Cooling fluid guide for gas turbine and gas turbine

Abstract

A cooling fluid guide for a gas turbine is provided with: a fixed part fixed to either a pipe for supplying a cooling fluid to a cooling fluid supply hole in a turbine housing or the turbine housing; and a first guide part configured so as to cover at least a part of the cooling fluid supply hole when viewed from the inside in the radial direction of the gas turbine along the axial direction of the cooling fluid supply hole in a state where the affixed part is affixed to the piping or the turbine housing.

Description

Technical Field

[0001] The present invention relates to a cooling fluid guide for a gas turbine and a gas turbine.

[0002] This application claims priority based on Japanese Patent Application No. 2022-140481 filed in Japan on September 5, 2022, and the contents are incorporated herein by reference. Background Art

[0003] Patent Document 1 describes a method of supplying cooling fluid from cooling fluid supply holes provided in a turbine casing to an outer cavity formed between an outer shroud of a gas turbine stationary blade and the turbine casing in order to cool the gas turbine stationary blade.

[0004] Previous technical literature

[0005] Patent Literature

[0006] Patent Document 1: International Publication No. 2017 / 090709 Summary of the invention

[0007] Technical issues to be solved by the invention

[0008] When cooling fluid is supplied to the gas turbine stationary blades from the cooling fluid supply holes provided in the turbine casing, the supply amount of the cooling fluid will vary between the gas turbine stationary blades located near the cooling fluid supply holes and the gas turbine stationary blades located far from the cooling fluid supply holes, and the cooling effect of the gas turbine stationary blades will vary between the above-mentioned plurality of gas turbine stationary blades.

[0009] In view of the above situation, an object of at least one embodiment of the present invention is to provide a cooling fluid guide for a gas turbine and a gas turbine including the cooling fluid guide for a gas turbine, wherein the cooling fluid guide for a gas turbine can suppress uneven cooling effect caused by cooling fluid between a plurality of gas turbine stationary blades.

[0010] Means for solving technical problems

[0011] In order to achieve the above-mentioned object, a cooling fluid guide for a gas turbine according to at least one embodiment of the present invention is a cooling fluid guide for a gas turbine for guiding a cooling fluid of a gas turbine, wherein:

[0012] The gas turbine comprises:

[0013] a plurality of turbine stationary blades; and

[0014] a turbine housing that accommodates the plurality of turbine stationary blades and is formed with cooling fluid supply holes for supplying cooling fluid to the plurality of turbine stationary blades,

[0015] The gas turbine cooling fluid guide comprises:

[0016] a fixed portion fixed to any one of a pipe for supplying the cooling fluid to the cooling fluid supply hole or the turbine housing; and

[0017] The first guide portion is configured to cover at least a portion of the cooling fluid supply hole when viewed from the inner side in the radial direction of the gas turbine along the axial direction of the cooling fluid supply hole in a state where the fixed portion is fixed to the pipe or the turbine casing.

[0018] In order to achieve the above-mentioned object, a gas turbine according to at least one embodiment of the present invention includes:

[0019] The above-mentioned cooling fluid guide for the gas turbine;

[0020] said turbine housing; and

[0021] The plurality of turbine stationary blades.

[0022] Effects of the Invention

[0023] According to at least one embodiment of the present invention, there is provided a gas turbine cooling fluid guide and a gas turbine including the gas turbine cooling fluid guide, which can suppress uneven cooling effect caused by cooling fluid between a plurality of gas turbine stationary blades. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 It is a diagram showing a schematic configuration of a gas turbine 2 according to an embodiment.

[0025] Figure 2 This is a schematic cross-sectional view showing an example of a cross section perpendicular to the axial direction in the turbine housing 10 .

[0026] Figure 3 This is a schematic cross-sectional view showing an example of a part of a cross section taken along the axial direction at the position of each cooling fluid supply hole 20 in the gas turbine 2 .

[0027] Figure 4 Yes Figure 3 The gas turbine cooling fluid guide 24A shown is a view viewed from the inside in the radial direction along the axis C of the cooling fluid supply hole 20 .

[0028] Figure 5 This is a schematic cross-sectional view showing another example of a part of the cross section taken along the axial direction at the position of each cooling fluid supply hole 20 in the gas turbine 2 . DETAILED DESCRIPTION

[0029] Hereinafter, some embodiments of the present invention will be described with reference to the accompanying drawings. The dimensions, materials, shapes, and relative arrangements of the components described or illustrated in the embodiments are not intended to limit the scope of the invention, but are merely illustrative examples.

[0030] For example, expressions such as "in a certain direction", "along a certain direction", "parallel", "orthogonal", "center", "concentric" or "coaxial" indicating relative or absolute configuration strictly speaking not only indicate such configuration, but also indicate the state of relative displacement at an angle or distance to the extent that there is a tolerance or the same function can be obtained.

[0031] For example, expressions such as “same”, “equal” and “uniform” that indicate that things are in an equal state not only strictly indicate an equal state but also indicate a state in which there is a tolerance or a difference in degree to which the same function can be obtained.

[0032] For example, expressions indicating shapes such as a quadrilateral or a cylinder not only indicate shapes such as a quadrilateral or a cylinder in a strict geometric sense, but also indicate shapes including concave-convex portions or chamfered portions as long as the same effect can be obtained.

[0033] On the other hand, describing a constituent element with words such as “having”, “configured”, “including”, “containing” or “having” is not an exclusive expression that excludes the existence of other constituent elements.

[0034] Figure 1 It is a diagram showing a schematic configuration of a gas turbine 2 according to an embodiment.

[0035] 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 the combustion gas generated by the combustor 6 .

[0036] like Figure 1 As shown, the turbine 8 includes: a rotor 9 (turbine rotor); a turbine housing 10; a plurality of turbine stationary blades 12 (gas turbine stationary blades) fixed to the inner surface of the turbine housing 10; and a plurality of turbine moving blades 16 implanted in the rotor 9 in a manner alternately arranged in the axial direction relative to the turbine stationary blades 12. The turbine housing 10 accommodates the rotor 9, the plurality of turbine stationary blades 12, and the plurality of turbine moving blades 16. Each stage of the turbine 8 includes a plurality of turbine stationary blades 12 arranged along the circumferential direction of the gas turbine 2 and a plurality of turbine moving blades 16 arranged along the circumferential direction of the gas turbine 2 on the downstream side of the plurality of turbine stationary blades 12.

[0037] Hereinafter, unless otherwise specified, the “circumferential direction” refers to the circumferential direction of the gas turbine 2, i.e., the circumferential direction of the rotor 9; unless otherwise specified, the “axial direction” refers to the axial direction of the gas turbine 2, i.e., the axial direction of the rotor 9; unless otherwise specified, the “radial direction” refers to the radial direction of the gas turbine 2, i.e., the radial direction of the rotor 9.

[0038] Figure 2 This is a schematic cross-sectional view showing an example of a cross section perpendicular to the axial direction in the turbine housing 10 .

[0039] like Figure 2 As shown, a plurality of turbine fixed blades 12 (see Figure 1 ) A plurality of cooling fluid supply holes 20 for supplying cooling fluid. The plurality of cooling fluid supply holes 20 are arranged at intervals in the circumferential direction. In the example shown in the figure, four cooling fluid supply holes 20 are arranged at equal intervals in the circumferential direction, and each of the cooling fluid supply holes 20 is a through hole that penetrates the outer surface 10a and the inner surface 10b of the turbine housing 10 in the radial direction.

[0040] Figure 3 1 is a schematic cross-sectional view showing an example of a part of a cross section cut along the axial direction at the position of each cooling fluid supply hole 20 in the gas turbine 2. In addition, since the cross sections cut along the axial direction at the position of each cooling fluid supply hole 20 in the gas turbine 2 are basically the same, the cross section cut along the axial direction of the gas turbine 2 at the position of one cooling fluid supply hole 20 will be described below.

[0041] like Figure 3 As shown, a pipe 5 for supplying a cooling fluid to the cooling fluid supply hole 20 is connected to the turbine housing 10. In the example shown in the figure, an orifice plate 41 having an orifice 40 having a diameter smaller than the inner diameter of the pipe 5 and the diameter of the cooling fluid supply hole 20 is sandwiched between a flange 5a formed at one end of the pipe 5 and the outer surface 10a of the turbine housing 10, and the flange 5a is fixed to the outer surface 10a of the turbine housing 10 by a fixing member 42 such as a bolt. In the example shown in the figure, the orifice 40 is located on the extension line of the axis C of the cooling fluid supply hole 20.

[0042] like Figure 3 As shown, each of the plurality of turbine fixed blades 12 includes an airfoil 80, an outer shroud 82, a sealing tube 84 and a heat shield 86. Figure 3 In the illustrated example, the gas turbine 2 includes a gas turbine cooling fluid guide 24A.

[0043] The airfoil 80 has an airfoil cross-sectional shape defined by a pressure surface and a negative pressure surface. The outer shroud 82 is connected to the outer end of the airfoil 80 in the blade height direction and is formed in a substantially plate-like shape along a surface intersecting the radial direction. The outer shroud 82 forms the outer peripheral wall 15 of the flow path 14 of the combustion gas in the turbine 8 (the main flow path of the combustion gas in the turbine 8). The turbine fixed blade 12 includes an inner shroud (not shown) connected to the inner end of the airfoil 80 in the blade height direction. The inner shroud is formed in a substantially plate-like shape along a surface intersecting the radial direction and forms the inner peripheral wall of the above-mentioned flow path 14. In addition, in this specification, "the upstream side in the axial direction" refers to the upstream side of the main flow of the combustion gas of the turbine 8 in the axial direction (the flow of the combustion gas flowing through the flow path 14), and "the downstream side in the axial direction" refers to the downstream side of the main flow of the combustion gas of the turbine 8 in the axial direction (the flow of the combustion gas flowing through the flow path 14).

[0044] The sealing tube 84 is arranged in an internal passage (not shown) of the airfoil 80 and is formed in a tubular shape. The sealing tube 84 is formed so as to guide air in the outer cavity 85 formed between the outer shroud 82 and the turbine casing 10 to the inner side of the turbine stator blade 12 through the inside of the airfoil 80 .

[0045] The compressed air from the compressor 4 is supplied as cooling air to the outer cavity 85 through the cooling fluid supply hole 20. The cooling air flowing from the outer cavity 85 into the sealing pipe 84 is guided to the inner side of the turbine stationary blade 12 in the radial direction and supplied to the turbine stationary blade 12 and the turbine rotor blade 16 adjacent to the upstream side of the turbine stationary blade 12 (see FIG. Figure 1 ) and further acts as cooling air in the interstage space (not shown) between the stages.

[0046] The heat shield 86 is attached to the radially outer surface 83 of the outer shroud 82 as an accessory of the turbine stator blade 12. The heat shield 86 is provided so as to cover at least a portion of the outer surface 83 of the outer shroud 82. In the example shown in the figure, the heat shield 86 includes: a plate-shaped top plate portion 87, which is arranged parallel to the surface 83 with a gap between it and the surface 83 in the blade height direction; and a side wall portion 88, which is connected to the periphery of the top plate portion 87 and is provided so as to surround the sealing tube 84. The side wall portion 88 is fixed to the surface 83 of the outer shroud 82 by welding, for example.

[0047] Figure 4 Yes Figure 3 The gas turbine cooling fluid guide 24A shown is a view viewed from the inside in the radial direction along the axis C of the cooling fluid supply hole 20 .

[0048] In some embodiments, for example, Figure 3 and Figure 4As shown, the gas turbine 2 is provided with a gas turbine cooling fluid guide 24A for guiding the cooling fluid of the gas turbine 2. The gas turbine cooling fluid guide 24A is provided for each cooling fluid supply hole 20. The gas turbine cooling fluid guide 24A includes a plurality of fixed portions 26, a first guide portion 28 (a baffle), and a plurality of second guide portions 30 (a plurality of side plates). In the example shown in the figure, each of the plurality of fixed portions 26, the first guide portion 28, and each of the plurality of second guide portions 30 is formed in a plate shape having a substantially quadrilateral cross section. In addition, the cooling fluid supply hole 20 has a circular cross-sectional shape. The first guide portion 28 is located radially inside the fixed portions 26a, 26b.

[0049] In the example shown in the figure, the plurality of fixed portions 26 include two fixed portions 26a and 26b, and the plurality of second guide portions 30 include two second guide portions 30a and 30b (an upstream second guide portion and a downstream second guide portion). The plate-shaped fixed portions 26a and 26b are each arranged along the inner surface 10b of the turbine housing 10, and are fixed to the inner surface 10b of the turbine housing 10 by a fixing member 27 such as a bolt. The fixed portion 26a is provided on the upstream side of the cooling fluid supply hole 20 in the axial direction, and the fixed portion 26b is provided on the downstream side of the cooling fluid supply hole 20 in the axial direction.

[0050] For example, Figure 3 As shown in FIG. 2 , the fixed portion 26a is connected to the outer end portion 31 (outer end) of the second guide portion 30a in the radial direction, and protrudes from the end portion 31 toward the downstream side in the axial direction. Figure 4 As shown in FIG. 1 , a notch-shaped recessed portion 33 is formed on the downstream end edge 32 of the fixed portion 26 in the axial direction, and the recessed portion 33 is recessed toward the upstream side in the axial direction. In the radial view, a portion of the cooling fluid supply hole 20 is located inside the recessed portion 33. In the radial view, the first guide portion 28 is sandwiched between the fixed portion 26a and is fixed to the inner surface 10b of the turbine housing 10 by the fixing member 27 on both sides in the circumferential direction (refer to FIG. 1 ). Figure 3 ).

[0051] For example, Figure 3 As shown in FIG. 2 , the fixed portion 26 b is connected to the outer end portion 34 (outer end) of the second guide portion 30 b in the radial direction, and protrudes from the end portion 34 toward the downstream side in the axial direction. Figure 4 As shown, the fixed portion 26b clamps the central position of the fixed portion 26b in the circumferential direction and is fixed to the inner surface 10b of the turbine housing 10 by the fixing members 27 on both sides (refer to Figure 3 ).

[0052] exist Figure 4In the illustrated exemplary embodiment, the dimension A2 of the fixed portion 26a in the circumferential direction is larger than the dimension A1 of the first guide portion 28 in the circumferential direction, and is larger than the diameter R of the cooling fluid supply hole 20. Furthermore, the dimension A3 of the fixed portion 26b in the circumferential direction is equal to the dimension A1 of the first guide portion 28 in the circumferential direction, and is larger than the diameter R of the cooling fluid supply hole 20. Furthermore, the dimension B2 of the fixed portion 26a in the axial direction is smaller than the dimension B1 of the first guide portion 28 in the axial direction, and is smaller than the diameter R of the cooling fluid supply hole 20. Furthermore, the dimension B3 of the fixed portion 26b in the axial direction is smaller than the dimension B1 of the first guide portion 28 in the axial direction, and is smaller than the diameter R of the cooling fluid supply hole 20.

[0053] For example, Figure 4 As shown, when the first guide portion 28 is observed from the radial inner side along the axial direction of the cooling fluid supply hole 20 (i.e., along the extension line C1 of the axial line C of the cooling fluid supply hole 20), the first guide portion 28 is provided in a manner to cover at least a portion of the cooling fluid supply hole 20 (in the example shown in the figure, the entire cooling fluid supply hole 20). That is, when the first guide portion 28 is observed from the radial inner side along the axial direction of the cooling fluid supply hole 20, the first guide portion 28 is provided in a manner to overlap at least a portion of the cooling fluid supply hole 20 (in the example shown in the figure, the entire cooling fluid supply hole 20). The first guide portion 28 is located on the extension line C1 of the axial line C of the cooling fluid supply hole 20, and includes a surface 35 intersecting the extension line C1 (in the example shown in the figure, the surface 35 orthogonal to the extension line C1). The first guide portion 28 is provided in a manner to guide at least a portion of the cooling fluid that has passed through the cooling fluid supply hole 20 along the surface 35 intersecting the extension line C1.

[0054] For example, Figure 3 As shown, the plurality of turbine stator blades 12 of the gas turbine 2 include a turbine stator blade 12A (turbine stator blade on the extension line) provided on the extension line C1 of the axis line C of the cooling fluid supply hole 20, and the first guide portion 28 is located between the turbine stator blade 12A on the extension line C1 and the cooling fluid supply hole 20. Furthermore, the first guide portion 28 is located between the heat shield 86 of the turbine stator blade 12A and the cooling fluid supply hole 20.

[0055] For example, Figure 3As shown, the second guide portion 30a is formed in a plate shape including a surface 38 intersecting the axial direction (a surface orthogonal to the axial direction in the example shown in the figure), and is provided in a manner extending from an end portion 36 (upstream end) on the upstream side of the first guide portion 28 in the axial direction toward the radially outer side to the fixed portion 26a. In the example shown in the figure, the second guide portion 30a is connected to an end portion (upstream end) on the upstream side of the fixed portion 26a in the axial direction. The second guide portion 30a is provided in a manner to guide at least a portion of the cooling fluid passing through the cooling fluid supply hole 20 along the surface 38 intersecting the axial direction.

[0056] For example, Figure 3 As shown, the second guide portion 30b is formed into a plate shape including a surface 39 intersecting the axial direction (a surface orthogonal to the axial direction in the example shown in the figure), and is provided in a manner extending from an end portion 37 (downstream end) on the downstream side of the first guide portion 28 in the axial direction toward the radially outer side to the fixed portion 26b. In the example shown in the figure, the second guide portion 30b is connected to an end portion (upstream end) on the upstream side of the fixed portion 26b in the axial direction. The second guide portion 30b is provided in a manner to guide at least a portion of the cooling fluid passing through the cooling fluid supply hole 20 along the surface 39 intersecting the axial direction.

[0057] Hereinafter, some effects exerted by the above-mentioned gas turbine cooling fluid guide 24A will be described.

[0058] exist Figure 3 In the structure shown in FIG. 1 , the cooling fluid supplied from the pipe 5 to the cooling fluid supply hole 20 flows along the axial direction of the cooling fluid supply hole 20 and collides with the first guide portion 28 of the gas turbine cooling fluid guide 24A, thereby changing the flow direction to a direction intersecting the axis C of the cooling fluid supply hole 20 and guiding along the surface 35 of the first guide portion 28. Therefore, it is possible to suppress the cooling effect caused by the cooling fluid from being concentrated on the turbine stator blade 12 near the cooling fluid supply hole 20 (especially the turbine stator blade 12A located on the extension line C1 of the axis C of the cooling fluid supply hole 20), and suppress the unevenness of the cooling effect caused by the cooling fluid between the plurality of turbine stator blades 12.

[0059] And, in Figure 3In the structure shown in the figure, the cooling fluid that has collided with the first guide portion 28 through the cooling fluid supply hole 20 can be guided to flow in the circumferential direction between the surface 38 intersecting the axial direction in the second guide portion 30a and the surface 39 intersecting the axial direction in the second guide portion 30b. As a result, the cooling effect caused by the cooling fluid can be suppressed from being concentrated on the turbine stator blade 12 near the cooling fluid supply hole 20 (especially the turbine stator blade 12A located on the extension line C1 of the axis C of the cooling fluid supply hole 20), and the unevenness of the cooling effect caused by the cooling fluid between the plurality of turbine stator blades 12 can be effectively suppressed.

[0060] Furthermore, according to the knowledge of the inventors of the present application, when the heat shield 86 (an accessory of the turbine stator blade 12A) of the turbine stator blade 12A is attached to the outer surface 83 of the outer shroud 82 in the radial direction, if the cooling fluid passing through the cooling fluid supply hole 20 collides with the heat shield 86, a large fluid force and fluid vibration act on the heat shield 86, and resonance may occur under certain conditions, thereby damaging the heat shield 86. In this regard, as described above, by locating the first guide portion 28 between the heat shield 86 of the turbine stator blade 12A and the cooling fluid supply hole 20, it is possible to suppress the cooling fluid passing through the cooling fluid supply hole 20 from colliding with the heat shield 86 of the turbine stator blade 12 on the extension line C1, thereby suppressing the damage of the heat shield 86 caused by the large fluid force and fluid vibration acting on the heat shield 86.

[0061] Furthermore, assuming that the gas turbine cooling fluid guide is directly fixed to the turbine stationary blade 12 on the extension line C1 instead of the turbine casing 10, even if the cooling fluid that has passed through the cooling fluid supply hole 20 is prevented from colliding with the heat shield 86 of the turbine stationary blade 12A on the extension line C1 by the gas turbine cooling fluid guide, the vibration of the gas turbine cooling fluid guide 24A is directly transmitted to the turbine stationary blade 12A on the extension line C1, so there is a possibility that the heat shield 86 will be damaged due to the vibration.

[0062] In contrast, in the above-described embodiment, since the fixed portions 26a, 26b of the gas turbine cooling fluid guide 24A are fixed to the turbine casing 10 instead of the turbine fixed blades 12, even if the cooling fluid from the cooling fluid supply hole 20 (the cooling fluid from the throttle hole 40) collides with the gas turbine cooling fluid guide 24A, the vibration is suppressed from being transmitted to the heat insulation plate 86, and the risk of damage to the heat insulation plate 86 due to the vibration is effectively reduced.

[0063] Figure 51 is a schematic cross-sectional view showing another example of a part of a cross section cut along the axial direction at the position of each cooling fluid supply hole 20 in the gas turbine 2. In addition, since the cross sections cut along the axial direction at the position of each cooling fluid supply hole 20 in the gas turbine 2 are basically the same, the cross section cut along the axial direction of the gas turbine 2 at the position of one cooling fluid supply hole 20 will be described below.

[0064] exist Figure 5 In the embodiment shown, due to the structure of the turbine fixed blade 12 and Figure 3 The structure of the turbine stator blades 12 shown is the same, so the description thereof is omitted. Figure 5 The gas turbine 2 shown in the figure is provided with a gas turbine cooling fluid guide 24B for guiding the cooling fluid of the gas turbine 2 instead of Figure 3 The cooling fluid guide 24A for the gas turbine is shown. The cooling fluid guide 24B for the gas turbine is provided on each cooling fluid supply hole 20 .

[0065] like Figure 5 As shown, a pipe 5 for supplying a cooling fluid to the cooling fluid supply hole 20 is connected to the turbine housing 10 .

[0066] exist Figure 5 In the example shown, the gas turbine cooling fluid guide 24B includes a fixed portion 50, a first guide portion 52 (baffle) and a second guide portion 54 (porous cylinder). In the example shown, the fixed portion 50 is formed in a disc shape, the first guide portion 52 is formed in a disc shape, and the second guide portion 54 is formed in a cylindrical shape.

[0067] The fixed portion 50 is a disc-shaped flange connected to the outer end 53 of the second guide portion 54 in the radial direction, and includes an outer peripheral flange portion 50a protruding from the end 53 of the second guide portion 54 to the outer peripheral side of the second guide portion 54 (the side opposite to the axis C of the cooling fluid supply hole 20); and an inner peripheral flange portion 50b protruding from the end 53 of the second guide portion 54 to the inner peripheral side of the second guide portion 54 (the side of the axis C of the cooling fluid supply hole 20). The outer peripheral flange portion 50a is fixed to the flange 5a of the pipe 5 and the turbine housing 10 by a fixing member 42 such as a bolt while being sandwiched between the flange 5a formed at one end of the pipe 5 and the outer surface 10a of the turbine housing 10. A throttle hole 55 having a diameter smaller than each diameter of the cooling fluid supply hole 20 is formed in the inner peripheral flange portion 50b. The throttle hole 55 is located on an extension line C1 of the axis C of the cooling fluid supply hole 20 .

[0068] As described above, the first guide portion 52 has a disk shape, is connected to the end portion 57 on the inner side of the second guide portion 54 in the radial direction, and is configured as a bottom plate that closes one end side of the cylindrical second guide portion 54. The first guide portion 52 is located radially inside the fixed portion 50 and inside the second guide portion 54. When the first guide portion 52 is observed from the radial inside along the axial direction of the cooling fluid supply hole 20 (i.e., along the extension line C1 of the axis C of the cooling fluid supply hole 20), the first guide portion 52 covers at least a portion of the cooling fluid supply hole 20 (in the direction of the axis C of the cooling fluid supply hole 20). Figure 5 In other words, when the first guide portion 52 is viewed from the radially inner side along the axial direction of the cooling fluid supply hole 20, the first guide portion 52 is disposed in a manner that is aligned with at least a portion of the cooling fluid supply hole 20 (in the structure shown). Figure 5 The first guide portion 52 is provided so as to overlap with the cooling fluid supply hole 20 (in the illustrated structure, substantially the entire cooling fluid supply hole 20). The first guide portion 52 is located on the extension line C1 of the axis C of the cooling fluid supply hole 20 and includes a surface 56 intersecting the extension line C1 (in the illustrated example, the surface 56 orthogonal to the extension line C1). The first guide portion 52 is provided so as to guide at least a portion of the cooling fluid that has passed through the cooling fluid supply hole 20 along the surface 56 intersecting the extension line C1.

[0069] For example, Figure 5 As shown, the plurality of turbine stationary blades 12 of the gas turbine 2 include turbine stationary blades 12A provided on an extension line C1 of the axis line C of the cooling fluid supply hole 20, and the first guide portion 52 is located between the turbine stationary blades 12A on the extension line C1 and the cooling fluid supply hole 20. Furthermore, the first guide portion 52 is located between the heat shield 86 and the cooling fluid supply hole 20.

[0070] As described above, the second guide portion 54 has a cylindrical shape, and extends from the fixed portion 50 through the cooling fluid supply hole 20 to the first guide portion 52 along the axial direction of the cooling fluid supply hole 20. On the outer peripheral surface 58 of the second guide portion 54, a plurality of through holes 60 are formed on the inner side of the cooling fluid supply hole 20 in the radial direction. The plurality of through holes 60 are arranged on the outer peripheral surface 58 in a staggered manner. The plurality of through holes 60 include a plurality of through holes 60a and a plurality of through holes 60b. The plurality of through holes 60a are arranged at intervals along the circumferential direction of the outer peripheral surface 58 at the same position (first position) in the axial direction of the cylindrical shape of the second guide portion 54. The plurality of through holes 60b are arranged at intervals along the circumferential direction of the outer peripheral surface 58 at the same position (second position) in the axial direction of the cylindrical shape of the second guide portion 54. The positions at which the through holes 60 a are provided are offset from the positions at which the through holes 60 b are provided in the axial direction of the cylindrical shape of the second guide portion 54 and in the circumferential direction of the outer peripheral surface 58 .

[0071] Hereinafter, some effects exerted by the gas turbine cooling fluid guide 24B will be described.

[0072] exist Figure 5 In the structure shown, the cooling fluid supplied from the pipe 5 through the throttle hole 55 to the inner side of the cylindrical second guide portion 54 in the cooling fluid supply hole 20 is guided to the inner peripheral surface 59 of the cylindrical second guide portion 54 and flows along the axial direction of the cooling fluid supply hole 20, and collides with the first guide portion 52, thereby changing the flow direction to a direction intersecting the axis C of the cooling fluid supply hole 20, and ejecting from the plurality of through holes 60 (60a, 60b) of the outer peripheral surface 58 of the second guide portion 54. As a result, it is possible to suppress the cooling effect caused by the cooling fluid from being concentrated on the turbine stator blade 12 near the cooling fluid supply hole 20 (especially the turbine stator blade 12A located on the extension line C1 of the axis C of the cooling fluid supply hole 20), and suppress the unevenness of the cooling effect caused by the cooling fluid between the plurality of turbine stator blades 12.

[0073] And, with Figure 3 In a manner similar to the structure shown in the figure, by locating the first guide portion 52 between the heat insulation plate 86 and the cooling fluid supply hole 20, it is possible to prevent the cooling fluid that has passed through the cooling fluid supply hole 20 (the cooling fluid that has passed through the inner side of the second guide portion 54) from colliding with the heat insulation plate 86 of the turbine fixed blade 12A on the extension line C1, thereby preventing the heat insulation plate 86 from being damaged due to large fluid force and fluid vibration acting on the heat insulation plate 86.

[0074] Furthermore, since the fixed portion 50 of the gas turbine cooling fluid guide 24B is fixed to the turbine casing 10 instead of the turbine fixed blade 12, even if the cooling fluid from the cooling fluid supply hole 20 (the cooling fluid that has passed through the throttle hole 55) collides with the first guide portion 52 of the gas turbine cooling fluid guide 24B, the vibration is suppressed from being transmitted to the heat insulation plate 86, and the risk of damage to the heat insulation plate 86 due to the vibration is effectively reduced.

[0075] The present invention is not limited to the above-described embodiment, and includes modified forms of the above-described embodiment, or forms in which these forms are appropriately combined.

[0076] For example, in Figure 3 In each of the gas turbine cooling fluid guides 24A and 24B illustrated in the examples, the fixed portion 26 and 50 are fixed to the turbine casing 10 by fixing members such as bolts, but the fixed portion of the gas turbine cooling fluid guide may not be fixed to the turbine casing 10, and may be fixed only to the pipe 5 by fixing members such as bolts.

[0077] The contents described in the above-mentioned embodiments can be understood, for example, as follows.

[0078] (1) A gas turbine cooling fluid guide according to at least one embodiment of the present invention (for example, the above-mentioned gas turbine cooling fluid guides 24A and 24B) is a gas turbine cooling fluid guide for guiding a cooling fluid of a gas turbine (for example, the above-mentioned gas turbine 2).

[0079] The gas turbine comprises:

[0080] a plurality of turbine stationary blades (eg, the plurality of turbine stationary blades 12 described above); and

[0081] a turbine housing (for example, the turbine housing 10 described above), accommodating the plurality of turbine stationary blades, and having cooling fluid supply holes (for example, the cooling fluid supply holes 20 described above) for supplying cooling fluid to the plurality of turbine stationary blades,

[0082] The gas turbine cooling fluid guide comprises:

[0083] A fixed portion (for example, the fixed portion 26, 26a, 26b, 50) is fixed to any one of a pipe (for example, the pipe 5) for supplying the cooling fluid to the cooling fluid supply hole or the turbine housing; and

[0084] The first guide portion (for example, the above-mentioned first guide portion 52) is constructed in a manner that covers at least a portion of the interior of the cooling fluid supply hole when viewed from the radial inner side of the gas turbine along the axial direction of the cooling fluid supply hole in a state where the fixed portion is fixed to the piping or the turbine casing.

[0085] According to the gas turbine cooling fluid guide described in (1), at least a portion of the cooling fluid that has passed through the cooling fluid supply hole flows along the axial direction of the cooling fluid supply hole and collides with the first guide portion, thereby changing the flow direction to a direction intersecting the axial direction of the cooling fluid supply hole. Therefore, it is possible to suppress the cooling effect caused by the cooling fluid from being concentrated on the turbine stator blades near the cooling fluid supply hole (particularly, the turbine stator blades located on the extension line of the axial direction of the cooling fluid supply hole), and suppress the unevenness of the cooling effect caused by the cooling fluid between the plurality of turbine stator blades.

[0086] According to the knowledge of the inventors of the present application, in a conventional gas turbine, when an accessory part (e.g., a heat shield plate, etc.) of a turbine stator blade is mounted on the outer surface of the outer shroud in the radial direction, if the cooling fluid passing through the cooling fluid supply hole collides with the accessory part of the turbine stator blade, a large fluid force and fluid vibration act on the accessory part, and resonance may occur under certain conditions, causing the accessory part to be damaged. Here, in the structure (1) above, even when an accessory part (e.g., a heat shield plate, etc.) of a turbine stator blade is mounted on the outer surface of the outer shroud in the radial direction, the first guide portion can suppress the cooling fluid passing through the cooling fluid supply hole from colliding with the accessory part of the turbine stator blade, thereby suppressing damage to the accessory part caused by the large fluid force and fluid vibration acting on the accessory part.

[0087] Furthermore, if the gas turbine cooling fluid guide is attached to the turbine stationary blade itself instead of the above-mentioned pipe or the turbine casing, even if the cooling fluid passing through the cooling fluid supply hole is prevented from colliding with the accessory parts of the turbine stationary blade by the gas turbine cooling fluid guide, the vibration of the gas turbine cooling fluid guide is transmitted to the turbine stationary blade and the accessory parts, so that the accessory parts may be damaged due to the vibration.

[0088] In contrast, since the fixed portion of the above-mentioned gas turbine cooling fluid guide is fixed to any one of the above-mentioned piping or turbine casing instead of the turbine fixed blade, even if the cooling fluid from the cooling fluid supply hole collides with the gas turbine cooling fluid guide, the vibration can be suppressed from being transmitted to the accessory parts, and the risk of damage to the accessory parts due to vibration can be effectively reduced.

[0089] (2) In some embodiments, in the cooling fluid guide for a gas turbine described in (1) above,

[0090] The plurality of turbine stator blades include an extended-line turbine stator blade (e.g., the turbine stator blade 12A described above), the extended-line turbine stator blade being arranged on an extended line (e.g., the extended line C1 described above) of an axis line (e.g., the axis line C described above) of the cooling fluid supply hole,

[0091] The first guide portion is configured to be located between the turbine fixed blade and the cooling fluid supply hole on the extension line in a state where the fixed portion is fixed to either the pipe or the turbine housing.

[0092] According to the gas turbine cooling fluid guide described in (2), the first guide portion can prevent the cooling fluid that has passed through the cooling fluid supply hole from colliding with the turbine stator blade on the extension line. This can prevent the cooling effect caused by the cooling fluid from being concentrated on the turbine stator blade on the extension line located on the extension line of the axis of the cooling fluid supply hole, and effectively prevent the unevenness of the cooling effect caused by the cooling fluid between the plurality of turbine stator blades.

[0093] (3) In some embodiments, in the cooling fluid guide for a gas turbine described in (2) above,

[0094] The turbine fixed blade on the extension line includes an airfoil portion and an outer shroud, the outer shroud is connected to the outer end of the airfoil portion in the radial direction of the gas turbine, and the accessory parts of the turbine fixed blade are installed on the outer surface of the outer shroud in the radial direction.

[0095] The first guide portion is configured to be located between the accessory component and the cooling fluid supply hole in a state where the fixed portion is fixed to either the pipe or the turbine housing.

[0096] According to the knowledge of the inventors of the present application, when an accessory (e.g., a heat shield, etc.) is mounted on the outer surface of the radially outer shroud, if the cooling fluid passing through the cooling fluid supply hole collides with the accessory of the turbine fixed blade on the extension line, a large fluid force and fluid vibration act on the accessory, and resonance may occur depending on the conditions, causing the accessory to be damaged. Therefore, as described in (3) above, in a state where the fixed portion is fixed to any one of the piping or the turbine housing, the first guide portion is located between the accessory and the cooling fluid supply hole, thereby preventing the cooling fluid passing through the cooling fluid supply hole from colliding with the accessory of the turbine fixed blade on the extension line, thereby preventing the accessory from being damaged due to the large fluid force and fluid vibration acting on the accessory.

[0097] Furthermore, assuming that the gas turbine cooling fluid guide is fixed to the turbine stationary blades on the extension line instead of to any of the above-mentioned piping or the turbine casing, even if the cooling fluid passing through the cooling fluid supply hole is prevented from colliding with the accessory parts of the turbine stationary blades on the extension line by the gas turbine cooling fluid guide, the vibration of the gas turbine cooling fluid guide is transmitted to the turbine stationary blades and the accessory parts on the extension line, so there is a possibility that the accessory parts may be damaged due to the vibration.

[0098] In contrast, since the fixed portion of the above-mentioned gas turbine cooling fluid guide is fixed to any one of the above-mentioned piping or turbine casing instead of the turbine fixed blade, even if the cooling fluid from the cooling fluid supply hole collides with the gas turbine cooling fluid guide, the vibration can be suppressed from being transmitted to the accessory parts, and the risk of damage to the accessory parts due to vibration can be effectively reduced.

[0099] (4) In some embodiments, in the cooling fluid guide for a gas turbine according to any one of (1) to (3),

[0100] The first guide portion is formed in a plate shape.

[0101] When the fixed portion is fixed to the pipe or the turbine housing, the first guide portion is configured to include a surface (eg, the surface 35, 56) intersecting an extension line (eg, the extension line C1) of the axis of the cooling fluid supply hole.

[0102] According to the gas turbine cooling fluid guide described in (4), the cooling fluid passing through the cooling fluid supply hole can be guided to a direction intersecting the extension line by the plate-shaped first guide portion. This can prevent the cooling effect caused by the cooling fluid from being concentrated on the turbine stator blades near the cooling fluid supply hole (especially the turbine stator blades located on the extension line of the axis of the cooling fluid supply hole), and prevent the cooling effect caused by the cooling fluid from being uneven among a plurality of turbine stator blades.

[0103] (5) In some embodiments, in the cooling fluid guide for a gas turbine described in any one of (1) to (4) above, when the fixed portion is fixed to the piping or the turbine casing, the first guide portion is located on the inner side of the fixed portion in the radial direction of the gas turbine, and when the fixed portion is fixed to the piping or the turbine casing, the cooling fluid guide for a gas turbine is constructed to include a second guide portion (for example, the second guide portion 30, 30a, 30b, 54 described above) extending from the first guide portion toward the outer side in the radial direction to the fixed portion.

[0104] According to the gas turbine cooling fluid guide described in (5), the first guide portion can be held at a position inside the fixed portion in the radial direction of the gas turbine in a state where the fixed portion is fixed to the pipe or the turbine casing.

[0105] (6) In some embodiments, in the cooling fluid guide for a gas turbine described in (5) above,

[0106] The second guide portion is formed in a plate shape.

[0107] The second guide portion is configured to include a surface (for example, the above-mentioned surfaces 38, 49 or the inner peripheral surface 59) intersecting the axial direction of the gas turbine in a state where the fixed portion is fixed to the pipe or the turbine housing.

[0108] According to the cooling fluid guide for a gas turbine described in (6), the cooling fluid that has passed through the cooling fluid supply hole and collided with the first guide portion can be guided along a surface intersecting the axial direction of the second guide portion. This can prevent the cooling effect caused by the cooling fluid from being concentrated on the turbine stator blades near the cooling fluid supply hole (especially the turbine stator blades located on the extension line of the axis of the cooling fluid supply hole), and prevent the cooling effect caused by the cooling fluid from being uneven among a plurality of turbine stator blades.

[0109] (7) In some embodiments, the gas turbine cooling fluid guide described in (1) above further includes:

[0110] an upstream second guide portion (for example, the above-mentioned second guide portion 30a) extending from an end portion (for example, the above-mentioned end portion 36) on the upstream side of the first guide portion in the axial direction of the gas turbine toward the outside in the radial direction of the gas turbine in a state where the fixed portion is fixed to the pipe or the turbine casing; and

[0111] The downstream second guide portion (for example, the above-mentioned second guide portion 30b) extends from an end portion (for example, the above-mentioned end portion 37) on the downstream side of the first guide portion in the axial direction of the gas turbine toward the outside in the radial direction of the gas turbine in a state where the fixed portion is fixed to the pipe or the turbine casing.

[0112] The upstream second guide portion and the downstream second guide portion are each formed in a plate shape.

[0113] In a state where the fixed portion is fixed to the pipe or the turbine housing, the upstream second guide portion and the downstream second guide portion are each configured to include a surface (for example, the above-mentioned surfaces 38 and 39 ) intersecting the axial direction.

[0114] According to the cooling fluid guide for a gas turbine described in (7), the cooling fluid that has passed through the cooling fluid supply hole and collided with the first guide portion can be guided so as to flow along the circumferential direction of the gas turbine between the surface intersecting the axial direction in the upstream second guide portion and the surface intersecting the axial direction in the downstream second guide portion. As a result, it is possible to suppress the cooling effect caused by the cooling fluid from being concentrated on the turbine stator blades near the cooling fluid supply hole (particularly, the turbine stator blades located on the extension line of the axis of the cooling fluid supply hole), and suppress the unevenness of the cooling effect caused by the cooling fluid between the plurality of turbine stator blades.

[0115] (8) In some embodiments, in the cooling fluid guide for a gas turbine described in (5) above,

[0116] The second guide portion is formed in a cylindrical shape.

[0117] The fixed portion includes a flange connected to an end portion (for example, the end portion 53 described above) of the second guide portion.

[0118] According to the cooling fluid guide for a gas turbine described in (8) above, the cylindrical second guide portion can be inserted into the interior of the cooling fluid supply hole, the flange can be arranged on the inlet side of the cooling fluid supply hole, and the first guide portion can be arranged on the outlet side of the cooling fluid supply hole. Furthermore, the cooling fluid can be guided by the inner peripheral surface of the cylindrical second guide portion so as to flow toward the first guide portion along the axial direction of the cooling fluid supply hole.

[0119] (9) In some embodiments, in the cooling fluid guide for a gas turbine described in (8) above,

[0120] The flange includes: an outer peripheral flange portion (for example, the outer peripheral flange portion 50a described above) protruding from the end portion of the second guide portion toward the outer peripheral side of the cylindrical shape of the second guide portion; and an inner peripheral flange portion (for example, the inner peripheral flange portion 50b described above) protruding from the end portion of the second guide portion toward the inner peripheral side of the cylindrical shape of the second guide portion.

[0121] A throttle hole (for example, the throttle hole 55 described above) having a diameter smaller than that of the cooling fluid supply hole is formed in the inner peripheral flange portion.

[0122] According to the cooling fluid guide for a gas turbine described in (9), the structure of (8) can be realized with a small number of parts, and the flow rate of the cooling fluid can be increased by the throttle hole.

[0123] (10) In some embodiments, in the gas turbine cooling fluid guide described in (8) or (9) above, a plurality of through holes (for example, the plurality of through holes 60, 60a, 60b described above) are formed on the outer peripheral surface of the second guide portion.

[0124] According to the cooling fluid guide for a gas turbine described in (10), the cooling fluid that has passed through the cooling fluid supply hole and collided with the first guide portion is ejected from the plurality of through holes on the outer peripheral surface of the second guide portion. This can prevent the cooling effect caused by the cooling fluid from being concentrated on the turbine stator blades near the cooling fluid supply hole (particularly, the turbine stator blades located on the extension line of the axis of the cooling fluid supply hole), and prevent the cooling effect caused by the cooling fluid from being uneven among the plurality of turbine stator blades.

[0125] (11) In some embodiments, in the cooling fluid guide for a gas turbine described in (10) above,

[0126] The plurality of through holes include:

[0127] a plurality of first through holes (for example, the plurality of through holes 60a described above) provided at intervals along the circumferential direction of the outer peripheral surface of the second guide portion at a first position in the axial direction of the cylindrical shape of the second guide portion; and

[0128] A plurality of second through holes (for example, the plurality of through holes 60 b described above) are provided at intervals in the circumferential direction of the outer peripheral surface of the second guide portion at second positions in the axial direction of the cylindrical shape of the second guide portion.

[0129] According to the cooling fluid guide for a gas turbine described in (11), the cooling fluid that has collided with the first guide portion through the cooling fluid supply hole is ejected from the plurality of first through holes and the plurality of second through holes on the outer peripheral surface of the second guide portion. As a result, the flow rate of the cooling fluid ejected from the second guide portion can be adjusted, and the ejection position of the cooling fluid in the second guide portion can be dispersed in the axial direction and circumferential direction of the cylindrical shape. Therefore, it is possible to suppress the cooling effect caused by the cooling fluid from being concentrated on the turbine stator blades near the cooling fluid supply hole (especially the turbine stator blades located on the extension line of the axis of the cooling fluid supply hole), and suppress the unevenness of the cooling effect caused by the cooling fluid between the plurality of turbine stator blades.

[0130] (12) A gas turbine according to at least one embodiment of the present invention includes:

[0131] The cooling fluid guide for a gas turbine according to any one of (1) to (11);

[0132] said turbine housing; and

[0133] The plurality of turbine stationary blades.

[0134] According to the gas turbine described in (12), since it is provided with the gas turbine cooling fluid guide described in any one of (1) to (11), it is possible to suppress the cooling effect caused by the cooling fluid from being concentrated on the turbine stator blades near the cooling fluid supply hole (especially the turbine stator blades located on the extension line of the axis of the cooling fluid supply hole), and to suppress the unevenness of the cooling effect caused by the cooling fluid between the plurality of turbine stator blades.

[0135] Explanation of symbols

[0136] 2-gas turbine, 4-compressor, 5-pipe, 5a-flange, 6-combustor, 8-turbine, 9-rotor (turbine rotor), 10-turbine casing, 10b-inner surface, 10a-outer surface, 12-turbine fixed blade, 12A-turbine fixed blade (turbine fixed blade on extension line), 14-flow path, 15-outer peripheral wall, 16-turbine moving blade, 20-cooling fluid supply hole, 24A, 24B-cooling fluid guide for gas turbine, 26, 26a, 26b, 50-fixed portion, 27, 42-fixing member, 28, 52-first guide portion, 30, 30a, 30b, 54-the second guide portion, 31, 34, 36, 37, 53, 57-an end portion, 32-an end edge, 33-a recessed portion, 35, 38, 39, 56-a surface (a guide surface), 40, 55-a throttle hole, 41-a throttle hole plate, 50a-an outer peripheral flange portion, 50b-an inner peripheral flange portion, 58-an outer peripheral surface, 59-an inner peripheral surface, 60, 60a, 60b-a through hole, 80-an airfoil portion, 82-an outer shroud, 83-an outer surface, 84-a sealing tube, 85-an outer cavity, 86-a heat insulation plate, 87-a plate portion, 88-a side wall portion.

Claims

1. A cooling fluid guide for a gas turbine, which is used to guide the cooling fluid of the gas turbine, wherein: The gas turbine comprises: a plurality of turbine stationary blades; and a turbine housing that accommodates the plurality of turbine stationary blades and is formed with cooling fluid supply holes for supplying cooling fluid to the plurality of turbine stationary blades, The gas turbine cooling fluid guide comprises: a fixed portion fixed to any one of a pipe for supplying the cooling fluid to the cooling fluid supply hole or the turbine housing; and The first guide portion is configured to cover at least a portion of the cooling fluid supply hole when viewed from the inner side in the radial direction of the gas turbine along the axial direction of the cooling fluid supply hole in a state where the fixed portion is fixed to the pipe or the turbine casing.

2. The cooling fluid guide for a gas turbine according to claim 1, wherein: The plurality of turbine stationary blades include an extended-line turbine stationary blade, wherein the extended-line turbine stationary blade is disposed on an extended line of the axis of the cooling fluid supply hole. The first guide portion is configured to be located between the turbine fixed blade and the cooling fluid supply hole on the extension line in a state where the fixed portion is fixed to either the pipe or the turbine housing.

3. The cooling fluid guide for a gas turbine according to claim 1, wherein: Each of the turbine stationary blades includes an airfoil portion and an outer shroud, wherein the outer shroud is connected to an outer end of the airfoil portion in a radial direction of the gas turbine, and an accessory part of the turbine stationary blade is mounted on an outer surface of the outer shroud in the radial direction. The first guide portion is configured to be located between the accessory component and the cooling fluid supply hole in a state where the fixed portion is fixed to the pipe or the turbine housing.

4. The cooling fluid guide for a gas turbine according to claim 1, wherein: The first guide portion is formed in a plate shape. The first guide portion is configured to include a surface intersecting an extension line of an axis line of the cooling fluid supply hole in a state where the fixed portion is fixed to the pipe or the turbine housing.

5. The cooling fluid guide for a gas turbine according to claim 1, wherein: In a state where the fixed portion is fixed to the pipe or the turbine housing, the first guide portion is located inside the fixed portion in the radial direction of the gas turbine. The gas turbine cooling fluid guide is configured to include a second guide portion extending from the first guide portion toward the outside in the radial direction to the fixed portion in a state where the fixed portion is fixed to the pipe or the turbine housing.

6. The cooling fluid guide for a gas turbine according to claim 5, wherein: The second guide portion is formed in a plate shape. The second guide portion is configured to include a surface intersecting with the axial direction of the gas turbine in a state where the fixed portion is fixed to the pipe or the turbine casing.

7. The gas turbine cooling fluid guide according to claim 1, further comprising: an upstream second guide portion extending from an upstream end portion of the first guide portion in the axial direction of the gas turbine toward an outer side in the radial direction of the gas turbine in a state where the fixed portion is fixed to the pipe or the turbine casing; and a downstream second guide portion extending from an end portion on the downstream side of the first guide portion in the axial direction of the gas turbine toward an outer side in the radial direction of the gas turbine in a state where the fixed portion is fixed to the pipe or the turbine casing, The upstream second guide portion and the downstream second guide portion are each formed in a plate shape. In a state where the fixed portion is fixed to the pipe or the turbine housing, each of the upstream second guide portion and the downstream second guide portion is configured to include a surface intersecting the axial direction.

8. The cooling fluid guide for a gas turbine according to claim 5, wherein: The second guide portion is formed in a cylindrical shape. The fixed portion includes a flange connected to an end portion of the second guide portion.

9. The cooling fluid guide for a gas turbine according to claim 8, wherein: The flange includes: an outer peripheral flange portion protruding from the end portion of the second guide portion toward the outer peripheral side of the cylindrical shape of the second guide portion; and an inner peripheral flange portion protruding from the end portion of the second guide portion toward the inner peripheral side of the cylindrical shape of the second guide portion. A throttle hole having a diameter smaller than that of the cooling fluid supply hole is formed in the inner peripheral flange portion.

10. The cooling fluid guide for a gas turbine according to claim 9, wherein: A plurality of through holes are formed on the outer peripheral surface of the second guide portion.

11. The cooling fluid guide member for a gas turbine according to claim 10, wherein: The plurality of through holes include: a plurality of first through holes provided at intervals in the circumferential direction of the outer peripheral surface of the second guide portion at first positions in the axial direction of the cylindrical shape of the second guide portion; and The plurality of second through holes are provided at intervals in the circumferential direction of the outer peripheral surface of the second guide portion at second positions in the axial direction of the cylindrical shape of the second guide portion.

12. A gas turbine comprising: The cooling fluid guide for a gas turbine according to any one of claims 1 to 11; said turbine housing; and The plurality of turbine stationary blades.

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