Cooling fluid guide for gas turbines and gas turbines

Abstract

A gas turbine cooling fluid guide includes a fixed portion fixed to either a pipe for supplying a cooling fluid to a cooling fluid supply hole of a turbine casing or the turbine casing, and a first guide portion configured to cover at least a portion of the cooling fluid supply hole when viewed from an interior of a gas turbine in a radial direction along a direction 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 casing.

Description

Technical area

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

[0002] This present application claims priority based on Japanese Patent Application No. 2022-140481 filed in the Japan Patent Office on September 5, 2022, the contents of which are incorporated herein by reference. State of the art

[0003] PTL 1 discloses that, in order to cool a gas turbine stator blade, a cooling fluid is supplied from a cooling fluid supply hole provided at a turbine casing to an outer cavity formed between an outer shell of the gas turbine stator blade and the turbine casing. Citation listPatent literature

[0004] [PTL 1] International Publication No. WO2017 / 090709 Summary of the inventionTechnical problem

[0005] In a case where the cooling fluid is supplied from the cooling fluid supply hole provided in the turbine casing to the gas turbine stator blade, a variation in the amount of supplied cooling fluid occurs between a gas turbine stator blade located near the cooling fluid supply hole and a gas turbine stator blade located far from the cooling fluid supply hole, and a variation in the cooling effect of the gas turbine stator blade occurs between the plurality of gas turbine stator blades.

[0006] In view of the above circumstances, an object of at least one embodiment of the present disclosure is to provide a gas turbine cooling fluid guide that can suppress fluctuation of a cooling effect by a cooling fluid between a plurality of gas turbine stator blades, and a gas turbine including the gas turbine cooling fluid guide. Solution to the problem

[0007] To achieve the above object, according to at least one embodiment of the present disclosure, there is provided a gas turbine cooling fluid guide for guiding a cooling fluid of a gas turbine, the gas turbine including a plurality of turbine stator blades and a turbine casing accommodating the plurality of turbine stator blades and having a cooling fluid supply hole formed therein for supplying the cooling fluid to the plurality of turbine stator blades, the gas turbine cooling fluid guide comprising: a fixed portion fixed to one of a pipe for supplying the cooling fluid to the cooling fluid supply hole and the turbine casing;and a first guide portion configured to cover at least a portion of the cooling fluid supply hole when viewed from an interior of the gas turbine in a radial direction along a direction 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 casing;

[0008] To achieve the above object, according to at least one embodiment of the present disclosure, there is provided a gas turbine comprising: the gas turbine cooling fluid guide; the turbine casing; and the plurality of turbine stator blades. Advantageous effects of the invention

[0009] According to at least one embodiment of the present disclosure, it is possible to provide a gas turbine cooling fluid guide that can suppress fluctuation of a cooling effect by a cooling fluid between a plurality of gas turbine stator blades, and a gas turbine including the gas turbine cooling fluid guide. Brief description of the drawings Fig. 1 is a diagram showing a schematic configuration of a gas turbine 2 according to an embodiment. Fig. 2 is a schematic cross-sectional view showing an example of a cross section perpendicular to an axial direction in a turbine housing 10. Fig. 3 is a schematic cross-sectional view showing an example of a portion of a cross section along an axial direction at a position of each cooling fluid supply hole 20 in the gas turbine 2. Fig. 4 is a view showing a Fig. 3 when viewed from an inside in a radial direction along an axis line C of the cooling fluid supply hole 20. Fig. 5 is a schematic cross-sectional view showing another example of a portion of the cross section along the axial direction at the position of each cooling fluid supply hole 20 in the gas turbine 2. Description of embodiments

[0010] Some embodiments of the present disclosure will be described below with reference to the accompanying drawings. Dimensions, materials, shapes, relative arrangements, and the like of components described as embodiments or shown in the drawings are not intended to limit the scope of the invention, but are merely illustrative examples. For example, it is assumed that, strictly speaking, an expression representing a relative or absolute arrangement, such as "in a certain direction", "along a certain direction", "parallel", "perpendicular", "center", "concentric" or "coaxial", not only strictly represents the arrangement, but also represents a state of relative displacement with a tolerance or a sufficient angle or distance to obtain equal function. For example, strictly speaking, expressions such as "identical," "equal," and "homogeneous," which represent things being in the same state, are assumed to represent not only strictly the same state, but also a state in which there is a tolerance or sufficient difference to maintain the same function. For example, an expression representing a shape such as a quadrangular shape or a cylindrical shape is considered to represent not only a shape such as a quadrangular shape or a cylindrical shape in a geometrically strict sense, but also a shape including an uneven portion, a chamfer portion, or the like within a range where the same effect is obtained.

[0011] However, an expression such as “being provided with”, “being equipped with”, “comprising”, “containing” or “having” a component is not an exclusive expression that excludes the presence of other components.

[0012] Fig. 1 is a diagram showing a schematic configuration of a gas turbine 2 according to an embodiment.

[0013] As in Fig. 1, the gas turbine 2 includes a compressor 4, a combustion chamber 6 that mixes compressed air generated by the compressor 4 with fuel and burns the mixture, and a turbine 8 for obtaining power from combustion gas generated by the combustion chamber 6.

[0014] As in Fig. 1, the turbine 8 includes a rotor 9 (turbine rotor), a turbine casing 10, a plurality of turbine stator blades 12 (gas turbine stator blades) fixed to an inner surface of the turbine casing 10, and a plurality of turbine rotor blades 16 implanted in the rotor 9 so as to be alternately arranged in an axial direction with respect to the turbine stator blades 12. The turbine casing 10 accommodates the rotor 9, the plurality of turbine stator blades 12, and the plurality of turbine rotor blades 16. Each stage of the turbine 8 includes a plurality of turbine stator blades 12 arranged along a circumferential direction of the gas turbine 2, and a plurality of turbine rotor blades 16 arranged along the circumferential direction of the gas turbine 2 on a downstream side of the plurality of turbine stator blades 12.

[0015] Hereinafter, the “circumferential direction” means a circumferential direction of the gas turbine 2, that is, a circumferential direction of the rotor 9, unless otherwise specified, the “axial direction” means an axial direction of the gas turbine 2, that is, an axial direction of the rotor 9, unless otherwise specified, and the “radial direction” means a radial direction of the gas turbine 2, that is, a radial direction of the rotor 9, unless otherwise specified.

[0016] Fig. 2 is a schematic cross-sectional view showing an example of a cross section perpendicular to the axial direction in the turbine housing 10.

[0017] As in Fig. 2, a plurality of cooling fluid supply holes 20 for supplying a cooling fluid to the plurality of turbine stator blades 12 (see Fig. 1) is formed in the turbine housing 10. The plurality of cooling fluid supply holes 20 are provided at intervals in the circumferential direction. Fig. 2, four cooling fluid supply holes 20 are provided at equal intervals in the circumferential direction, and each of the cooling fluid supply holes 20 is a through hole penetrating an outer surface 10a and an inner surface 10b of the turbine housing 10 in the radial direction.

[0018] Fig. 3 is a schematic cross-sectional view showing an example of a portion of a cross section along the axial direction at a position of each of the cooling fluid supply holes 20 in the gas turbine 2. Moreover, since the cross sections along the axial direction at the positions of the cooling fluid supply holes 20 in the gas turbine 2 are substantially the same, the cross section along the axial direction at the position of a cooling fluid supply hole 20 in the gas turbine 2 will be described below.

[0019] As in Fig. 3, a pipe 5 for supplying the cooling fluid to the cooling fluid supply hole 20 is connected to the turbine housing 10. In the Fig. 3, a flange 5a in a state in which an orifice plate 41, on which an orifice 40 having a smaller diameter than each of the inner diameter of the tube 5 and the diameter of the cooling fluid supply hole 20 is formed, is inserted between the flange 5a formed at one end of the tube 5 and the outer surface 10a of the turbine housing 10, is fixed to the outer surface 10a of the turbine housing 10 by fastening elements 42 such as bolts. Fig. 3, the opening 40 is located on an extension line of an axis line C of the cooling fluid supply hole 20.

[0020] As in Fig. 3, each of the plurality of turbine stator blades 12 includes a blade profile section 80, an outer shroud 82, a seal tube 84, and a heat shield plate 86. In addition, in the turbine stator shown in Fig. In the example shown in Figure 3, the gas turbine 2 has a gas turbine cooling fluid guide 24A.

[0021] The blade profile portion 80 has a blade profile cross-sectional shape defined by a pressure surface and a suction surface. The outer shroud 82 is connected to an outer end of the blade profile portion 80 in a blade height direction and is formed in a substantially plate shape along a plane intersecting the radial direction. The outer shroud 82 forms an outer peripheral wall 15 of a combustion gas flow path 14 of the turbine 8 (a flow path of a main flow of the combustion gas in the turbine 8). The turbine stator blade 12 includes an inner shroud (not shown) connected to an inner end of the blade profile portion 80 in the blade height direction. The inner shroud is formed in a substantially plate shape along the plane intersecting the radial direction and forms an inner peripheral wall of the flow path 14.Moreover, in the present specification, the “upstream side in the axial direction” means an upstream side of the main flow of the combustion gas of the turbine 8 (the flow of the combustion gas through the flow path 14) in the axial direction, and the “downstream side in the axial direction” means a downstream side of the main flow of the combustion gas of the turbine 8 (the flow of the combustion gas through the flow path 14) in the axial direction.

[0022] The seal tube 84 is disposed in an internal channel (not shown) of the airfoil section 80 and is configured in a tubular shape. The seal tube 84 is configured to guide air in an external cavity 85 formed between the outer shroud 82 and the turbine casing 10, via the interior of the airfoil section 80 to the interior of the turbine stator blade 12.

[0023] The compressed air from the compressor 4 is supplied through the cooling fluid supply hole 20 to the outer cavity 85 as cooling air, and the cooling air flowed from the outer cavity 85 into the seal pipe 84 is guided to the inside of the turbine stator blade 12 in the radial direction, is supplied to an interstage space (not shown) between the turbine stator blade 12 and the turbine rotor blade 16 (see Fig. 1) adjacent to the upstream side of the turbine stator blade 12 and also functions as cooling air.

[0024] The heat shield plate 86 is attached as an additional component of the turbine stator blade 12 to an outer surface 83 of the outer shell 82 in the radial direction. The heat shield plate 86 is provided so that it covers at least a portion of the outer surface 83 of the outer shell 82. In the Fig. 3, the heat shield plate 86 includes a cover plate portion 87 having a plate shape and arranged parallel to the surface 83 with a gap between the cover plate portion 87 and the surface 83 in the blade height direction, and a side wall portion 88 connected to a peripheral edge of the cover plate portion 87 and provided to surround the seal tube 84. The side wall portion 88 is fixed to the surface 83 of the outer shell 82 by, for example, welding or the like.

[0025] Fig. 4 is a view showing the Fig. 3 shows the gas turbine cooling fluid guide 24A as viewed from the inside in the radial direction along the axis line C of the cooling fluid supply hole 20.

[0026] For example, in some embodiments, as shown in Fig. 3 and Fig. 4, the gas turbine 2 includes the 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 sections 26, a first guide section 28 (baffle plate), and a plurality of second guide sections 30 (a plurality of side plates). Fig. In the example shown in FIG. 4, each of the plurality of fixed portions 26, the first guide portion 28, and each of the plurality of second guide portions 30 are formed in a plate shape having a substantially quadrangular cross section. Furthermore, 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 and 26b.

[0027] In the Fig. In the example shown in FIG. 4, 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-side second guide portion and a downstream-side second guide portion). Each of the plate-shaped fixed portions 26a and 26b is arranged along the inner surface 10b of the turbine housing 10 and is fixed to the inner surface 10b of the turbine housing 10 by fastening members 27 such as bolts. 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.

[0028] For example, as in Fig. 3, the fixed portion 26a is connected to an outer end portion 31 (outer end) of the second guide portion 30a in the radial direction and protrudes from the end portion 31 to the downstream side in the axial direction. For example, as shown in Fig. 4, a cutout-shaped recessed portion 33, which is recessed in the axial direction toward the upstream side, is formed at an end edge 32 of the fixed portion 26 on the downstream side in the axial direction, and a portion of the cooling fluid supply hole 20 is located inside the recessed portion 33 when viewed from the radial direction. The fixed portion 26a is fixed to the inner surface 10b (see Fig. 3) of the turbine housing 10 by the fastening members 27 on both sides in the circumferential direction, with the first guide portion 28 interposed therebetween when viewed from the radial direction.

[0029] For example, as in Fig. 3, the fixed portion 26b is connected to an outer end portion 34 (outer end) of the second guide portion 30b in the radial direction and protrudes from the end portion 34 to the downstream side in the axial direction. As shown in Fig. 4, for example, the fixed portion 26b is on the inner surface 10b (see Fig. 3) of the turbine housing 10 by the fastening members 27 on both sides, with a center position of the fixed portion 26b in the circumferential direction interposed therebetween.

[0030] At the Fig. 4, a dimension A2 of the fixed portion 26a in the circumferential direction is larger than a dimension A1 of the first guide portion 28 in the circumferential direction and is larger than a diameter R of the cooling fluid supply hole 20. Furthermore, a dimension A3 of the fixed portion 26b in the circumferential direction is identical 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. Further, a dimension B2 of the fixed portion 26a in the axial direction is smaller than a dimension B1 of the first guide portion 28 in the axial direction and smaller than the diameter R of the cooling fluid supply hole 20. Furthermore, a 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 smaller than the diameter R of the Cooling fluid supply hole 20.

[0031] For example, as in Fig. 4, in a case where the first guide portion 28 is viewed from the inside in the radial direction along the direction of the axis line of the cooling fluid supply hole 20 (that is, along an extension line C1 of the axis line C of the cooling fluid supply hole 20), the first guide portion 28 is provided so as to guide at least a portion of the cooling fluid supply hole 20 (in the case of Fig. 4 example, covers all the cooling fluid supply holes 20). In a case where the first guide portion 28 is viewed from the inside in the radial direction along the direction of the axis line of the cooling fluid supply hole 20, the first guide portion 28 is provided to cover at least a portion of the cooling fluid supply hole 20 (in the example shown in Fig. 4 example, all cooling fluid supply holes 20). The first guide section 28 is located on the extension line C1 of the axis line C of the cooling fluid supply hole 20 and includes a surface 35 that intersects the extension line C1 (in the example shown in Fig. 4, the surface 35 is perpendicular to the extension line C1). The first guide portion 28 is provided 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.

[0032] For example, as in Fig. 3, the plurality of turbine stator blades 12 of the gas turbine 2 includes a turbine stator blade 12A (turbine stator blade on 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 and the cooling fluid supply hole 20 on the extension line C1. Furthermore, the first guide portion 28 is located between the heat shield plate 86 of the turbine stator blade 12A and the cooling fluid supply hole 20.

[0033] For example, as in Fig. 3, the second guide portion 30a is formed in a plate shape having a surface 38 which defines the axial direction (in the case of Fig. 3, and is provided so as to extend outwardly from an upstream end portion 36 (upstream end) of the first guide portion 28 in the axial direction to the fixed portion 26a in the radial direction. In the example shown in Fig. In the example shown in Figure 3, the second guide portion 30a is connected to an upstream end portion (upstream end) of the fixed portion 26a in the axial direction. The second guide portion 30a is provided to guide at least a portion of the cooling fluid that has passed through the cooling fluid supply hole 20 along the surface 38 intersecting the axial direction.

[0034] For example, as in Fig. 3, the second guide portion 30b is formed in a plate shape having a surface 39 which defines the axial direction (in the case of Fig. 3, and is provided so as to extend outwardly from a downstream end portion 37 (downstream end) of the first guide portion 28 in the axial direction to the fixed portion 26b in the radial direction. In the example shown in Fig. In the example shown in Figure 3, the second guide portion 30b is connected to an upstream end portion (upstream end) of the fixed portion 26b in the axial direction. The second guide portion 30b is provided to guide at least a portion of the cooling fluid that has passed through the cooling fluid supply hole 20 along the surface 39 intersecting the axial direction.

[0035] Some effects of the gas turbine cooling fluid guide 24A are described below.

[0036] At the Fig. 3 and the like, the cooling fluid supplied from the pipe 5 to the cooling fluid supply hole 20 flows along the direction of the axis line of the cooling fluid supply hole 20 and encounters the first guide portion 28 of the gas turbine cooling fluid guide 24A, so that the direction of the flow is changed to a direction intersecting the axis line C of the cooling fluid supply hole 20. The cooling fluid is guided along the surface 35 of the first guide portion 28. Therefore, it is possible to suppress the concentration of the cooling effect by the cooling fluid on the turbine stator blade 12 (especially the turbine stator blade 12A located on the extension line C1 of the axis line C of the cooling fluid supply hole 20) in the vicinity of the cooling fluid supply hole 20 and to suppress fluctuation of the cooling effect by the cooling fluid between the plurality of turbine stator blades 12.

[0037] In addition, in Fig. 3 and the like, the cooling fluid that has passed through the cooling fluid supply hole 20 and that has encountered the first guide portion 28 can be guided to flow in the circumferential direction between the surface 38 of the second guide portion 30a that intersects the axial direction and the surface 39 of the second guide portion 30b that intersects the axial direction. Therefore, it is possible to suppress the concentration of the cooling effect by the cooling fluid on the turbine stator blade 12 (especially the turbine stator blade 12A located on the extension line C1 of the axial line C of the cooling fluid supply hole 20) in the vicinity of the cooling fluid supply hole 20 and effectively suppress fluctuation of the cooling effect by the cooling fluid between the plurality of turbine stator blades 12.

[0038] Furthermore, according to the present inventors' findings, in a case where the heat shield plate 86 (an auxiliary component of the turbine stator blade 12A) of the turbine stator blade 12A is attached to the outer surface 83 of the outer shell 82 in the radial direction, when the cooling fluid that has passed through the cooling fluid supply hole 20 collides with the heat shield plate 86, a large fluid force and fluid vibration act on the heat shield plate 86, and resonance may occur depending on the conditions. As a result, the heat shield plate 86 may be damaged.In this regard, as described above, since the first guide portion 28 is located between the heat shield plate 86 of the turbine stator blade 12A and the cooling fluid supply hole 20, it is possible to suppress the collision of the cooling fluid that has passed through the cooling fluid supply hole 20 with the heat shield plate 86 of the turbine stator blade 12 on the extension line C1 and suppress the damage to the heat shield plate 86 caused by the action of the large fluid force and the fluid vibration on the heat shield plate 86.

[0039] Furthermore, in a case where the gas turbine cooling fluid guide is directly attached to the turbine stator blade 12 on the extension line C1 rather than to the turbine casing 10, even if the collision of the cooling fluid that has passed through the cooling fluid supply hole 20 with the heat shield plate 86 of the turbine stator blade 12A on the extension line C1 is suppressed by the gas turbine cooling fluid guide, the vibration of the gas turbine cooling fluid guide 24A is transmitted to the turbine stator blade 12A on the extension line C1. Therefore, there is a concern that the heat shield plate 86 will be damaged due to the vibration.

[0040] In contrast, in the above-described embodiment, the fixed portions 26a and 26b of the gas turbine cooling fluid guide 24A are fixed to the turbine casing 10 instead of the turbine stator blade 12. Therefore, even in a case where the cooling fluid from the cooling fluid supply hole 20 (the cooling fluid from the opening 40) collides with the gas turbine cooling fluid guide 24A, the transmission of vibration to the heat shield plate 86 is suppressed, and it is possible to effectively reduce the risk of damage to the heat shield plate 86 caused by the vibration.

[0041] Fig. 5 is a schematic cross-sectional view showing another example of a portion of the cross section along the axial direction at the position of each cooling fluid supply hole 20 in the gas turbine 2. Moreover, since the cross sections along the axial direction at the positions of the cooling fluid supply holes 20 in the gas turbine 2 are substantially the same, the cross section along the axial direction at the position of a cooling fluid supply hole 20 in the gas turbine 2 will be described below.

[0042] At the Fig. 5, since the configuration of the turbine stator blade 12 is identical to the configuration of the Fig. 3, a description thereof is omitted. The turbine stator blade 12 shown in Fig. 5 includes a gas turbine cooling fluid guide 24B for guiding the cooling fluid of the gas turbine 2 instead of the Fig. 3. The gas turbine cooling fluid guide 24B is provided for each cooling fluid supply hole 20.

[0043] As in Fig. 5, the pipe 5 for supplying the cooling fluid to the cooling fluid supply hole 20 is connected to the turbine housing 10.

[0044] In the Fig. 5, the gas turbine cooling fluid guide 24B includes a fixed portion 50, a first guide portion 52 (baffle plate), and a second guide portion 54 (porous cylinder). In the example shown in Fig. 5, 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.

[0045] The fixed portion 50 is a disk-shaped flange connected to an outer end portion 53 of the second guide portion 54 in the radial direction and includes an outer peripheral side flange portion 50a protruding from the end portion 53 of the second guide portion 54 to an outer peripheral side (a side opposite to the axis line C of the cooling fluid supply hole 20) of the second guide portion 54, and an inner peripheral side flange portion 50b protruding from the end portion 53 of the second guide portion 54 to an inner peripheral side (a side closer to the axis line C of the cooling fluid supply hole 20) of the second guide portion 54.The outer peripheral flange portion 50a is fixed to the flange 5a of the pipe 5 and the turbine housing 10 by fastening members 42 such as bolts, in a state where it is sandwiched between the flange 5a formed at one end of the pipe 5 and the outer surface 10a of the turbine housing 10. An opening 55 having a smaller diameter than each cooling fluid supply hole 20 is formed in the inner peripheral flange portion 50b. The opening 55 is located on an extension line C1 of the axis line C of the cooling fluid supply hole 20.

[0046] The first guide portion 52 has a disc shape as described above, is connected to an inner end portion 57 of the second guide portion 54 in the radial direction, and is configured as a bottom plate closing one end side of the cylindrical second guide portion 54. The first guide portion 52 is located inside the fixed portion 50 and inside the second guide portion 54 in the radial direction. In a case where the first guide portion 28 is viewed from the inside in the radial direction along the direction of the axis line of the cooling fluid supply hole 20 (that is, along the extension line C1 of the axis line C of the cooling fluid supply hole 20), the first guide portion 52 is provided to cover at least a portion of the cooling fluid supply hole 20 (substantially the entire cooling fluid supply hole 20 in the Fig. 5). In a case where the first guide portion 52 is viewed from the inside in the radial direction along the direction of the axis line of the cooling fluid supply hole 20, the first guide portion 52 is provided to cover at least a portion of the cooling fluid supply hole 20 (substantially the entire cooling fluid supply hole 20 in the configuration shown in Fig. 5). The first guide portion 52 is located on the extension line C1 of the axis line C of the cooling fluid supply hole 20 and includes a surface 56 that intersects the extension line C1 (in the configuration shown in Fig. 5, a surface 56 perpendicular to the extension line C1). The first guide portion 52 is provided 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.

[0047] For example, as in Fig. 5, the plurality of turbine stator blades 12 of the gas turbine 2 includes a turbine stator blade 12A provided on the 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 stator blade 12A and the cooling fluid supply hole 20 on the extension line C1. Furthermore, the first guide portion 52 is located between the heat shield plate 86 and the cooling fluid supply hole 20.

[0048] The second guide portion 54 has a cylindrical shape as described above and extends from the fixed portion 50 to the first guide portion 52 through the cooling fluid supply hole 20 along the direction of the axial line of the cooling fluid supply hole 20. A plurality of through holes 60 are formed on an outer peripheral surface 58 of the second guide portion 54 inside the cooling fluid supply hole 20 in the radial direction. The plurality of through holes 60 are arranged in a zigzag pattern on the outer peripheral surface 58. The plurality of through holes 60 includes a plurality of through holes 60a and a plurality of through holes 60b. The plurality of through holes 60a are provided at the same position (first position) in the axial direction of the cylindrical shape of the second guide portion 54 at intervals in the circumferential direction of the outer peripheral surface 58.The plurality of through holes 60b are provided at the same position (second position) in the axial direction of the cylindrical shape of the second guide portion 54 at intervals in the circumferential direction of the outer peripheral surface 58. The position where each of the through holes 60a is provided and the position where each of the through holes 60b is provided differ from each other 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.

[0049] Some effects of the gas turbine cooling fluid guide 24B are described below.

[0050] At the Fig. 5, the cooling fluid supplied from the pipe 5 to the interior of the cylindrical second guide portion 54 at the cooling fluid supply hole 20 through the opening 55 flows along the direction of the axis line of the cooling fluid supply hole 20 while being guided by an inner peripheral surface 59 of the cylindrical second guide portion 54, and impacts the first guide portion 52 so that the direction of the flow is changed to a direction intersecting the axis line C of the cooling fluid supply hole 20. Then, the cooling fluid is ejected from the plurality of through holes 60 (60a and 60b) on the outer peripheral surface 58 of the second guide portion 54.Therefore, it is possible to suppress the concentration of the cooling effect by the cooling fluid on the turbine stator blade 12 (especially the turbine stator blade 12A located on the extension line C1 of the axis line C of the cooling fluid supply hole 20) in the vicinity of the cooling fluid supply hole 20 and to suppress fluctuation of the cooling effect by the cooling fluid between the plurality of turbine stator blades 12.

[0051] In addition, as with the Fig. 3, the first guide portion 52 is disposed between the heat shield plate 86 and the cooling fluid supply hole 20. Therefore, it is possible to suppress the collision of the cooling fluid (the cooling fluid that has passed through the inside of the second guide portion 54) that has passed through the cooling fluid supply hole 20 with the heat shield plate 86 of the turbine stator blade 12A on the extension line C1, and to suppress the damage to the heat shield plate 86 caused by the action of the large fluid force and the fluid vibration on the heat shield plate 86.

[0052] Furthermore, the fixed portion 50 of the gas turbine cooling fluid guide 24B is fixed to the turbine casing 10 instead of the turbine stator blade 12. Therefore, even if the cooling fluid (the cooling fluid that has passed through the opening 55) from the cooling fluid supply hole 20 collides with the first guide portion 52 of the gas turbine cooling fluid guide 24B, it is possible to suppress the transmission of vibration to the heat shield plate 86 and effectively reduce the risk of damage to the heat shield plate 86 caused by the vibration.

[0053] The present disclosure is not limited to the above-described embodiments and also includes modifications of the above-described embodiments and suitable combinations of the modifications.

[0054] For example, each of the Fig.3, the fixed portion 26 or 50 is fixed to the turbine casing 10 by the fastening members such as bolts. However, the fixed portion of the gas turbine cooling fluid guide does not need to be fixed to the turbine casing 10 and may be fixed only to the pipe 5 by the fastening members such as bolts.

[0055] For example, the content described in each of the above-described embodiments is understood as follows.

[0056] (1) According to at least one embodiment of the present disclosure, there is provided a gas turbine cooling fluid guide (e.g., the gas turbine cooling fluid guide 24A or 24B) for guiding a cooling fluid of a gas turbine (e.g., the gas turbine 2), the gas turbine including a plurality of turbine stator blades (e.g., the plurality of turbine stator blades 12) and a turbine casing (e.g., the turbine casing 10) accommodating the plurality of turbine stator blades and having a cooling fluid supply hole (e.g., the cooling fluid supply hole 20) formed therein for supplying the cooling fluid to the plurality of turbine stator blades, the gas turbine cooling fluid guide comprising: a fixed portion (e.g., the fixed portions 26, 26a, 26b, or 50) fixed to either a pipe (e.g., the pipe 5) for supplying the cooling fluid to the cooling fluid supply hole or the turbine housing;and a first guide portion (for example, the first guide portion 52) configured to cover at least a portion of an interior of the cooling fluid supply hole when viewed from an interior of the gas turbine in a radial direction along a direction 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 casing;

[0057] 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 encounters the first guide portion, so that the flow direction is changed to a direction intersecting the axial line of the cooling fluid supply hole. Therefore, it is possible to suppress the concentration of the cooling effect by the cooling fluid on the turbine stator blade near the cooling fluid supply hole (especially the turbine stator blade located on the extension line of the axial line of the cooling fluid supply hole) and suppress fluctuation of the cooling effect by the cooling fluid among the plurality of turbine stator blades.

[0058] Furthermore, according to the findings of the present inventors, in the prior art gas turbine, in a case where an auxiliary component (e.g., a heat shield plate or the like) of a turbine stator blade is attached to an outer surface of an outer shell in the radial direction, when the cooling fluid that has passed through the cooling fluid supply hole collides with the auxiliary component of the turbine stator blade, a large fluid force and fluid vibration act on the auxiliary component, and resonance may occur depending on the conditions. As a result, the auxiliary component may be damaged.In this regard, in the configuration according to (1), even in a case where the auxiliary component (for example, the heat shield plate or the like) of the turbine stator blade is attached to the outer surface of the outer shell in the radial direction, the collision of the cooling fluid that has passed through the cooling fluid supply hole with the auxiliary component of the turbine stator blade can be suppressed by the first guide portion, and it is possible to suppress the damage to the auxiliary component caused by the action of the large fluid force and fluid vibration on the auxiliary component.

[0059] Furthermore, in a case where the gas turbine cooling fluid guide is attached to the turbine stator blade instead of the pipe or the turbine casing, even if the collision of the cooling fluid that has passed through the cooling fluid supply hole with the auxiliary component of the turbine stator blade is suppressed by the gas turbine cooling fluid guide, the vibration of the gas turbine cooling fluid guide is transmitted to the turbine stator blade and the auxiliary component. Therefore, there is a concern that the auxiliary component may be damaged due to the vibration.

[0060] In contrast, the fixed portion of the gas turbine cooling fluid guide is fixed to either the pipe or the turbine casing, rather than to the turbine stator blade. Therefore, even if the cooling fluid from the cooling fluid supply hole collides with the gas turbine cooling fluid guide, the transmission of vibration to the auxiliary component is suppressed, and it is possible to effectively reduce the risk of damage to the auxiliary component due to vibration.

[0061] (2) In some embodiments, in the gas turbine cooling fluid guide according to (1), the plurality of turbine stator blades include a turbine stator blade (for example, the turbine stator blade 12A) on the extension line provided on an extension line (for example, the extension line C1) of the axis line (for example, the axis line C) of the cooling fluid supply hole, and the first guide portion is configured to be located between the turbine stator blade on the extension line and the cooling fluid supply hole in a state where the fixed portion is fixed to either the pipe or the turbine casing.

[0062] According to the gas turbine cooling fluid guide described in (2), the first guide portion can suppress the collision of the cooling fluid that has passed through the cooling fluid supply hole with the turbine stator blade on the extension line. Therefore, it is possible to suppress the concentration of the cooling effect of the cooling fluid on the turbine stator blade on the extension line located on the extension line of the axis line of the cooling fluid supply hole, and effectively suppress fluctuation of the cooling effect of the cooling fluid between the plurality of turbine stator blades.

[0063] (3) In some embodiments, in the gas turbine cooling fluid guide according to (2), the turbine stator blade on the extension line includes a blade profile portion and an outer shroud connected to an outer end of the blade profile portion in the radial direction of the gas turbine, an auxiliary component of the turbine stator blade is attached to an outer surface of the outer shroud in the radial direction, and the first guide portion is configured to be located between the auxiliary component and the cooling fluid supply hole in a state where the attached portion is attached to either the pipe or the turbine casing.

[0064] According to the present inventors' findings, in a case where the auxiliary component (e.g., the heat shield plate or the like) is attached to the outer surface of an outer shell in the radial direction, when the cooling fluid that has passed through the cooling fluid supply hole collides with the auxiliary component of the turbine stator blade on the extension line, a large fluid force and fluid vibration act on the auxiliary component, and resonance may occur depending on the conditions. As a result, the auxiliary component may be damaged.Therefore, as described in (3), when the first guide portion between the auxiliary component and the cooling fluid supply hole is in a state where the fixed portion is fixed to either the pipe or the turbine casing, it is possible to suppress the collision of the cooling fluid that has passed through the cooling fluid supply hole with the auxiliary component of the turbine stator blade on the extension line and suppress the damage caused by the action of the large fluid force and fluid vibration on the auxiliary component.

[0065] Furthermore, in a case where the gas turbine cooling fluid guide is attached to the turbine stator blade on the extension line instead of either the pipe or the turbine casing, even if the collision of the cooling fluid that has passed through the cooling fluid supply hole with the auxiliary component of the turbine stator blade on the extension line is suppressed by the gas turbine cooling fluid guide, the vibration of the gas turbine cooling fluid guide is transmitted to the turbine stator blade on the extension line and the auxiliary component. Therefore, there is a concern that the auxiliary component may be damaged due to the vibration.

[0066] In contrast, the fixed portion of the gas turbine cooling fluid guide is fixed to either the pipe or the turbine casing, rather than to the turbine stator blade. Therefore, even if the cooling fluid from the cooling fluid supply hole collides with the gas turbine cooling fluid guide, the transmission of vibration to the auxiliary component is suppressed, and it is possible to effectively reduce the risk of damage to the auxiliary component due to vibration.

[0067] (4) In some embodiments, in the gas turbine cooling fluid guide according to any one of (1) to (3), the first guide portion is formed in a plate shape, and the first guide portion is configured to include a surface (for example, the surface 35 or 56) that intersects an extension line (for example, the extension line C1) of the axis line of the cooling fluid supply hole in a state where the fixed portion is fixed to the pipe or the turbine casing.

[0068] According to the gas turbine cooling fluid guide described in (4), the cooling fluid that has passed through the cooling fluid supply hole can be guided by the plate-shaped first guide portion in a direction intersecting the extension line. Therefore, it is possible to suppress the concentration of the cooling effect of the cooling fluid on the turbine stator blade near the cooling fluid supply hole (especially the turbine stator blade located on the extension line of the axis line of the cooling fluid supply hole) and suppress fluctuation of the cooling effect of the cooling fluid among the plurality of turbine stator blades.

[0069] (5) In some embodiments, in the gas turbine cooling fluid guide according to any one of (1) to (4), the first guide portion is located 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, and the gas turbine cooling fluid guide is configured to include a second guide portion (for example, the second guide portion 30, 30a, 30b or 54) extending outward in the radial direction from the first guide portion to the fixed portion in a state where the fixed portion is fixed to the pipe or the turbine casing.

[0070] According to the gas turbine cooling fluid guide described in (5), in a state where the fixed portion is fixed to the pipe or the turbine casing, the first guide portion can be held at a position inside the fixed portion in the radial direction of the gas turbine.

[0071] (6) In some embodiments, in the gas turbine cooling fluid guide according to (5), the second guide portion is formed in a plate shape, and the second guide portion is configured to include a surface (for example, the surface 38 or 49 or the inner peripheral surface 59) that intersects an axial direction of the gas turbine in a state where the fixed portion is fixed to the tube or the turbine casing.

[0072] According to the gas turbine cooling fluid guide 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 the surface of the second guide portion intersecting the axial direction. Therefore, it is possible to suppress the concentration of the cooling effect of the cooling fluid on the turbine stator blade near the cooling fluid supply hole (especially the turbine stator blade located on the extension line of the axial line of the cooling fluid supply hole) and suppress fluctuation of the cooling effect of the cooling fluid among the plurality of turbine stator blades.

[0073] (7) In some embodiments, the gas turbine cooling fluid guide according to (1) further comprises: an upstream-side second guide portion (for example, the second guide portion 30a) extending outward in the radial direction of the gas turbine from an upstream-side end portion (for example, the end portion 36) of the first guide portion in an axial direction of the gas turbine in a state where the fixed portion is fixed to the pipe or the turbine casing;and a downstream-side second guide portion (for example, the second guide portion 30b) extending outward in the radial direction of the gas turbine from a downstream-side end portion (for example, the end portion 37) of the first guide portion in the axial direction of the gas turbine in a state where the fixed portion is fixed to the tube or the turbine casing, wherein the upstream-side second guide portion and the downstream-side second guide portion are each formed in a plate shape, and the upstream-side second guide portion and the downstream-side second guide portion are each configured to include a surface (for example, the surface 38 or 39) that intersects the axial direction in a state where the fixed portion is fixed to the tube or the turbine casing.

[0074] According to the gas turbine cooling fluid guide 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 to flow between the surface of the upstream-side second guide portion intersecting the axial direction and the surface of the downstream-side second guide portion intersecting the axial direction in the circumferential direction of the gas turbine. Therefore, it is possible to suppress the concentration of the cooling effect by the cooling fluid on the turbine stator blade near the cooling fluid supply hole (especially the turbine stator blade located on the extension line of the axial line of the cooling fluid supply hole) and to suppress fluctuation of the cooling effect by the cooling fluid among the plurality of turbine stator blades.

[0075] (8) In some embodiments, in the gas turbine cooling fluid guide according to (5), the second guide portion is formed in a cylindrical shape, and the fixed portion includes a flange connected to an end portion (for example, the end portion 53) of the second guide portion.

[0076] According to the gas turbine cooling fluid guide described in (8), the cylindrical second guide portion may be inserted into the cooling fluid supply hole such that the flange is located on an inlet side of the cooling fluid supply hole and the first guide portion is located on an outlet side of the cooling fluid supply hole. Furthermore, the cooling fluid may be guided by the inner peripheral surface of the cylindrical second guide portion to flow toward the first guide portion along the axis line direction of the cooling fluid supply hole.

[0077] (9) In some embodiments, in the gas turbine cooling fluid guide according to (8), the flange includes an outer peripheral flange portion (for example, the outer peripheral flange portion 50a) protruding from the end portion of the second guide portion to an outer peripheral side in the cylindrical shape of the second guide portion, and an inner peripheral flange portion (for example, the inner peripheral flange portion 50b) protruding from the end portion of the second guide portion to an inner peripheral side in the cylindrical shape of the second guide portion, and an opening (for example, the opening 55) having a smaller diameter than the cooling fluid supply hole is formed at the inner peripheral flange portion.

[0078] According to the gas turbine cooling fluid guide described in (9), the configuration according to (8) can be achieved with a small number of components, and a flow rate of the cooling fluid through the opening can be increased.

[0079] (10) In some embodiments, in the gas turbine cooling fluid guide according to (8) or (9), a plurality of through holes (for example, the plurality of through holes 60, 60a or 60b) are formed on an outer peripheral surface of the second guide portion.

[0080] According to the gas turbine cooling fluid guide 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. Therefore, it is possible to suppress the concentration of the cooling effect of the cooling fluid on the turbine stator blade near the cooling fluid supply hole (especially the turbine stator blade located on the extension line of the axis line of the cooling fluid supply hole) and suppress fluctuation of the cooling effect of the cooling fluid between the plurality of turbine stator blades.

[0081] (11) In some embodiments, in the gas turbine cooling fluid guide according to (10), the plurality of through holes include: a plurality of first through holes (for example, the plurality of through holes 60a) provided at intervals in a circumferential direction of the outer peripheral surface of the second guide portion at a first position in an axial direction of the cylindrical shape of the second guide portion; and a plurality of second through holes (for example, the plurality of through holes 60b) provided in the circumferential direction of the outer peripheral surface of the second guide portion at a second position in the axial direction of the cylindrical shape of the second guide portion.

[0082] According to the gas turbine cooling fluid guide described in (11), 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 first through holes and the plurality of second through holes on the outer peripheral surface of the second guide portion. This makes it possible to adjust the flow rate of the cooling fluid ejected from the second guide portion and to distribute an ejection position of the cooling fluid in the second guide portion in the axial direction and the circumferential direction of the cylindrical shape.Therefore, it is possible to suppress the concentration of the cooling effect by the cooling fluid on the turbine stator blade near the cooling fluid supply hole (especially the turbine stator blade located on the extension line of the axis line of the cooling fluid supply hole) and to suppress fluctuation of the cooling effect by the cooling fluid between the plurality of turbine stator blades.

[0083] (12) According to at least one embodiment of the present disclosure, there is provided a gas turbine comprising: the gas turbine cooling fluid guide according to any one of (1) to (11); the turbine casing; and the plurality of turbine stator blades.

[0084] According to the gas turbine described in (12), since the gas turbine cooling fluid guide according to any one of (1) to (11) is provided, it is possible to suppress the concentration of the cooling effect by the cooling fluid on the turbine stator blade (especially the turbine stator blade located on the extension line of the axis line of the cooling fluid supply hole) in the vicinity of the cooling fluid supply hole and suppress fluctuation of the cooling effect by the cooling fluid between the plurality of turbine stator blades. List of reference symbols 2 gas turbines 4 Compressor 5 pipe 5a Flange 6 combustion chamber 8 turbines 9 Rotor (turbine rotor) 10 turbine housings 10b inner surface 10a Outer surface 12 turbine stator blades 12A Turbine stator blade (turbine stator blade on extension line) 14 Flow path 15 Outer peripheral wall 16 turbine rotor blades 20 Cooling fluid supply hole 24A, 24B Gas turbine cooling fluid guide 26, 26a, 26b, 50 paved section 27, 42 Fastening element 28, 52 first guide section 30, 30a, 30b, 54 second guide section 31, 34, 36, 37, 53, 55 final section 32 End margin 33 Recess section 35, 38, 39, 56 surface (guide surface) 40, 55 opening 41 Opening plate 50a outer peripheral flange section 50b inner peripheral flange section 58 Outer peripheral surface 59 inner circumferential surface 60, 60a, 60b through hole 80 blade profile section 82 outer sheath 83 exterior area 84 Sealing tube 85 External cavity 86 Heat shield plate 87 Cover plate section 88 side wall section QUOTES CONTAINED IN THE DESCRIPTION

[0000] This list of documents submitted by the applicant was generated automatically and is included solely for the convenience of the reader. This list is not part of the German patent or utility model application. The DPMA assumes no liability for any errors or omissions. Cited patent literature

[0000] JP 2022-140481

[0002] WO 2017 / 090709

[0004]

Claims

[1] A gas turbine cooling fluid guide for guiding a cooling fluid of a gas turbine, the gas turbine including a plurality of turbine stator blades and a turbine casing accommodating the plurality of turbine stator blades and having a cooling fluid supply hole formed therein for supplying the cooling fluid to the plurality of turbine stator blades, the gas turbine cooling fluid guide comprising: a fixed portion fixed to either a pipe for supplying the cooling fluid to the cooling fluid supply hole or the turbine housing; and a first guide portion configured to cover at least a portion of the cooling fluid supply hole when viewed from an interior of the gas turbine in a radial direction along a direction 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 casing. [2] The gas turbine cooling fluid guide according to claim 1, wherein the plurality of turbine stator blades includes a turbine stator blade on extension line provided on an extension line of the axis line of the cooling fluid supply hole, and the first guide portion is configured to be located between the turbine stator blade on extension line and the cooling fluid supply hole in a state where the fixed portion is fixed to either the pipe or the turbine casing. [3] Gas turbine cooling fluid guide according to claim 1, wherein each of the turbine stator blades includes a blade profile section and an outer shroud connected to an outer end of the blade profile section in the radial direction of the gas turbine, an additional component of the turbine stator blade is attached to an outer surface of the outer shell in the radial direction, and the first guide portion is configured to be located between the auxiliary component and the cooling fluid supply hole in a state where the fixed portion is fixed to the pipe or the turbine casing. [4] Gas turbine cooling fluid guide according to claim 1, wherein the first guide portion is formed in a plate shape, and the first guide portion is configured to include a surface intersecting an extension line of the 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] Gas turbine cooling fluid guide according to claim 1, wherein the first guide portion is located inside the fixed portion in the radial direction of the gas turbine in a state in which the fixed portion is fixed to the pipe or the turbine casing, and the gas turbine cooling fluid guide is configured to include a second guide portion extending outward in the radial direction from the first guide portion to the fixed portion in a state where the fixed portion is fixed to the pipe or the turbine casing. [6] Gas turbine cooling fluid guide according to claim 5, wherein the second guide portion is formed in a plate shape, and the second guide portion is configured to include a surface intersecting an axial direction of the gas turbine in a state where the fixed portion is fixed to the pipe or the turbine casing. [7] Gas turbine cooling fluid guide according to claim 1, further comprising: an upstream-side second guide portion extending outward in the radial direction of the gas turbine from an upstream-side end portion of the first guide portion in an axial direction of the gas turbine in a state in which the fixed portion is fixed to the pipe or the turbine casing; and a downstream-side second guide portion extending outward in the radial direction of the gas turbine from a downstream-side end portion of the first guide portion in the axial direction of the gas turbine in a state in which the fixed portion is fixed to the pipe or the turbine casing, wherein the upstream-side second guide portion and the downstream-side second guide portion are each formed in a plate shape, and the upstream-side second guide portion and the downstream-side second guide portion are each configured to include a surface intersecting the axial direction in a state where the fixed portion is fixed to the pipe or the turbine casing. [8] Gas turbine cooling fluid guide according to claim 5, wherein the second guide portion is formed in a cylindrical shape, and the fixed portion includes a flange connected to an end portion of the second guide portion. [9] Gas turbine cooling fluid guide according to claim 8, wherein the flange includes an outer peripheral flange portion protruding from the end portion of the second guide portion to an outer peripheral side in the cylindrical shape of the second guide portion, and an inner peripheral flange portion protruding from the end portion of the second guide portion to an inner peripheral side in the cylindrical shape of the second guide portion, and an opening having a smaller diameter than the cooling fluid supply hole is formed in the inner peripheral flange portion. [10] A gas turbine cooling fluid guide according to claim 9, wherein a plurality of through holes are formed on an outer peripheral surface of the second guide portion. [11] A gas turbine cooling fluid guide according to claim 10, wherein the plurality of through holes comprise: a plurality of first through holes provided at intervals in a circumferential direction of the outer peripheral surface of the second guide portion at a first position in an axial direction of the cylindrical shape of the second guide portion; and a plurality of second through holes provided at intervals in the circumferential direction of the outer peripheral surface of the second guide portion at a second position in the axial direction of the cylindrical shape of the second guide portion. [12] Gas turbine, comprising: the gas turbine cooling fluid guide according to one of claims 1 to 11; the turbine housing; and the multiple turbine stator blades.

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