet 72a of the outer second film-cooling hole 721 toward the outlet 72b of the outer second film-cooling hole 721 .

[0088] For example, Fig. 10B As shown, the inner second film-cooling hole 722 extends toward the outer side in the blade height direction as it goes from the inlet 72a of the inner second film-cooling hole 722 toward the outlet 72b of the inner second film-cooling hole 722 .

[0089] For example, Figure 5 and Fig.12 As shown, the plurality of third film cooling holes 73 belonging to the third film cooling hole row R73 include a plurality of outer third film cooling holes 731 located outside the first position K1 in the blade height direction and a plurality of inner third film cooling holes 732 located inside the first position K1 in the blade height direction.

[0090] For example, Fig.13A As shown, the outer third film-cooling hole 731 extends toward the inner side in the blade height direction as going from the inlet 73a of the outer third film-cooling hole 731 toward the outlet 73b of the outer third film-cooling hole 731 .

[0091] For example, Fig. 13B As shown, the inner third film-cooling hole 732 extends toward the outer side in the blade height direction as it goes from the inlet 73 a of the inner third film-cooling hole 732 toward the outlet 73 b of the inner third film-cooling hole 732 .

[0092] For example, Figure 5 , Fig. 7A as well as Fig. 8A As shown, the outer first film cooling hole 711 includes a circular hole portion 74 and a special-shaped hole portion 75. The circular hole portion 74 is a portion on the inlet 71a side of the outer first film cooling hole 711, and has a circular cross-sectional shape. Regardless of the position of the circular hole portion 74 in the direction of the axis L74, the cross-sectional area of ​​the circular hole portion 74 is constant. The special-shaped hole portion 75 is a portion on the outlet 71b side of the outer first film cooling hole 711, and is connected to the circular hole portion 74. The cross-sectional area of ​​the special-shaped hole portion 75 increases as it approaches the outlet 71b of the outer first film cooling hole 711 (the outlet of the special-shaped hole portion 75). When the special-shaped hole portion 75 is viewed in the direction of the axis L74 of the circular hole portion 74, the cross-sectional area only expands toward the inner side in the blade height direction relative to the circular hole portion 74, and does not expand toward the outer side in the blade height direction relative to the circular hole portion 74. Furthermore, when viewed in the direction of the axis L74 of the circular hole 74 , the irregular hole 75 does not have a cross-sectional area that is expanded relative to the circular hole 74 in a direction orthogonal to the blade height direction.

[0093] For example, Fig. 7A As shown, the center C1b of the outlet 71b of the outer first film cooling hole 711 is located at a position inside the blade height direction relative to the extension line of the axis L74 of the circular hole portion 74 of the outer first film cooling hole 711. More specifically, the center C1b of the outlet 71b of the outer first film cooling hole 711 is located at a position inside the blade height direction relative to the intersection S11 of the extension line of the axis L74 of the circular hole portion 74 of the outer first film cooling hole 711 and the outlet 71b of the outer first film cooling hole 711.

[0094] For example, Figure 5 , Figure 7B as well as Figure 8B As shown, the inner first film cooling hole 712 includes a circular hole portion 76 and a special-shaped hole portion 77. The circular hole portion 76 is a portion on the inlet 71a side of the inner first film cooling hole 712, and has a circular cross-sectional shape. The cross-sectional area of ​​the circular hole portion 76 is constant regardless of the position of the circular hole portion 76 in the direction of the axis L76. The special-shaped hole portion 77 is a portion on the outlet 71b side of the inner first film cooling hole 712, and is connected to the circular hole portion 76. The cross-sectional area of ​​the special-shaped hole portion 77 increases as it approaches the outlet 71b of the inner first film cooling hole 712 (the outlet of the special-shaped hole portion 77). When the special-shaped hole portion 77 is viewed in the direction of the axis L76 of the circular hole portion 76, the cross-sectional area only expands toward the outside in the blade height direction relative to the circular hole portion 76, and does not expand toward the inside in the blade height direction relative to the circular hole portion 76. Furthermore, when viewed in the direction of the axis L76 of the circular hole 76 , the irregular hole 77 does not expand in cross-sectional area relative to the circular hole 76 in the direction orthogonal to the blade height direction.

[0095] For example, Figure 7B As shown, the center C1b of the outlet 71b of the inner first film cooling hole 712 is located at a position on the outside in the blade height direction relative to the extension line of the axis L76 of the circular hole portion 76 of the inner first film cooling hole 712. More specifically, the center C1b of the outlet 71b of the inner first film cooling hole 712 is located at a position on the outside in the blade height direction relative to the intersection S12 of the extension line of the axis L76 of the circular hole portion 76 of the inner first film cooling hole 712 and the outlet 71b of the inner first film cooling hole 712.

[0096] For example, Figure 5 , Fig. 10A as well as Fig.11AAs shown, the outer second film cooling hole 721 includes a circular hole portion 78 and a special-shaped hole portion 79. The circular hole portion 78 is a portion on the inlet 72a side of the outer second film cooling hole 721, and has a circular cross-sectional shape. The cross-sectional area of ​​the circular hole portion 78 is constant regardless of the position of the circular hole portion 78 in the direction of the axis L78. The special-shaped hole portion 79 is a portion on the outlet 72b side of the outer second film cooling hole 721, and is connected to the circular hole portion 78. The cross-sectional area of ​​the special-shaped hole portion 79 increases as it approaches the outlet 72b (the outlet of the special-shaped hole portion 79) of the outer second film cooling hole 721. When the special-shaped hole portion 79 is viewed in the direction of the axis L78 of the circular hole portion 78, the cross-sectional area only expands toward the inner side in the blade height direction relative to the circular hole portion 78, and does not expand toward the outer side in the blade height direction relative to the circular hole portion 78. Furthermore, when viewed in the direction of the axis line L78 of the circular hole portion 78 , the irregular hole portion 79 does not have a cross-sectional area that is expanded relative to the circular hole portion 78 in a direction orthogonal to the blade height direction.

[0097] For example, Fig. 10A As shown, the center C2b of the outlet 72b of the outer second film-cooling hole 721 is located at a position inside the blade height direction relative to the extension line of the axis L78 of the circular hole portion 78 of the outer second film-cooling hole 721. More specifically, the center C2b of the outlet 72b of the outer second film-cooling hole 721 is located at a position inside the blade height direction relative to the intersection S21 of the extension line of the axis L78 of the circular hole portion 78 of the outer second film-cooling hole 721 and the outlet 72b of the outer second film-cooling hole 721.

[0098] For example, Figure 5 , Fig. 10B as well as Fig. 11B As shown, the inner second film cooling hole 722 includes a circular hole portion 80 and a special-shaped hole portion 81. The circular hole portion 80 is a portion on the inlet 72a side of the inner second film cooling hole 722, and has a circular cross-sectional shape. Regardless of the position of the circular hole portion 80 in the direction of the axis L80, the cross-sectional area of ​​the circular hole portion 80 is constant. The special-shaped hole portion 81 is a portion on the outlet 72b side of the inner second film cooling hole 722, and is connected to the circular hole portion 80. The cross-sectional area of ​​the special-shaped hole portion 81 increases as it approaches the outlet 72b of the inner second film cooling hole 722 (the outlet of the special-shaped hole portion 81). When the special-shaped hole portion 81 is viewed in the direction of the axis L80 of the circular hole portion 80, the cross-sectional area only expands to the outside in the blade height direction relative to the circular hole portion 80, and does not expand to the inside in the blade height direction relative to the circular hole portion 80. Furthermore, when the irregular hole portion 81 is viewed in the direction of the axis L80 of the circular hole portion 80 , the cross-sectional area is not expanded relative to the circular hole portion 80 in the direction orthogonal to the blade height direction.

[0099] For example, Fig. 10BAs shown, the center C2b of the outlet 72b of the inner second film-cooling hole 722 is located outside the blade height direction relative to the extension line of the axis L80 of the circular hole portion 80 of the inner second film-cooling hole 722. More specifically, the center C2b of the outlet 72b of the inner second film-cooling hole 722 is located outside the blade height direction relative to the intersection S22 of the outlet 72b of the inner second film-cooling hole 722 and the extension line of the axis L80 of the circular hole portion 80 of the inner second film-cooling hole 722.

[0100] For example, Figure 5 , Fig.13A as well as Fig.14A As shown, the outer third film cooling hole 731 includes a circular hole portion 82 and a special-shaped hole portion 83. The circular hole portion 82 is a portion on the inlet 73a side of the outer third film cooling hole 731, and has a circular cross-sectional shape. Regardless of the position of the circular hole portion 82 in the direction of the axis L82, the cross-sectional area of ​​the circular hole portion 82 is constant. The special-shaped hole portion 83 is a portion on the outlet 73b side of the outer third film cooling hole 731, and is connected to the circular hole portion 82. The cross-sectional area of ​​the special-shaped hole portion 83 increases as it approaches the outlet 73b (the outlet of the special-shaped hole portion 83) of the outer third film cooling hole 731. When the special-shaped hole portion 83 is viewed in the direction of the axis L82 of the circular hole portion 82, the cross-sectional area only expands toward the inner side in the blade height direction relative to the circular hole portion 82, and does not expand toward the outer side in the blade height direction relative to the circular hole portion 82. Furthermore, when the irregular hole portion 83 is viewed in the direction of the axis line L82 of the circular hole portion 82 , the cross-sectional area is not expanded relative to the circular hole portion 82 in the direction orthogonal to the blade height direction.

[0101] For example, Fig.13A As shown, the center C3b of the outlet 73b of the outer third film-cooling hole 731 is located at a position inside the blade height direction relative to the extension line of the axis L82 of the circular hole portion 82 of the outer third film-cooling hole 731. More specifically, the center C3b of the outlet 73b of the outer third film-cooling hole 731 is located at a position inside the blade height direction relative to the intersection S31 of the outlet 73b of the outer third film-cooling hole 731 and the extension line of the axis L82 of the circular hole portion 82 of the outer third film-cooling hole 731.

[0102] For example, Figure 5 , Fig. 13B as well as Fig. 14BAs shown, the inner third film cooling hole 732 includes a circular hole portion 84 and a special-shaped hole portion 85. The circular hole portion 84 is a portion on the inlet 73a side of the inner third film cooling hole 732, and has a circular cross-sectional shape. Regardless of the position of the circular hole portion 84 in the direction of the axis L84, the cross-sectional area of ​​the circular hole portion 84 is constant. The special-shaped hole portion 85 is a portion on the outlet 73b side of the inner third film cooling hole 732, and is connected to the circular hole portion 84. The cross-sectional area of ​​the special-shaped hole portion 85 increases as it approaches the outlet 73b (the outlet of the special-shaped hole portion 83) of the inner third film cooling hole 732. When the special-shaped hole portion 85 is viewed in the direction of the axis L84 of the circular hole portion 84, the cross-sectional area is expanded only toward the outside in the blade height direction relative to the circular hole portion 84, and the cross-sectional area is not expanded toward the inside in the blade height direction relative to the circular hole portion 84. Furthermore, when the irregular hole portion 85 is viewed in the direction of the axis line L84 of the circular hole portion 84 , the cross-sectional area of ​​the irregular hole portion 85 is not expanded relative to the circular hole portion 84 in the direction orthogonal to the blade height direction.

[0103] For example, Fig. 13B As shown, the center C3b of the outlet 73b of the inner third film cooling hole 732 is located at a position on the outside in the blade height direction relative to the extension line of the axis L84 of the circular hole portion 84 of the inner third film cooling hole 732. More specifically, the center C3b of the outlet 73b of the inner third film cooling hole 732 is located at a position on the outside in the blade height direction relative to the intersection S32 of the outlet 73b of the inner third film cooling hole 732 and the extension line of the axis L84 of the circular hole portion 84 of the inner third film cooling hole 732.

[0104] For example, Fig.12 As shown, in the axis including the third film cooling hole 73 (the axis L82 of the circular hole portion 82 of the outer third film cooling hole 731 in FIG. 13, Fig. 13B In the cross section in the direction of blade height (the axis L84 of the circular hole portion 84 of the inner third film cooling hole 732 and their extension lines) and the blade height direction, when the outer shroud 22 and the inner shroud 24 with a larger protrusion from the leading edge portion 21 in the direction orthogonal to the blade height direction is defined as the large shroud 90, and the outer shroud 22 and the inner shroud 24 that is not the large shroud 90 is defined as the small shroud 91, the distance V90 between the first position K1 in the blade height direction and the large shroud 90 is greater than the distance V91 between the first position K1 in the blade height direction and the small shroud 91. Fig.12 In the example shown, in the cross section including the axis of the third film cooling hole 73 and the blade height direction, when the protrusion amount of the outer shroud 22 from the leading edge portion 21 in the direction perpendicular to the blade height direction is set to A3 and the protrusion amount of the inner shroud 24 from the leading edge portion 21 in the direction perpendicular to the blade height direction is set to B3, A3>B3, so the outer shroud 22 is a large shroud 90 and the inner shroud 24 is a small shroud 91.

[0105] For example, Figure 6 As shown, on the axis including the first film cooling hole 71 ( Fig. 7A The axis L74 of the circular hole portion 74 of the outer first film cooling hole 711, Figure 7B In the cross section of the inner first film cooling hole 712 (the axis L76 of the circular hole portion 76 and their extension lines) and the blade height direction, the protrusion amount of the outer shroud 22 from the leading edge portion 21 in the direction perpendicular to the blade height direction is set to A1, and the protrusion amount of the inner shroud 24 from the leading edge portion 21 in the direction perpendicular to the blade height direction is set to B1. In addition, for example, Fig. 9 As shown, on the axis including the second film cooling hole 72 ( Fig. 10A The axis L78 of the circular hole portion 78 of the outer second film cooling hole 721, Fig. 10B In the cross section of the inner second film cooling hole 722 (the axis L80 of the circular hole portion 80 and their extension lines) and the blade height direction, the protrusion amount of the outer shroud 22 from the leading edge portion 21 in the direction perpendicular to the blade height direction is set to A2, and the protrusion amount of the inner shroud 24 from the leading edge portion 21 in the direction perpendicular to the blade height direction is set to B2. In addition, for example, Fig.12 As shown, on the axis including the third film cooling hole 73 ( Fig.13A The axis L82 of the circular hole portion 82 of the outer third film cooling hole 731, Fig. 13B In a cross section along the blade height direction (the axis line L84 of the circular hole portion 84 of the inner third film cooling hole 732 and their extension lines), the protrusion amount of the outer shroud 22 from the leading edge portion 21 in the direction perpendicular to the blade height direction is set to A3, and the protrusion amount of the inner shroud 24 from the leading edge portion 21 in the direction perpendicular to the blade height direction is set to B3.

[0106] Here, when the one of the outer shroud 22 and the inner shroud 24 having the largest protrusion amount among the protrusion amounts A1, A2, A3, B1, B2, and B3 is defined as the large shroud 92, and the one of the outer shroud 22 and the inner shroud 24 that is not the large shroud 92 is defined as the small shroud 93, the distance V92 between the first position K1 in the blade height direction and the large shroud 92 is greater than the distance V93 between the first position K1 in the blade height direction and the small shroud 93. Figure 6 , Fig. 9 and Fig.12 In the example shown, the largest protrusion amount among the protrusion amounts A1 , A2 , A3 , B1 , B2 , and B3 is A3 , so the outer shroud 22 is a large shroud 92 and the inner shroud 24 is a small shroud 93 .

[0107] Next, the effects achieved by the turbine vane 12 will be described.

[0108] For example, Figure 4 As shown, the first film cooling hole 71, the second film cooling hole 72 and the third film cooling hole 73 extend in a direction inclined relative to the wall thickness direction of the leading edge portion 21, respectively. The center C1b of the outlet 71b of the first film cooling hole 71 is located at a position downstream of the flow F of the combustion gas along the leading edge portion 21 than the position P1 where the above-mentioned first plane H1 intersects with the outer surface 25 of the leading edge portion 21, the outlet 72b of the second film cooling hole 72 is located at a position P2 where the above-mentioned second plane H2 intersects with the outer surface 25 of the leading edge portion 21, and the center C3b of the outlet 73b of the third film cooling hole 73 is located at a position downstream of the flow F of the combustion gas along the leading edge portion 21 than the position P3 where the above-mentioned third plane H3 intersects with the outer surface 25 of the leading edge portion 21.

[0109] Therefore, by positioning the second film cooling holes 72 at the position P0 (see Figure 4 ) or in the vicinity thereof, the cooling air used for film cooling can flow out from the first film cooling hole 71 and the third film cooling hole 73 along the outer surface 25 of the leading edge portion 21 toward the downstream side of the flow of the combustion gas on both sides of the boundary at the position P0 of the stagnation point of the flow of the combustion gas on the outer surface 25 of the leading edge portion 21. Therefore, the film cooling of the outer surface 25 of the leading edge portion 21 can be effectively performed with a small amount of cooling air, and the amount of cooling air can be reduced and the reduction in the film efficiency of the film cooling on the blade surface can be suppressed.

[0110] In addition, if Figure 5 , Figure 6 and Fig. 7A As shown, the outer first film cooling hole 711 located on the outer shroud 22 side in the blade height direction extends in a manner tending to the inner side in the blade height direction as it goes from the inlet 71a of the outer first film cooling hole 711 to the outlet 71b. Therefore, compared with the case where the outer first film cooling hole 711 extends in a manner tending to the outer side in the blade height direction as it goes from the inlet 71a of the outer first film cooling hole 711 to the outlet 71b, when the outer first film cooling hole 711 is formed from the outer surface 25 side of the blade-shaped portion 20 using a clamp, for example by laser processing, interference between the clamp and the outer shroud 22 can be suppressed.

[0111] In addition, if Figure 5 , Figure 6 and Figure 7BAs shown, the inner first film cooling hole 712 located on the inner shroud 24 side in the blade height direction extends in a manner tending to the outer side in the blade height direction as it goes from the inlet 71a of the inner first film cooling hole 712 to the outlet 71b. Therefore, compared with the case where the inner first film cooling hole 712 extends in a manner tending to the inner side in the blade height direction as it goes from the inlet 71a of the inner first film cooling hole 712 to the outlet 71b, when the inner first film cooling hole 712 is formed from the outer surface 25 side of the blade-shaped portion 20 using a clamp, interference between the clamp and the inner shroud 24 can be suppressed.

[0112] In addition, if Figure 5 , Fig. 9 and Fig. 10A As shown, the outer second film cooling hole 721 located on the outer shroud 22 side in the blade height direction extends in a manner tending to the inner side in the blade height direction as it goes from the inlet 72a of the outer second film cooling hole 721 to the outlet 72b. Therefore, compared with the case where the outer second film cooling hole 721 extends in a manner tending to the outer side in the blade height direction as it goes from the inlet 72a of the outer second film cooling hole 721 to the outlet 72b, when the outer second film cooling hole 721 is formed from the outer surface 25 side of the blade-shaped portion 20 using a clamp, for example by laser processing, interference between the clamp and the outer shroud 22 can be suppressed.

[0113] In addition, if Figure 5 , Fig. 9 and Fig. 10B As shown, the inner second film cooling hole 722 located on the inner shroud 24 side in the blade height direction extends in a manner tending to the outer side in the blade height direction as it goes from the inlet 72a of the inner second film cooling hole 722 to the outlet 72b. Therefore, compared with the case where the inner second film cooling hole 722 extends in a manner tending to the inner side in the blade height direction as it goes from the inlet 72a of the inner second film cooling hole 722 to the outlet 72b, when the inner second film cooling hole 722 is formed from the outer surface 25 side of the blade-shaped portion 20 using a clamp, interference between the clamp and the inner shroud 24 can be suppressed.

[0114] In addition, if Figure 5 , Fig.12 and Fig.13AAs shown, the outer third film cooling hole 731 located on the outer shroud 22 side in the blade height direction extends in a manner tending to the inner side in the blade height direction as it goes from the inlet 73a of the outer third film cooling hole 731 to the outlet 73b. Therefore, compared with the case where the outer third film cooling hole 731 extends in a manner tending to the outer side in the blade height direction as it goes from the inlet 73a of the outer third film cooling hole 731 to the outlet 73b, when the outer third film cooling hole 731 is formed from the outer surface 25 side of the blade-shaped portion 20 using a clamp, for example by laser processing, interference between the clamp and the outer shroud 22 can be suppressed.

[0115] In addition, if Figure 5 , Fig.12 and Fig. 13B As shown, the inner third film cooling hole 732 located on the inner shroud 24 side in the blade height direction extends in a manner tending to the outer side in the blade height direction as it goes from the inlet 73a of the inner third film cooling hole 732 to the outlet 73b. Therefore, compared with the case where the inner third film cooling hole 732 extends in a manner tending to the inner side in the blade height direction as it goes from the inlet 73a of the inner third film cooling hole 732 to the outlet 73b, when the inner third film cooling hole 732 is formed from the outer surface 25 side of the blade-shaped portion 20 using a clamp, interference between the clamp and the inner shroud 24 can be suppressed.

[0116] In addition, about Fig.12 In the structure shown in the figure, when the outer third film cooling hole 731 and the inner third film cooling hole 732 are formed from the outer surface 25 side of the blade-shaped portion 20 by laser processing, the outer shroud 22 with a large protrusion from the leading edge portion 21 in the direction perpendicular to the blade height direction is more likely to cause interference with the jig than the inner shroud 24 with a small protrusion from the leading edge portion 21 in the direction perpendicular to the blade height direction. Therefore, Fig.12 As shown in FIG. 1 , by making the boundary between the range where the outer third film cooling holes 731 are formed and the range where the inner third film cooling holes 732 are formed in the blade height direction, that is, the distance V90 between the first position K1 and the outer shroud 22 is greater than the distance V91 between the first position K1 and the inner shroud 24 in the blade height direction, the interference between the clamp and each of the outer shroud 22 and the inner shroud 24 can be suppressed, and the outer third film cooling holes 731 and the inner third film cooling holes 732 can be formed respectively.

[0117] In addition, when the first to third film cooling holes 71 to 73 are formed from the outer surface 25 side of the blade-shaped portion 20 using a jig, for example, by laser processing, the large shroud 92 having the maximum protrusion amount A3 from the leading edge portion 21 in the direction orthogonal to the blade height direction is more likely to cause interference with the jig than the small shroud 93. Therefore, by making the distance V92 between the first position K1 in the blade height direction and the large shroud 92 greater than the distance V93 between the first position K1 in the blade height direction and the small shroud 93, the interference between the jig and each of the outer shroud 22 and the inner shroud 24 can be suppressed, and the first to third film cooling holes 71 to 73 can be formed.

[0118] In addition, if you use Figure 5 , Figure 6 , Fig. 9 as well as Fig.12 As described in the above, the first film cooling hole 71, the second film cooling hole 72, and the third film cooling hole 73 extend in a direction inclined relative to a plane orthogonal to the blade height direction. Therefore, compared with the case where the first film cooling hole 71, the second film cooling hole 72, and the third film cooling hole 73 extend in the wall thickness direction of the leading edge portion 21, the film cooling of the outer surface 25 of the leading edge portion 21 can be effectively performed with a smaller amount of cooling air, and the cooling air amount can be reduced and the decrease in the film efficiency of the film cooling of the blade surface can be suppressed.

[0119] In addition, if you use Fig. 7A , Fig. 10A as well as Fig.13A As described in the drawings, the first outer film cooling hole 711, the second outer film cooling hole 721, and the third outer film cooling hole 731 are formed by expanding the cross-sectional area of ​​the irregular hole portions 75, 79, 83 only toward the inner side in the blade height direction relative to the circular hole portions 74, 78, 82, respectively, so that the first outer film cooling hole 711, the second outer film cooling hole 721, and the third outer film cooling hole 731 can be formed easily by laser processing or the like. In addition, the first inner film cooling hole 712, the second inner film cooling hole 722, and the third inner film cooling hole 732 are formed by expanding the cross-sectional area of ​​the irregular hole portions 77, 81, 85 only toward the outer side in the blade height direction relative to the circular hole portions 76, 80, 84, respectively, so that the first inner film cooling hole 712, the second inner film cooling hole 722, and the third inner film cooling hole 732 can be formed easily by laser processing or the like.

[0120] Fig.15 It is a diagram showing a cross section perpendicular to the blade height direction of the turbine stator blade 012 according to the first comparative embodiment. Fig.16It is a graph showing the relationship between the distance from the second film cooling hole row R72 of the turbine stator blade 12 of the above-mentioned embodiment and the average film efficiency in the blade span direction, and the relationship between the distance from the third film cooling hole row 07 (the film cooling hole row at a position corresponding to the second film cooling hole row R72) of the turbine stator blade 012 of the first comparative embodiment and the average film efficiency in the blade span direction.

[0121] exist Fig.15 In the first comparative embodiment shown, five film cooling hole rows 07 are formed at the leading edge portion 021 of the turbine stator blade 012, and each of the film cooling hole rows 07 includes a plurality of film cooling holes 007 arranged along the blade height direction. In addition, in each film cooling hole row 07, the film cooling hole 007 has a circular cross-sectional shape, and when a plane including the wall thickness direction of the leading edge portion 021 and the blade height direction at the center of the inlet of the film cooling hole 007 is defined as a vertical plane, the outlet of the film cooling hole 007 is located at a position where the vertical plane intersects with the outer surface 025 of the leading edge portion 021.

[0122] exist Fig.16 In the figure, the solid line represents the relationship between the distance of the turbine stator blade 12 of the above embodiment from the second film cooling hole row R72 and the average film efficiency in the blade span direction, the dotted line represents the relationship between the distance of the turbine stator blade 012 of the first comparison method from the third film cooling hole row 07 and the average film efficiency in the blade span direction, and the single-dash line represents the relationship between the distance of the turbine stator blade 012 of the second comparison method in which the film cooling hole rows are reduced by two rows to three rows compared with the structure of the first comparison method and the average film efficiency in the blade span direction.

[0123] like Fig.16 As shown, in the second comparative embodiment, the number of film cooling hole rows 07 is reduced from five rows to three rows compared to the first comparative embodiment, so the film efficiency is reduced. In contrast, it can be seen that in the above embodiment, although the number of film cooling hole rows is reduced from five rows to three rows compared to the first comparative embodiment, since the third film cooling hole row R73 includes the above-mentioned irregular hole portions 83 and 85, the film efficiency is improved on the downstream side of the third film cooling hole row R73 in the flow direction of the combustion gas along the leading edge portion 21. In this way, in the above-mentioned turbine stator blade 12, film cooling of the outer surface 25 of the leading edge portion 21 can be effectively performed with a small amount of cooling air, and the amount of cooling air can be reduced and the reduction in the film efficiency of film cooling on the blade surface can be suppressed.

[0124] The present disclosure is not limited to the above-described embodiments, and also includes modified embodiments of the above-described embodiments and embodiments in which these embodiments are appropriately combined.

[0125] For example, the irregular hole portion 75 may be such that, when viewed in the direction of the axis L74 of the circular hole portion 74, the cross-sectional area is expanded not only toward the inner side but also toward the outer side in the blade height direction relative to the circular hole portion 74, and the cross-sectional area may be expanded in a direction orthogonal to the blade height direction. In addition, the irregular hole portion 77 may be such that, when viewed in the direction of the axis L76 of the circular hole portion 76, the cross-sectional area is expanded not only toward the outer side but also toward the inner side in the blade height direction relative to the circular hole portion 76, and the cross-sectional area may be expanded in a direction orthogonal to the blade height direction.

[0126] In addition, the irregular hole portion 79 may be such that, when viewed in the direction of the axis L78 of the circular hole portion 78, the cross-sectional area is expanded not only toward the inner side but also toward the outer side in the blade height direction relative to the circular hole portion 78, and the cross-sectional area may be expanded in a direction orthogonal to the blade height direction. In addition, the irregular hole portion 81 may be such that, when viewed in the direction of the axis L80 of the circular hole portion 80, the cross-sectional area is expanded not only toward the outer side but also toward the inner side in the blade height direction relative to the circular hole portion 80, and the cross-sectional area may be expanded in a direction orthogonal to the blade height direction.

[0127] In addition, the irregular hole portion 83 may be such that, when viewed in the direction of the axis L82 of the circular hole portion 82, the cross-sectional area is expanded not only toward the inner side but also toward the outer side in the blade height direction relative to the circular hole portion 82, and the cross-sectional area may be expanded in a direction orthogonal to the blade height direction. In addition, the irregular hole portion 85 may be such that, when viewed in the direction of the axis L84 of the circular hole portion 84, the cross-sectional area is expanded not only toward the outer side but also toward the inner side in the blade height direction relative to the circular hole portion 84, and the cross-sectional area may be expanded in a direction orthogonal to the blade height direction.

[0128] The contents described in each of the above-mentioned embodiments can be understood, for example, as follows.

[0129] (1) A gas turbine stator blade according to at least one embodiment of the present disclosure is a gas turbine stator blade (for example, the turbine stator blade 12 described above),

[0130] The gas turbine stator blade includes a blade-shaped portion (for example, the blade-shaped portion 20 described above) having a cavity (for example, the blade inner chamber 42 described above) formed inside.

[0131] The leading edge of the blade-shaped portion (such as the leading edge 21 described above) is formed with:

[0132] A first film cooling hole array (such as the first film cooling hole array R71 described above), comprising a plurality of first film cooling holes (such as the plurality of first film cooling holes 71 described above) arranged along the blade height direction;

[0133] A second film cooling hole array (such as the second film cooling hole array R72 described above), comprising a plurality of second film cooling holes (such as the plurality of second film cooling holes 72 described above) arranged along the blade height direction; and

[0134] A third film cooling hole row (such as the third film cooling hole row R73 mentioned above), comprising a plurality of third film cooling holes (such as the third film cooling holes 73 mentioned above) arranged along the height direction of the blade,

[0135] The second film cooling hole row is arranged between the first film cooling hole row and the third film cooling hole row,

[0136] The first film cooling hole extends in a direction inclined with respect to the wall thickness direction of the leading edge portion, and when a plane including the wall thickness direction of the leading edge portion and the blade height direction at the center (e.g., the center C1a) of the inlet (e.g., the inlet 71a) of the first film cooling hole is defined as a first plane (e.g., the first plane H1), a center (e.g., the center C1b) of the outlet (e.g., the outlet 71b) of the first film cooling hole is located downstream of a flow of the combustion gas along the leading edge portion (e.g., the flow F) than a position (e.g., the position P1) where the first plane intersects with an outer surface of the leading edge portion (e.g., the outer surface 25).

[0137] The second film cooling hole extends in a direction inclined relative to the wall thickness direction of the leading edge portion, and when a plane including the wall thickness direction of the leading edge portion and the blade height direction at the center (e.g., the center C2a) of the inlet of the second film cooling hole (e.g., the inlet 72a described above) is defined as a second plane (e.g., the second plane H2 described above), the outlet of the second film cooling hole (e.g., the outlet 72b described above) is located at a position where the second plane intersects the outer surface of the leading edge portion (e.g., the position P2 described above),

[0138] The third film cooling hole extends in a direction inclined relative to the wall thickness direction of the leading edge portion, and when a plane including the wall thickness direction of the leading edge portion and the blade height direction at the center (e.g., the center C3a) of the inlet (e.g., the inlet 73a) of the third film cooling hole is defined as a third plane (e.g., the third plane H3), the center (e.g., the center C3b) of the outlet (e.g., the outlet 73b) of the third film cooling hole is located downstream of the flow of the combustion gas along the leading edge portion (e.g., the flow F) than the position where the third plane intersects the outer surface of the leading edge portion (e.g., the position P3) mentioned above.

[0139] According to the gas turbine stator blade described in (1) above, a first film cooling hole row, a second film cooling hole row, and a third film cooling hole row are formed in the leading edge portion exposed to the flow of high-temperature combustion gas, which are arranged along the blade height direction. Here, the first film cooling hole 71, the second film cooling hole 72, and the third film cooling hole 73 extend in a direction inclined relative to the wall thickness direction of the leading edge portion 21, respectively. The center of the outlet of the first film cooling hole is located at a position downstream of the flow of the combustion gas along the leading edge portion relative to the position where the first plane intersects with the outer surface of the leading edge portion, the outlet of the second film cooling hole is located at a position where the second plane intersects with the outer surface of the leading edge portion, and the center of the outlet of the third film cooling hole is located at a position downstream of the flow of the combustion gas along the leading edge portion relative to the position where the third plane intersects with the outer surface of the leading edge portion. Therefore, by arranging the second film cooling hole row in such a manner that the second film cooling hole is located at or near the stagnation point of the flow of the combustion gas on the outer surface of the leading edge portion of the blade-shaped portion, the cooling air used for film cooling can be made to flow out from the first film cooling hole and the third film cooling hole toward the downstream side of the flow of the combustion gas on both sides of the position of the stagnation point of the flow of the combustion gas on the outer surface of the leading edge portion of the blade-shaped portion as a boundary. Therefore, the film cooling of the outer surface of the leading edge portion can be effectively performed with a small amount of cooling air, and a gas turbine stator blade can be provided that reduces the amount of cooling air and can suppress the reduction of the film efficiency of the film cooling on the blade surface.

[0140] (2) In some embodiments, in addition to the gas turbine stator blade described in (1) above,

[0141] The first film cooling hole, the second film cooling hole, and the third film cooling hole are respectively located on the pressure surface side (eg, the pressure surface 40 ) of the camber line (eg, the camber line CL) in a cross section of the blade-shaped portion orthogonal to the blade height direction.

[0142] Since the stagnation point of the flow of the combustion gas on the outer surface of the leading edge of the blade-shaped portion is generated at a position closer to the pressure surface than the median camber line, according to the gas turbine stator described in (2) above, by arranging the second film cooling hole row in such a manner that the second film cooling hole is located at or near the stagnation point of the flow of the combustion gas on the outer surface of the leading edge of the blade-shaped portion, the cooling air used for film cooling can flow out from the first film cooling hole and the third film cooling hole toward the downstream side of the flow of the combustion gas on both sides of the position of the stagnation point of the flow of the combustion gas on the outer surface of the leading edge of the blade-shaped portion as a boundary. As a result, the film cooling of the outer surface of the leading edge portion can be effectively performed with a small amount of cooling air, and a gas turbine stator blade that can reduce the amount of cooling air and suppress the reduction of the film efficiency of film cooling on the blade surface can be provided.

[0143] (3) In some embodiments, in addition to the gas turbine stator blade described in (1) or (2),

[0144] In a cross section of the blade-shaped portion that is orthogonal to the blade height direction, when the intersection of the median camber line and the outer surface of the leading edge portion is set as E1 and the most upstream position of the blade-shaped portion in the axial direction of the gas turbine is set as E2, the outlet of the first film cooling hole is located between the intersection E1 and the most upstream position E2 of the outer surface of the blade-shaped portion, and the outlet of the third film cooling hole is located on the outer surface of the blade-shaped portion on the opposite side of the intersection E1 across the most upstream position E2.

[0145] According to the gas turbine stator blade described in (3) above, the cooling air used for film cooling can be made to flow out from the first film cooling hole and the third film cooling hole toward the downstream side of the flow of the combustion gas on both sides of the most upstream position E2, so that the film cooling of the outer surface of the leading edge portion can be effectively performed with a smaller amount of cooling air, and a gas turbine stator blade can be provided that can reduce the amount of cooling air and suppress the reduction in the film efficiency of film cooling on the blade surface.

[0146] (4) In some embodiments, in addition to the gas turbine stator blade described in (3) above,

[0147] In a cross section of the blade-shaped portion orthogonal to the blade height direction, the outlet of the second film-cooling hole is located on the outer surface of the blade-shaped portion on the opposite side of the intersection E1 across the most upstream position E2.

[0148] According to the gas turbine stator blade described in (4) above, it is possible to provide a gas turbine stator blade capable of reducing the amount of cooling air and suppressing a decrease in the film efficiency of film cooling on the blade surface.

[0149] (5) In some embodiments, in the gas turbine stator blade described in any one of (1) to (4) above,

[0150] The blade-shaped portion comprises:

[0151] a pressure surface forming wall (such as the pressure surface forming wall 44 described above) that forms a pressure surface (such as the pressure surface 40 described above);

[0152] A negative pressure surface forming wall (such as the negative pressure surface forming wall 38 described above) that forms a negative pressure surface (such as the negative pressure surface 36 described above); and

[0153] a leading edge partition wall (such as the leading edge partition wall 48 described above) extending from the inner surface of the negative pressure surface forming wall to the inner surface of the pressure surface forming wall in a manner that divides the cavity inside the blade-shaped portion,

[0154] In a cross section of the blade-shaped portion that is orthogonal to the blade height direction, the first film cooling hole, the second film cooling hole, and the third film cooling hole are each located upstream of a position (e.g., the above-mentioned position G) where the pressure surface forming wall is connected to the leading edge partition wall in the axial direction of the gas turbine.

[0155] Since the stagnation point of the flow of the combustion gas on the outer surface of the leading edge portion of the blade-shaped portion occurs at a position on the upstream side of the position where the pressure surface forming wall is connected to the leading edge portion partition wall, according to the gas turbine stator described in (5) above, by arranging the second film cooling hole row in such a manner that the second film cooling holes are located at the position of the stagnation point of the flow of the combustion gas on the outer surface of the leading edge portion of the blade-shaped portion or in the vicinity of the position, the film cooling of the outer surface of the leading edge portion can be effectively performed with a smaller amount of cooling air, and a gas turbine stator blade can be provided that can reduce the amount of cooling air and suppress the reduction in the film efficiency of film cooling on the blade surface.

[0156] (6) In some embodiments, in the gas turbine stator blade described in any one of (1) to (5) above,

[0157] The first film-cooling hole, the second film-cooling hole, and the third film-cooling hole each extend in a direction inclined with respect to a plane orthogonal to the blade height direction.

[0158] According to the gas turbine stator blade described in (6) above, compared with the case where the first film cooling hole, the second film cooling hole and the third film cooling hole extend respectively in the wall thickness direction of the leading edge portion, film cooling of the outer surface of the leading edge portion can be effectively performed with a smaller amount of cooling air, and a gas turbine stator blade can be provided that can reduce the amount of cooling air and suppress the reduction in film efficiency of film cooling on the blade surface.

[0159] (7) In some embodiments, in the gas turbine stator blade described in any one of (1) to (6) above,

[0160] The plurality of third film cooling holes include: a plurality of outer third film cooling holes (such as the plurality of outer third film cooling holes 731 mentioned above), which are located at a position further outward than the first position (such as the first position K1 mentioned above) in the blade height direction; and a plurality of inner third film cooling holes (such as the plurality of inner third film cooling holes 732 mentioned above), which are located at a position further inward than the first position in the blade height direction.

[0161] The outer third film cooling hole extends in a manner tending to the inner side in the blade height direction as it goes from the inlet (for example, the inlet 73a described above) to the outlet (for example, the outlet 73b described above) of the outer third film cooling hole.

[0162] The inner third film-cooling hole extends toward the outer side in the blade height direction as it goes from an inlet (for example, the inlet 73 a described above) to an outlet (for example, the outlet 73 b described above) of the inner third film-cooling hole.

[0163] According to the gas turbine stator blade described in (7) above, compared with the case where the outer third film cooling hole and the inner third film cooling hole extend in the wall thickness direction of the leading edge portion, respectively, film cooling of the outer surface of the leading edge portion can be effectively performed with a smaller amount of cooling air. In addition, the outer third film cooling hole extends in a manner that approaches the inner side in the blade height direction as it moves from the inlet of the outer third film cooling hole to the outlet. Therefore, compared with the case where the outer third film cooling hole extends in a manner that approaches the outer side in the blade height direction as it moves from the inlet of the outer third film cooling hole to the outlet, when the outer third film cooling hole is formed from the outer surface side of the blade-shaped portion using a jig, for example, by laser processing, interference between the jig and each of the outer shroud and the inner shroud can be suppressed. In addition, since the inner third film cooling hole extends in a manner tending to the outside in the blade height direction as it goes from the inlet to the outlet of the inner third film cooling hole, compared with the case where the inner third film cooling hole extends in a manner tending to the inside in the blade height direction as it goes from the inlet to the outlet of the inner third film cooling hole, when the inner third film cooling hole is formed from the outer surface side of the blade-shaped portion by laser processing or the like using a clamp, interference between the clamp and each of the outer shroud and the inner shroud can be suppressed.

[0164] (8) In some embodiments, in addition to the gas turbine stator blade described in (7),

[0165] The gas turbine stator blade comprises:

[0166] An outer shroud (such as the outer shroud 22 described above), connected to the outer end of the blade-shaped portion in the blade height direction; and

[0167] An inner shroud (such as the inner shroud 24 mentioned above) connected to the inner end of the blade-shaped portion in the blade height direction,

[0168] In a cross section including the axis of the third film cooling hole and the blade height direction (eg Fig.12In the cross-section shown in the figure, when the outer shroud and the inner shroud having a larger protrusion from the leading edge portion in the direction perpendicular to the blade height direction is defined as a large shroud (for example, the large shroud 90 mentioned above), and the outer shroud and the inner shroud that is not the large shroud is defined as a small shroud (for example, the small shroud 91 mentioned above), the distance between the first position in the blade height direction and the large shroud (for example, the distance V90 mentioned above) is greater than the distance between the first position in the blade height direction and the small shroud (for example, the distance V91 mentioned above).

[0169] When the outer third film cooling hole and the inner third film cooling hole are formed from the outer surface side of the blade-shaped portion by laser processing, for example, using a jig, the large shroud having a large protrusion from the leading edge in the direction perpendicular to the blade height direction is more likely to cause interference with the jig than the small shroud. Therefore, as described in (8) above, by making the distance between the first position in the blade height direction and the large shroud larger than the distance between the first position in the blade height direction and the small shroud, the interference between the jig and each of the outer and inner shrouds can be suppressed, and the outer third film cooling hole and the inner third film cooling hole can be formed respectively.

[0170] (9) In some embodiments, in addition to the gas turbine stator blade described in (7) or (8),

[0171] The plurality of first film cooling holes include: a plurality of outer first film cooling holes (such as the plurality of outer first film cooling holes 711 mentioned above), which are located at a position further outward than the first position in the blade height direction; and a plurality of inner first film cooling holes (such as the plurality of inner first film cooling holes 712 mentioned above), which are located at a position further inward than the first position in the blade height direction.

[0172] The outer first film cooling hole extends in a manner tending to the inner side in the blade height direction as it goes from the inlet (for example, the inlet 71 a described above) to the outlet (for example, the outlet 71 b described above) of the outer first film cooling hole.

[0173] The inner first film cooling hole extends toward the outer side in the blade height direction as it goes from the inlet (for example, the inlet 71 a described above) to the outlet (for example, the outlet 71 b described above) of the inner first film cooling hole.

[0174] The plurality of second film cooling holes include: a plurality of outer second film cooling holes (such as the plurality of outer second film cooling holes 721 mentioned above), which are located at a position further outward than the first position in the blade height direction; and a plurality of inner second film cooling holes (such as the plurality of inner second film cooling holes 722 mentioned above), which are located at a position further inward than the first position in the blade height direction.

[0175] The outer second film cooling hole extends in a manner tending to the inner side in the blade height direction as it goes from the inlet (for example, the inlet 72 a described above) to the outlet (for example, the outlet 72 b described above) of the outer second film cooling hole.

[0176] The inner second film-cooling hole extends toward the outer side in the blade height direction as it goes from an inlet (for example, the inlet 72 a described above) to an outlet (for example, the outlet 72 b described above) of the inner second film-cooling hole.

[0177] According to the gas turbine stator blade described in (9) above, compared with the case where the outer first film cooling hole and the inner first film cooling hole extend in the wall thickness direction of the leading edge portion, respectively, film cooling of the outer surface of the leading edge portion can be effectively performed with a smaller amount of cooling air. In addition, the outer first film cooling hole extends in a manner that approaches the inner side in the blade height direction as it moves from the inlet of the outer first film cooling hole to the outlet. Therefore, compared with the case where the outer first film cooling hole extends in a manner that approaches the outer side in the blade height direction as it moves from the inlet of the outer first film cooling hole to the outlet, when the outer first film cooling hole is formed from the outer surface side of the blade-shaped portion using a jig, for example, by laser processing, interference between the jig and each of the outer shroud and the inner shroud can be suppressed. In addition, since the inner first film cooling hole extends in a manner that goes toward the outside in the blade height direction as it goes from the inlet to the outlet of the inner first film cooling hole, when the inner first film cooling hole is formed from the outer surface side of the blade-shaped portion by laser processing or the like using a jig, interference between the jig and each of the outer shroud and the inner shroud can be suppressed. In addition, compared with the case where the outer second film cooling hole and the inner second film cooling hole extend in the wall thickness direction of the leading edge portion, respectively, film cooling of the outer surface of the leading edge portion can be effectively performed with a smaller amount of cooling air. In addition, the outer second film cooling hole extends inwardly in the blade height direction as it goes from the inlet to the outlet of the outer second film cooling hole, so when the outer second film cooling hole is formed from the outer surface side of the blade-shaped portion using a jig, for example, by laser processing, it is possible to suppress interference between the jig and each of the outer shroud and the inner shroud, compared with a case where the outer second film cooling hole extends inwardly in the blade height direction as it goes from the inlet to the outlet of the outer second film cooling hole. In addition, since the inner second film cooling hole extends inwardly in the blade height direction as it goes from the inlet to the outlet of the inner second film cooling hole, when the inner second film cooling hole is formed from the outer surface side of the blade-shaped portion using a jig, it is possible to suppress interference between the jig and each of the outer shroud and the inner shroud, compared with a case where the inner second film cooling hole extends inwardly in the blade height direction as it goes from the inlet to the outlet of the inner second film cooling hole.

[0178] (10) In some embodiments, in the gas turbine stator blade described in any one of (9) above,

[0179] The gas turbine stator blade comprises:

[0180] An outer shroud (such as the outer shroud 22 described above), connected to the outer end of the blade-shaped portion in the blade height direction; and

[0181] An inner shroud (such as the inner shroud 24 mentioned above) connected to the inner end of the blade-shaped portion in the blade height direction,

[0182] If the cross section including the axis of the first film cooling hole and the blade height direction (for example Figure 6 In the cross section shown in FIG. 1 , the protrusion amount of the outer shroud from the leading edge portion in the direction perpendicular to the blade height direction is set to A1, and the protrusion amount of the inner shroud from the leading edge portion in the direction perpendicular to the blade height direction is set to B1,

[0183] In a cross section including the axis of the second film cooling hole and the blade height direction (eg Fig. 9 In the cross section shown in FIG. 1 , the protrusion amount of the outer shroud from the leading edge portion in the direction perpendicular to the blade height direction is set to A2, and the protrusion amount of the inner shroud from the leading edge portion in the direction perpendicular to the blade height direction is set to B2,

[0184] In a cross section including the axis of the third film cooling hole and the blade height direction (eg Fig.12 In the cross section shown in FIG. 1 , the protrusion amount of the outer shroud from the leading edge portion in the direction perpendicular to the blade height direction is set to A3, and the protrusion amount of the inner shroud from the leading edge portion in the direction perpendicular to the blade height direction is set to B3,

[0185] When the outer shroud and the inner shroud that has the largest protrusion amount among the protrusion amounts A1, A2, A3, B1, B2, and B3 is defined as a large shroud (for example, the large shroud 90 mentioned above), and the outer shroud and the inner shroud that is not the large shroud is defined as a small shroud (for example, the small shroud 91 mentioned above), the distance between the first position in the blade height direction and the large shroud (for example, the distance V90 mentioned above) is greater than the distance between the first position in the blade height direction and the small shroud (for example, the distance V91 mentioned above).

[0186] When the first to third film cooling holes are formed from the outer surface side of the blade-shaped portion using a jig, for example, by laser processing, the large shroud having the maximum protrusion amount from the leading edge portion in the direction perpendicular to the blade height direction is more likely to cause interference with the jig than the small shroud. Therefore, as described in (10) above, by making the distance between the first position in the blade height direction and the large shroud greater than the distance between the first position in the blade height direction and the small shroud, the interference between the jig and each of the outer shroud and the inner shroud can be suppressed, and the first to third film cooling holes can be formed respectively.

[0187] (11) In some embodiments, in the gas turbine stator blade described in any one of (7) to (10) above,

[0188] The outer third film cooling hole comprises:

[0189] a circular hole portion (such as the circular hole portion 82 described above), which is a portion of the inlet side of the outer third film-cooling hole and has a circular cross-sectional shape; and

[0190] a special-shaped hole portion (such as the special-shaped hole portion 83 described above), which is a portion on the outlet side of the outer third film cooling hole and is connected to the circular hole portion, and whose cross-sectional area increases as it approaches the outlet of the outer third film cooling hole,

[0191] The inner third film cooling hole comprises:

[0192] a circular hole portion (such as the circular hole portion 84 described above), which is a portion of the inlet side of the inner third film-cooling hole and has a circular cross-sectional shape; and

[0193] a special-shaped hole portion (such as the special-shaped hole portion 85 described above), which is a portion on the outlet side of the inner third film cooling hole and is connected to the circular hole portion, and whose cross-sectional area increases as it approaches the outlet of the inner third film cooling hole,

[0194] The center of the outlet of the outer third film cooling hole (eg Fig.13A The center C3b) is located at a position on the inner side in the blade height direction than the intersection point (for example, the intersection point S31) of the extension line of the axis line (for example, the above-mentioned axis line L82) of the circular hole portion of the outer third film cooling hole and the outlet of the outer third film cooling hole,

[0195] The center of the outlet of the inner third film cooling hole (eg Fig. 13B The center C3b) is located at a position further outward in the blade height direction than an intersection point (for example, the above-mentioned intersection point S32) of an extension line of the axis line of the circular hole portion of the inner third film-cooling hole (for example, the above-mentioned axis line L84) and the outlet of the inner third film-cooling hole.

[0196] According to the gas turbine stator blade described in (11) above, compared with the case where the center of the outlet of the outer third film cooling hole and the center of the outlet of the inner third film cooling hole are respectively located on the extension line of the axis of the circular hole portion of the outer third film cooling hole and the extension line of the axis of the circular hole portion of the inner third film cooling hole, it is possible to effectively perform film cooling on the outer surface of the leading edge portion with a smaller amount of cooling air, and a gas turbine stator blade can be provided that can reduce the amount of cooling air and suppress the reduction in film efficiency of film cooling on the blade surface.

[0197] (12) In some embodiments, in the gas turbine stator blade described in any one of (9) to (11) above,

[0198] The outer first film cooling hole comprises:

[0199] a circular hole portion (such as the circular hole portion 74 described above), which is a portion of the inlet side of the outer first film-cooling hole and has a circular cross-sectional shape; and

[0200] a special-shaped hole portion (such as the special-shaped hole portion 75 described above), which is a portion on the outlet side of the outer first film cooling hole and is connected to the circular hole portion, and whose cross-sectional area increases as it approaches the outlet of the outer first film cooling hole,

[0201] The inner first film cooling hole comprises:

[0202] a circular hole portion (such as the circular hole portion 76 described above), which is a portion of the inlet side of the inner first film-cooling hole and has a circular cross-sectional shape; and

[0203] a special-shaped hole portion (e.g., the special-shaped hole portion 77 described above), which is a portion on the outlet side of the inner first film cooling hole and is connected to the circular hole portion of the inner first film cooling hole, and whose cross-sectional area increases as it approaches the outlet of the inner first film cooling hole,

[0204] The center of the outlet of the outer first film cooling hole (eg Fig. 7A The center C1b) is located at a position on the inner side in the blade height direction than the intersection point (for example, the intersection point S11) of the extension line of the axis line of the circular hole portion of the outer first film cooling hole (for example, the above-mentioned axis line L74) and the outlet of the outer first film cooling hole,

[0205] The center of the outlet of the inner first film cooling hole (eg Figure 7B The center C1b) is located at a position outside the blade height direction relative to the intersection point (for example, the intersection point S12) of the extension line of the axis line of the circular hole portion of the inner first film cooling hole (for example, the above-mentioned axis line L76) and the outlet of the inner first film cooling hole,

[0206] The outer second film cooling hole comprises:

[0207] a circular hole portion (such as the circular hole portion 78 described above), which is a portion of the inlet side of the outer second film-cooling hole and has a circular cross-sectional shape; and

[0208] a shaped hole portion (e.g., the shaped hole portion 79 described above), which is a portion on the outlet side of the outer second film cooling hole and is connected to the circular hole portion of the outer second film cooling hole, and whose cross-sectional area increases as it approaches the outlet of the outer second film cooling hole,

[0209] The inner second film cooling hole comprises:

[0210] a circular hole portion (such as the circular hole portion 80 described above), which is a portion of the inlet side of the inner second film-cooling hole and has a circular cross-sectional shape; and

[0211] a special-shaped hole portion (such as the special-shaped hole portion 81 described above), which is a portion on the outlet side of the inner second film cooling hole and is connected to the circular hole portion of the inner second film cooling hole, and whose cross-sectional area increases as it approaches the outlet of the inner second film cooling hole,

[0212] The center of the outlet of the outer second film cooling hole (eg Fig. 10A The center C2b) is located at a position on the inner side in the blade height direction than the intersection point (for example, the intersection point S21) of the extension line of the axis line (for example, the above-mentioned axis line L78) of the circular hole portion of the outer second film cooling hole and the outlet of the outer second film cooling hole,

[0213] The center of the outlet of the inner second film cooling hole (eg Fig. 10B The center C2b) is located at a position further outward in the blade height direction than an intersection point (for example, the above-mentioned intersection point S22) of an extension line of the axis line of the circular hole portion of the inner second film-cooling hole (for example, the above-mentioned axis line L80) and the outlet of the inner second film-cooling hole.

[0214] According to the gas turbine stator blade described in (12), compared with a case where the center of the outlet of the outer first film cooling hole and the center of the outlet of the inner first film cooling hole are respectively located on the extension line of the axis of the circular hole portion of the outer first film cooling hole and the extension line of the axis of the circular hole portion of the inner first film cooling hole, film cooling of the outer surface of the leading edge portion can be effectively performed with a smaller amount of cooling air, and a gas turbine stator blade can be provided that can reduce the amount of cooling air and suppress the reduction of the film efficiency of film cooling on the blade surface. In addition, compared with a case where the center of the outlet of the outer second film cooling hole and the center of the outlet of the inner second film cooling hole are respectively located on the extension line of the axis of the circular hole portion of the outer second film cooling hole and the extension line of the axis of the circular hole portion of the inner second film cooling hole, film cooling of the outer surface of the leading edge portion can be effectively performed with a smaller amount of cooling air, and a gas turbine stator blade can be provided that can reduce the amount of cooling air and suppress the reduction of the film efficiency of film cooling on the blade surface.

[0215] (13) In some embodiments, in the gas turbine stator blade described in (12) above,

[0216] When the irregular hole portion of the outer first film cooling hole is viewed in the axial direction of the circular hole portion of the outer first film cooling hole, the cross-sectional area is expanded only toward the inner side in the blade height direction relative to the circular hole portion of the outer first film cooling hole.

[0217] When the irregular hole portion of the inner first film cooling hole is viewed in the axial direction of the circular hole portion of the inner first film cooling hole, the cross-sectional area is expanded only toward the outside in the blade height direction relative to the circular hole portion of the inner first film cooling hole.

[0218] When the irregular hole portion of the outer second film cooling hole is viewed in the axial direction of the circular hole portion of the outer second film cooling hole, the cross-sectional area is expanded only toward the inner side in the blade height direction relative to the circular hole portion of the outer second film cooling hole.

[0219] When the irregular hole portion of the inner second film cooling hole is viewed in the axial direction of the circular hole portion of the inner second film cooling hole, the cross-sectional area is expanded only toward the outside in the blade height direction relative to the circular hole portion of the inner second film cooling hole.

[0220] When the irregular hole portion of the outer third film cooling hole is viewed in the axial direction of the circular hole portion of the outer third film cooling hole, the cross-sectional area is expanded only toward the inner side in the blade height direction relative to the circular hole portion of the outer third film cooling hole.

[0221] The irregular hole portion of the third inner film cooling hole expands its cross-sectional area only toward the outer side in the blade height direction relative to the circular hole portion of the third inner film cooling hole when viewed in the axial direction of the circular hole portion of the third inner film cooling hole.

[0222] According to the gas turbine stator blade described in (13) above, by making the cross-sectional area of ​​each of the irregularly shaped hole portions of the outer first film cooling hole, the outer second film cooling hole and the outer third film cooling hole expand only toward the inner side in the blade height direction relative to the circular hole portion, the outer first film cooling hole, the outer second film cooling hole and the outer third film cooling hole can be easily formed by laser processing or the like. In addition, by making the cross-sectional area of ​​each of the irregularly shaped hole portions of the inner first film cooling hole, the inner second film cooling hole and the inner third film cooling hole expand only toward the outer side in the blade height direction relative to the circular hole portion, the inner first film cooling hole, the inner second film cooling hole and the inner third film cooling hole can be easily formed by laser processing or the like. Therefore, the manufacture of the gas turbine stator blade becomes easy.

[0223] (14) A gas turbine according to at least one embodiment of the present disclosure includes a compressor (for example, the compressor 4 described above), a combustor (for example, the combustor 6 described above), and a turbine (for example, the turbine 8 described above).

[0224] The turbine includes the gas turbine stator blade described in any one of (1) to (13) above.

[0225] According to the gas turbine stator described in (14) above, since it is equipped with the gas turbine stator described in any one of (1) to (13) above, it is possible to effectively perform film cooling on the outer surface of the leading edge portion with a smaller amount of cooling air, and it is possible to provide a gas turbine stator blade that can reduce the amount of cooling air and suppress the reduction in the film efficiency of film cooling on the blade surface.

[0226] Description of reference numerals:

[0227] 2 Gas Turbine

[0228] 4. Compressor

[0229] 6 Burners

[0230] 8 Turbine

[0231] 9 rotors

[0232] 10 Turbine housing

[0233] 12 turbine stator blades

[0234] 16 turbine blades

[0235] 20 blade-shaped portion

[0236] 20a Outer end

[0237] 20b medial end

[0238] 21 Front edge

[0239] 22 Outer shroud

[0240] 24 Inner shroud

[0241] 25 External surface

[0242] 26, 39, 45 inner surface

[0243] 31 flow path

[0244] 32 Outer chamber

[0245] 33 Outer wall

[0246] 34Inner chamber

[0247] 35 Inner wall

[0248] 36 Negative pressure surface

[0249] 38 Negative pressure surface forming wall

[0250] 40 Pressure surface

[0251] 42 blade inner chamber

[0252] 44 Pressure surface forming wall

[0253] 46 Leading edge side chamber

[0254] 48 front edge next door

[0255] 49 trailing edge chamber

[0256] 50 Inserts

[0257] 51 Interior Space

[0258] 52 impact cooling holes

[0259] 71 First film cooling hole

[0260] 711 outer first film cooling hole

[0261] 712 Inner first film cooling hole

[0262] 72 Second film cooling holes

[0263] 721 Outer second film cooling hole

[0264] 722 inner second film cooling hole

[0265] Entrances 71a, 72a, 73a

[0266] Exits 71b, 72b, 73b

[0267] 73 Third film cooling hole

[0268] 731 Outer third film cooling hole

[0269] 732 inner third film cooling hole

[0270] 74, 76, 78, 80, 82, 84 round hole

[0271] 75, 77, 79, 81, 83, 85 special-shaped holes

[0272] 90, 92 large shield

[0273] 91, 93 small shields.

Claims

1. A gas turbine stator blade, wherein: The gas turbine stator blade includes a blade-shaped portion having a cavity formed therein. The leading edge of the blade-shaped portion is formed with: A first film cooling hole row, comprising a plurality of first film cooling holes arranged along a height direction of the blade; A second film cooling hole array, comprising a plurality of second film cooling holes arranged along a height direction of the blade; as well as a third film cooling hole row, comprising a plurality of third film cooling holes arranged along the height direction of the blade, The second film cooling hole row is arranged between the first film cooling hole row and the third film cooling hole row, The first film cooling hole extends in a direction inclined with respect to the wall thickness direction of the leading edge portion, and when a plane including the wall thickness direction of the leading edge portion and the blade height direction at the center of the inlet of the first film cooling hole is defined as a first plane, the center of the outlet of the first film cooling hole is located at a position downstream of a flow of the combustion gas along the leading edge portion relative to a position where the first plane intersects with an outer surface of the leading edge portion, The second film cooling hole extends in a direction inclined relative to the wall thickness direction of the leading edge portion, and when a plane including the wall thickness direction of the leading edge portion and the blade height direction at the center of the inlet of the second film cooling hole is defined as a second plane, an outlet of the second film cooling hole is located at a position where the second plane intersects an outer surface of the leading edge portion, The third film cooling hole extends in a direction inclined relative to the wall thickness direction of the leading edge portion, and when a plane including the wall thickness direction of the leading edge portion and the blade height direction at the center of the inlet of the third film cooling hole is defined as a third plane, the center of the outlet of the third film cooling hole is located on the downstream side of the flow of the combustion gas along the leading edge portion than a position where the third plane intersects with the outer surface of the leading edge portion.

2. The gas turbine stator blade according to claim 1, wherein: The first film-cooling hole, the second film-cooling hole, and the third film-cooling hole are respectively located closer to the pressure surface side than the camber line in a cross section of the blade-shaped portion orthogonal to the blade height direction.

3. The gas turbine stator blade according to claim 2, wherein: In a cross section of the blade-shaped portion that is orthogonal to the blade height direction, when the intersection of the median camber line and the outer surface of the leading edge portion is set as E1 and the most upstream position of the blade-shaped portion in the axial direction of the gas turbine is set as E2, the outlet of the first film cooling hole is located between the intersection E1 and the most upstream position E2 of the outer surface of the blade-shaped portion, and the outlet of the third film cooling hole is located on the outer surface of the blade-shaped portion on the opposite side of the intersection E1 across the most upstream position E2.

4. The gas turbine stator blade according to claim 3, wherein: In a cross section of the blade-shaped portion orthogonal to the blade height direction, the outlet of the second film-cooling hole is located on the outer surface of the blade-shaped portion on the opposite side of the intersection E1 across the most upstream position E2.

5. The gas turbine stator blade according to claim 1, wherein: The blade-shaped portion comprises: The pressure surface forms a wall, which forms a pressure surface; a suction surface forming wall forming a suction surface; and a leading edge partition wall extending from the inner surface of the negative pressure surface forming wall to the inner surface of the pressure surface forming wall in a manner that divides the cavity inside the blade-shaped portion, In a cross section of the blade-shaped portion orthogonal to the blade height direction, the first film cooling hole, the second film cooling hole, and the third film cooling hole are each located upstream of a position where the pressure surface forming wall is connected to the leading edge partition wall in the axial direction of the gas turbine.

6. The gas turbine stator blade according to claim 1, wherein: The first film-cooling hole, the second film-cooling hole, and the third film-cooling hole each extend in a direction inclined with respect to a plane orthogonal to the blade height direction.

7. The gas turbine stator blade according to claim 1, wherein: The plurality of third film cooling holes include: a plurality of outer third film cooling holes located at a position outward from a first position in the blade height direction; and a plurality of inner third film cooling holes located at a position inward from the first position in the blade height direction. The outer third film cooling hole extends in a manner that it approaches the inner side in the blade height direction as it approaches from the inlet to the outlet of the outer third film cooling hole. The inner third film-cooling hole extends toward an outer side in the blade height direction as going from an inlet to an outlet of the inner third film-cooling hole.

8. The gas turbine stator blade according to claim 7, wherein: The gas turbine stator blade comprises: an outer shroud connected to an outer end of the blade-shaped portion in the blade height direction; and an inner shroud connected to the inner end of the blade-shaped portion in the blade height direction, In a cross section including the axis of the third film cooling hole and the blade height direction, when the outer shroud and the inner shroud having a larger protrusion amount from the portion of the blade-shaped portion having the third film cooling hole row formed therein in a direction perpendicular to the blade height direction is defined as a large shroud and the outer shroud and the inner shroud that is not the large shroud is defined as a small shroud, the distance between the first position in the blade height direction and the large shroud is greater than the distance between the first position in the blade height direction and the small shroud.

9. The gas turbine stator blade according to claim 7, wherein: The plurality of first film cooling holes include: a plurality of outer first film cooling holes located at positions outward from the first position in the blade height direction; and a plurality of inner first film cooling holes located at positions inward from the first position in the blade height direction. The outer first film cooling hole extends in a manner tending to the inner side in the blade height direction as it goes from the inlet to the outlet of the outer first film cooling hole. The inner first film cooling hole extends in a manner tending toward the outer side in the blade height direction as it goes from the inlet to the outlet of the inner first film cooling hole. The plurality of second film cooling holes include: a plurality of outer second film cooling holes located at positions outward from the first position in the blade height direction; and a plurality of inner second film cooling holes located at positions inward from the first position in the blade height direction. The outer second film-cooling hole extends in a manner that it approaches the inner side in the blade height direction as it approaches from the inlet to the outlet of the outer second film-cooling hole. The inner second film-cooling hole extends toward an outer side in the blade height direction as going from an inlet to an outlet of the inner second film-cooling hole.

10. The gas turbine stator blade according to claim 9, wherein: The gas turbine stator blade comprises: an outer shroud connected to an outer end of the blade-shaped portion in the blade height direction; and an inner shroud connected to the inner end of the blade-shaped portion in the blade height direction, If, in a cross section including the axis of the first film cooling hole and the blade height direction, the amount of protrusion of the outer shroud from the portion of the blade-shaped portion where the first film cooling hole row is formed in the direction perpendicular to the blade height direction is set to A1, and the amount of protrusion of the inner shroud from the portion of the blade-shaped portion where the first film cooling hole row is formed in the direction perpendicular to the blade height direction is set to B1, In a cross section including the axis of the second film cooling hole and the blade height direction, a protrusion amount of the outer shroud from a portion of the blade-shaped portion where the second film cooling hole row is formed in a direction perpendicular to the blade height direction is set to A2, and a protrusion amount of the inner shroud from a portion of the blade-shaped portion where the second film cooling hole row is formed in a direction perpendicular to the blade height direction is set to B2, In a cross section including the axis of the third film cooling hole and the blade height direction, a protrusion amount of the outer shroud from a portion of the blade-shaped portion where the third film cooling hole row is formed in a direction perpendicular to the blade height direction is set to A3, and a protrusion amount of the inner shroud from a portion of the blade-shaped portion where the third film cooling hole row is formed in a direction perpendicular to the blade height direction is set to B3, When the outer shroud and the inner shroud that has the largest protrusion amount among the protrusion amounts A1, A2, A3, B1, B2, and B3 is defined as a large shroud, and the outer shroud and the inner shroud that is not the large shroud is defined as a small shroud, the distance between the first position in the blade height direction and the large shroud is greater than the distance between the first position in the blade height direction and the small shroud.

11. The gas turbine stator blade according to claim 7, wherein: The outer third film cooling hole comprises: a circular hole portion which is a portion of the inlet side of the outer third film-cooling hole and has a circular cross-sectional shape; and a special-shaped hole portion which is a portion on the outlet side of the outer third film cooling hole and is connected to the circular hole portion, and whose cross-sectional area increases as it approaches the outlet of the outer third film cooling hole, The inner third film cooling hole comprises: a circular hole portion which is a portion of the inlet side of the inner third film-cooling hole and has a circular cross-sectional shape; and a special-shaped hole portion which is a portion on the outlet side of the inner third film cooling hole and is connected to the circular hole portion, and whose cross-sectional area increases as it approaches the outlet of the inner third film cooling hole, The center of the outlet of the outer third film cooling hole is located inward of the intersection of the extension line of the axis of the circular hole portion of the outer third film cooling hole and the outlet of the outer third film cooling hole in the blade height direction. The center of the outlet of the inner third film cooling hole is located outside the blade height direction relative to an intersection of an extension line of the axis of the circular hole portion of the inner third film cooling hole and the outlet of the inner third film cooling hole.

12. The gas turbine stator blade according to claim 9, wherein: The outer first film cooling hole comprises: a circular hole portion which is a portion of the inlet side of the outer first film-cooling hole and has a circular cross-sectional shape; and a special-shaped hole portion which is a portion on the outlet side of the outer first film cooling hole and is connected to the circular hole portion, and whose cross-sectional area increases as it approaches the outlet of the outer first film cooling hole, The inner first film cooling hole comprises: a circular hole portion which is a portion of the inlet side of the inner first film-cooling hole and has a circular cross-sectional shape; and a special-shaped hole portion which is a portion on the outlet side of the inner first film cooling hole and is connected to the circular hole portion of the inner first film cooling hole, and whose cross-sectional area increases as it approaches the outlet of the inner first film cooling hole, The center of the outlet of the outer first film cooling hole is located inward of the intersection of the extension line of the axis of the circular hole portion of the outer first film cooling hole and the outlet of the outer first film cooling hole in the blade height direction. The center of the outlet of the inner first film cooling hole is located outside the intersection of the extension line of the axis of the circular hole portion of the inner first film cooling hole and the outlet of the inner first film cooling hole in the blade height direction. The outer second film cooling hole comprises: a circular hole portion which is a portion of the inlet side of the outer second film-cooling hole and has a circular cross-sectional shape; and a special-shaped hole portion which is a portion on the outlet side of the outer second film cooling hole and is connected to the circular hole portion of the outer second film cooling hole, and whose cross-sectional area increases as it approaches the outlet of the outer second film cooling hole, The inner second film cooling hole comprises: a circular hole portion which is a portion of the inlet side of the inner second film-cooling hole and has a circular cross-sectional shape; and a special-shaped hole portion which is a portion on the outlet side of the inner second film cooling hole and is connected to the circular hole portion of the inner second film cooling hole, and whose cross-sectional area increases as it approaches the outlet of the inner second film cooling hole, The center of the outlet of the outer second film cooling hole is located inward of the intersection of the extension line of the axis of the circular hole portion of the outer second film cooling hole and the outlet of the outer second film cooling hole in the blade height direction. The center of the outlet of the inner second film cooling hole is located outside the blade height direction relative to an intersection point of an extension line of an axis of the circular hole portion of the inner second film cooling hole and the outlet of the inner second film cooling hole.

13. The gas turbine stator blade according to claim 12, wherein: When the irregular hole portion of the outer first film cooling hole is viewed in the axial direction of the circular hole portion of the outer first film cooling hole, the cross-sectional area is expanded only toward the inner side in the blade height direction relative to the circular hole portion of the outer first film cooling hole. When the irregular hole portion of the inner first film cooling hole is viewed in the axial direction of the circular hole portion of the inner first film cooling hole, the cross-sectional area is expanded only toward the outside in the blade height direction relative to the circular hole portion of the inner first film cooling hole. When the irregular hole portion of the outer second film cooling hole is viewed in the axial direction of the circular hole portion of the outer second film cooling hole, the cross-sectional area is expanded only toward the inner side in the blade height direction relative to the circular hole portion of the outer second film cooling hole. When the irregular hole portion of the inner second film cooling hole is viewed in the axial direction of the circular hole portion of the inner second film cooling hole, the cross-sectional area is expanded only toward the outside in the blade height direction relative to the circular hole portion of the inner second film cooling hole. When the irregular hole portion of the outer third film cooling hole is viewed in the axial direction of the circular hole portion of the outer third film cooling hole, the cross-sectional area is expanded only toward the inner side in the blade height direction relative to the circular hole portion of the outer third film cooling hole. The irregular hole portion of the third inner film cooling hole expands its cross-sectional area only toward the outer side in the blade height direction relative to the circular hole portion of the third inner film cooling hole when viewed in the axial direction of the circular hole portion of the third inner film cooling hole.

14. A gas turbine, wherein: The gas turbine includes a compressor, a combustor, and a turbine. The turbine includes the gas turbine stator blade according to claim 1.

Images