Stationary vane and gas turbine having stationary vane

Abstract

The fixed blade of the present invention comprises: an insertion cylinder disposed within a blade air passage penetrating a first shroud body, a blade body, and a second shroud body; and an insertion support body supporting the insertion cylinder. The insertion cylinder has: a cylindrical body formed therein, having a plurality of impact holes extending from the inner circumferential side to the outer circumferential side; and a flange protruding from the inner circumferential surface of the cylindrical body toward the inner circumferential side of the cylindrical body. The insertion support body has: a support plate fixed to the second shroud body; and a position-limiting protrusion protruding from the support plate. A protrusion insertion groove for embedding the position-limiting protrusion is formed on the insertion cylinder.

Description

Technical Field

[0001] This invention relates to a fixed blade and a gas turbine equipped with the fixed blade.

[0002] This application claims priority based on Japanese Patent Application No. 2023-198160, filed on November 22, 2023, the contents of which are incorporated herein by reference. Background Technology

[0003] A gas turbine includes: a compressor capable of compressing air to generate compressed air; a combustor capable of burning fuel in the compressed air to generate combustion gases; and a turbine capable of being driven by the combustion gases. The turbine includes a rotor rotating about an axis and a turbine housing covering the rotor. The rotor includes: a rotor shaft extending along the axis; and a plurality of rotating blades mounted on the rotor shaft. The plurality of rotating blades are arranged at intervals along the axis. Each of the plurality of rotating blades has a plurality of rotating blades arranged circumferentially relative to the axis. Inside the turbine housing, a plurality of fixed blades are provided. The plurality of fixed blades are arranged at intervals along the axis. Each of the plurality of fixed blades has a plurality of fixed blades arranged circumferentially relative to the axis.

[0004] Patent Document 1 discloses a fixed blade for a gas turbine. This fixed blade includes: a blade body extending radially relative to an axis; an outer shroud disposed radially outward of the blade body; an inner shroud disposed radially inward of the blade body; and a blade cooling air passage. The blade body of the fixed blade is disposed within a combustion gas flow path through which combustion gases pass. The outer shroud includes: an outer shroud body extending in a direction perpendicular to the radial direction of the blade body and defining an edge on the radially outer side of the combustion gas flow path; and a peripheral wall protruding radially outward from the outer peripheral edge of the outer shroud body. The outer shroud body and the peripheral wall together form a recessed portion radially inward on the radially outer side of the outer shroud body. The inner shroud includes: an inner shroud body extending in a direction perpendicular to the radial direction of the blade body and defining an edge on the radially inner side of the combustion gas flow path; and a peripheral wall protruding radially inward from the outer peripheral edge of the inner shroud body. The inner shroud body and the peripheral wall together form a recess that is radially recessed outward on the radially inner side of the inner shroud body. The opening of this recess is sealed by a baffle plate engaged with the edge of the opening. The blade cooling air passage runs radially through the outer shroud body, the blade body, and the inner shroud body.

[0005] The fixed blade also includes an insert (or insert tube) disposed within the blade air passage. The insert has a radially extending, cylindrical body. Multiple impact holes are formed on this cylindrical body, extending from the inner circumferential side to the outer circumferential side. In this fixed blade, cooling air flowing into the recess of the outer shroud flows into the insert within the blade cooling air passage. After passing through the multiple impact holes of the insert, the cooling air flows into a recess formed radially inward on the inner side of the inner shroud body.

[0006] Furthermore, Patent Document 2 also discloses a fixed blade for a gas turbine. This fixed blade, similar to the one disclosed in Patent Document 1, includes: a blade body extending radially relative to an axis; an outer shroud disposed radially outward of the blade body; an inner shroud disposed radially inward of the blade body; and a blade air passage. The blade body of the fixed blade is disposed within a combustion gas flow path through which combustion gases pass. The outer shroud has an outer shroud body extending in a direction perpendicular to the radial extension of the blade body and defining the radially outer edge of the combustion gas flow path. Similarly, the inner shroud has an inner shroud body extending in a direction perpendicular to the radial extension of the blade body and defining the radially inner edge of the combustion gas flow path. The blade air passage radially extends through the outer shroud body, the blade body, and the inner shroud body. The fixed blade also includes an insert (or insert sleeve) disposed within the blade air passage and a retaining member (or insert support) supporting the insert. The insert has a radially extending, cylindrical body. Multiple impact holes are formed on this cylindrical body, extending from the inner circumferential side to the outer circumferential side. The retaining member has: a support plate extending in a direction perpendicular to the direction of extension of the cylindrical body and fixed to the outer shroud body; and a positioning portion (protrusion) protruding radially outward from the support plate and facing the inner circumferential surface of the cylindrical body. This positioning portion restricts the relative position of the insert with respect to the retaining member in a radially perpendicular direction. On the other hand, to allow for the difference in radial thermal expansion between the insert and the blade body, the radially inner end of the insert can move radially relative to the retaining member. Cooling air located on the inner circumferential side of the insert collides with the channel defining surface that defines the air passage for the blade via the multiple impact holes of the insert. Therefore, the channel defining surface is subjected to impact cooling by the cooling air passing through the multiple impact holes of the insert.

[0007] In this fixed blade, the portion of the support plate opposite the area on the inner circumference of the cylinder is not open. Therefore, cooling air flowing into the cylinder from the radially outer side of the cylinder will not flow to the radially inner side of the inner shroud body.

[0008] Previous technical documents

[0009] Patent documents

[0010] Patent Document 1: Japanese Patent Application Publication No. 2013-019348

[0011] Patent Document 2: Japanese Patent Application Publication No. 2017-150333 Summary of the Invention

[0012] The technical problem to be solved by the invention

[0013] As with the fixed blade described in Patent Document 1, even when cooling air flows from the recess of the outer shroud into the recess of the inner shroud through the insert tube in the blade air passage, it is necessary to both restrict the movement of the insert tube in the direction perpendicular to the radial direction and allow for the difference in thermal expansion between the insert tube and the blade body in the radial direction. Therefore, in this case, by adopting the structure of the retaining member (or insert support) in the fixed blade described in Patent Document 2, the movement of the insert tube in the direction perpendicular to the radial direction (blade height direction) is restricted, while allowing for the difference in thermal expansion between the insert tube and the blade body in the radial direction. Furthermore, in this case, the support plate of the retaining member (or insert support) needs to have an opening in the portion opposite to the area on the inner circumference of the insert tube.

[0014] When cooling air flows from the recess of the outer shroud into the recess of the inner shroud through the insert tube in the blade air passage, if the structure of the retaining member (or insert support) in the fixed blade described in Patent Document 2 is adopted, a portion of the cooling air in the insert tube leaks from the gap between the inner circumferential surface of the insert tube and the protruding piece of the insert support to the outer circumferential side of the insert tube. If a portion of the cooling air in the insert tube leaks to the outer circumferential side of the insert tube from the portion other than the impact holes, the pressure difference between the inner and outer circumferential sides of the insert tube decreases. Therefore, the velocity of the cooling air on the inner circumferential side of the insert tube decreases when it passes through the multiple impact holes of the insert tube, thereby reducing the impact cooling effect on the channel defining surface that defines the blade air passage.

[0015] Therefore, the object of the present invention is to provide a fixed blade and a gas turbine having the fixed blade, wherein the fixed blade restricts the movement of the insert in a direction perpendicular to the blade height direction, and allows the thermal elongation difference between the insert and the blade body in the blade height direction, while suppressing the reduction of the impact cooling effect on the channel limiting surface that defines the air passage of the blade.

[0016] means for solving technical problems

[0017] As one aspect of the invention for achieving the aforementioned objective, the fixed blade comprises:

[0018] The blade body has an airfoil-shaped cross-section and extends along a blade height direction having a component perpendicular to the cross-section; a blade air passage extends within the blade body along the blade height direction, allowing cooling air to circulate therethrough; a first shroud is disposed at an end of the blade body on a first side of the blade height in the blade height direction; a second shroud is disposed at an end of the blade body on the opposite side of the first side of the blade height, i.e., a second side of the blade height; an insert cylinder, at least a portion of which is disposed within the blade air passage; and an insert support body supporting the insert cylinder. The first shroud has a first shroud body extending from the end of the blade body on the first side of the blade height in a direction perpendicular to the blade height direction. The second shroud has a second shroud body extending from the end of the blade body on the second side of the blade height in a direction perpendicular to the blade height direction. The blade air passage extends through the first shroud body, the blade body, and the second shroud body along the blade height direction. The insertion cylinder has: a cylindrical body extending along the blade height direction and cylindrical in shape, with openings at an end on a first side of the blade height and an end on a second side of the blade height, and forming a plurality of impact holes penetrating from the inner circumferential side to the outer circumferential side; and a flange portion protruding from a position near the second side of the blade height toward the inner circumferential side of the cylindrical body in the inner circumferential surface of the cylindrical body, thereby narrowing the air passage inside the cylindrical body. The insertion support has: a support plate extending in a direction perpendicular to the blade height direction and fixed to the second protective cover body; and a position limiting protrusion protruding from the support plate toward the first side of the blade height. The support plate has a support plate opening, which penetrates along the blade height direction at a portion opposite to the region on the inner circumferential side of the cylindrical body. The position-limiting protrusion extends from the support plate toward the first side of the blade height along the entire circumference of the opening edge of the support plate, forming a cylindrical shape. It faces the inner or outer circumferential surface of the second end portion of the cylinder, which includes the second side of the blade height, thereby limiting the relative position of the insertion cylinder with respect to the insertion support in a direction perpendicular to the blade height direction. One of the insertion cylinder and the insertion support has: a groove bottom extending in a direction perpendicular to the blade height direction; and a groove sidewall portion protruding from the groove bottom toward the blade height direction. When the insertion cylinder is the one in question, the groove sidewall portion is cylindrical, extending along the entire circumference of the cylinder and spaced apart from the second end portion of the cylinder. The groove bottom extends along the entire circumference of the cylinder, connecting the cylinder and the groove sidewall portion, thereby forming an annular protrusion insertion groove in which the position-limiting protrusion is embedded by the cylinder, the groove sidewall portion, and the groove bottom.In the case where one of them is the insert support, the groove sidewall is cylindrical, extending across the entire circumference of the cylinder and spaced apart from the position limiting protrusion. The groove bottom extends across the entire circumference of the cylinder, connecting the position limiting protrusion to the groove sidewall. Thus, the position limiting protrusion, the groove sidewall, and the groove bottom form an annular cylindrical insertion groove into which the second side end of the cylinder is embedded. The insert cylinder engages with the insert support in a manner that allows relative movement.

[0019] In this configuration, the insert cylinder engages with the insert support in a manner that allows for relative movement. In this configuration, the annular position-limiting protrusion of the insert support, fixed to the second shield body, faces the inner or outer circumferential surface of the insert cylinder. Therefore, in this configuration, on the one hand, movement of the insert cylinder in a direction perpendicular to the blade height direction can be restricted, and on the other hand, the second end of the insert cylinder can move relative to the blade body in the blade height direction. Therefore, in this configuration, the thermal expansion difference between the insert cylinder and the blade body in the blade height direction can be tolerated.

[0020] In this method, cooling air located on the first side of the blade height, further than the first shroud body, flows into the cylinder of an insert tube disposed within the blade air passage. The cooling air flowing into the cylinder moves along the cylinder towards the second side of the blade height. During this process, a portion of the cooling air passes through multiple impact holes in the cylinder. The remaining cooling air flows through an opening in the support plate to a space on the second side of the blade height, further than the second shroud body. The cooling air passing through the multiple impact holes in the cylinder impinges on the channel defining surface that defines the blade air passage, providing impact cooling.

[0021] In this method, to accommodate the difference in thermal expansion between the insert cylinder and the blade body in the blade height direction, the insert cylinder is not joined to the insert support. Therefore, a portion of the cooling air flowing into the space on the second side of the blade height, which is further from the second shroud body than the second shroud body, through the opening in the support plate, may leak into the space within the blade air passage and on the outer periphery of the cylinder via the gap between the insert support and the insert cylinder. Assuming that the flow rate of cooling air leaking into the space within the blade air passage and on the outer periphery of the cylinder via the gap between the insert support and the insert cylinder increases, the pressure difference between the inner and outer periphery of the cylinder decreases. Consequently, the velocity of the cooling air on the inner periphery of the cylinder decreases as it passes through the multiple impact holes of the cylinder, thereby reducing the impact cooling effect on the channel defining surface that defines the blade air passage.

[0022] In this embodiment, when one of the components is an insert cylinder, the gap between the insert support and the insert cylinder becomes the gap between the protrusion insertion groove and the position-limiting protrusion embedded in the groove. Therefore, the flow path of the cooling air formed by this gap is also wavy and curved in the blade height direction. Furthermore, in this embodiment, when one of the components is an insert support, it becomes the gap between the cylinder insertion groove and the second side end of the cylinder embedded in the groove. Therefore, the flow path of the cooling air formed by this gap is also wavy and curved in the blade height direction. Therefore, in this embodiment, the resistance of the cooling air flowing in the flow path formed by the gap between the insert support and the insert cylinder increases. In particular, the resistance of the cooling air at the corners of this flow path increases.

[0023] Furthermore, in this embodiment, since a flange portion is provided inside the cylinder to narrow the air passage within the cylinder, the pressure of the cooling air passing through the flange portion inside the cylinder can be reduced. Therefore, in this embodiment, the pressure of the cooling air flowing out of the cylinder and into the gap between the insert support and the insert cylinder can be reduced.

[0024] As described above, in this method, the resistance of the cooling air flowing in the flow path formed by the gap between the insert support and the insert cylinder increases, and the pressure of the cooling air flowing into the gap between the insert support and the insert cylinder decreases. Therefore, the flow rate of cooling air leaking into the space on the outer periphery of the cylinder into the blade air passage can be reduced. Therefore, in this method, the reduction in the impact cooling effect on the channel defining surface that defines the blade air passage can be suppressed.

[0025] A gas turbine, as one aspect of the invention for achieving the aforementioned objective, comprises:

[0026] As one embodiment, the rotor comprises a fixed blade, a rotor capable of rotating about an axis, and a turbine housing covering the rotor. The fixed blade is mounted inside the turbine housing such that the height direction of the blade is radial relative to the axis.

[0027] Invention Effects

[0028] According to one aspect of the present invention, on the one hand, the movement of the insert cylinder in a direction perpendicular to the blade height direction is restricted, and on the other hand, the thermal elongation difference between the insert and the blade body in the blade height direction is allowed, while suppressing the reduction of the impact cooling effect on the channel defining surface that defines the air passage of the blade. Attached Figure Description

[0029] Figure 1 This is a schematic cross-sectional view of a gas turbine according to one embodiment of the present invention.

[0030] Figure 2 This is a cross-sectional view of the main part of a gas turbine in one embodiment of the present invention.

[0031] Figure 3 This is a perspective view of the fixed blade in one embodiment of the present invention, viewed from the radial outer side.

[0032] Figure 4 This is a perspective view of the fixed blade in one embodiment of the present invention, viewed from the radial inside.

[0033] Figure 5 This is a cross-sectional view of a section cut along the arc of a fixed blade in one embodiment of the present invention.

[0034] Figure 6 This is a cross-sectional view of the main part of the fixed blade in one embodiment of the present invention.

[0035] Figure 7 This is a perspective view of the insert support body in one embodiment of the present invention.

[0036] Figure 8 This is a cross-sectional view of the main part of the blade body in one embodiment of the present invention.

[0037] Figure 9 This is a flowchart illustrating the manufacturing sequence of the fixed blade in one embodiment of the present invention.

[0038] Figure 10 This is a cross-sectional view of the main part of the blade body during the manufacturing process of the fixed blade in one embodiment of the present invention.

[0039] Figure 11 This is a cross-sectional view of the insert cylinder and insert support body in the first modified example of the present invention.

[0040] Figure 12 This is a cross-sectional view of the main part of the fixed blade in the second variation of the present invention.

[0041] Figure 13 This is a cross-sectional view of the main part of the fixed blade in the third variation of the present invention.

[0042] Figure 14 This is a cross-sectional view of the main part of the fixed blade in the fourth variation of the present invention.

[0043] Figure 15 This is a perspective view of the insert support body in the fourth variation of the present invention.

[0044] Figure 16This is a perspective view of the insert support body in the fifth modified example of the present invention. Detailed Implementation

[0045] Hereinafter, an embodiment and variations thereof of the present invention will be described in detail with reference to the accompanying drawings.

[0046] "Implementation Methods of Gas Turbines"

[0047] Reference for implementation methods of gas turbines Figure 1 and Figure 2 Please provide an explanation.

[0048] The gas turbine in this embodiment is as follows: Figure 1 As shown, it includes: a compressor 10 capable of compressing external air A to generate compressed air Acom; a burner 20 capable of burning fuel F from a fuel supply source in the compressed air Acom to generate combustion gas G; and a turbine 30 capable of being driven by the combustion gas G.

[0049] The compressor 10 includes: a compressor rotor 11 that rotates about an axis Ar; a compressor housing 18 that covers the compressor rotor 11; and a plurality of fixed blades 15. The turbine 30 includes: a turbine rotor 31 that rotates about an axis Ar; a turbine housing 38 that covers the turbine rotor 31; and a plurality of fixed blades 35. Furthermore, the direction in which the axis Ar extends is referred to as the axial direction Da, the circumferential direction centered on the axis Ar is simply referred to as the circumferential direction Dc, and the direction perpendicular to the axis Ar is referred to as the radial direction Dr. Furthermore, one side of the axial direction Da is designated as the upstream side Dau, and the opposite side is designated as the downstream side Dad. Furthermore, in the radial direction Dr, the side closest to the axis Ar is designated as the radially inner side Dri, and the opposite side is designated as the radially outer side Dro.

[0050] The compressor 10 is positioned on the upstream side of the shaft relative to the turbine 30, in the Dau configuration.

[0051] The compressor rotor 11 and the turbine rotor 31 are located on the same axis Ar and are connected to each other to form the gas turbine rotor 1. For example, a generator rotor GEN is connected to this gas turbine rotor 1. The gas turbine also includes an intermediate casing 6. This intermediate casing 6 is disposed between the compressor casing 18 and the turbine casing 38 in the axial direction Da. The compressor casing 18, the intermediate casing 6, and the turbine casing 38 are connected to each other to form the gas turbine casing 8.

[0052] Compressor rotor 11 Figure 1 and Figure 2As shown, the compressor includes: a rotor shaft 12 extending along the axial direction Da with axis Ar as its center; and a plurality of rotating blade grids 13 mounted on the rotor shaft 12. The plurality of rotating blade grids 13 are arranged along the axial direction Da. Each rotating blade grid 13 is composed of a plurality of rotating blades arranged circumferentially Dc. One of a plurality of fixed blade grids 15 is disposed downstream of each of the rotating blade grids 13 on the axis Dad. Each fixed blade grid 15 is disposed inside the compressor housing 18. Each fixed blade grid 15 is composed of a plurality of fixed blades arranged circumferentially Dc.

[0053] The turbine rotor 31 has a rotor shaft 32 extending along the axial direction Da with the axis Ar as the center, and a plurality of rotating blade grates 33 mounted on the rotor shaft 32. The plurality of rotating blade grates 33 are arranged along the axial direction Da. Each rotating blade grates 33 is composed of a plurality of rotating blades arranged circumferentially Dc. One of a plurality of fixed blade grates 35 is disposed on the upstream side Dau of each of the plurality of rotating blade grates 33. Each fixed blade grates 35 is disposed inside the turbine housing 38. Each fixed blade grates 35 is composed of a plurality of fixed blades arranged circumferentially Dc.

[0054] An annular space, in which rotating blades 33 and fixed blades 35 are arranged between the outer periphery of the rotor shaft 32 and the inner periphery of the turbine housing 38 along the axial direction Da, forms a combustion gas flow path 39 for the combustion gas G from the combustor 20 to flow. This combustion gas flow path 39 is annular about the axis Ar and extends along the axial direction Da.

[0055] Inside the turbine housing 38, in addition to a plurality of fixed blade slats 35, a plurality of dividing rings 37 are provided. The dividing rings 37 are located in the axial direction Da at positions where rotating blade slats 33 are located and are radially outer (Dro) of the rotating blade slats 33. Therefore, the dividing rings 37 are positioned between the plurality of fixed blade slats 35 arranged along the axial direction Da. The dividing rings 37 define a portion of the edge of the radially outer (Dro) of the combustion gas flow path 39.

[0056] The burner 20 is mounted on the intermediate housing 6. The burner 20 is as follows: Figure 2 As shown, it has: a tail tube (or combustion tube) 22, in which fuel F is burned; and a plurality of combustion furnaces 21, into which fuel is injected.

[0057] In this embodiment, a cooling device 40 is connected to the gas turbine. This cooling device 40 includes an extraction pipe 41, a cooler 42, a booster compressor 43, and a cooling air pipe 44. One end of the extraction pipe 41 is connected to the intermediate housing 6, and the other end is connected to the intake port of the booster compressor 43. The extraction pipe 41 can extract compressed air from the intermediate housing 6 to the outside of the gas turbine housing 8. The cooler 42 is provided in the extraction pipe 41 and can cool the compressed air flowing in the extraction pipe 41. The booster compressor 43 can pressurize the compressed air cooled by the cooler 42. The cooling air pipe 44 has one end and multiple other ends. One end of the cooling air pipe 44 is connected to the outlet of the booster compressor 43. The multiple other ends of the cooling air pipe 44 are connected to any one of multiple high-temperature components such as fixed blades exposed to the combustion gases G. The cooling air duct 44 can introduce compressed air from the booster compressor 43 as cooling air Acl into the high-temperature components.

[0058] "Implementation Method of Fixed Blades"

[0059] For implementation methods of fixed blades, refer to Figures 3 to 10 This will be explained. Furthermore, the fixed blades described below refer to the fixed blades that constitute the fixed blade grid 35 described in the "Embodiment of the Gas Turbine" above.

[0060] like Figures 3-5 As shown, the fixed blade 50 of this embodiment has a blade body 51, an inner shield (second shield) 60i, an outer shield (first shield) 60o, a plurality of blade air channels 56, a plurality of leading edge injection channels 59f and a plurality of trailing edge injection channels 59b.

[0061] The blade body 51 has an airfoil-shaped cross-section and extends along the blade height direction Dr, which has a directional component perpendicular to the cross-section. Additionally, as... Figure 2 As shown, when the fixed blade 50 is mounted on the turbine housing 38, the blade height direction Dr becomes radial Dr. The blade body 51 (36b) is positioned in the combustion gas flow path 39 for the combustion gas G to flow (see reference). Figure 2The inner shield 60i is disposed at the end of the second side Dri of the blade height direction on both sides of the blade body 51 in the blade height direction Dr. In other words, the inner shield 60i is disposed at the end of the radially inner side Dri of the blade body 51. The inner shield 60i defines the edge of the radially inner side Dri of the annular combustion gas flow path 39. The outer shield 60o is disposed at the end of the first side Dro of the blade height direction on both sides of the blade body 51 in the blade height direction Dr. In other words, the outer shield 60o is disposed at the end of the radially outer side Dro of the blade body 51. Furthermore, the outer shield 60o defines the edge of the radially outer side Dro of the annular combustion gas flow path 39. In addition, the blade height direction Dr is referred to as radial Dr below. The first side Dro of the blade height is referred to as radially outer Dro, and the second side Dri of the blade height is referred to as radially inner Dri.

[0062] The blade body 51 has: a leading edge 52; a trailing edge 53; a positive pressure surface 55 for connecting the leading edge 52 and the trailing edge 53; and a negative pressure surface 54, which is back-to-back with the positive pressure surface 55 and also for connecting the leading edge 52 and the trailing edge 53. The leading edge 52, trailing edge 53, positive pressure surface 55, and negative pressure surface 54 all extend radially along the direction Dr. The leading edge is the end of the upstream side (Dau) of the axis in the blade body 51. The trailing edge is the end of the downstream side (Dad) of the axis in the blade body 51. The positive pressure surface 55 is concave, and the negative pressure surface 54 is convex. The positive pressure surface 55 faces the circumferential positive pressure side (Dcp). The negative pressure surface 54 faces the other side of the circumferential negative pressure side (Dcn).

[0063] Inner shield (second shield) 60i Figure 4 and Figure 5 As shown, the blade body 61i has an inner shield body (second shield body) 61i and a peripheral wall 65i. The inner shield body 61i extends from the radially inner end of the blade body 51 (Dri) in a direction perpendicular to the radial direction (Dr). The inner shield body 61i has: an airflow path surface 64p facing the radially outer side (Dro); an airflow reverse path surface 64a facing the radially inner side (Dri); a front end surface 62f, which is the end face of the upstream side (Dau) of the axis; a rear end surface 62b, which is the end face of the downstream side (Dad) of the axis; a positive pressure side end surface 63p, which is the end face of the circumferential positive pressure side (Dcp); and a negative pressure side end surface 63n, which is the end face of the circumferential negative pressure side (Dcn). The front end surface 62f and the rear end surface 62b are substantially parallel. Furthermore, the positive pressure side end surface 63p and the negative pressure side end surface 63n are substantially parallel. Therefore, the inner shield body 61i is parallelogram-shaped when viewed from the radial direction (Dr).

[0064] A peripheral wall 65i protrudes radially inward from the reverse airflow path surface 64a of the inner shield body 61i. This peripheral wall 65i is provided along the end face of the inner shield body 61i. The peripheral wall 65i has: a front wall 65f and a rear wall 65b, which are opposite to each other in the axial direction Da; and a positive pressure side wall 65p and a negative pressure side wall 65n, which are opposite to each other in the circumferential direction Dc. The front wall 65f is located along the front end face 62f of the inner shield body 61i. The rear wall 65b is located along the rear end face 62b of the inner shield body 61i. The positive pressure side wall 65p is located along the positive pressure side end face 63p of the inner shield body 61i. The negative pressure side wall 65n is located along the negative pressure side end face 63n of the inner shield body 61i. In the inner shield 60i, a recess 66 is formed by the inner shield body 61i and the peripheral wall 65i, recessed towards the radially outward direction (Dro). Furthermore, the circumferential positive pressure side (Dcp) surface of the positive pressure side wall 65p is a single surface with the positive pressure side end face 63p of the inner shield body 61i. Similarly, the circumferential negative pressure side (Dcn) surface of the negative pressure side wall 65n is a single surface with the negative pressure side end face 63n of the inner shield body 61i. The rear wall 65b is formed along the rear end face 62b of the inner shield body 61i, but is formed on the upstream side (Dau) of the axis, further upstream than the rear end face 62b.

[0065] exist Figure 2 On any of the fixed blades constituting one of the plurality of fixed blade grids 35 shown, a fixing member 69 is provided, protruding radially inward from the positive pressure side wall 65p and negative pressure side wall 65n of the inner shroud 60i. This fixing member 69 is located between the front wall 65f and the rear wall 65b in the axial direction Da, and is formed from the positive pressure side end face 63p to the negative pressure side end face 63n. This fixing member 69 is responsible for contacting the radially outer end of the inner cover 7 fixed to the gas turbine housing 8, such that a portion of the radially inner side Dri of the fixed blade 50 is supported by the radially outer end of the inner cover 7.

[0066] Outer shield (first shield) 60° Figure 3 and Figure 5As shown, the blade body 51 has an outer shield body (first shield body) 61o, a peripheral wall 65o, a front hook 68f, and a rear hook 68b. The outer shield body 61o extends from the radially outer end of the blade body 51 (Dro) in a direction perpendicular to the radial direction (Dr). Like the inner shield body 61i, the outer shield body 61o also has an airflow path surface 64p, a reverse airflow path surface 64a, a front end surface 62f, a rear end surface 62b, a positive pressure side end surface 63p, and a negative pressure side end surface 63n. Like the inner shield body 61i, the outer shield body 61o is also parallelogram-shaped when viewed from the radial direction (Dr). Furthermore, the airflow path surface 64p of the inner shield body 61i faces the radially outer direction (Dro), but the airflow path surface 64p of the outer shield body 61o faces the radially inner direction (Dri).

[0067] A peripheral wall 65o protrudes radially outward from the reverse airflow path surface 64a of the outer shield body 61o. This peripheral wall 65o is provided along the end face of the outer shield body 61o. The peripheral wall 65o of the outer shield 60o, like the peripheral wall 65i of the inner shield 60i, also has a front wall 65f, a rear wall 65b, a positive pressure side wall 65p, and a negative pressure side wall 65n. The front wall 65f is located along the front end face 62f of the outer shield body 61o. The rear wall 65b is located along the rear end face 62b of the outer shield body 61o. The positive pressure side wall 65p is located along the positive pressure side end face 63p of the outer shield body 61o. The negative pressure side wall 65n is located along the negative pressure side end face 63n of the outer shield body 61o. On the outer shield 60o, a recess 66 is formed by the outer shield body 61o and the peripheral wall 65o, recessed towards the radially inward direction (Dri). Furthermore, the circumferential positive pressure side (Dcp) surface of the positive pressure side wall 65p is a single surface with the positive pressure side end face 63p of the outer shield body 61o. Similarly, the circumferential negative pressure side (Dcn) surface of the negative pressure side wall 65n is a single surface with the negative pressure side end face 63n of the outer shield body 61o.

[0068] The front hook 68f is formed to protrude radially outward from the front wall 65f. The rear hook 68b is formed to protrude radially outward from the rear wall 65b. Both the front hook 68f and the rear hook 68b are used for the purpose of mounting the fixed blade 50 onto the turbine housing 38.

[0069] Multiple blade air channels 56 Figure 3 and Figure 5As shown, the blade has a first blade air passage 56a, a second blade air passage 56b, and a third blade air passage 56c. The first blade air passage 56a, the second blade air passage 56b, and the third blade air passage 56c are arranged in this order along the arc CL of the blade body 51, from the leading edge 52 side to the trailing edge 53 side of the blade body 51. The first blade air passage 56a, the second blade air passage 56b, and the third blade air passage 56c all extend radially Dr. The first blade air passage 56a penetrates the outer shroud body 61o, the blade body 51, and the inner shroud body 61i radially Dr. Therefore, the first blade air passage 56a has openings at both the radially outer Dro end and the radially inner Dri end. That is, the first blade air passage 56a has: an outer opening 56ao, which is the opening at the radially outer Dro end; and an inner opening 56ai, which is the opening at the radially inner Dri end. The radially inner end of the second blade air passage 56b (Dri) opens at the reverse airflow path surface 64a of the inner shroud body 61i. That is, the second blade air passage 56b has an opening at the radially inner end (Dri), which is the inner opening 56bi. The radially outer end (Dro) of the second blade air passage 56b is closed by the outer shroud body 61o. The radially inner end of the third blade air passage 56c (Dri) is closed by the inner shroud body 61i, and the radially outer end (Dro) of the third blade air passage 56c is closed by the outer shroud body 61o. The radially outer portion (Dro) of the second blade air passage 56b and the radially outer portion (Dro) of the third blade air passage 56c are connected to each other.

[0070] The first blade air passage 56a, the second blade air passage 56b, and the third blade air passage 56c are all defined by multiple channel defining surfaces. Multiple leading-edge injection channels 59f extend from the channel defining surface of the first blade air passage 56a through the leading edge of the blade body 51, so that a portion of the cooling air Acl flowing in the first blade air passage 56a flows from near the leading edge of the blade body 51 to the combustion gas flow path 39 outside the blade body 51 (see reference). Figure 2 Internal injection. Multiple trailing edge injection channels 59b extend from the channel defining surface of the third blade air passage 56c through the trailing edge of the blade body 51, so that a portion of the cooling air Acl flowing in the third blade air passage 56c is injected from the trailing edge 53 of the blade body 51 into the combustion gas flow path 39 outside the blade body 51.

[0071] The fixed blade 50 in this embodiment is as follows Figure 5 As shown, it also includes an outer impact plate 95o, an inner impact plate 95i, an insertion cylinder 70, an insertion support body 80, and a baffle plate 90.

[0072] outer impact plate 95° Figure 3 and Figure 5 As shown, it is fixed to the outer shield 60o. The outer impact plate 95o is disposed within the recess 66 of the outer shield 60o, and divides the recess 66 of the outer shield 60o into a radially outer space (Dro) and a radially inner space (Dri). Multiple impact holes 95h are formed on the outer impact plate 95o, extending radially through the outer shield 60o. Figure 2 The cooling air Acl from the cooling device 40 flows into the recess 66 of the outer shroud 60o and is located in a space further radially outward (Dro) than the outer impact plate 95o. This cooling air Acl impacts and cools the reverse airflow path surface 64a of the outer shroud body 61o through multiple impact holes 95h in the outer impact plate 95o. The cooling air Acl that has undergone impact cooling of the reverse airflow path surface 64a is injected, for example, from the front end face 62f and / or the rear end face 62b of the outer shroud body 61o to the outside of the outer shroud body 61o. The outer opening 56ao of the first blade air passage 56a is located further radially outward (Dro) than the outer impact plate 95o. Therefore, a portion of the cooling air Acl from the cooling device 40 flows into the first blade air passage 56a from this outer opening 56ao.

[0073] A baffle plate 90 is fixed to the inner shroud 60i. The baffle plate 90 is arranged radially inwardly Dri away from the inner shroud body 61i, and separates the cooling air space within the recess 66 of the inner shroud 60i from a space further radially inwardly Dri than the cooling air space. The baffle plate 90 includes: a front baffle plate 90f, disposed upstream of the fixing member 69 on the axial direction Dau; and a rear baffle plate 90b, disposed downstream of the fixing member 69 on the axial direction Dad.

[0074] An inner impact plate 95i is disposed within a recess 66 of an inner shield 60i, and divides the cooling air space into a first space S1 radially outward (Dro) and a second space S2 radially inward (Dri). A plurality of impact holes 95h are formed on the inner impact plate 95i, extending from the second space S2 to the first space S1.

[0075] The insert 70 is cylindrical and is disposed within the first blade air passage 56a. The insert support 80 is fixed to the inner shroud body 61i to support the insert 70.

[0076] Insert tube 70 Figure 5 and Figure 6 As shown, it has: a cylindrical body 71 that extends radially Dr and is cylindrical, a flange portion 73 that narrows the air passage inside the cylindrical body 71; and a groove sidewall portion 74.

[0077] The cylinder 71 has openings at its radially outer end (Dro) and radially inner end (Dri). Multiple impact holes 71h are formed on the cylinder 71, extending from the inner circumferential side towards the outer circumferential side. A flange 73 is annular. The outer periphery of the annular flange 73 is joined to the inner circumferential surface of the cylinder 71. This flange 73 protrudes from a position near the radially inner side (Dri) of the cylinder 71 towards the inner circumferential side of the cylinder 71. Therefore, the air passage within the cylinder 71 is narrowed by this flange 73. In this embodiment, the projected area of ​​the flange 73 in the blade height direction (Dr) is more than half the area of ​​the airflow path within the cylinder 71 in the direction perpendicular to the blade height direction (Dr). A groove sidewall 74 is cylindrical, connected to the inner periphery of the flange 73, and extends from the flange 73 along the radially inner side (Dri). The annular groove sidewall 74 penetrates the inner impact plate 95i. Therefore, the radially inner end of the groove sidewall 74 (Dri) is located further radially inner than the inner impact plate 95i and further radially inner than the baffle plate 90 (Dri). The outer peripheral surface of the annular groove sidewall 74 is spaced apart from and opposite to the inner peripheral surface of the radially inner end 72, which includes the radially inner end of the annular cylinder 71. The annular groove sidewall 74 and the annular cylinder 71 are connected together by an annular flange 73. Therefore, an annular protruding insert groove 76 is formed between the annular groove sidewall 74 and the annular cylinder 71, with the annular flange 73 as the bottom of the groove. This protruding insert groove 76 is recessed radially outward (Dro).

[0078] Insert support body 80 such Figures 6-8 As shown, it includes: a support plate 81 that extends in a direction perpendicular to the radial direction Dr and is fixed on the reverse airflow path surface 64a of the inner shield body 61i; a position limiting protrusion 82 that is provided on the support plate 81; and a first pressing part 83a and a second pressing part 83b that are similarly provided on the support plate 81 as the position limiting protrusion 82.

[0079] The support plate 81 has a support plate opening 81o, which extends radially Dr through a portion of the support plate opening 81o opposite to the inner circumferential side of the cylinder 71. An annular groove sidewall portion 74 of the insertion cylinder 70 is inserted through this support plate opening 81o. A position-limiting protrusion 82 extends radially outward from the support plate 81 and is cylindrical, covering the entire circumference of the opening edge of the support plate opening 81o. This cylindrical position-limiting protrusion 82 is embedded in the annular protrusion insertion groove 76 of the insertion cylinder 70. Therefore, the inner circumferential surface of the cylindrical position-limiting protrusion 82 faces the outer circumferential surface of the annular groove sidewall portion 74 of the insertion cylinder 70, and the outer circumferential surface of the cylindrical position-limiting protrusion 82 faces the inner circumferential surface of the radially inner end portion 72 of the annular cylinder 71 of the insertion cylinder 70, which includes the radially inner end portion Dr. Furthermore, the insertion cylinder 70 and the insertion support body 80 are engaged in a manner that allows relative movement.

[0080] The radially outer end of the insertion tube 70, Dro, is connected to the edge of the outer opening 56ao of the first blade air passage 56a (reference). Figure 5 On the other hand, the radially inner end 72 of the insert cylinder 70 is restricted in movement of the protruding piece 82 by an annular position restriction in the insert support 80. Although movement in the direction perpendicular to the radial direction Dr is restricted, movement in the radial direction Dr relative to the insert support 80 is permitted. Therefore, in this embodiment, on the one hand, movement of the insert cylinder 70 in the direction perpendicular to the radial direction Dr can be restricted, and on the other hand, the difference in thermal expansion between the insert cylinder 70 and the blade body 51 in the radial direction Dr can be permitted.

[0081] like Figure 8 As shown, the plurality of channel defining surfaces defining the first blade air passage 56a include: a first channel defining surface 57a extending radially Dr; and a second channel defining surface 57b connected to the first channel defining surface 57a, extending radially Dr and extending in a direction intersecting the first channel defining surface 57a. The first channel defining surface 57a is a surface facing the circumferential positive pressure side Dcp, defining the edge of the circumferential negative pressure side Dcn of the first blade air passage 56a. The second channel defining surface 57b is a surface facing the upstream side Dau of the axis, defining the edge of the downstream side Dad of the first blade air passage 56a.

[0082] First push section 83a Figures 6-8As shown, the second pressing portion 83b has a first contact surface 84a, which protrudes radially outward from the support plate 81 towards the first channel defining surface 57a in a direction perpendicular to the radial Dr. The second contact surface 84b protrudes radially outward from the support plate 81 towards the second channel defining surface 57b in a direction perpendicular to the radial Dr. The second pressing portion 83b has a second contact surface 84b, which protrudes radially outward from the support plate 81 towards the second channel defining surface 57b in a direction perpendicular to the radial Dr. The second pressing portion 83b is located closer to the second channel defining surface 57b than the position limiting protrusion 82 and contacts the second channel defining surface 57b.

[0083] Front bumper 90f Figures 4-6 As shown, the device includes: a channel-facing portion 91, which is radially opposite to the first blade air passage 56a in the radial direction Dr; a transition portion 92, which is connected around the channel-facing portion 91; and an outer peripheral portion 93, which is connected around the transition portion 92 and at least partially connected to the peripheral wall of the inner shroud 60i. The channel-facing portion 91 is located further radially inward in the direction Dr than the outer peripheral portion 93. The transition portion 92 is formed to gradually move towards the radially inward direction Dr as it approaches the channel-facing portion 91 from the outer peripheral portion 93. The outer peripheral portion 93 has a curved portion 93a, which gradually moves towards the radially inward direction Dr in a direction perpendicular to the radial direction Dr as it moves away from the channel-facing portion 91. The edge of the curved portion 93a is connected to a fastener 69.

[0084] Next, the manufacturing method of the fixed blades described above will be carried out according to... Figure 9 The flowchart shown is used for illustration.

[0085] First, prepare the fixed blade body, outer impact plate 95o, inner impact plate 95i, baffle plate 90, insertion cylinder 70 and insertion support body 80 (preparation step S10).

[0086] The fixed blade body is integrally formed by the outer shroud 60o, the blade body 51, and the inner shroud 60i. This fixed blade body is formed, for example, by casting.

[0087] Next, the insertion tube 70 is configured (tube configuration step S11). In this tube configuration step S11, at least a portion of the radially outer Dro end of the insertion tube 70 is joined to the outer protective cover body 61o by welding or the like.

[0088] Next, the insert support 80 is fixed to the fixed blade body (support fixing step S12). This support fixing step S12 includes a configuration step S12a, a pressing step S12b, and a joining step S12c. In the configuration step S12a, firstly, the position limiting protrusion 82 of the insert support 80 is aligned with the radially inner end 72 of the cylinder 71. Specifically, the insert cylinder 70 is configured such that the position limiting protrusion 82 of the insert support 80 is embedded in the protrusion insertion groove 76 between the cylinder 71 and the groove sidewall portion 74 of the insert cylinder 70, and the outer peripheral surface of the annular position limiting protrusion 82 is aligned with the inner peripheral surface of the cylinder 71. Furthermore, in the configuration step S12a, as... Figure 10 As shown, the first contact surface 84a of the insert support 80 is aligned with the first channel defining surface 57a of the first blade air passage 56a, and the second contact surface 84b of the insert support 80 is aligned with the second channel defining surface 57b of the first blade air passage 56a. In the pushing process S12b, as... Figure 8 As shown, the first contact surface 84a is pressed against the first channel defining surface 57a, and the second contact surface 84b is pressed against the second channel defining surface 57b. In the joining process S12c, with the first contact surface 84a in contact with the first channel defining surface 57a and the second contact surface 84b in contact with the second channel defining surface 57b, the outer periphery of the support plate 81 is joined to the reverse airflow path surface 64a of the inner protective cover body 61i.

[0089] Next, the outer impact plate 95o is joined to the outer shield 60o, and the inner impact plate 95i is joined to the inner shield 60i (impact plate configuration process S13).

[0090] Next, the baffle plate 90 is joined to the inner cover 60i (baffle plate configuration process S14).

[0091] The fixed blade 50 in this embodiment has been completed. Furthermore, the timing of configuring the insert support 80, i.e., the timing of executing the configuration step S12a, can be after or before the cylinder configuration step S11, so that the position limiting protrusion 82 of the insert support 80 can be embedded in the protrusion insertion groove 76 of the insert cylinder 70.

[0092] refer to Figure 5 and Figure 6 The direction of airflow for cooling within the fixed blade 50 is explained.

[0093] use Figure 2The cooling air Acl from the cooling device 40 flows into the recess 66 of the outer shroud 60o and is located in a space further radially outward than the outer impact plate 95o. A portion of this cooling air Acl impacts and cools the reverse airflow path surface 64a of the outer shroud body 61o through the multiple impact holes 95h of the outer impact plate 95o. The cooling air Acl that has been impact-cooled on the reverse airflow path surface 64a is injected, for example, from the front end face 62f and / or the rear end face 62b of the outer shroud body 61o to the outside of the outer shroud body 61o. Furthermore, another portion of the cooling air Acl flows into the cylinder 71 of the insertion cylinder 70 disposed in the first blade air passage 56a.

[0094] Cooling air Acl flows into the cylinder 71 of the insertion cylinder 70 and flows radially inward along the inside of the cylinder 71 towards the inner side Dri. During this process, a portion of the cooling air Acl passes through the multiple impact holes 71h of the cylinder 71. The remaining cooling air Acl flows through the annular groove sidewall portion 74 fixed to the cylinder 71 into the second space S2 between the baffle plate 90 and the inner impact plate 95i in the recess 66 of the inner shroud 60i. Therefore, the annular groove sidewall portion 74 fixed to the cylinder 71 forms a guide cylinder portion that guides the cooling air Acl flowing into the cylinder 71 into the second space S2.

[0095] Cooling air Acl, passing through multiple impact holes 71h in the cylinder 71, impinges and cools the channel defining surface that defines the air passage 56a of the first blade. The cooling air Acl, having undergone impingement cooling of the channel defining surface, flows into multiple leading-edge injection channels 59f. A portion near the leading edge of the blade body 51 is convectively cooled by the cooling air Acl flowing through the multiple leading-edge injection channels 59f. This cooling air Acl is injected from near the leading edge of the blade body 51 into the combustion gas flow path 39 outside the blade body 51.

[0096] Cooling air Acl, flowing into the second space S2 within the recess 66 of the inner shroud 60i, impacts the reverse airflow path surface 64a of the inner shroud body 61i through multiple impact holes 95h of the inner impact plate 95i. The cooling air Acl, having undergone impact cooling of the reverse airflow path surface 64a of the inner shroud body 61i, flows into the second blade air passage 56b and moves radially outward along the second blade air passage 56b. During its flow within the second blade air passage 56b, the cooling air Acl convectively cools the area surrounding the second blade air passage 56b within the blade body 51.

[0097] Cooling air Acl then flows into the third blade air passage 56c and flows radially inward along the third blade air passage 56c. During its flow within the third blade air passage 56c, the cooling air Acl provides convective cooling to the area surrounding the third blade air passage 56c within the blade body 51. Furthermore, the cooling air Acl flows into multiple trailing edge injection channels 59b. The portion near the trailing edge of the blade body 51 is convectively cooled by the cooling air Acl flowing in the multiple trailing edge injection channels 59b. This cooling air Acl is injected from near the trailing edge of the blade body 51 into the combustion gas flow path 39 outside the blade body 51.

[0098] In this embodiment, as described above, in order to accommodate the difference in thermal expansion between the insert cylinder 70 and the blade body 51 in the radial direction Dr, the insert cylinder 70 is not joined to the insert support 80. Therefore, a portion of the cooling air Acl flowing into the space further radially inward (Dri) than the inner shroud body 61i may leak through the gap between the insert support 80 and the insert cylinder 70 into the space within the first blade air passage 56a and the outer periphery of the cylinder 71. Assuming that the flow rate of cooling air Acl leaking into the space within the first blade air passage 56a and the outer periphery of the cylinder 71 through the gap between the insert support 80 and the insert cylinder 70 increases, the pressure difference between the inner and outer periphery of the cylinder 71 decreases. Therefore, the velocity of the cooling air Acl on the inner periphery of the cylinder 71 as it passes through the plurality of impact holes 71h of the cylinder 71 decreases, thereby reducing the impact cooling effect on the channel defining surface of the first blade air passage 56a.

[0099] In this embodiment, the gap between the insert support 80 and the insert cylinder 70 becomes the gap between the protrusion insertion groove 76 and the position-limiting protrusion 82 embedded in the groove 76. Therefore, the flow path of the cooling air Acl formed by this gap is wavy and tortuous in the radial direction Dr. Consequently, in this embodiment, the resistance to the cooling air Acl flowing in the flow path formed by the gap between the insert support 80 and the insert cylinder 70 increases. In particular, the resistance to the cooling air Acl at the corners of this flow path increases.

[0100] Furthermore, in this embodiment, since a flange portion 73 is provided inside the cylinder 71 to narrow the air passage within the cylinder 71, the pressure of the cooling air Acl passing through the flange portion 73 inside the cylinder 71 can be reduced. In particular, in this embodiment, the projected area of ​​the flange portion 73 in the blade height direction Dr is more than half the area of ​​the airflow path inside the cylinder 71 in the direction perpendicular to the blade height direction Dr. Therefore, in this embodiment, the pressure of the cooling air Acl flowing out of the cylinder 71 and into the gap between the insert support 80 and the insert cylinder 70 can be reduced.

[0101] As described above, in this embodiment, the resistance to the cooling air Acl flowing in the flow path formed by the gap between the insert support 80 and the insert cylinder 70 increases, and the pressure of the cooling air Acl flowing into the gap between the insert support 80 and the insert cylinder 70 decreases. Therefore, the flow rate of cooling air Acl leaking into the space within the first blade air passage 56a and the outer periphery of the cylinder 71 can be reduced. Therefore, in this embodiment, the reduction in the impact cooling effect on the channel defining surface of the first blade air passage 56a can be suppressed.

[0102] In this embodiment, as described above, the position of the protruding piece 82 can be limited by the position of the insert support 80, thereby limiting the relative position of the insert cylinder 70 with respect to the insert support 80 in the direction perpendicular to the radial direction Dr. Furthermore, in this embodiment, since the first contact surface 84a of the insert support 80 contacts the first channel defining surface 57a, and the second contact surface 84b of the insert support 80 contacts the second channel defining surface 57b, the relative position of the insert support 80 with respect to the first blade air passage 56a in the direction perpendicular to the radial direction Dr can be accurately determined. Therefore, in this embodiment, the distance from the outer peripheral surface of the cylinder 71 of the insert cylinder 70 to the plurality of channel defining surfaces including the first channel defining surface 57a and the second channel defining surface 57b can be accurately set as the target distance. Therefore, in this embodiment, the impact cooling performance of the plurality of channel defining surfaces can be appropriately managed by the cooling air Acl ejected through the plurality of impact holes 71h of the cylinder 71.

[0103] The outer shroud 60o, blade body 51, and inner shroud 60i are exposed to the high-temperature combustion gas G. On the other hand, the baffle plate 90, which is attached to the inner shroud 60i, is in contact with the cooling air Acl and is not exposed to the combustion gas G. Therefore, a thermal expansion difference is generated between the inner shroud 60i and the baffle plate 90. In this embodiment, even if a thermal expansion difference is generated between the inner shroud 60i and the baffle plate 90, deformation can occur at the connection between the channel opposite portion 91 and the transition portion 92, and at the connection between the transition portion 92 and the outer peripheral portion 93, so that the baffle plate 90 can withstand the thermal expansion difference without stress. Therefore, in this embodiment, damage to the connection between the inner shroud 60i and the baffle plate 90, and to the baffle plate 90, can be suppressed. Furthermore, even if a thermal elongation difference occurs between the inner shield 60i and the baffle plate 90, damage at the joint between the bent portion 93a in the outer peripheral portion 93 and the fastener 69 can be suppressed by deforming the bent portion 93a in the outer peripheral portion 93.

[0104] Furthermore, in this embodiment, the distance between the channel-facing portion 91 and the inner shield body 61i is greater than the distance between the connection portion of the outer peripheral portion 93 and the transition portion 92 and the inner shield body 61i. In this embodiment, the distance between the channel-facing portion 91 and the inner shield body 61i is set to be consistent with the distance between the connection portion of the outer peripheral portion 93 and the transition portion 92 and the inner shield body 61i, which increases the distance between the channel-facing portion 91 and the inner shield body 61i. Therefore, in this embodiment, the pressure drop of the cooling air Acl caused by the collision between the cooling air Acl passing through the first blade air channel 56a and the channel-facing portion 91 of the baffle plate 90 can be suppressed. Therefore, in this embodiment, the cooling air Acl that passes through the insertion tube 70 in the first blade air channel 56a and flows into the recess 66 of the inner shield 60i can be effectively utilized for the cooling of the inner shield 60i. Furthermore, in this embodiment, the baffle plate 90 can prevent interference with the radially inner end of the groove sidewall (guide cylinder) 74 due to the thermal expansion of a portion of the fixed blade 50.

[0105] "First Deformation Example of Insert Cylinder and Insert Support"

[0106] like Figure 11 As shown, the insert support 80a in this modified example differs from the insert support 80 in the described embodiment. On the other hand, the insert cylinder 70 in this modified example is the same as the insert cylinder 70 in the described embodiment.

[0107] In this modified example, the insert support 80a, in addition to having the support plate 81, position limiting protrusion 82, first pressing portion 83a, and second pressing portion 83b present in the insert support 80 of the described embodiment, also has a shrink ring 85. The shrink ring 85 is fixed to the surface facing the radially inner side Dri of the support plate 81. The shrink ring 85 has a shrink opening 85o into which the annular groove sidewall portion 74 of the insert cylinder 70 is inserted. The average interval d2 between the shrink opening 85o and the annular groove sidewall portion 74 is narrower than the average interval d1 between the annular position limiting protrusion 82 of the insert support 80a and the annular groove sidewall portion 74 of the insert cylinder 70.

[0108] Therefore, in this modification, the flow rate of cooling air Acl from the space radially inner Dri, which is closer to the inner shield body 61i, into the gap between the insert support 80a and the insert cylinder 70 can be reduced. Therefore, in this embodiment, the flow rate of cooling air Acl leaking into the space of the first blade air passage 56a and the outer peripheral side of the cylinder 71 can be reduced.

[0109] "Second variation of the insert cylinder and insert support body"

[0110] like Figure 12 As shown, the insertion cylinder 70b in this modified example differs from the insertion cylinder 70 of the described embodiment. On the other hand, the insertion support 80 in this modified example is the same as the insertion support 80 of the described embodiment.

[0111] like Figure 12 As shown, the insertion cylinder 70b in this modified example, like the insertion cylinder 70 in the above embodiment, has: a cylinder body 71b extending radially Dr and in a cylindrical shape, a flange portion 73b that narrows the air passage within the cylinder body 71b; and a groove sidewall portion 74b. The insertion cylinder 70b in this modified example also has a groove bottom 75b.

[0112] In this modified example, the radially inner end of the cylinder 71b, Dri, is located further radially inner than the inner impact plate 95i and further radially inner than the baffle plate 90. Similar to the cylinder 71 in the previous embodiment, the cylinder 71b has openings at both the radially outer end, Dro, and the radially inner end, Dri. Therefore, cooling air Acl flowing into the cylinder 71b from the opening at the radially outer Dro can pass through the interior of the cylinder 71b into the second space S2 between the baffle plate 90 and the inner impact plate 95i within the recess 66 of the inner shroud 60i. Thus, the cylinder 71b forms a guide cylinder portion that guides the cooling air Acl flowing into the cylinder 71b into the second space S2. Multiple impact holes 71h extending from the inner circumferential side to the outer circumferential side are also formed on the cylinder 71b. The flange portion 73b is annular. The outer periphery of the annular flange 73b is joined to the inner circumferential surface of the cylinder 71b. The flange 73b protrudes from a position near the radially inner side (Dri) of the cylinder 71b towards its inner circumferential side. Therefore, the air passage within the cylinder 71b is narrowed by the flange 73b. The groove bottom 75b is annular. The outer periphery of the annular groove bottom 75b is joined to the outer circumferential surface of the cylinder 71b. The groove bottom 75b protrudes from a position near the radially inner side (Dri) of the cylinder 71b towards its outer circumferential side. The groove sidewall 74b is cylindrical, joined to the outer periphery of the annular groove bottom 75b, and extends radially inner (Dri). The inner circumferential surface of the annular groove sidewall 74b is spaced apart from the outer circumferential surface of the annular cylinder 71b. Therefore, an annular protruding piece insertion groove 76b is formed between the annular groove sidewall portion 74b and the annular cylinder 71b. This protruding piece insertion groove 76b is recessed radially outward. The annular position-limiting protruding piece 82 of the insert support 80 is embedded in this annular protruding piece insertion groove 76b.

[0113] In the embodiment described above, the insertion cylinder 70 has a protruding insert groove 76 formed on the inner circumferential side of the cylinder body 71. On the other hand, in this modified example, the insertion cylinder 70b has a protruding insert groove 76b formed on the outer circumferential side of the cylinder body 71b.

[0114] As described above, in this modified example, the gap between the insert support 80 and the insert cylinder 70b becomes the gap between the protruding piece insertion groove 76b and the position-limiting protruding piece 82 embedded in the groove 76b. Therefore, the flow path of the cooling air Acl formed by this gap is wavy and curved in the radial direction Dr. Therefore, in this modified example, similar to the described embodiment, the resistance to the cooling air Acl flowing in the flow path formed by the gap between the insert support 80 and the insert cylinder 70b increases.

[0115] Furthermore, in this modified example, since a flange portion 73b is provided inside the cylinder 71b to narrow the air passage within the cylinder 71b, the pressure of the cooling air Acl passing through the flange portion 73b inside the cylinder 71b can be reduced. Therefore, in this modified example, the pressure of the cooling air Acl flowing out of the cylinder 71b and into the gap between the insert support 80 and the insert cylinder 70b can also be reduced.

[0116] As described above, in this modified example, similarly to the previous embodiment, the resistance to the cooling air Acl flowing in the flow path formed by the gap between the insert support 80 and the insert cylinder 70b increases, and the pressure of the cooling air Acl flowing into the gap between the insert support 80 and the insert cylinder 70b decreases. Therefore, the flow rate of cooling air Acl leaking into the space within the first blade air passage 56a and the outer periphery of the cylinder 71b can be reduced. Therefore, in this modified example, the reduction in the impact cooling effect on the channel defining surface of the first blade air passage 56a can also be suppressed.

[0117] In this modified example, the radially inner end of the cylinder 71b forming the guide tube portion is located further radially inner than the inner impact plate 95i and further radially outer than the baffle plate 90. However, the channel-facing portion 91 of the baffle plate 90 is located further radially inner than the outer peripheral portion 93 of the baffle plate 90. Therefore, interference between the baffle plate 90 and the radially inner end of the cylinder 71b forming the guide tube portion due to thermal expansion of a portion of the fixed blades 50 can be avoided.

[0118] In addition, a shrink ring 85 as described in the first modification example can be provided on the support plate 81 of the insert support body 80 in this modified example.

[0119] "Third variation of the insert cylinder and insert support body"

[0120] like Figure 13 As shown, the insertion cylinder 70c in this modified example differs from the insertion cylinder 70 of the described embodiment. Furthermore, the insertion support 80c in this modified example also differs from the insertion support 80 of the described embodiment.

[0121] The insertion tube 70c in this modified example, like the insertion tube 70 in the above embodiment, has: a tube body 71 extending radially Dr and in a cylindrical shape; and a flange portion 73c that narrows the air passage within the tube body 71. However, the insertion tube 70c in this modified example does not have the groove bottom and groove sidewall portion of the insertion tube 70 in the above embodiment. Therefore, the protruding insert groove 76 of the insertion tube 70 in the above embodiment is not formed on the insertion tube 70c in this modified example. The tube body 71, like the tube body 71 in the above embodiment, has openings at the ends of the radially outer side Dro and the radially inner side Dri. A plurality of impact holes 71h extending from the inner peripheral side to the outer peripheral side are also formed on the tube body 71. The flange portion 73c is annular. The outer peripheral edge of the annular flange portion 73c is joined to the inner peripheral surface of the tube body 71. The flange 73c protrudes from a position near the radially inner side Dri of the cylinder 71 toward the inner circumferential side of the cylinder 71. Therefore, the air passage inside the cylinder 71 is narrowed by the flange 73c.

[0122] In this modified example, the insert support 80c, like the insert support 80 in the aforementioned embodiment, includes: a support plate 81 extending in a direction perpendicular to the radial direction Dr and fixed to the reverse airflow path surface 64a of the inner protective cover body 61i; a position limiting protrusion 82c; a first pressing part 83a; a second pressing part 83b; a groove sidewall part 87; and a guide cylinder part 88. The position limiting protrusion 82c, the first pressing part 83a, the second pressing part 83b, the groove sidewall part 87, and the guide cylinder part 88 are all provided on the support plate 81.

[0123] The support plate 81 has a support plate opening 81o, which extends radially Dr through the portion of the support plate opening 81o opposite to the inner circumferential side of the cylinder 71. A position-limiting protrusion 82c is cylindrical and protrudes radially outward Dro along the entire circumference of the opening edge of the support plate opening 81o. This position-limiting protrusion 82c is located on the inner circumferential side of the cylinder 71 and faces the inner circumferential surface of the radially inner end 72 of the cylinder 71. Therefore, this position-limiting protrusion 82c forms an inner position-limiting protrusion. A groove sidewall portion 87 is cylindrical and protrudes radially outward Dro from the support plate 81 along the entire circumference of the opening edge of the support plate opening 81o. This groove sidewall portion 87 is located on the outer circumferential side of the cylinder 71 and faces the outer circumferential surface of the radially inner end 72 of the cylinder 71. Therefore, this groove sidewall portion 87 forms an outer position-limiting protrusion. In the support plate 81, the portion between the position-limiting protrusion 82c and the groove sidewall portion 87, that is, between the inner position-limiting protrusion 82c and the outer position-limiting protrusion 87, forms the groove bottom 81c. In the insert support body 80c, an annular cylindrical insertion groove 89 is formed between the inner position-limiting protrusion 82c and the outer position-limiting protrusion 87. This cylindrical insertion groove 89 is recessed radially inward. The radially inward end 72 of the cylindrical body 71 is embedded in the cylindrical insertion groove 89.

[0124] The first pressing part 83a has a first contact surface 84a (reference) Figure 8 The first contact surface 84a protrudes radially outward from the support plate 81, and is located further than the inner position limiting protrusion 82c and the outer position limiting protrusion 87 in a direction perpendicular to the radial Dr than the first channel defining surface 57a (see reference). Figure 8 The second pressing part 83b is positioned on the side and contacts the first channel defining surface 57a. The second pressing part 83b has a second contact surface 84b (see reference). Figure 8 The second contact surface 84b protrudes radially outward from the support plate 81, and is located further than the inner position limiting protrusion 82c and the outer position limiting protrusion 87 in a direction perpendicular to the radial Dr than the second channel defining surface 57b (see reference). Figure 8 It is positioned on the side and contacts the second channel defining surface 57b.

[0125] The guide cylinder portion 88 is cylindrical and protrudes radially inward along the entire circumference of the opening edge of the support plate opening 81o. The end of the radially inward side Dri of the guide cylinder portion 88 is located within the second space S2. Therefore, the guide cylinder portion 88 can guide the cooling air Acl flowing into the cylinder body 71 to the second space S2.

[0126] In this modified example, the gap between the insert support 80c and the insert cylinder 70c becomes the gap between the cylinder insertion groove 89 and the radially inner end 72 of the cylinder 71 embedded in the groove 89. Therefore, the flow path of the cooling air Acl formed by this gap is wavy and curved in the radial direction Dr. Therefore, in this modified example, similar to the described embodiment and the second modified example, the resistance to the cooling air Acl flowing in the flow path formed by the gap between the insert support 80c and the insert cylinder 70c increases.

[0127] Furthermore, in this modified example, since a flange portion 73c is provided inside the cylinder 71 to narrow the air passage within the cylinder 71, the pressure of the cooling air Acl passing through the flange portion 73c inside the cylinder 71 can be reduced. Therefore, in this modified example, the pressure of the cooling air Acl flowing out of the cylinder 71 and into the gap between the insert support 80c and the insert cylinder 70c can also be reduced.

[0128] As described above, in this modified example, similarly to the previous embodiment and the second modified example, the resistance to the cooling air Acl flowing in the flow path formed by the gap between the insert support 80c and the insert cylinder 70c increases, and the pressure of the cooling air Acl flowing into the gap between the insert support 80c and the insert cylinder 70c decreases. Therefore, the flow rate of cooling air Acl leaking into the space within the first blade air passage 56a and the outer periphery of the cylinder 71 can be reduced. Therefore, in this modified example, the reduction in the impact cooling effect on the channel defining surface of the first blade air passage 56a can also be suppressed.

[0129] In this modified example, the radially inner end of the guide cylinder portion 88 (Dri) is located further radially inner than the inner impact plate 95i and further radially outer than the baffle plate 90 (Dro). However, the channel-facing portion 91 of the baffle plate 90 is located further radially inner than the outer peripheral portion 93 of the baffle plate 90. Therefore, interference between the baffle plate 90 and the radially inner end of the guide cylinder portion 88 due to thermal expansion of a portion of the fixed blades 50 can be avoided.

[0130] "Fourth variation of the insert cylinder and insert support body"

[0131] like Figure 14 and Figure 15 As shown, the insertion cylinder 70 in this modified example is the same as the insertion cylinder 70 in the described embodiment. On the other hand, the insertion support 80d in this modified example is different from the insertion support 80 in the described embodiment.

[0132] like Figure 14 and Figure 15As shown, the insert support 80d in this modified example, like the insert support 80 in the above embodiment, has: a support plate 81 that extends in a direction perpendicular to the radial direction Dr and is fixed on the reverse airflow path surface 64a of the inner shield body 61i; a position limiting protrusion 82 that is provided on the support plate 81; and a first pressing part 83da and a second pressing part 83db that are provided on the support plate 81 in the same way as the position limiting protrusion 82.

[0133] In this modified example, the first pressing portion 83da, like the first pressing portion 83a in the described embodiment, has a first contact surface 84a. The first contact surface 84a protrudes radially outward from the support plate 81 (Dro), and is located closer to the first channel defining surface 57a than the position limiting protrusion 82 in a direction perpendicular to the radial Dr, and contacts the first channel defining surface 57a. Similarly, in this modified example, the second pressing portion 83db, like the first pressing portion 83a in the described embodiment, has a second contact surface 84b. The second contact surface 84b protrudes radially outward from the support plate 81 (Dro), and is located closer to the second channel defining surface 57b than the position limiting protrusion 82 in a direction perpendicular to the radial Dr, and contacts the second channel defining surface 57b.

[0134] In this modified example, a first groove 86a is formed between the annular position-restricting protrusion 82 and the first pressing portion 83da. The first groove 86a is recessed radially inward toward Dri, so that the end 71i of the radially inward Dri of the cylinder 71 is embedded therein. Furthermore, in this modified example, a second groove 86b is formed between the annular position-restricting protrusion 82 and the second pressing portion 83db. The second groove 86b is recessed radially inward toward Dri, so that the end 71i of the radially inward Dri of the cylinder 71 is embedded therein.

[0135] In this modified example, even though the insert support 80d has a first pressing portion 83da and a second pressing portion 83db, it is still possible to insert the end 71i of the radially inner side Dri of the cylinder 71 into the first groove 86a and the second groove 86b, so that the position of the end 71i of the radially inner side Dri of the cylinder 71 is close to the position of the reverse airflow path surface 64a of the inner shield body 61i. Therefore, in this modified example, while maintaining the overlap between the cylinder 71 and the position limiting protrusion 82 in the radial Dr, it is possible to make the position of the impact hole 71h closest to the radially inner side Dri of the cylinder 71 close to the position of the reverse airflow path surface 64a of the inner shield body 61i.

[0136] "Fifth variation of the insert cylinder and insert support body"

[0137] In this modified example, only the insert support body differs from the fourth modified example; the other structures in this modified example are the same as those in the fourth modified example.

[0138] like Figure 16 As shown, the insert support 80e in this modified example, like the insert support 80d in the fourth modified example, has: a support plate 81 that extends in a direction perpendicular to the radial direction Dr and is fixed on the reverse airflow path surface 64a of the inner shield body 61i; a position limiting protrusion 82 that is provided on the support plate 81; and a first pressing part 83ea and a second pressing part 83eb that are provided on the support plate 81 in the same way as the position limiting protrusion 82.

[0139] In this modified example, similar to the fourth modified example, a first groove 86a is formed between the annular position-restricting protrusion 82 and the first pressing portion 83ea. The first groove 86a is recessed radially inward toward Dri, so that the end 71i of the radially inward Dri of the cylinder 71 is embedded therein. Furthermore, in this modified example, a second groove 86b is formed between the annular position-restricting protrusion 82 and the second pressing portion 83eb. The second groove 86b is recessed radially inward toward Dri, so that the end 71i of the radially inward Dri of the cylinder 71 is embedded therein.

[0140] However, in this modified example, the second pressing portion 83eb is located away from the first pressing portion 83ea. Therefore, in this modified example, when the machining tool is moved along the direction of the first contact surface 84a to machine the first groove 86a between the first pressing portion 83ea and the position limiting protrusion 82, the machining tool can be moved along the direction of the first contact surface 84a to a position having the second pressing portion 83eb. Furthermore, in this modified example, when the machining tool is moved along the direction of the second contact surface 84b to machine the second groove 86b between the second pressing portion 83eb and the position limiting protrusion 82, the machining tool can be moved along the direction of the second contact surface 84b to a position having the first pressing portion 83ea. Therefore, in this modified example, the first groove 86a and the second groove 86b can be machined easily.

[0141] Other variations

[0142] In the above embodiments and variations, the fixed blade 50 has three blade air channels 56. However, the fixed blade 50 may also have four or more blade air channels 56.

[0143] In the fixed blade 50 of the above embodiments and variations, among the multiple blade air channels 56, the insertion cylinders 70, 70b, and 70c are arranged in the first blade air channel 56a closest to the upstream side of the axis (Dau). However, the insertion cylinders 70, 70b, and 70c can be arranged in the blade air channel 56 further downstream of the axis (Dad) than the first blade air channel 56a closest to the upstream side of the axis (Dau).

[0144] In the above embodiments and variations, the first channel defining surface 57a of the blade air passage 56 defining the fixed blade 50 is a surface that faces the circumferential positive pressure side Dcp and defines the edge of the circumferential negative pressure side Dcn of the first blade air passage 56a. Alternatively, the second channel defining surface 57b is a surface that faces the upstream side Dau of the axis and defines the edge of the downstream side Dad of the axis of the first blade air passage 56a. However, both the first channel defining surface 57a and the second channel defining surface 57b can extend radially Dr, and the second channel defining surface 57b can be connected to the first channel defining surface 57a and extend in a direction intersecting the first channel defining surface 57a. For example, the first channel defining surface 57a is set to face the circumferential positive pressure side Dcp and define the edge of the circumferential negative pressure side Dcn of the blade air passage 56. In this case, as long as the channel defining surface that defines the edge of the blade air passage 56 on the upstream side of the axis, Dad, is connected to the first channel defining surface 57a and extends in a direction intersecting the first channel defining surface 57a, the channel defining surface can be set as the second channel defining surface 57b.

[0145] Furthermore, the present invention is not limited to the one embodiment and variations described above. Various additions, modifications, substitutions, partial deletions, etc., can be made without departing from the conceptual idea and spirit of the present invention derived from the content specified in the patent claim and its equivalents.

[0146] "appendix"

[0147] The fixed blade 50 in the above embodiments and variations can be understood as follows.

[0148] (1) The fixed blade in the first method has:

[0149] The blade body 51 has an airfoil-shaped cross-section and extends along a blade height direction Dr having a directional component perpendicular to the cross-section; a blade air passage 56a extends within the blade body 51 along the blade height direction Dr, allowing cooling air Acl to circulate therethrough; a first shield 60o is disposed at the end of the blade body 51 on the blade height direction Dr at the first side of the blade height Dr; a second shield 60i is disposed at the end of the blade body 51 on the side opposite to the first side of the blade height Dr, i.e., the second side of the blade height Dri; and insertion cylinders 70, 70b, and 70c, at least a portion of which are disposed within the blade air passage 56a; and insertion support bodies 80, 80a, 80c, 80d, and 80e, supporting the insertion cylinders 70, 70b, and 70c. The first shield 60o has a first shield body 61o, which extends from the end of the blade body 51 on the first side of the blade height Dr in a direction perpendicular to the blade height direction Dr. The second shield 60i has a second shield body 61i, which extends from the end of the blade body 51 on the second side Dri of the blade height in a direction perpendicular to the blade height direction Dr. The blade air passage 56a passes through the first shield body 61o, the blade body 51, and the second shield body 61i along the blade height direction Dr. The insertion cylinders 70, 70b, and 70c have: cylinders 71 and 71b, which extend along the blade height direction Dr and are cylindrical, with openings at the ends on the first side Dro of the blade height and the second side Dri of the blade height, and forming a plurality of impact holes 71h that penetrate from the inner circumferential side to the outer circumferential side; and flanges 73, 73b, and 73c, which protrude from a position near the second side Dri of the blade height towards the inner circumferential side of the cylinders 71 and 71b, thereby narrowing the air passages within the cylinders 71 and 71b. The insert support bodies 80, 80a, 80c, 80d, and 80e each have: a support plate 81 extending in a direction perpendicular to the blade height direction Dr and fixed to the second shroud body 61i; and position limiting protrusions 82 and 82c protruding from the support plate 81 toward the first side of the blade height Dro. The support plate 81 has a support plate opening 81o, and the portion of the support plate 81 opposite to the inner circumferential side of the cylinders 71 and 71b in the blade height direction Dr extends through the blade height direction Dr.The position limiting protrusions 82 and 82c extend along the entire circumference of the opening edge of the support plate opening 81o from the support plate 81 toward the first blade height side Dro and are cylindrical in shape. They are opposite to the inner or outer circumferential surface of the second side end 72 of the cylindrical bodies 71 and 71b, which includes the end of the second blade height side Dri, thereby limiting the relative position of the insertion cylinders 70, 70b, and 70c with respect to the insertion support bodies 80, 80a, 80c, 80d, and 80e in a direction perpendicular to the blade height direction Dr. One of the insertion cylinders 70, 70b, and 70c and the insertion support bodies 80, 80a, 80c, 80d, and 80e has: groove bottoms 73, 75b, and 81c extending in a direction perpendicular to the blade height direction Dr; and groove sidewall portions 74, 74b, and 87 protruding from the groove bottoms 73, 75b, and 81c toward the blade height direction Dr. When one of them is the insertion cylinder 70, 70b, the groove sidewall portions 74, 74b are cylindrical, extending across the entire circumference of the cylinder body 71, 71b and spaced apart from the second side end 72 of the cylinder body 71, 71b. The groove bottoms 73, 75b extend across the entire circumference of the cylinder body 71, 71b, connecting the cylinder body 71, 71b with the groove sidewall portions 74, 74b. Thus, the cylinder body 71, 71b, the groove sidewall portions 74, 74b, and the groove bottoms 73, 75b form an annular protrusion insertion groove 76, 76b in which the position limiting protrusion 82 is embedded. When one of them is the insert support 80c, the groove sidewall portion 87 is cylindrical, extending across the entire circumference of the cylindrical body 71 and spaced apart from the position limiting protrusion 82c. The groove bottom 81c extends across the entire circumference of the cylindrical body 71, connecting the position limiting protrusion 82c to the groove sidewall portion 87. Thus, the position limiting protrusion 82c, the groove sidewall portion 87, and the groove bottom 81c form an annular cylindrical insertion groove 89 into which the second side end 72 of the cylindrical body 71 is embedded. The insertion cylinders 70, 70b, and 70c engage with the insert supports 80, 80a, 80c, 80d, and 80e in a manner that allows for relative movement.

[0150] In this configuration, the insertion cylinders 70, 70b, and 70c are engaged with the insertion support bodies 80, 80a, 80c, 80d, and 80e in a manner that allows for relative movement. In this configuration, the annular position-limiting protrusions 82 and 82c of the insertion support bodies 80, 80a, 80c, 80d, and 80e, fixed to the second cover body 61i, are opposite to the inner or outer circumferential surfaces of the cylinder bodies 71 and 71b of the insertion cylinders 70, 70b, and 70c. Therefore, in this configuration, on the one hand, movement of the insertion cylinders 70, 70b, and 70c in a direction perpendicular to the blade height direction Dr can be restricted; on the other hand, the second side end 72 of the insertion cylinders 70, 70b, and 70c can move relative to the blade body 51 in the blade height direction Dr. Therefore, in this configuration, the thermal expansion difference between the insertion cylinders 70, 70b, and 70c and the blade body 51 in the blade height direction Dr can be tolerated.

[0151] In this configuration, cooling air Acl, located at the first blade height side Dro, which is higher than the first shroud body 61o, flows into the cylinders 71 and 71b of the insertion cylinders 70, 70b, and 70c disposed within the blade air passage 56a. The cooling air Acl flowing into the cylinders 71 and 71b flows along the cylinders 71 and 71b toward the second blade height side Dri. During this process, a portion of the cooling air Acl passes through multiple impact holes 71h in the cylinders 71 and 71b. The remaining cooling air Acl flows through the support plate opening 81o into the space at the second blade height side Dri, which is higher than the second shroud body 61i. The cooling air Acl passing through the multiple impact holes 71h in the cylinders 71 and 71b performs impact cooling on the channel defining surface of the blade air passage 56a.

[0152] In this configuration, to accommodate the thermal expansion difference between the insert cylinders 70, 70b, 70c and the blade body 51 in the blade height direction Dr, the insert cylinders 70, 70b, 70c and the insert support bodies 80, 80a, 80c, 80d, 80e are engaged in a relatively movable manner. Therefore, a portion of the cooling air Acl flowing into the space on the second side Dri of the blade height, which is closer to the blade height than the second shield body 61i, through the support plate opening 81o, may leak through the gap between the insert support bodies 80, 80a, 80c, 80d, 80e and the insert cylinders 70, 70b, 70c into the space on the outer periphery of the cylinders 71, 71b in the blade air passage 56a. Assuming that the flow rate of cooling air Acl leaking into the blade air passage 56a through the gap between the insert supports 80, 80a, 80c, 80d, 80e and the insert cylinders 70, 70b, 70c increases, and the flow rate of cooling air Acl in the space on the outer periphery of cylinders 71, 71b also increases, then the pressure difference between the space on the inner periphery of cylinders 71, 71b and the space on the outer periphery of cylinders 71, 71b decreases. Therefore, the velocity of the cooling air Acl on the inner periphery of cylinders 71, 71b decreases as it passes through the multiple impact holes 71h of cylinders 71, 71b, thereby reducing the impact cooling effect on the channel defining surface of the blade air passage 56a.

[0153] In this embodiment, when one of the inserts is an insert cylinder 70 or 70b, the gap between the insert supports 80, 80a, 80d, 80e and the insert cylinder 70 or 70b becomes the gap between the protruding insert grooves 76 or 76b and the position-limiting protruding piece 82 embedded in the grooves 76 or 76b. Therefore, the flow path of the cooling air Acl formed by this gap is wavy in the blade height direction Dr and becomes a curved flow path. Furthermore, in this embodiment, when one of the inserts is an insert support 80c, it becomes the gap between the cylinder insert groove 89 and the second side end 72 of the cylinder 71 embedded in the groove 89. Therefore, the flow path of the cooling air Acl formed by this gap is wavy in the blade height direction Dr and becomes a curved flow path. Therefore, in this configuration, the resistance to the cooling air Acl flowing in the flow path formed by the gaps between the insert supports 80, 80a, 80c, 80d, 80e and the insert cylinders 70, 70b, 70c increases. In particular, the resistance to the cooling air Acl at the corners of this flow path increases.

[0154] Furthermore, in this embodiment, since flange portions 73, 73b, and 73c are provided inside the cylinders 71 and 71b to narrow the air passage within the cylinders 71 and 71b, the pressure of the cooling air Acl passing through the flange portions 73, 73b, and 73c inside the cylinders 71 and 71b can be reduced. Therefore, in this embodiment, the pressure of the cooling air Acl flowing out of the cylinders 71 and 71b and into the gap between the insert support bodies 80, 80a, 80c, 80d, and 80e and the insert cylinders 70, 70b, and 70c can be reduced.

[0155] As described above, in this embodiment, the resistance to the cooling air Acl flowing in the flow path formed by the gaps between the insert supports 80, 80a, 80c, 80d, 80e and the insert cylinders 70, 70b, 70c increases, and the pressure of the cooling air Acl flowing into the gaps between the insert supports 80, 80a, 80c, 80d, 80e and the insert cylinders 70, 70b, 70c decreases. Therefore, the flow rate of cooling air Acl leaking into the space within the blade air passage 56a and the outer periphery of the cylinders 71, 71b can be reduced. Therefore, in this embodiment, the reduction in the impact cooling effect on the channel defining surface that defines the blade air passage 56a can be suppressed.

[0156] (2) In the second method, the fixed blade is the same as the fixed blade 50 in the first method, and the one is the insertion tube 70.

[0157] The position-limiting protrusions 82 of the insert supports 80, 80a, 80d, and 80e are located on the inner circumferential side of the cylinder 71 and are opposite to the inner circumferential surface of the cylinder 71. The flange portion 73 of the insert cylinder 70 forms the bottom of the groove. The groove sidewall portion 74 extends from the edge of the inner circumferential side of the flange portion 73 forming the bottom of the groove toward the second side of the blade height Dri, so that the position-limiting protrusions 82 are located between the groove sidewall portion 74 and the cylinder 71. The protrusion insertion groove 76 is formed by the cylinder 71, the groove sidewall portion 74, and the flange portion 73 forming the bottom of the groove.

[0158] In this embodiment, where the insert cylinder 70 has a groove sidewall portion 74 and a groove bottom 73, the gap between the insert support bodies 80, 80a, 80c, 80d, 80e and the insert cylinder 70 becomes the gap between the protruding piece insertion groove 76 and the position-limiting protruding piece 82 embedded in the groove 76. Therefore, the flow path of the cooling air Acl formed by this gap is wavy in the blade height direction Dr and becomes a curved flow path. Consequently, in this embodiment, the resistance to the cooling air Acl flowing in the flow path formed by the gap between the insert support bodies 80, 80a, 80c, 80d, 80e and the insert cylinder 70 increases.

[0159] (3) In the fixed blade 50 of the second method, the end of the blade height second side Dri of the groove sidewall portion 74 is located closer to the blade height second side Dri than the support plate 81.

[0160] Cooling air Acl flows into the cylinder 71 of the insertion cylinder 70 through the inner circumferential side of the cylindrical groove sidewall 74 disposed on the inner circumferential side of the cylinder 71. Therefore, if the end of the groove sidewall 74 at the blade height second side Dri is located closer to the blade height second side Dri than the support plate 81, the pressure of the cooling air Acl passing through the inner circumferential side of the cylindrical groove sidewall 74 can be reduced.

[0161] (4) The fixed blade in the fourth method is a baffle plate 90 and an impact plate 95i fixed on the second protective cover 60i.

[0162] The second shield 60i has a peripheral wall 65i that protrudes from the outer periphery of the second shield body 61i toward the second blade height side Dri. The second shield body 61i and the peripheral wall 65i together form a recess 66 on the second blade height side Dri of the second shield body 61i, recessed toward the first blade height side Dro. The baffle plate 90 is disposed at a distance from the second shield body 61i on the second blade height side Dri, and separates the cooling air space within the recess 66 from a space further along the second blade height side Dri than the cooling air space. The impact plate 95i separates the first space S1 on the first blade height side Dro from the second space S2 on the second blade height side Dri within the cooling air space, and forms a plurality of impact holes 95h extending from the second space S2 to the first space S1. The end of the groove sidewall portion 74 on the second side of the blade height Dri is located closer to the second side of the blade height Dri than the impact plate 95i and closer to the first side of the blade height Dro than the baffle plate 90.

[0163] In this configuration, a portion of the cooling air Acl flowing into the inner circumferential side of the cylinder 71 of the insertion cylinder 70 flows into the second space S2 within the recess 66 of the second shield 60i through the inner circumferential side of the cylindrical groove sidewall 74 disposed on the inner circumferential side of the cylinder 71. The cooling air Acl flowing into the second space S2 impacts and cools the second shield body 61i through the multiple impact holes 95h of the impact plate 95i. Therefore, in this configuration, the second shield body 61i can be cooled by a portion of the cooling air Acl located at a position closer to the first blade height Dro than the first shield body 61o.

[0164] (5) In the fifth method, in the fixed blade 50 of the third or fourth method, the insert support 80a has a shrink ring 85, the shrink ring 85 has a shrink opening 85o for the annular groove sidewall portion 74 to be inserted, and is fixed on the surface of the support plate 81 facing the second side Dri of the blade height.

[0165] The average interval d2 between the contraction opening 85o and the annular groove sidewall portion 74 is narrower than the average interval d1 between the annular position limiting protrusion 82 of the insert support 80a and the annular groove sidewall portion 74 of the insert cylinder 70.

[0166] In this method, by making the average interval d2 narrower than the average interval d1, the resistance to cooling air Acl is increased, which reduces the flow rate of cooling air Acl from the space on the second side Dri, which is closer to the blade height than the second shield body 61i, into the gap between the insert support 80a and the insert cylinder 70. Therefore, in this method, the flow rate of cooling air Acl leaking into the space within the blade air passage 56a and the outer periphery of the cylinder 71 can be reduced.

[0167] (6) In the sixth method, the fixed blade is the same as the fixed blade 50 in the first method, wherein the one is the insertion tube 70b.

[0168] The position-limiting protrusion 82 of the insert support 80 is located on the outer peripheral side of the cylinder 71b and faces the outer peripheral surface of the cylinder 71b. The groove bottom 75b extends from the outer peripheral surface of the cylinder 71b along its outer peripheral side. The groove sidewall portion 74b extends from the edge of the outer peripheral side of the groove bottom 75b toward the second side Dri of the blade height, so that the position-limiting protrusion 82 is located between the groove sidewall portion 74b and the cylinder 71b. The protrusion insertion groove 76b is formed by the cylinder 71b, the groove sidewall portion 74b, and the groove bottom 75b.

[0169] In this embodiment, where the insert cylinder 70b has a groove sidewall portion 74b and a groove bottom 75b, the gap between the insert support 80 and the insert cylinder 70b becomes the gap between the protruding piece insertion groove 76b and the position-limiting protruding piece 82 embedded in the groove 76b. Therefore, the flow path of the cooling air Acl formed by this gap is wavy in the blade height direction Dr, and becomes a curved flow path. Consequently, in this embodiment, the resistance of the cooling air Acl flowing in the flow path formed by the gap between the insert support 80 and the insert cylinder 70b also increases. In particular, the resistance of the cooling air Acl at the corners of this flow path increases.

[0170] (7) In the seventh method, the fixed blade in the first method is the fixed blade 50, one of which is the insert support body 80c.

[0171] The position-limiting protrusion 82c of the insert support 80c is located on the inner circumference of the cylinder 71, forming an inner position-limiting protrusion 82c opposite to the inner circumferential surface of the cylinder 71. The groove sidewall portion 87 protrudes from the support plate 81 toward the first side of the blade height Dro along the entire circumference of the opening edge of the support plate opening 81o, and is located on the outer circumference of the cylinder 71, forming an outer position-limiting protrusion 87 opposite to the outer circumferential surface of the cylinder 71. The groove bottom 81c is the portion in the support plate 81 located between the inner position-limiting protrusion 82c and the outer position-limiting protrusion 87. The inner position-limiting protrusion 82c, the outer position-limiting protrusion 87, and the groove bottom 81c form an annular cylinder insertion groove 89.

[0172] In this embodiment, where the insert support 80c has a groove sidewall portion 87 and a groove bottom 81c, the gap between the insert support 80c and the insert cylinder 70c becomes the gap between the cylinder insertion groove 89 and the cylinder 71 embedded in the groove 89. Therefore, the flow path of the cooling air Acl formed by this gap is wavy in the blade height direction Dr, and becomes a curved flow path. Consequently, in this embodiment as well, the resistance of the cooling air Acl flowing in the flow path formed by the gap between the insert support 80c and the insert cylinder 70c increases.

[0173] (8) In the fixed blade 50 of any of the first to seventh methods, the projected area of ​​the flange portion 73 in the blade height direction Dr is more than 1 / 2 of the area of ​​the air flow path in the cylinder 71 in the direction perpendicular to the blade height direction Dr.

[0174] In this method, the pressure of cooling air Acl passing through flanges 73, 73b, and 73c within cylinders 71 and 71b can be reduced. Therefore, in this method, the pressure of cooling air Acl flowing out of cylinders 71 and 71b and into the gap between the insert supports 80, 80a, 80c, 80d, and 80e and the insert cylinders 70, 70b, and 70c can be reduced. Thus, in this method, the flow rate of cooling air Acl leaking from this gap can be reduced.

[0175] (9) In the fixed blade 50 of any of the first to eighth embodiments in the ninth embodiment, the blade air passage 56a is defined by a plurality of channel defining surfaces including a first channel defining surface 57a and a second channel defining surface 57b, the first channel defining surface 57a extending along the blade height direction Dr, the second channel defining surface 57b being connected to the first channel defining surface 57a and extending along the blade height direction Dr and extending in a direction intersecting the first channel defining surface 57a.

[0176] The insert support bodies 80, 80a, 80c, 80d, and 80e each have: first pressing portions 83a, 83da, and 83ea, each having a first contact surface 84a that protrudes from the support plate 81 toward the first side of the blade height (Dro), and is located closer to the first channel defining surface 57a than the position limiting protrusions 82 and 82c in a direction perpendicular to the blade height direction (Dr), and contacts the first channel defining surface 57a; and second pressing portions 83b, 83db, and 83eb, each having a second contact surface 84b that protrudes from the support plate 81 toward the first side of the blade height (Dro), and is located closer to the second channel defining surface 57b than the position limiting protrusions 82 and 82c in a direction perpendicular to the blade height direction (Dr), and contacts the second channel defining surface 57b. The support plate 81 is joined to the second protective cover body 61i at its outer periphery.

[0177] In this method, the position limiting protrusions 82 and 82c of the insert supports 80, 80a, 80c, 80d, and 80e can limit the relative positions of the insert cylinders 70, 70b, and 70c with respect to the insert supports 80, 80a, 80c, 80d, and 80e in a direction perpendicular to the blade height direction Dr. Furthermore, in this method, since the first contact surface 84a of the insert supports 80, 80a, 80c, 80d, and 80e contacts the first channel defining surface 57a, and the second contact surface 84b of the insert supports 80, 80a, 80c, 80d, and 80e contacts the second channel defining surface 57b, the relative positions of the insert supports 80, 80a, 80c, 80d, and 80e with respect to the blade air passage 56a in a direction perpendicular to the blade height direction Dr can be accurately determined. Therefore, in this method, the target distance can be accurately set from the outer peripheral surface of the cylinders 71 and 71b of the insertion cylinders 70, 70b, and 70c to the multiple channel defining surfaces including the first channel defining surface 57a and the second channel defining surface 57b. Therefore, in this method, the impact cooling performance of the channel defining surfaces that define the blade air passage 56a can be appropriately managed by the cooling air Acl ejected from the multiple impact holes 71h of the cylinders 71 and 71b.

[0178] (10) In the tenth embodiment, in any one of the fixed blades 50 of the first to the fifth, the seventh and the eighth embodiments, the blade air passage 56a is defined by a plurality of channel defining surfaces including a first channel defining surface 57a and a second channel defining surface 57b, the first channel defining surface 57a extending along the blade height direction Dr, the second channel defining surface 57b being connected to the first channel defining surface 57a and extending along the blade height direction Dr and in a direction intersecting the first channel defining surface 57a.

[0179] The insert support bodies 80d and 80e each have: first pressing portions 83da and 83ea, each having a first contact surface 84a that protrudes from the support plate 81 toward the first side of the blade height Dr, and is located closer to the first channel defining surface 57a than the position limiting protrusion 82 in a direction perpendicular to the blade height direction Dr, and contacts the first channel defining surface 57a; and second pressing portions 83db and 83eb, each having a second contact surface 84b that protrudes from the support plate 81 toward the first side of the blade height Dr, and is located closer to the second channel defining surface 57b than the position limiting protrusion 82c in a direction perpendicular to the blade height direction Dr, and contacts the second channel defining surface 57b. The support plate 81 is joined to the second protective cover body 61i at its outer periphery. The position limiting protrusion 82 is located on the inner periphery of the cylinder 71 and faces the inner periphery of the cylinder 71. A first groove 86a is formed between the position limiting protrusion 82 and the first pressing portions 83da and 83ea. The first groove 86a is recessed towards the second side of the blade height Dri, so that the end of the cylinder 71 at the second side of the blade height Dri is embedded therein. A second groove 86b is formed between the position limiting protrusion 82 and the second pressing portions 83db and 83eb. The second groove 86b is recessed towards the second side of the blade height Dri, so that the end of the cylinder 71 at the second side of the blade height Dri is embedded therein.

[0180] In this method, similar to the fixed blade 50 in the eighth method, the target distance can be accurately set from the outer peripheral surface of the cylinder 71 to the multiple channel defining surfaces, including the first channel defining surface 57a and the second channel defining surface 57b. Therefore, in this method, the impact cooling performance of the multiple channel defining surfaces can be appropriately managed by the cooling air Acl ejected from the multiple impact holes 71h of the cylinder 71.

[0181] Furthermore, in this method, even though the insert support bodies 80d and 80e have first pressing portions 83da and 83ea and second pressing portions 83db and 83eb, they can still be inserted into the first groove 86a and the second groove 86b through the end of the cylinder 71 on the second side of the blade height Dr, so that the position of the end of the cylinder 71 on the second side of the blade height Dr is close to the position of the reverse airflow path surface 64a of the second shield body 61i. Therefore, in this method, while maintaining the overlap between the cylinder 71 and the position limiting protrusion 82 in the blade height direction Dr, the position of the cylinder 71 closest to the impact hole 71h formed on the second side of the blade height Dr is close to the position of the reverse airflow path surface 64a of the second shield body 61i.

[0182] (11) In the fixed blade of the eleventh embodiment, the second pressing part 83eb is away from the first pressing part 83ea in the fixed blade 50 of the tenth embodiment.

[0183] In this method, the first groove 86a and the second groove 86b can be easily processed.

[0184] (12) In the twelfth embodiment, the fixed blade 50 in any one of the first embodiment to the third embodiment, the sixth embodiment to the eighth embodiment, has a baffle plate 90 fixed to the second protective cover 60i.

[0185] The second shield 60i has a peripheral wall 65i that protrudes from the outer periphery of the second shield body 61i toward the second blade height side Dri. A recess 66, recessed toward the first blade height side Dri, is formed jointly by the second shield body 61i and the peripheral wall 65i on the second blade height side Dri of the second shield body 61i. The baffle plate 90 is disposed at a distance from the second shield body 61i on the second blade height side Dri, and separates the cooling air space within the recess 66 from a space further along the second blade height side Dri than the cooling air space. The baffle plate 90 has: a channel opposing portion 91, which is opposite to the blade air channel 56a in the blade height direction Dr; a transition portion 92, which is connected around the channel opposing portion 91; and an outer peripheral portion 93, which is connected around the transition portion 92 and at least partially engages with the peripheral wall 65i. The channel-facing portion 91 is located further toward the second blade height side Dri than the connection portion of the outer peripheral portion 93 to the transition portion 92. The transition portion 92 is formed such that it gradually moves toward the second blade height side Dri as it approaches the channel-facing portion 91 from the outer peripheral portion 93.

[0186] The first shield 60o, the blade body 51, and the second shield 60i are exposed to the high-temperature combustion gases. On the other hand, the baffle plate 90, which is attached to the second shield 60i, is in contact with the cooling air Acl and is not exposed to the combustion gases G. Therefore, a thermal expansion difference is generated between the second shield 60i and the baffle plate 90. In this configuration, even if a thermal expansion difference is generated between the second shield 60i and the baffle plate 90, deformation can occur at the connection between the channel opposite portion 91 and the transition portion 92, and at the connection between the transition portion 92 and the outer peripheral portion 93, so that the baffle plate 90 can withstand the thermal expansion difference without stress. Therefore, in this configuration, damage to the joint between the second shield 60i and the baffle plate 90, and to the baffle plate 90, can be suppressed.

[0187] Furthermore, in this embodiment, the distance between the channel-facing portion 91 and the second shield body 61i is greater than the distance between the connecting portion of the outer peripheral portion 93 and the transition portion 92 and the second shield body 61i. In this embodiment, setting the distance between the channel-facing portion 91 and the second shield body 61i to match the distance between the connecting portion of the outer peripheral portion 93 and the transition portion 92 and the second shield body 61i increases the distance between them. Therefore, in this embodiment, the pressure drop of the cooling air Acl caused by the collision between the cooling air Acl passing through the blade air passage 56a and the channel-facing portion 91 of the baffle plate 90 can be suppressed. Therefore, in this embodiment, the cooling air Acl flowing into the recess 66 of the second shield 60i through the blade air passage 56a can be effectively utilized for cooling the second shield 60i. Furthermore, in this method, when the end of the groove sidewall 74 on the second side of the blade height Dri is located closer to the second side of the blade height Dri than the impact plate 95i, even if the insertion cylinders 70, 70b and the blade body 51 have a thermal expansion difference in the blade height direction Dr, contact between the groove sidewall 74 and the baffle plate 90 can be avoided.

[0188] (13) In the fixed blade 50 of the 12th embodiment, the outer peripheral portion 93 has a curved portion 93a, which gradually moves toward the second side Dri of the blade height in a direction perpendicular to the blade height direction Dr, as it moves away from the channel opposite portion 91.

[0189] In this method, even if a thermal expansion difference occurs between the second shield 60i and the baffle plate 90, except for the connection between the channel opposite portion 91 and the transition portion 92 and the connection between the transition portion 92 and the outer peripheral portion 93, the bent portion 93a in the outer peripheral portion 93 can also deform, so that the baffle plate 90 can withstand the thermal expansion difference without pressure. Therefore, in this method, damage to the joint between the second shield 60i and the baffle plate 90 and to the baffle plate 90 can be suppressed.

[0190] (14) In the fixed blade of the fourteenth embodiment, the blade body 51 has: a leading edge 52; a trailing edge 53; a positive pressure surface 55 for connecting the leading edge 52 and the trailing edge 53; and a negative pressure surface 54, which is back-to-back with the positive pressure surface 55 and is used to connect the leading edge 52 and the trailing edge 53.

[0191] The second shield 60i has a fastener 69 connected to the peripheral wall 65i. The peripheral wall 65i of the second shield 60i has: a positive pressure sidewall 65p, located on the positive pressure side Dcp with respect to the negative pressure surface 54 relative to the blade body 51, and a negative pressure sidewall 65n, located on the negative pressure side Dcn opposite to the positive pressure side Dcp with respect to the blade body 51. The fastener 69 is connected to the positive pressure sidewall 65p and the negative pressure sidewall 65n. The bent portion 93a engages with the fastener 69.

[0192] In this method, by deforming the bent portion 93a, damage at the joint between the bent portion 93a in the outer peripheral portion 93 and the fixing member 69 can be suppressed.

[0193] The gas turbine in the above embodiments and variations can be understood as follows.

[0194] (15) The gas turbine in the fifteenth configuration has:

[0195] The fixed blade 50 in any one of the first to the fourteenth embodiments; the rotor 31, rotatable about an axis Ar; and the turbine housing 38, covering the rotor 31. The fixed blade 50 is mounted inside the turbine housing 38 such that the blade height direction Dr is radial Dr relative to the axis Ar.

[0196] Industrial availability

[0197] According to one aspect of the present invention, on the one hand, the movement of the insert cylinder in a direction perpendicular to the blade height direction is restricted, and on the other hand, the thermal elongation difference between the insert and the blade body in the blade height direction is allowed, while suppressing the reduction of the impact cooling effect on the channel defining surface that defines the air passage of the blade.

[0198] Symbol Explanation

[0199] 1-Gas turbine rotor, 6-Intermediate casing, 7-Inner cover, 8-Gas turbine casing, 10-Compressor, 11-Compressor rotor, 12-Rotor shaft, 13-Rotating blade grid, 15-Fixed blade grid, 18-Compressor casing, 20-Burner, 21-Combustion furnace, 22-Tail stack (or combustion chamber), 30-Turbine, 31-Turbine rotor, 32-Rotor shaft, 33-Rotating blade grid, 35-Fixed blade grid, 37-Divider ring, 38-Turbine casing, 39-Combustion gas flow path, 40-Cooling device, 41-Extraction line, 42-Cooler, 43-Boost compressor, 44-Cooling air line, 45-Cooling air exhaust line, 50-Fixed blade, 51-Blade body, 52-Leading edge, 53- - Trailing edge, 54- Negative pressure surface, 55- Positive pressure surface, 56- Blade air passage, 56a- First blade air passage (or simply blade air passage), 56ai- Inner opening, 56ao- Outer opening, 56b- Second blade air passage, 56bi- Inner opening, 56c- Third blade air passage, 57a- First passage defining surface, 57b- Second passage defining surface, 59f- Leading edge injection passage, 59b- Trailing edge injection passage, 60i- Inner shield (or second shield), 60o- Outer shield (or first shield), 61i- Inner shield body (or second shield body), 61o- Outer shield body (or first shield body), 62f- Front end face, 62b- Rear end face, 63n- Negative pressure Side end face, 63p-positive pressure side end face, 64p-airflow path face, 64a-reverse airflow path face, 65i, 65o-peripheral wall, 65f-front wall, 65b-rear wall, 65n-negative pressure side wall, 65p-positive pressure side wall, 66-recess, 68f-front hook, 68b-rear hook, 69-fixing part, 70, 70b, 70c-insertion cylinder, 71-cylinder body, 71b-cylinder body (or guide cylinder part), 71h-impact hole, 72-radial inner end (or second side end), 73-flange part (or groove bottom), 73b, 73c-flange part, 74-groove side wall part (or guide cylinder part), 74b-groove side wall part, 75b-groove bottom, 76, 76b-protruding piece insertion groove, 80, 80a, 80c, 8 0d, 80e - Insert support body; 81 - Support plate; 81c - Groove bottom; 81o - Support plate opening; 82 - Position limiting protrusion; 82c - Position limiting protrusion (or inner position limiting protrusion); 83a, 83da - First pressing part; 83b, 83db - Second pressing part; 84a - First contact surface; 84b - Second contact surface; 85 - Shrink ring; 85o - Shrink opening; 86a - First groove; 86b - Second groove; 87 - Groove sidewall (or outer position limiting protrusion); 88 - Guide cylinder; 89 - Cylinder insertion groove; 90 - Baffle plate; 90f - Front baffle plate; 90b - Rear baffle plate; 91 - Channel opposite part; 92 - Transition part; 93 - Outer periphery; 93a - Bending part.95i - Inner impact plate (or simply impact plate), 95o - Outer impact plate, 95h - Impact hole, A - External air, Acom - Compressed air, Acl - Cooling air, G - Combustion gas, F - Fuel, CL - Curve, S1 - First space, S2 - Second space, Ar - Axis, Da - Axis direction, Dau - Upstream side of axis, Dad - Downstream side of axis, Dc - Circumferential, Dcn - Circumferential negative pressure side, Dcp - Circumferential positive pressure side, Dr - Radial (or blade height direction), Dri - Radial inner side (or second side of blade height), Dro - Radial outer side (or first side of blade height).

Claims

1. A fixed blade, comprising: The blade body has an airfoil-shaped cross-section and extends along the blade height direction having a directional component perpendicular to the cross-section; The blade air passage extends along the height of the blade within the blade body, allowing cooling air to circulate therethrough; The first protective cover is disposed at the end of the blade body on the first side of the blade height in the blade height direction; The second protective cover is disposed at the end of the blade body on the side opposite to the first side of the blade height, i.e., the second side of the blade height. An insert tube, at least a portion of which is disposed within the air passage of the blade; and Insert support body, supporting the insert cylinder The first shield has a first shield body that extends from an end of the blade body on a first side of the blade height in a direction perpendicular to the blade height direction. The second shield has a second shield body that extends from an end of the blade body on a second side of the blade height in a direction perpendicular to the blade height direction. The blade air passage extends along the blade height direction through the first shield body, the blade body, and the second shield body. The insertion cylinder has: a cylindrical body extending along the blade height direction and being cylindrical, with openings at an end on a first side of the blade height and at an end on a second side of the blade height, and having a plurality of impact holes extending from the inner circumferential side to the outer circumferential side; and a flange portion protruding from a position near the second side of the blade height toward the inner circumferential side of the cylindrical body, thereby narrowing the air passage within the cylindrical body. The insert support body has: a support plate extending in a direction perpendicular to the blade height direction and fixed to the second cover body; and a position limiting protrusion protruding from the support plate toward a first side of the blade height. The support plate has a support plate opening, which extends through the region of the inner circumference of the cylinder in the blade height direction. The position-restricting protrusion extends from the support plate toward the first side of the blade height along the entire circumference of the opening edge of the support plate, forming a cylindrical shape. It is opposite to the inner or outer circumferential surface of the second end portion of the cylinder, which includes the end portion of the blade height, thereby restricting the relative position of the insertion cylinder with respect to the insertion support body in a direction perpendicular to the blade height direction. One of the insertion cylinder and the insertion support body has: a groove bottom extending in a direction perpendicular to the blade height direction; and a groove sidewall portion protruding from the groove bottom in the blade height direction. In the case where one of them is the insertion cylinder, the groove sidewall is cylindrical, extending across the entire circumference of the cylinder and spaced apart from the second side end of the cylinder. The groove bottom extends across the entire circumference of the cylinder, connecting the cylinder and the groove sidewall, thereby forming an annular protrusion insertion groove in which the position-limiting protrusion is embedded by the cylinder, the groove sidewall, and the groove bottom. When one of them is the insert support, the groove sidewall is cylindrical, extending across the entire circumference of the cylinder and spaced apart from the position limiting protrusion. The groove bottom extends across the entire circumference of the cylinder, connecting the position limiting protrusion to the groove sidewall. Thus, the position limiting protrusion, the groove sidewall, and the groove bottom form an annular cylindrical insertion groove into which the second side end of the cylinder is embedded. The insertion cylinder engages with the insertion support in a manner that allows for relative movement.

2. The fixed blade according to claim 1, wherein, One of them is the insertion tube. The position-limiting protrusion of the insert support is located on the inner circumferential side of the cylinder and is opposite to the inner circumferential surface of the cylinder. The flange portion of the insertion tube forms the bottom of the groove. The groove sidewall extends from the inner circumferential edge of the flange forming the bottom of the groove along the second side of the blade height, so that the position limiting protrusion is located between the groove sidewall and the cylinder. The protruding piece insertion groove is formed by the cylinder, the sidewall of the groove, and the flange forming the bottom of the groove.

3. The fixed blade according to claim 2, wherein, The end of the groove sidewall portion on the second side of the blade height is located further back on the second side of the blade height than the support plate.

4. The fixed blade according to claim 2, comprising a baffle plate and an impact plate fixed to the second protective cover. The second shield has a peripheral wall that protrudes from the outer periphery of the second shield body toward the second side of the blade height. The second shield body and the peripheral wall together form a recess on the second side of the blade height, which is recessed towards the first side of the blade height. The baffle plate is positioned at a distance from the second shield body on the second side of the blade height, and separates the cooling air space within the recess from a space further on the second side of the blade height than the cooling air space. The impact plate divides the cooling air space into a first space on the first side of the blade height and a second space on the second side of the blade height, and forms a plurality of impact holes extending from the second space to the first space. The end of the groove sidewall on the second side of the blade height is located closer to the second side of the blade height than the impact plate and closer to the first side of the blade height than the blocking plate.

5. The fixed blade according to claim 3, wherein, The insert support has a contraction ring with a contraction opening through which the annular groove sidewall portion is inserted, and is fixed to the support plate on the surface facing the second side of the blade height. The average interval between the contraction opening and the annular groove sidewall is narrower than the average interval between the annular position-restricting protrusion of the insert support and the annular groove sidewall of the insert cylinder.

6. The fixed blade according to claim 1, wherein, One of them is the insertion tube. The position-limiting protrusion of the insert support is located on the outer peripheral side of the cylinder and faces the outer peripheral surface of the cylinder. The bottom of the groove extends from the outer peripheral surface of the cylinder along the outer peripheral side. The groove sidewall extends from the outer peripheral edge of the groove bottom along the second side of the blade height, so that the position limiting protrusion is located between the groove sidewall and the cylinder. The protruding piece insertion groove is formed by the cylinder, the side wall of the groove, and the bottom of the groove.

7. The fixed blade according to claim 1, wherein, One of them is the insert support body. The position-limiting protrusion of the insert support is located on the inner circumferential side of the cylinder, forming an inner position-limiting protrusion opposite to the inner circumferential surface of the cylinder. The groove sidewall portion protrudes from the support plate toward the first side of the blade height along the entire circumference of the opening edge of the support plate opening, and is located on the outer circumference of the cylinder, forming an outer position limiting protrusion opposite to the outer circumferential surface of the cylinder. The bottom of the groove is the portion located in the support plate between the inner position limiting protrusion and the outer position limiting protrusion. The inner position limiting protrusion, the outer position limiting protrusion, and the bottom of the groove form an annular cylindrical insertion groove.

8. The fixed blade according to claim 1, wherein, The projected area of ​​the flange in the blade height direction is more than 1 / 2 of the area of ​​the airflow path inside the cylinder in the direction perpendicular to the blade height direction.

9. The fixed blade according to any one of claims 1 to 8, wherein, The blade air passage is defined by a plurality of channel defining surfaces, including a first channel defining surface and a second channel defining surface. The first channel defining surface extends along the blade height direction, and the second channel defining surface is connected to the first channel defining surface and extends along the blade height direction while also extending in a direction intersecting the first channel defining surface. The insert support body has: The first pressing part has a first contact surface, which protrudes from the support plate toward the first side of the blade height, and is located in a direction perpendicular to the blade height direction, closer to the first channel defining surface than the position limiting protrusion, and is in contact with the first channel defining surface. and The second pressing part has a second contact surface that protrudes from the support plate toward the first side of the blade height. In a direction perpendicular to the blade height direction, it is located closer to the second channel defining surface than the position limiting protrusion and contacts the second channel defining surface. The support plate is joined to the second protective cover body at the outer periphery of the support plate.

10. The fixed blade according to any one of claims 1 to 5, 7 and 8, wherein, The blade air passage is defined by a plurality of channel defining surfaces, including a first channel defining surface and a second channel defining surface. The first channel defining surface extends along the blade height direction, and the second channel defining surface is connected to the first channel defining surface and extends along the blade height direction while also extending in a direction intersecting the first channel defining surface. The insert support body has: The first pressing part has a first contact surface, which protrudes from the support plate toward the first side of the blade height, and is located in a direction perpendicular to the blade height direction, closer to the first channel defining surface than the position limiting protrusion, and is in contact with the first channel defining surface. and The second pressing part has a second contact surface that protrudes from the support plate toward the first side of the blade height. In a direction perpendicular to the blade height direction, it is located closer to the second channel defining surface than the position limiting protrusion and contacts the second channel defining surface. The support plate is joined to the second protective cover body at the outer periphery of the support plate. The position limiting protrusion is located on the inner circumferential side of the cylinder and is opposite to the inner circumferential surface of the cylinder. A first groove is formed between the position-limiting protrusion and the first pressing part. The first groove is recessed towards the second side of the blade height, so that the end of the cylinder on the second side of the blade height is embedded therein. A second groove is formed between the position limiting protrusion and the second pressing part. The second groove is recessed toward the second side of the blade height, so that the end of the cylinder on the second side of the blade height is embedded therein.

11. The fixed blade according to claim 10, wherein, The second pressing part is away from the first pressing part.

12. The fixed blade according to any one of claims 1 to 3, 6 to 8, comprising a baffle plate fixed to the second protective cover. The second shield has a peripheral wall that protrudes from the outer periphery of the second shield body toward the second side of the blade height. On the second shield body and the peripheral wall, a recess is formed on the second side of the blade height of the second shield body, which is recessed towards the first side of the blade height. The baffle plate is positioned at a distance from the second shield body on the second side of the blade height, and separates the cooling air space within the recess from a space further on the second side of the blade height than the cooling air space. The baffle plate has: a channel-opposing portion opposite to the air passage of the blade in the blade height direction; a transition portion connected to the periphery of the channel-opposing portion; and an outer peripheral portion connected to the periphery of the transition portion and at least partially engaged with the peripheral wall. The channel-facing portion is located further along the second side of the blade height than the connection portion between the outer peripheral portion and the transition portion. The transition portion is formed such that it gradually moves toward the second side of the blade height as it approaches the opposite portion of the channel from the outer periphery.

13. The fixed blade according to claim 12, wherein, The outer peripheral portion has a curved portion that gradually moves toward the second side of the blade height in a direction perpendicular to the blade height direction as it moves away from the opposite portion of the channel.

14. The fixed blade according to claim 13, wherein, The blade body has: a leading edge; a trailing edge; a positive pressure surface for connecting the leading edge and the trailing edge; and a negative pressure surface, which is back-to-back with the positive pressure surface and is used to connect the leading edge and the trailing edge. The second protective cover has a fastener connected to the peripheral wall. The peripheral wall of the second shield has: a positive pressure sidewall, located on the positive pressure side relative to the negative pressure surface, with the blade body as a reference; and a negative pressure sidewall, located on the negative pressure side opposite to the positive pressure side, with the blade body as a reference. The fastener is connected to the positive pressure sidewall and the negative pressure sidewall. The curved portion engages with the fastener.

15. A gas turbine comprising: The fixed blade according to any one of claims 1 to 8; The rotor is capable of rotating about its axis; and Turbine housing, covering the rotor, The fixed blade is mounted on the inner side of the turbine housing such that the height direction of the blade is radial relative to the axis.

Images