Stator blade and gas turbine having the same

Abstract

The present application provides a stationary vane, which is provided with a vane main body, a first embedded member, a second embedded member, and an end cover. The vane main body is provided with a first vane air passage and a second vane air passage which extend in the vane height direction within the vane main body. In each passage, the end on the second vane height side is open. The first embedded member and the second embedded member are provided with a cylindrical peripheral plate portion. A plurality of impact holes are formed in the peripheral plate portion. The peripheral plate portion is open on the side of the cylinder height opening in the cylinder height direction. The peripheral plate portion of the first embedded member is arranged in the first vane air passage in such a manner that cooling air flows into the peripheral plate portion from the opening of the first embedded member. The peripheral plate portion of the second embedded member is arranged in the second vane air passage in such a manner that cooling air flows into the peripheral plate portion from the opening of the second embedded member. The end cover is arranged on the second vane height side of the vane main body and covers the opening of the first vane air passage and the opening of the second embedded member.

Description

Technical Field

[0001] The present invention relates to a stationary blade and a gas turbine having the stationary blade.

[0002] This application claims priority based on Japanese Patent Application No. 2021-053113, filed on March 26, 2021, the contents of which are incorporated herein by reference. Background Technology

[0003] A gas turbine comprises a compressor that compresses air to generate compressed air, a combustor that burns fuel in the compressed air to generate fuel gas, and a turbine driven by the combustion gas. The turbine comprises a turbine rotor rotating about an axis, a turbine housing covering the rotor, and multiple rows of stationary blades. The turbine rotor has a rotor shaft centered on the axis and multiple rows of moving blades mounted on the rotor shaft. The multiple rows of moving blades are arranged along the axial direction extending from the axis. Each row of moving blades has multiple moving blades arranged circumferentially relative to the axis. Multiple rows of stationary blades are arranged along the axial direction and mounted on the inner circumference of the turbine housing. Each row of stationary blades is positioned upstream of the axial direction of any one of the multiple rows of moving blades. Each row of stationary blades has multiple stationary blades arranged circumferentially relative to the axis.

[0004] The stationary blade has a blade body extending radially relative to its axis and shaped like a leaf, an inner shroud disposed radially inward of the blade body, and an outer shroud disposed radially outward of the blade body. The blade body of the stationary blade is positioned within a combustion gas flow path through which the combustion gas passes. The inner shroud defines the radially inner edge of the combustion gas flow path. The outer shroud defines the radially outer edge of the combustion gas flow path.

[0005] The stationary blades of a gas turbine are exposed to high-temperature combustion gases. Therefore, they are typically cooled by air or similar means.

[0006] For example, in the stationary blade described in Patent Document 1, multiple cooling air channels are formed in the blade body for the passage of cooling air. Each of the multiple cooling air channels extends radially relative to the axis, i.e., in the blade height direction Dh. The stationary blade includes an impact plate disposed within one of the multiple cooling air channels. This impact plate extends along the blade height direction Dh within a cooling air channel and is disposed within that channel in a manner that divides the cooling air channel into a blade surface side and an opposite side, i.e., an inner side, of the blade body. Multiple impact holes are formed in the impact plate.

[0007] In this stationary blade, within a cooling channel, cooling air flowing into the inner side with the impact plate as a reference is ejected from multiple impact holes in the impact plate toward the blade surface. The cooling air ejected from the multiple impact holes collides with the portion of the cooling air channel that is back-to-back with the blade surface, thereby subjecting that portion to impact cooling.

[0008] Previous technical documents

[0009] Patent documents

[0010] Patent Document 1: Japanese Patent No. 4885275 Summary of the Invention

[0011] The technical problem to be solved by the invention

[0012] Regarding the stationary blades of the gas turbine, it is required to cool the stationary blades to improve their durability and to minimize the amount of air used for cooling them.

[0013] Therefore, the present invention aims to provide a stationary blade that can be effectively cooled and a gas turbine having the stationary blade.

[0014] means for solving technical problems

[0015] An invention relating to achieving the aforementioned objective includes a stationary blade disposed in a gas turbine, the stationary blade comprising: a blade body having a blade-shaped cross-section and extending along a blade height direction having a directional component perpendicular to the cross-section; a first insert and a second insert, cylindrical in shape, extending along a cylindrical height direction and disposed within the blade body such that the cylindrical height direction is oriented toward the blade height direction; and an end cap.

[0016] The blade body has a plurality of blade air channels extending along the blade height direction within the blade body. The first and second blade air channels are both end openings on one side of the blade height direction, i.e., one side of the blade height. The first and second inserts each have a cylindrical outer peripheral plate extending along the cylindrical height direction and a sealing plate that closes one end of the outer peripheral plate on one side of the cylindrical height direction, i.e., the cylindrical height sealing side. A plurality of impact holes are formed on the outer peripheral plate, penetrating from the inside to the outside of the cylindrical outer peripheral plate. The other side of the outer peripheral plate on the cylindrical height direction, i.e., the cylindrical height opening side, is also open. A gap exists between the outer peripheral plate of the first insert and the first channel demarcation surface of the blade body that defines the first blade air channel, and the insert is positioned within the first blade air channel such that cooling air flows into the outer peripheral plate from the opening of the first insert. The outer peripheral plate of the second insert is arranged such that the cylinder height opening side of the second insert faces the blade height side, and a gap exists between the outer peripheral plate of the second insert and the second channel defining surface of the blade body defining the air channel of the second blade, and cooling air flows in from the opening of the second insert into the air channel of the second blade. The end cover is arranged on the blade height side of the blade body such that cooling air ejected from the plurality of impact holes of the first insert into the space between the outer peripheral plate of the first insert and the first channel defining surface is guided into the second insert through the opening of the first blade air channel from the opening of the second insert, and covers the opening of the first blade air channel and the opening of the second insert.

[0017] In this method, cooling air flowing into a first insert disposed within the air passage of the first blade impinges on the first passage's defining surface. Furthermore, at least a portion of this cooling air flows into a second insert disposed within the air passage of the second blade. The cooling air flowing into the second insert impinges on the second passage's defining surface. Therefore, in this method, compared to the case where cooling air Ac flowing into one insert impinges on the blade body and is then immediately ejected into the combustion gas flow path, the stationary blades can be cooled more effectively, thus reducing the amount of cooling air used.

[0018] The invention for achieving the stated purpose includes a gas turbine comprising stationary blades of the stated manner, a rotor rotating about an axis, and a housing covering the outer periphery of the rotor.

[0019] The stationary blade is fixed to the inner circumferential surface of the housing.

[0020] Invention Effects

[0021] According to one aspect of the present invention, the stationary blades can be effectively cooled, thereby improving durability and reducing the amount of cooling air used. Attached Figure Description

[0022] Figure 1 This is a schematic cross-sectional view of a gas turbine in one embodiment of the present invention.

[0023] Figure 2 This is a cross-sectional view of the main part of the gas turbine in one embodiment of the present invention.

[0024] Figure 3 This is a perspective view of the stationary blade in the first embodiment of the present invention.

[0025] Figure 4 This is a cross-sectional view of the stationary blade on the curved surface in the first embodiment of the present invention.

[0026] Figure 5 yes Figure 4 The VV line section view in the diagram.

[0027] Figure 6 This is a perspective view of the insert in the first embodiment of the present invention.

[0028] Figure 7 This is a cross-sectional view of the stationary blade on a plane perpendicular to the axis in the second embodiment of the present invention.

[0029] Figure 8 yes Figure 7 Sectional view along line VIII-VIII.

[0030] Figure 9 This is a cross-sectional view of a stationary blade on a curved surface in a first variation of the first embodiment of the present invention.

[0031] Figure 10 This is a cross-sectional view of the stationary blade on the curved surface in the second variation of the first embodiment of the present invention.

[0032] Figure 11 This is a cross-sectional view showing the stationary blade on the curved surface in the third variation of the first embodiment of the present invention. Detailed Implementation

[0033] Hereinafter, various embodiments and variations of the present invention will be described in detail with reference to the accompanying drawings.

[0034] "Implementation Methods of Gas Turbines"

[0035] refer to Figure 1 and Figure 2 The implementation method of the gas turbine is described.

[0036] like Figure 1 As shown, the gas turbine 10 of this embodiment includes a compressor 20 for compressing air A, a burner 30 for generating combustion gas G by burning fuel F in the air A compressed by the compressor 20, and a turbine 40 driven by the combustion gas G.

[0037] The compressor 20 has a compressor rotor 21 rotating around an axis Ar, a compressor housing 25 covering the compressor rotor 21, and multiple rows of stationary blades 26. The turbine 40 has a turbine rotor 41 rotating around an axis Ar, a turbine housing 45 covering the turbine rotor 41, and multiple rows of stationary blades 46. Hereinafter, the direction in which the axis Ar extends is defined as the axial direction Da, the circumferential direction centered on the axis Ar is simply defined as the circumferential direction Dc, and the direction perpendicular to the axis Ar is defined as the radial direction Dr. Furthermore, one side in the axial direction Da is defined as the upstream side Dau, and the opposite side is defined as the downstream side Dad. Also, in the radial direction Dr, the side closer to the axis Ar is defined as the radially inner side Dri, and the opposite side is defined as the radially outer side Dro.

[0038] The compressor 20 is positioned on the upstream side of the shaft relative to the turbine 40, in the Dau configuration.

[0039] The compressor rotor 21 and the turbine rotor 41 are located on the same axis Ar and are connected to each other to form the gas turbine rotor 11. For example, a generator rotor GEN is connected to this gas turbine rotor 11. The gas turbine 10 also includes an intermediate housing 16. This intermediate housing 16 is disposed between the compressor housing 25 and the turbine housing 45 in the axial direction Da. The compressor housing 25, the intermediate housing 16, and the turbine housing 45 are connected to each other to form the gas turbine housing 15.

[0040] The compressor rotor 21 has a rotor shaft 22 extending along the axial direction Da with axis Ar as its center, and multiple rows of moving blades 23 mounted on the rotor shaft 22. The multiple rows of moving blades 23 are arranged along the axial direction Da. Each row of moving blades 23 consists of multiple moving blades 23a arranged circumferentially Dc. One of multiple rows of stationary blades 26 is disposed downstream of each row of moving blades 23 on the axial direction Dad. Each row of stationary blades 26 is located inside the compressor housing 25. Each row of stationary blades 26 consists of multiple stationary blades 26a arranged circumferentially Dc.

[0041] like Figure 1 and Figure 2As shown, the turbine rotor 41 has a rotor shaft 42 extending along the axial direction Da with axis Ar as its center, and a plurality of moving blade rows 43 mounted on the rotor shaft 42. The plurality of moving blade rows 43 are arranged along the axial direction Da. Each moving blade row 43 is composed of a plurality of moving blades 43a arranged circumferentially Dc. One of a plurality of stationary blade rows 46 is disposed on the upstream side Dau of each of the plurality of moving blade rows 43. Each stationary blade row 46 is not located inside the turbine housing 45. Each stationary blade row 46 is composed of a plurality of stationary blades 46a arranged circumferentially Dc.

[0042] The turbine housing 45 has a cylindrical outer housing 45a constituting its outer shell, an inner housing 45b fixed inside the outer housing 45a, and a plurality of segmented rings 45c fixed inside the inner housing 45b. The plurality of segmented rings 45c are positioned between the plurality of stationary blade rows 46. Therefore, a moving blade row 43 is arranged radially inward (Dri) on each segmented ring 45c.

[0043] An annular space between the outer peripheral side of the rotor shaft 42 and the inner peripheral side of the turbine housing 45, and in the axial direction Da, with stationary blades 46a and moving blades 43a arranged therein, constitutes a combustion gas flow path 49 for the combustion gas G from the burner 30 to flow.

[0044] The burner 30 is mounted on the intermediate housing 16.

[0045] like Figure 1 As shown, compressor 20 compresses air A to generate compressed air. This compressed air flows into burner 30. Fuel F is supplied to burner 30. Inside burner 30, fuel F burns in the compressed air to generate high-temperature, high-pressure combustion gas G. This combustion gas G is delivered from burner 30 to combustion gas flow path 49 within turbine 40. As combustion gas G flows downstream of axis 41 in combustion gas flow path 49, it causes turbine rotor 41 to rotate. The rotation of turbine rotor 41 causes the rotor of generator GEN, connected to gas turbine rotor 11, to rotate. As a result, generator GEN generates electricity.

[0046] Hereinafter, various embodiments relating to the stationary blades constituting the primary stationary blade row 46 will be described.

[0047] "First Embodiment of the Stationary Blade"

[0048] The following is for reference. Figures 3-6 The first embodiment of the stationary blade according to the present invention will be described.

[0049] like Figure 3As shown, the stationary blade 50 of this embodiment has a blade body 51, an inner shield 60i, and an outer shield 60o. The blade body 51 has a leaf-shaped cross-section and extends along the blade height direction Dh, which has a directional component perpendicular to the cross-section. The inner shield 60i is provided at one end of the blade body 51 in the blade height direction Dh. The outer shield 60o is provided at the other end of the blade body 51 in the blade height direction Dh. The blade body 51, the inner shield 60i, and the outer shield 60o are integrally formed from a casting or the like.

[0050] With the stationary blade 50 installed on the turbine housing 45 (reference) Figure 2 In this configuration, the blade height direction Dh becomes radial Dr. Furthermore, one side of the blade height direction Dh, namely the first blade height side Dh1, becomes radially inner Dri, and the other side of the blade height direction Dh, namely the second blade height side Dh2, becomes radially outer Dro. Therefore, the inner shield 60i is disposed on the radially inner side Dri of the blade body 51, and the outer shield 60o is disposed on the radially outer side Dro of the blade body 51. Therefore, in this embodiment, the blade height direction Dh is sometimes referred to as radial Dr, the first blade height side Dh1 as radially inner Dri, and the second blade height side Dh2 as radially outer Dro.

[0051] like Figures 3-5 As shown, the outer surface of the blade body 51, i.e., the blade surface, has a leading edge 52, a trailing edge 53, a convex surface (i.e., a negative pressure surface 54), and a concave surface (i.e., a positive pressure surface 55). The leading edge 52 and the trailing edge 53 exist in the portion where the negative pressure surface 54 and the positive pressure surface 55 connect. The leading edge 52, the trailing edge 53, the negative pressure surface 54, and the positive pressure surface 55 all extend radially along the blade height direction Dh, i.e., Dr. When the stationary blade 50 is mounted on the turbine housing 45, the leading edge 52 is located upstream of the axis (Dau) relative to the trailing edge 53. Furthermore, when the stationary blade 50 is mounted on the turbine housing 45, the negative pressure surface 54 faces the side on the circumferential direction Dc, i.e., the circumferential negative pressure side Dcn, and the positive pressure surface 55 faces the other side on the circumferential direction Dc, i.e., the circumferential positive pressure side Dcp.

[0052] The blade body 51 is disposed within the combustion gas flow path 49 through which the combustion gas G passes. The blade body 51 has a plurality of blade air passages 80 extending radially Dr within the blade body 51. An inner shroud 60i defines the radially inner edge Dri of the annular combustion gas flow path 49. Furthermore, an outer shroud 60o defines the radially outer edge Dro of the annular combustion gas flow path 49.

[0053] The inner cover 60i has a cover body 61, a peripheral wall 71 and a retainer 76.

[0054] The shield body 61 is a plate-shaped component extending along a direction that includes a directional component perpendicular to the blade height direction Dh, i.e., radial Dr. The shield body 61 has a gas path surface 64, a gas path opposite surface 65, a front end surface 62f, a rear end surface 62b, a negative pressure side end surface 63n, and a positive pressure side end surface 63p.

[0055] The gas path surface 64 faces the second side of the blade height, Dh2 (radially outward Dro), and is in contact with the combustion gas G. The opposite gas path surface 65 faces the first side of the blade height, Dh1 (radially inward Dri). This opposite gas path surface 65 and the gas path surface 64 are in a back-to-back relationship. The front end surface 62f is located upstream of the blade body 51 on the axis, facing the upstream side of the axis, Dau. The rear end surface 62b is located downstream of the blade body 51 on the axis, Dad, and faces the downstream side of the axis, Dad. The negative pressure side end surface 63n is located within the shield body 61, further circumferentially on the negative pressure side, Dcn than the blade body 51, and faces the circumferential negative pressure side, Dcn. This negative pressure side end surface 63n connects the front end surface 62f and the rear end surface 62b. The positive pressure side end face 63p is located within the shield body 61, further along the circumferential positive pressure side Dcp than the blade body 51, and faces the circumferential positive pressure side Dcp. This positive pressure side end face 63p connects the front end face 62f and the rear end face 62b. The rear end face 62b is located downstream of the axis from the front end face 62f by a gap, and is substantially parallel to the front end face 62f. Furthermore, the positive pressure side end face 63p is located on one side of the circumferential Dc from the negative pressure side end face 63n by a gap, and is substantially parallel to the negative pressure side end face 63n. Therefore, when viewed radially Dr, the shield body 61 appears as a parallelogram.

[0056] The peripheral wall 71 is a wall that protrudes radially inward from the outer periphery of the shield body 61 towards the inner side Dri. The peripheral wall 71 has a front peripheral wall 71f and a rear peripheral wall 71b that are opposed to each other in the axial direction Da, and a positive pressure side peripheral wall 71p and a negative pressure side peripheral wall 71n that are opposed to each other in the circumferential direction Dc. The front peripheral wall 71f is located upstream of the blade body 51 on the axial side Dau. The surface of the front peripheral wall 71f facing upstream of the axial side Dau forms part of the front end face 62f of the inner shield 60i. The rear peripheral wall 71b is located downstream of the blade body 51 on the axial side Dad. The positive pressure side peripheral wall 71p is located circumferentially on the positive pressure side Dcp, which is further from the blade body 51. The surface of this positive pressure side peripheral wall 71p facing circumferentially on the positive pressure side Dcp forms part of the positive pressure side end face 63p of the inner shield 60i. The negative pressure side peripheral wall 71n is located further along the circumferential negative pressure side Dcn than the blade body 51. The surface of this negative pressure side peripheral wall 71n facing the circumferential negative pressure side Dcn forms part of the negative pressure side end face 63n of the inner shroud 60i.

[0057] Within the inner shield 60i, a cavity 72 is formed by the shield body 61 and the peripheral wall 71, recessed towards the radially inward direction Dri. This cavity 72 is defined by the gas path opposite surface 65 of the shield body 61, the surface of the front peripheral wall 71f facing the downstream side Dad of the axis, the surface of the rear peripheral wall 71b facing the upstream side Dau of the axis, the surface of the positive pressure side peripheral wall 71p facing the circumferential negative pressure side Dcn, and the surface of the negative pressure side peripheral wall 71n facing the circumferential positive pressure side Dcp.

[0058] The retainer 76 is located between the front peripheral wall 71f and the rear peripheral wall 71b in the axial direction Da, and is formed from the negative pressure side end face 63n to the positive pressure side end face 63p. This retainer 76 is attached to the radially outer end 17a of the inner shroud 17 of the gas turbine housing 15 (reference). Figure 2 and Figure 4 It connects and serves to support the radially inner side Dri of the stationary blade 50 to the inner cover 17.

[0059] The outer shield 600 has a structure that is basically the same as that of the inner shield 60i. Therefore, like the inner shield 60i, the outer shield 60o also has a shield body 61 and a peripheral wall 71. However, the outer shield 60o does not have a portion equivalent to the retainer 76 of the inner shield 60i. Like the shield body 61 of the inner shield 60i, the shield body 61 of the outer shield 60o also has a gas path surface 64, a gas path opposite surface 65, a front end surface 62f, a rear end surface 62b, a negative pressure side end surface 63n, and a positive pressure side end surface 63p. Furthermore, like the peripheral wall 71 of the inner shield 60i, the peripheral wall 71 of the outer shield 60o also has a front peripheral wall 71f, a rear peripheral wall 71b, a positive pressure side peripheral wall 71p, and a negative pressure side peripheral wall 71n. The front peripheral wall 71f and rear peripheral wall 71b of the outer shroud 60o serve to mount the stationary blade 50 onto the turbine housing 45 (reference). Figure 2 The function of the inner peripheral side of ).

[0060] like Figure 3 and Figure 5As shown, a plurality of blade air channels 80 formed within the blade body 51 are arranged along the arc CL of the blade body 51. Among the plurality of blade air channels 80, the blade air channel 80 closest to the upstream side (Dau) of the axis is designated as the front blade air channel 80f, and the blade air channel 80 closest to the downstream side (Dad) of the axis is designated as the rear blade air channel 80b. Furthermore, among the plurality of blade air channels 80, the two blade air channels 80 between the front blade air channel 80f and the rear blade air channel 80b are designated as intermediate blade air channels 80m. Moreover, of the two intermediate blade air channels 80m, the intermediate blade air channel 80m closest to the upstream side (Dau) of the axis is designated as the first blade air channel 81, and the intermediate blade air channel 80m closest to the downstream side (Dad) of the axis is designated as the second blade air channel 85.

[0061] In the front blade air passage 80f, the end on the first side of the blade height, Dh1 (i.e., the radially inner side Dri), is closed, while the end on the second side of the blade height, Dh2 (i.e., the radially outer side Dro), is open. Multiple front exhaust holes 80fa are formed on the leading side portion of the blade body 51, including the leading edge 52, extending from the front blade air passage 80f into the combustion gas flow path 49. Furthermore, the end on the radially inner side Dri of the blade body 51 forms part of the gas path opposite surface 65 of the inner shroud 60i, and the end on the radially outer side Dro of the blade body 51 forms part of the gas path opposite surface 65 of the outer shroud 60o. Therefore, the opening 80fo of the front blade air passage 80f opens on the gas path opposite surface 65 of the outer shroud 60o.

[0062] In the rear blade air passage 80b, the end on the first side of the blade height, Dh1 (radially inner Dri), is closed, while the end on the second side of the blade height, Dh2 (radially outer Dro), is open. The opening 80bo of the rear blade air passage 80b opens on the opposite side 65 of the gas path of the outer shroud 60o. Multiple rear exhaust holes 80ba are formed on the rear portion of the blade body 51, including the trailing edge 53, extending from the rear blade air passage 80b to the combustion gas flow path 49.

[0063] In the first blade air passage 81, the end at the first blade height side Dh1 (radially inward Dri) and the end at the second blade height side Dh2 (radially outward Dro) are open. The opening at the first blade height side Dh1 of the first blade air passage 81, i.e., the first opening 82f, opens on the opposite side 65 of the gas path of the inner shroud 60i. Furthermore, the opening at the second blade height side Dh2 of the first blade air passage 81, i.e., the second opening 82s, opens on the opposite side 65 of the gas path of the outer shroud 60o. In the blade body 51, a plurality of positive pressure side first ejection holes 83pf are formed, extending from the first channel defining surface 81p of the first blade air passage 81 that defines the blade body 51 to a portion of the positive pressure surface 55, i.e., the positive pressure side first blade portion 55f. Additionally, the positive pressure side first blade portion 55f is a portion on the positive pressure surface 55 of the blade body 51 that is back-to-back with the first blade air passage 81. Furthermore, a plurality of negative pressure side first ejection holes 83nf are formed in the blade body 51, extending from the first channel demarcation surface 81p of the first blade air passage 81 that defines the blade body 51 to a portion of the negative pressure surface 54, namely the negative pressure side first blade part 54f. In addition, the negative pressure side first blade part 54f is a portion on the negative pressure surface 54 of the blade body 51 that is in a back-to-back relationship with the first blade air passage 81.

[0064] In the second blade air passage 85, the end on the first side of blade height Dh1, i.e., the radially inner side Dri, is closed, while the end on the second side of blade height Dh2, i.e., the radially outer side Dro, is open. The opening 86 of the second blade air passage 85 opens on the opposite side 65 of the gas path of the outer shroud 60o. In the blade body 51, a plurality of second exhaust holes 87ps on the positive pressure side are formed, extending from the second channel defining surface 85p of the second blade air passage 85 that defines the blade body 51 to a part of the positive pressure surface 55, i.e., the positive pressure side second blade surface 55s.

[0065] Furthermore, the positive pressure side second blade section 55s is a portion on the positive pressure surface 55 of the blade body 51 that is back-to-back with the second blade air passage 85. Also, a plurality of negative pressure side second ejection holes 87ns are formed in the blade body 51, extending from the second channel demarcation surface 85p that defines the second blade air passage 85 of the blade body 51 to a portion of the negative pressure surface 54, i.e., the negative pressure side second blade section 54s. Additionally, the negative pressure side second blade section 54s is a portion on the negative pressure surface 54 of the blade body 51 that is back-to-back with the second blade air passage 85.

[0066] As described above, the first blade air passage 81 and the second blade air passage 85 are both end openings on the second side of the blade height Dh2, i.e., the radially outer side Dro.

[0067] like Figures 3-6As shown, the stationary blade of this embodiment also includes a first insert 90, a second insert 95, an end cover 100, a plurality of first guides 110 and second guides 115.

[0068] The first insert 90 is disposed within the air passage 81 of the first blade, and the second insert 95 is disposed within the air passage 85 of the second blade. For example... Figure 6 As shown, the first insert 90 has an outer peripheral plate portion 91, a sealing plate portion 93, and a flange portion 94. The second insert 95 also has an outer peripheral plate portion 96, a sealing plate portion 98, and a flange portion 99. The outer peripheral plate portions 91 and 96 of the first insert 90 and the second insert 95 are cylindrical and extend along the cylinder height direction Dih. Here, one side of the two sides in the cylinder height direction Dih is designated as the cylinder height sealing side Dih1, and the other side is designated as the cylinder height opening side Dih2. The sealing plate portions 93 and 98 close the ends of the cylinder height sealing side Dih1 of the outer peripheral plate portions 91 and 96. On the other hand, no sealing plate portion is provided at the end of the cylinder height opening side Dih2 of the outer peripheral plate portions 91 and 96. Therefore, insert openings 90o and 95o are formed at the end of the cylinder height opening side Dih2 of the outer peripheral plate portions 91 and 96 to guide cooling air into the outer peripheral plate portions 91 and 96. Flange portions 94 and 99 extend outward from the end of the cylinder height opening side Dih2 in the entire outer peripheral surface of the outer peripheral plate portions 91 and 96 toward the outer peripheral side.

[0069] The outer peripheral plate portion 91 of the first insert 90 is disposed within the first blade air passage 81 such that its cylinder height opening side Dih2 faces the first blade height side Dh1, and a gap exists between the outer peripheral plate portion 91 and the first channel defining surface 81p of the blade body 51 defining the first blade air passage 81. The flange portion 94 is connected to the edge of the first opening 82f of the first blade air passage 81 in such a way as to close the gap between the outer peripheral plate portion 91 and the first channel defining surface 81p. The gap between the outer peripheral side of the outer peripheral plate portion 91 of the first insert 90 and the first channel defining surface 81p forms the first cavity C1 inside the blade into which cooling air Ac flows in.

[0070] In the outer peripheral plate portion 91 of the first insert 90, a plurality of impact holes 92 are formed in the portion opposite to the first leaf portion 55f on the positive pressure side and the portion opposite to the first leaf portion 54f on the negative pressure side, extending from the inner side to the outer side of the outer peripheral plate portion 91.

[0071] The outer peripheral plate portion 96 of the second insert 95 is disposed within the second blade air passage 85 such that its cylinder height opening side Dih2 faces the blade height second side Dh2, and a gap exists between the outer peripheral plate portion 96 and the second channel defining surface 85p of the blade body 51 defining the second blade air passage 85. The flange portion 99 is connected to the edge of the opening 86 of the second blade air passage 85 in such a way as to close the gap between the outer peripheral plate portion 96 and the second channel defining surface 85p. The gap between the outer peripheral side of the outer peripheral plate portion 96 of the second insert 95 and the second channel defining surface 85p forms a second cavity C2 within the blade into which cooling air Ac flows.

[0072] In the outer peripheral plate portion 96 of the second insert 95, a plurality of impact holes 97 are formed in the portion opposite to the second leaf portion 55s on the positive pressure side and the portion opposite to the second leaf portion 54s on the negative pressure side, extending from the inner side to the outer side of the outer peripheral plate portion 96.

[0073] The second blade sections 54s and 55s are located further downstream of the axis than the first blade sections 54f and 55f. Therefore, the positions of the second blade sections 54s and 55s result in the pressure on the outer side of the blade body 51 and along the second blade sections 54s and 55s being lower than the pressure on the outer side of the blade body 51 and along the first blade sections 54f and 55f during the operation of the gas turbine 10.

[0074] The end cover 100 has a top plate portion 101 and an outer peripheral plate portion 102. The outer peripheral plate portion 102 extends along the edge of the top plate portion 101 in a direction substantially perpendicular to the top plate portion 101. The end cover 100 is disposed on the second side Dh2 of the blade height of the blade body 51. The top plate portion 101 is spaced apart from the region where the first blade air passage 81 and the second air passage are disposed in the blade height direction Dh in the gas path opposite surface 65 of the outer shroud 60o. The outer peripheral plate portion 102 of the end cover 100 is connected to the edge of the region where the first blade air passage 81 and the second air passage are located in the gas path opposite surface 65 of the outer shroud 60o. Therefore, the end cover 100 can guide the cooling air Ac flowing out from the second opening 82s of the first blade air passage 81 into the second blade air passage 85 from the opening 86 of the second blade air passage 85.

[0075] like Figure 6 As shown, each of the plurality of first guide members 110 includes a first groove member 111 having a first groove 112 extending along the cylinder height direction Dih and a first protruding member 113 entering the first groove 112 and movable relative to the first groove 112 along the cylinder height direction Dih. The plurality of first groove members 111 are fixed to the first channel defining surface 81p at intervals in the circumferential direction of the first channel defining surface 81p (see reference). Figure 4 and Figure 5 The plurality of first protruding members 113 are respectively configured to enter any one of the first grooves 112 of each of the plurality of first groove members 111, and are fixed to the outer peripheral plate portion 91 of the first insert 90. Therefore, the first guide member 110 allows the first insert 90 to be displaced in the cylinder height direction Dih, and restricts the displacement of the first insert 90 in a direction perpendicular to the cylinder height direction Dih.

[0076] like Figure 6 As shown, the second guide member 115 includes a second groove member 116 having a second groove 117 extending along the cylinder height direction Dih, and a second protrusion member 118 entering the second groove 117 and movable relative to the second groove 117 along the cylinder height direction Dih. The second groove member 116 is fixed in the second channel defining surface 85p to the bottom surface of the surface defining the first side Dh1 of the blade height of the second blade air channel 85 (see reference). Figure 4 The second protruding member 118 is configured to enter the second groove 117 of the second groove member 116 and is fixed to the sealing plate portion 98 of the second insert 95. Therefore, the second guide member 115 allows the second insert 95 to be displaced in the cylinder height direction Dih and restricts the displacement of the second insert 95 in a direction perpendicular to the cylinder height direction Dih.

[0077] Cooling air Ac flows into the cavity 72 of the outer shroud 60o from the radially outer side (Dro). Similarly, cooling air Ac flows into the cavity 72 of the inner shroud 60i from the radially inner side (Dri). For example, compressed air via the compressor 20 can be used as the cooling air Ac.

[0078] Cooling air Ac flows into the cavity 72 of the outer shield 60o, cooling the outer shield 60o. This cooling air Ac particularly cools the gas path surface of the outer shield 60o.

[0079] A portion of the cooling air Ac flowing into the cavity 72 of the outer shroud 60o flows into the front blade air passage 80f from the opening 80fo. This cooling air Ac convectively cools the portion surrounding the front blade air passage 80f within the blade body 51. Furthermore, this cooling air Ac is ejected from multiple front nozzles 80fa towards the upstream side Dau of the axis into the combustion gas flow path 49. As the cooling air Ac flows through the multiple front nozzles 80fa, it convectively cools the portion surrounding the multiple front nozzles 80fa. A portion of the cooling air Ac ejected into the combustion gas flow path 49 prevents the front portion of the blade surface, including the leading edge 52, from being exposed to the combustion gas G, and prevents the front portion of the blade surface from being heated by the combustion gas G.

[0080] Another portion of the cooling air Ac flowing into the cavity 72 of the outer shroud 60o flows into the rear blade air passage 80b from the opening 80bo. This cooling air Ac convectively cools the portion around the rear blade air passage 80b in the blade body 51. Furthermore, this cooling air Ac is ejected from multiple rear exhaust holes 80ba toward the downstream side Dad of the axis into the combustion gas flow path 49. As the cooling air Ac flows through the multiple rear exhaust holes 80ba, it convectively cools the portion around the multiple rear exhaust holes 80ba. A portion of the cooling air Ac ejected into the combustion gas flow path 49 prevents the rear portion of the blade surface, including the trailing edge 53, from being exposed to the combustion gas G, and prevents the rear portion of the blade surface from being heated by the combustion gas G. Moreover, a portion of the cooling air Ac ejected into the combustion gas flow path 49 prevents the formation of vortices in the downstream side Dad of the blade body 51.

[0081] Cooling air Ac flows into the cavity 72 of the inner shroud 60i, cooling the inner shroud 60i. This cooling air Ac particularly cools the gas path surface 64 of the inner shroud 60i.

[0082] Cooling air Ac flows into the cavity 72 of the inner shroud 60i from the first opening 82f of the first blade air passage 81 and the insert opening 90o of the first insert 90 into the outer peripheral plate portion 91 of the first insert 90. The cooling air Ac flowing into the outer peripheral plate portion 91 is ejected from the outer peripheral side of the outer peripheral plate portion 91 through a plurality of impact holes 92 formed therein and flows into the first cavity C1 inside the blade. This cooling air Ac collides with the portion of the first blade portion 55f that is back-to-back with the positive pressure side and the portion of the first blade portion 54f that is back-to-back with the negative pressure side in the first passage demarcation surface 81p, thus performing impact cooling on these portions. This impact cooling is more effective than convection cooling. The distance between the outlet of the cooling air Ac and the surface from which the cooling air Ac collides affects the cooling effect during impact cooling. Therefore, in this embodiment, a first guide 110 is provided that allows the first insert 90 to be displaced in the cylinder height direction Dih and restricts the displacement of the first insert 90 in a direction perpendicular to the cylinder height direction Dih.

[0083] In this embodiment, the first groove member 111 of the first guide member 110 is fixed to the first channel marking surface 81p, and the first protruding member 113 of the first guide member 110 is fixed to the outer peripheral plate portion 91 of the first insert member 90. However, it is also possible to fix the first groove member 111 to the outer peripheral plate portion 91 of the first insert member 90 and fix the first protruding member 113 to the first channel marking surface 81p. Furthermore, it is also possible to fix one of the first groove member 111 and the first protruding member 113 to the first insert member 90 and fix the other member to the end cover 100. However, the end cover 100 has lower rigidity than the blade body 51, so from the viewpoint of limiting the displacement of the first insert member 90 in the direction perpendicular to the cylinder height direction Dih, it is preferable to fix the other member to one side of the blade body 51.

[0084] A portion of the cooling air Ac flowing into the first cavity C1 within the blade is ejected from the multiple positive-pressure side first ejector holes 83pf and the multiple negative-pressure side first ejector holes 83nf into the combustion gas flow path 49. The cooling air Ac ejected from the multiple positive-pressure side first ejector holes 83pf primarily performs thin-film cooling on the downstream portion of the positive-pressure side first blade section 55f. Furthermore, the cooling air Ac ejected from the multiple negative-pressure side first ejector holes 83nf primarily performs thin-film cooling on the downstream portion of the negative-pressure side first blade section 54f.

[0085] The remaining portion of the cooling air Ac flowing into the first cavity C1 within the blade flows towards the second side of the blade height Dh2, i.e., the radially outer side Dro, within the first cavity C1, and flows out from the second opening 82s of the first blade air passage 81 and into the end cover 100. As the cooling air Ac flows through the first cavity C1 within the blade, it provides convective cooling to the area surrounding the first cavity C1 within the blade body 51.

[0086] Cooling air Ac flows into the end cover 100 from the opening 86 of the second blade air passage 85 and the insert opening 95o of the second insert 95 into the outer peripheral plate portion 96 of the second insert 95. The cooling air Ac flowing into the outer peripheral plate portion 96 is ejected from the multiple impact holes 97 formed in the outer peripheral plate portion 96 toward the outer peripheral side of the outer peripheral plate portion 96 and flows into the second cavity C2 inside the blade. The cooling air Ac collides with the portion of the second blade portion 55s that is back-to-back with the positive pressure side and the portion of the second blade portion 54s that is back-to-back with the negative pressure side in the second passage demarcation surface 85p, thereby performing impact cooling on these portions. As mentioned above, the distance between the outlet of the cooling air Ac and the surface that the cooling air Ac ejected from the outlet collides with affects the cooling effect during impact cooling. Therefore, in this embodiment, a first guide 110 is provided to allow the second insert 95 to displace in the cylinder height direction Dih and to limit the displacement of the second insert 95 in a direction perpendicular to the cylinder height direction Dih.

[0087] In this embodiment, the second groove member 116 of the second guide member 115 is fixed to the second channel marking surface 85p, and the second protruding member 118 of the second guide member 115 is fixed to the sealing plate portion 98 of the second insert member 95. However, it is also possible to fix the second groove member 116 to the sealing plate portion 98 of the second insert member 95 and fix the second protruding member 118 to the second channel marking surface 85p.

[0088] Cooling air Ac, flowing into the second cavity C2 within the blade, is ejected from multiple positive-pressure side second ejector holes 87ps and multiple negative-pressure side second ejector holes 87ns into the combustion gas flow path 49. The cooling air Ac ejected from the multiple positive-pressure side second ejector holes 87ps primarily provides thin-film cooling to the downstream portion of the positive-pressure side second blade section 55s. Furthermore, the cooling air Ac ejected from the multiple negative-pressure side second ejector holes 87ns primarily provides thin-film cooling to the downstream portion of the negative-pressure side second blade section 54s.

[0089] As described above, in this embodiment, the cooling air Ac flowing into the first insert 90 disposed within the first blade air passage 81 performs impingement cooling on the first passage demarcation surface 81p. Furthermore, a portion of this cooling air Ac performs film cooling on the downstream portion of the positive-pressure side first blade section 55f and the downstream portion of the negative-pressure side second blade section 54s, while the remaining portion, during its flow through the first cavity C1 within the blade body 51, performs convective cooling around the first cavity C1. In this embodiment, the remaining portion of the cooling air Ac flows into the second insert 95 disposed within the second blade air passage 85. The cooling air Ac flowing into the second insert 95 performs impingement cooling on the second passage demarcation surface 85p. Furthermore, this cooling air Ac performs film cooling on the downstream portion of the positive-pressure side second blade section 55s and the downstream portion of the negative-pressure side second blade section 54s. Therefore, in this embodiment, compared to the case where the blade body is subjected to impact cooling by cooling air Ac flowing into an insert and then immediately ejected into the combustion gas flow path, the stationary blade 50 can be cooled effectively, thereby reducing the amount of cooling air Ac used.

[0090] "Second Embodiment of the Stationary Blade"

[0091] The following is for reference. Figure 7 and Figure 8 A second embodiment of the stationary blade according to the present invention will be described. Furthermore, Figure 7 It is a cross-sectional view on a plane perpendicular to the axis Ar of the stationary blade. Furthermore, Figure 8 yes Figure 7 Sectional view along line VIII-VIII.

[0092] like Figure 7 As shown, the stationary blade 50a of this embodiment also has a blade body 51a, an inner shield 60i, and an outer shield 60o. The inner shield 60i and outer shield 60o of this embodiment are the same as those of the inner shield 60i and outer shield 60o of the first embodiment.

[0093] like Figure 7 and Figure 8As shown, similar to the blade body 51 of the first embodiment, a plurality of blade air channels 80 are also formed in the blade body 51a of this embodiment. Among the plurality of blade air channels 80, the blade air channel 80 furthest upstream on the axis (Dau) constitutes the front blade air channel 80f, and the blade air channel 80 furthest downstream on the axis (Dad) constitutes the rear blade air channel 80b. The structure of the front blade air channel 80f is the same as that of the front blade air channel 80f in the first embodiment. Furthermore, the structure of the rear blade air channel 80b is the same as that of the rear blade air channel 80b in the first embodiment. Moreover, among the plurality of blade air channels 80, the two blade air channels 80 between the front blade air channel 80f and the rear blade air channel 80b constitute the intermediate blade air channel 80ma. The two intermediate blade air channels 80ma differ from the two intermediate blade air channels 80m in the first embodiment and are arranged circumferentially (Dc). Here, in the two intermediate blade air passages 80ma, the intermediate blade air passage 80ma on the circumferential positive pressure side Dcp is designated as the first blade air passage 81a, and the intermediate blade air passage 80ma on the circumferential negative pressure side Dcn is designated as the second blade air passage 85a.

[0094] In the first blade air passage 81a, the ends of the first blade height side Dh1 (radially inward Dri) and the second blade height side Dh2 (radially outward Dro) are open. The opening of the first blade air passage 81a at the radially inward Dri, i.e., the first opening 82f, opens on the opposite side 65 of the gas path of the inner shroud 60i. Furthermore, the opening of the first blade air passage 81a at the radially outward Dro, i.e., the second opening 82s, opens on the opposite side 65 of the gas path of the outer shroud 60o. In the blade body 51a, a plurality of positive pressure side first ejection holes 83pf are formed, extending from the first channel defining surface 81p of the first blade air passage 81a that defines the blade body 51a to a portion of the positive pressure surface 55, i.e., the positive pressure side first blade portion 55f. Additionally, the positive pressure side first blade portion 55f is a portion of the positive pressure surface 55 of the blade body 51a that is back-to-back with the first blade air passage 81a.

[0095] In the second blade air passage 85a, the end on the first side of blade height Dh1 (radially inward Dri) is closed, while the end on the second side of blade height Dh2 (radially outward Dro) is open. The opening 86 of the second blade air passage 85a opens on the opposite side 65 of the gas path of the outer shroud 60o. Multiple negative pressure side second ejection holes 87ns are formed in the blade body 51a, extending from the second channel defining surface 85p of the second blade air passage 85a that defines the blade body 51a to a portion of the negative pressure surface 54, namely the negative pressure side second blade section 54s. Furthermore, the negative pressure side second blade section 54s is a portion of the negative pressure surface 54 of the blade body 51a that is back-to-back with the second blade air passage 85a.

[0096] In the embodiment, the first blade air passage 81a and the second blade air passage 85a are both end openings on the second side of the blade height Dh2, i.e., the radially outer side Dro.

[0097] The stationary blade 50a of this embodiment also includes a first insert 90a, a second insert 95a, an end cover 100a, a plurality of first guides 110 and second guides 115.

[0098] The first insert 90a is disposed within the first blade air passage 81a, and the second insert 95a is disposed within the second blade air passage 85a. Similar to the first insert 90 in the first embodiment, the first insert 90a has an outer peripheral plate portion 91, a sealing plate portion 93, and a flange portion 94. Similarly to the second insert 95 in the first embodiment, the second insert 95a has an outer peripheral plate portion 96, a sealing plate portion 98, and a flange portion 99. The outer peripheral plate portions 91 and 96 of the first insert 90a and the second insert 95a are cylindrical and extend along the cylinder height direction Dih. The sealing plate portions 93 and 98 close the cylinder height sealing side Dih1 end of the outer peripheral plate portions 91 and 96. On the other hand, no sealing plate portion is provided at the cylinder height opening side Dih2 end of the outer peripheral plate portions 91 and 96. Therefore, at the end of the cylinder height opening side Dih2 of the outer peripheral plate portions 91 and 96, an insert opening 90° and 95° are formed to guide cooling air Ac into the outer peripheral plate portions 91 and 96. The flange portions 94 and 99 extend outward from the end of the cylinder height opening side Dih2 in the entire outer peripheral surface of the outer peripheral plate portions 91 and 96 toward the outer peripheral side.

[0099] The outer peripheral plate portion 91 of the first insert 90a is disposed within the first blade air passage 81a such that the cylinder height opening side Dih2 faces the first blade height side Dhl, and a gap exists between the outer peripheral plate portion 91 and the first channel defining surface 81p of the blade body 51a defining the first blade air passage 81a. The flange portion 94 is connected to the edge of the first opening 82f of the first blade air passage 81a in such a way as to close the gap between the outer peripheral plate portion 91 and the first channel defining surface 81p. The gap between the outer peripheral side of the outer peripheral plate portion 91 of the first insert 90a and the first channel defining surface 81p forms the first cavity C1 inside the blade into which cooling air Ac flows in.

[0100] In the outer peripheral plate portion 91 of the first insert 90a, a plurality of impact holes 92 are formed in the portion opposite to the first leaf portion 55f on the positive pressure side, extending from the inner side to the outer side of the outer peripheral plate portion 91.

[0101] The outer peripheral plate portion 96 of the second insert 95a is disposed within the second blade air passage 85a such that the cylinder height opening side Dih2 faces the blade height second side Dh2, and a gap exists between its outer peripheral plate portions 91, 96 and the second passage defining surface 85p of the blade body 51a defining the second blade air passage 85a. Flange portions 94, 99 are connected to the edge of the opening of the second blade air passage 85a in such a way that they close the gap between the outer peripheral plate portions 91, 96 and the second passage defining surface 85p. A second cavity C2 within the blade into which cooling air Ac flows is formed in the gap between the outer peripheral sides of the outer peripheral plate portions 91, 96 of the second insert 95a and the second passage defining surface 85p.

[0102] In the outer peripheral plate portion 96 of the second insert 95a, a plurality of impact holes 97 are formed in the portion opposite to the second leaf portion 54s on the negative pressure side, extending from the inner side to the outer side of the outer peripheral plate portion 96.

[0103] The second blade section 54s is part of the negative pressure surface 54, and the first blade section 55f is part of the positive pressure surface 55. Therefore, the position of the second blade section 54s is such that during the driving of the gas turbine 10, the pressure on the outer side of the blade body 51a and along the portion of the second blade section 54s is lower than the pressure on the outer side of the blade body 51a and along the portion of the first blade section 55f.

[0104] Similar to the end cover 100 of the first embodiment, the end cover 100a has a top plate portion 101a and an outer peripheral plate portion 102. However, in this embodiment, the arrangement direction of the second blade air passage 85a relative to the first blade air passage 81a is different from that of the first embodiment, therefore the shape of the top plate portion 101a is different from the shape of the top plate portion 101 in the first embodiment. Similar to the end cover 100 of the first embodiment, this end cover 100a can also guide the cooling air Ac flowing out from the second opening 82s of the first blade air passage 81a into the second blade air passage 85a from the opening 86.

[0105] The first guide member 110 is the same as the first guide member 110 in the first embodiment. Furthermore, the second guide member 115 is the same as the second guide member 115 in the first embodiment.

[0106] The flow of cooling air Ac in this embodiment is the same as that in the first embodiment. Therefore, in this embodiment, the cooling air Ac flowing into the first insert 90a disposed in the first blade air passage 81a performs impact cooling on the first passage demarcation surface 81p. Furthermore, a portion of this cooling air Ac performs film cooling on the downstream portion of the positive pressure side first blade section 55f, and the remaining portion, while flowing through the first cavity C1 within the blade, performs convective cooling around the first cavity C1 within the blade body 51a. This remaining portion of cooling air Ac flows into the second insert 95a disposed in the second blade air passage 85a. The cooling air Ac flowing into the second insert 95a performs impact cooling on the second passage demarcation surface 85p. Furthermore, this cooling air Ac performs film cooling on the downstream portion of the negative pressure side second blade section 54s. Therefore, in this embodiment, compared to the case where the blade body is subjected to impact cooling by cooling air Ac flowing into an insert and then immediately ejected into the combustion gas flow path, the stationary blade 50a can be cooled effectively, thereby reducing the amount of cooling air Ac used.

[0107] As described above, in the first embodiment, the second blade air passage can be configured on the downstream side Dad of the first blade air passage 81, and in this embodiment, it can also be configured on the circumferential negative pressure side Dcn of the first blade air passage 81a.

[0108] "The first variation of the stationary blade"

[0109] The following is for reference. Figure 9 A first variation of the first embodiment of the stationary blade according to the present invention will be described.

[0110] Compared with the stationary blade 50 of the first embodiment, the stationary blade 50b of this modified example has different shapes and installation methods of the first insert 90b and the second insert 95b, but the other structures are the same.

[0111] The first insert 90b of this modified example has an outer peripheral plate portion 91, a sealing plate portion 93, and a flange portion 94b. The outer peripheral plate portion 91 is cylindrical and extends along the cylindrical height direction Dih. The sealing plate portion 93 closes the cylindrical height sealing side Dih1 end of the outer peripheral plate portion 91. On the other hand, no sealing plate portion is provided at the cylindrical height opening side Dih2 end of the outer peripheral plate portion 91. Therefore, an insert opening 90o for guiding cooling air Ac into the outer peripheral plate portion 91 is formed at the cylindrical height opening side Dih2 end of the outer peripheral plate portion 91. The flange portion 94b differs from the flange portion 94 of the first insert 90 in the first embodiment, extending from a portion of the cylindrical height sealing side Dih1 end of the outer peripheral surface of the outer peripheral plate portion 91 toward the outer peripheral side. Therefore, the flange portion 94b of the first insert 90b has a partially cut-out shape.

[0112] The outer peripheral plate portion 91 of the first insert 90b is disposed within the first blade air passage 81 such that the cylinder height opening side Dih2 faces the blade height first side Dh1, and there is a gap between the outer peripheral plate portion 91 and the first channel defining surface 81p. The outer edge of the flange portion 94b is connected near the second opening 82s of the first blade air passage 81. Therefore, the first insert 90b of this modified example differs from the first insert 90 in the first embodiment, with the cylinder height sealing side Dih1 fixed to the blade body 51. A sealing flange 84 is provided at the edge of the first opening 82f of the first blade air passage 81, protruding toward the center side of the first blade air passage 81 and opposing the outer peripheral plate portion 91 of the first insert 90b. This sealing flange 84 serves to prevent the cooling air Ac flowing into the cavity 72 of the inner shroud 60i from flowing into the first cavity C1 inside the blade in the first blade air passage 81. In addition, the sealing flange 84 allows the first insert 90b to be displaced in the blade height direction Dh, and therefore is not fixed to the outer peripheral plate portion 91 of the first insert 90b.

[0113] Similar to the outer peripheral plate portion 91 of the first insert 90 in the first embodiment, a plurality of impact holes 92 are formed in the portion of the outer peripheral plate portion 91 of the first insert 90b that faces the positive pressure side first leaf portion 55f and the portion that faces the negative pressure side first leaf portion 54f, extending from the inner side to the outer side of the outer peripheral plate portion 91.

[0114] The second insert 95b in this modified example has an outer peripheral plate portion 96 and a sealing plate portion 98, but no flange portion. The outer peripheral plate portion 96 is cylindrical and extends along the cylinder height direction Dih. The sealing plate portion 98 closes the cylinder height sealing side Dih1 end of the outer peripheral plate portion 96. On the other hand, no sealing plate portion is provided at the cylinder height opening side Dih2 end of the outer peripheral plate portion 96. Therefore, an insert opening 95o for guiding cooling air Ac into the outer peripheral plate portion 96 is formed at the cylinder height opening side Dih2 end of the outer peripheral plate portion 96.

[0115] The outer peripheral plate portion 96 of the second insert 95b is disposed within the second blade air passage 85 such that the cylinder height opening side Dih2 faces the blade height second side Dh2, and there is a gap between the outer peripheral plate portion 96 and the second channel defining surface 85p. The sealing plate portion 98 of the second insert 95b is fixed in the second channel defining surface 85p to the surface of the second blade air passage 85 on the blade height first side Dh1, i.e., the bottom surface. Therefore, the second insert 95b in this modified example differs from the second insert 95 in the first embodiment in that the cylinder height sealing side Dih1 is fixed to the blade body 51. A sealing flange 88 is provided at the edge of the opening 86 of the second blade air passage 85, protruding toward the center side of the second blade air passage 85 and opposing the outer peripheral plate portion 96 of the second insert 95b. This sealing flange 88 serves to prevent the cooling air Ac in the end cover 100 from flowing into the second cavity C2 inside the blade in the second blade air passage 85. In addition, the sealing flange 88 allows the second insert 95b to be displaced in the blade height direction Dh, and therefore is not fixed to the outer peripheral plate portion 96 of the second insert 95b.

[0116] Similar to the outer peripheral plate portion 96 of the first insert 90 in the first embodiment, a plurality of impact holes 97 are formed in the portion of the outer peripheral plate portion 96 of the second insert 95b that faces the positive pressure side second leaf portion 55s and the portion that faces the negative pressure side second leaf portion 54s, extending from the inside to the outside of the outer peripheral plate portion 96.

[0117] In this modified example, cooling air Ac flows into the cavity 72 of the outer shield 60o from the radially outer side Dro. Furthermore, cooling air Ac flows into the cavity 72 of the inner shield 60i from the radially inner side Dri.

[0118] Similar to the first embodiment, a portion of the cooling air Ac flowing into the cavity 72 of the outer shroud 60o flows into the front blade air passage 80f from the opening 80fo. Similarly, also similar to the first embodiment, another portion of the cooling air Ac flowing into the cavity 72 of the outer shroud 60o flows into the rear blade air passage 80b from the opening 80bo.

[0119] Most of the cooling air Ac flowing into the cavity 72 of the inner shroud 60i flows into the outer peripheral plate portion 91 of the first insert 90b from the first opening 82f of the first blade air passage 81 and the insert opening 90o of the first insert 90b. However, a small portion of the cooling air Ac flowing into the cavity 72 of the inner shroud 60i flows into the first blade cavity C1 within the first blade air passage 81 from the gap between the sealing flange 84 located at the edge of the first opening 82f of the first blade air passage 81 and the outer peripheral plate portion 91 of the first insert 90b. The cooling air Ac flowing into the outer peripheral plate portion 91 is ejected from the plurality of impact holes 92 formed in the outer peripheral plate portion 91 toward the outer peripheral side of the outer peripheral plate portion 91 and flows into the first blade cavity C1. The cooling air Ac collides with the portion of the first blade section 55f on the positive pressure side and the portion of the first blade section 54f on the negative pressure side in the first channel demarcation surface 81p, thereby subjecting these parts to impact cooling.

[0120] A portion of the cooling air Ac flowing into the first cavity C1 inside the blade is ejected from the multiple positive pressure side first ejection holes 83pf and the multiple negative pressure side first ejection holes 83nf into the combustion gas flow path 49. The remaining portion of the cooling air Ac flowing into the first cavity C1 inside the blade flows within the first cavity C1 to the second side of the blade height Dh2, i.e., the radially outer side Dro, and flows into the end cover 100 through the cut portion of the flange 94b of the first insert 90b and the second opening 82s of the first blade air passage 81.

[0121] Most of the cooling air Ac flowing into the end cap 100 flows into the outer peripheral plate portion 96 of the second insert 95b from the opening 86 of the second blade air passage 85 and the insert opening 95o of the second insert 95b. However, a small portion of the cooling air Ac flowing into the end cap 100 flows into the second cavity C2 within the blade of the second blade air passage 85 from the gap between the sealing flange 88 at the edge of the opening 86 of the second blade air passage 85 and the outer peripheral plate portion 96 of the second insert 95b. The cooling air Ac flowing into the outer peripheral plate portion 96 is ejected from the multiple impact holes 97 formed in the outer peripheral plate portion 96 toward the outer peripheral side of the outer peripheral plate portion 96 and flows into the second cavity C2 within the blade. This cooling air Ac impacts and cools the portions that are back-to-back with the positive pressure side second blade portion 55s and the portions that are back-to-back with the negative pressure side second blade portion 54s by colliding with the second passage demarcation surface 85p.

[0122] Cooling air Ac flows into the second cavity C2 inside the blade and is ejected from multiple positive pressure side second ejection holes 87ps and multiple negative pressure side second ejection holes 87ns into the combustion gas flow path 49.

[0123] In this modified example, similarly to the first embodiment, cooling air Ac flowing into the first insert 90b disposed within the first blade air passage 81 impinges and cools the first passage marking surface 81p. Furthermore, a portion of this cooling air Ac flows into the second insert 95b and impinges and cools the second passage marking surface 85p. Therefore, in this modified example, similarly to the first embodiment, compared to the case where cooling air Ac flowing into one insert impinges and cools the blade body before immediately being ejected into the combustion gas flow path, the stationary blade 50b can be cooled more effectively, thus reducing the amount of cooling air Ac used.

[0124] However, in this modified example, a portion of the cooling air Ac flowing into the cavity 72 of the inner shroud 60i does not provide impact cooling to the first channel defining surface 81p. As mentioned above, it flows into the first cavity C1 inside the blade from the gap between the sealing flange 84 at the edge of the first opening 82f of the first blade air passage 81 and the outer peripheral plate portion 91 of the first insert 90b. Furthermore, in this modified example, a portion of the cooling air Ac flowing into the end cover 100 does not provide impact cooling to the second channel defining surface 85p. As mentioned above, it flows into the second cavity C2 inside the blade from the gap between the sealing flange 88 at the edge of the opening 86 of the second blade air passage 85 and the outer peripheral plate portion 96 of the second insert 95b. Therefore, the impact cooling effect of the blade body 51 in this modified example is lower than that in the first embodiment. In other words, the impact cooling effect of the blade body 51 in the first embodiment is higher than that in this modified example.

[0125] As described above, in the first insert 90b and the second insert 95b, as in the first embodiment, the cylinder height opening side Dih2 can be fixed to the blade body 51, and as in this modified example, the cylinder height sealing side Dih1 can be fixed to the blade body 51.

[0126] Furthermore, this modified example is a modification of the first embodiment, but the second embodiment may also have the same structure as this modified example.

[0127] "The second variation of the stationary blade"

[0128] The following is for reference. Figure 10 A second variation of the first embodiment of the stationary blade according to the present invention will be described.

[0129] Compared to the stationary blade 50 of the first embodiment, the stationary blade 50c of this modified example differs in the arrangement of the openings of the first blade air passage 81c and the second blade air passage 85c, as well as the end cover 100c. Furthermore, compared to the stationary blade 50 of the first embodiment, the stationary blade 50c of this modified example differs in the shape and mounting method of the first insert 90c and the mounting method of the second insert 95c, while other structural features remain the same.

[0130] Similar to the first embodiment, both the first blade air passage 81c and the second blade air passage 85c in this modified example extend along the blade height direction Dh. However, in the first blade air passage 81c of this modified example, the end at the first blade height side Dh1 (i.e., the radially inner side Dri) is open, while the end at the second blade height side Dh2 (i.e., the radially outer side Dro) is closed. The opening 82f of the radially inner side Dri of the first blade air passage 81c opens on the gas path opposite surface 65 of the inner shroud 60i. Similarly, in the second blade air passage 85c, the end at the first blade height side Dh1 (i.e., the radially inner side Dri) is open, while the end at the second blade height side Dh2 (i.e., the radially outer side Dro) is closed. The opening 86c of the second blade air passage 85c opens on the gas path opposite surface 65 of the inner shroud 60i.

[0131] As described above, in this modified example, the first blade air passage 81c and the second blade air passage 85c are both end openings on the first side Dh1 of the blade height, i.e., the radially inner side Dri.

[0132] The first insert 90c of this modified example has an outer peripheral plate portion 91, a sealing plate portion 93, and a flange portion 94c. The outer peripheral plate portion 91 is cylindrical and extends along the cylinder height direction Dih. The sealing plate portion 93 closes the cylinder height sealing side Dih1 end of the outer peripheral plate portion 91. On the other hand, no sealing plate portion is provided at the cylinder height opening side Dih2 end of the outer peripheral plate portion 91. Therefore, an insert opening 90o for guiding cooling air Ac into the outer peripheral plate portion 91 is formed at the cylinder height opening side Dih2 end of the outer peripheral plate portion 91. The flange portion 94c differs from the flange portion 94 of the first insert 90 in the first embodiment, extending outward from a position on the outer peripheral surface of the outer peripheral plate portion 91 and separated from the cylinder height opening side Dih2 end of the outer peripheral plate portion 91 by a predetermined distance towards the cylinder height sealing side Dih1. Therefore, the flange portion 94c of the first insert 90c has a partially cut shape. In addition, the distance is specified to be greater than the height of the outer peripheral plate portion 103 of the end cover 100.

[0133] The outer peripheral plate portion 91 of the first insert 90c is disposed within the first blade air passage 81c such that the cylinder height opening side Dih2 faces the first blade height side Dhl, and there is a gap between the outer peripheral plate portion 91 and the first channel defining surface 81p. The flange portion 94c is connected to the edge of the first opening 82f of the first blade air passage 81c.

[0134] Similar to the second insert 95 of the first embodiment, the second insert 95c of this modified example has an outer peripheral plate portion 96, a sealing plate portion 98, and a flange portion 99. However, unlike the first embodiment, the outer peripheral plate portion 96 of the second insert 95c of this modified example faces the first blade height portion Dh1 from the cylinder height opening side Dih2, and is disposed within the second blade air passage 85c with a gap between the outer peripheral plate portion 96 and the second channel defining surface 85p of the blade body 51 that defines the second blade air passage 85c. The flange portion 99 is connected to the edge of the opening 86c of the second blade air passage 85c in a manner that closes the gap between the outer peripheral plate portion 96 and the second channel defining surface 85p.

[0135] Similar to the end cover 100 of the first embodiment, the end cover 100c has a top plate portion 101 and an outer peripheral plate portion 102. However, in this modified example, the end cover 100c is disposed on the first blade height side Dh1 of the blade body 51. The top plate portion 101 of the end cover 100c is positioned at a distance from the region where the first blade air passage 81c and the second blade air passage 85c are disposed in the blade height direction Dh in the gas path opposite surface 65 of the inner shield 60i. The outer peripheral plate portion 102 of the end cover 100c is connected to the edge of the region where the first blade air passage 81c and the second blade air passage 85c are located in the gas path opposite surface 65 of the inner shield 60i. The cylinder height opening side Dih2 of the outer peripheral plate portion 91 in the first insert 90c protrudes radially inward from the top plate portion 101 of the end cover 100c.

[0136] In this modified example, cooling air Ac flows into the cavity 72 of the outer shield 60o from the radially outer side Dro. Furthermore, cooling air Ac flows into the cavity 72 of the inner shield 60i from the radially inner side Dri.

[0137] Similar to the first embodiment, a portion of the cooling air Ac flowing into the cavity 72 of the outer shroud 60o flows into the front blade air passage 80f from the opening 80fo. Similarly, also similar to the first embodiment, another portion of the cooling air Ac flowing into the cavity 72 of the outer shroud 60o flows into the rear blade air passage 80b from the opening 80bo.

[0138] Cooling air Ac flows into the cavity 72 of the inner shroud 60i from the insert opening 90o of the first insert 90c into the outer peripheral plate portion 91 of the first insert 90c. The cooling air Ac flowing into the outer peripheral plate portion 91 is ejected from the multiple impact holes 92 formed in the outer peripheral plate portion 91 toward the outer peripheral side of the outer peripheral plate portion 91 and flows into the first cavity C1 inside the blade. This cooling air Ac collides with the first channel demarcation surface 81p and is subjected to impact cooling.

[0139] A portion of the cooling air Ac flowing into the first cavity C1 inside the blade is ejected from the multiple positive pressure side first ejection holes 83pf and the multiple negative pressure side first ejection holes 83nf into the combustion gas flow path 49. The remaining portion of the cooling air Ac flowing into the first cavity C1 inside the blade flows within the first cavity C1 inside the blade toward the first side of the blade height Dh1, i.e., the radially inner side Dri, and flows into the end cover 100c through the cut portion of the flange 94c of the first insert 90c and the opening 82f of the first blade air passage 81c.

[0140] Cooling air Ac flows into the end cap 100c from the opening 86c of the second blade air passage 85c and the insert opening 95o of the second insert 95c into the outer peripheral plate portion 96 of the second insert 95c. The cooling air Ac flowing into the outer peripheral plate portion 96 is ejected from the multiple impact holes 97 formed in the outer peripheral plate portion 96 toward the outer peripheral side of the outer peripheral plate portion 96 and flows into the second cavity C2 inside the blade. This cooling air Ac collides with the second passage demarcation surface 85p and performs impact cooling on it.

[0141] Cooling air Ac flows into the second cavity C2 inside the blade and is ejected from multiple positive pressure side second ejection holes 87ps and multiple negative pressure side second ejection holes 87ns into the combustion gas flow path 49.

[0142] In this modified example, similarly to the first embodiment, cooling air Ac flowing into the first insert 90c disposed within the first blade air passage 81c impinges and cools the first passage defining surface 81p. Furthermore, a portion of this cooling air Ac flows into the second insert 95c and impinges and cools the second passage defining surface 85p. Therefore, in this modified example, similarly to the first embodiment, compared to the case where cooling air Ac flowing into one insert impinges and cools the blade body before immediately being ejected into the combustion gas flow path, the stationary blade 50c can be cooled more effectively, thus reducing the amount of cooling air Ac used.

[0143] However, in this modified example, the cooling air Ac flowing into the first insert 90c flows through the first insert 90c past the second side of the blade height Dh2 and is ejected from the impact hole 92. Then, it flows through the first cavity C1 inside the blade to the first side of the blade height Dh1 and then flows into the second insert 95c. Therefore, in this modified example, the cooling air Ac oscillates along the blade height direction Dh in the first blade air passage 81c, resulting in a longer flow path length for the cooling air Ac and a greater flow path resistance. As a result, in this modified example, the pressure of the cooling air Ac flowing into the second insert 95c is reduced. Therefore, the impact cooling effect of the blade body 51c in this modified example is lower than that in the first embodiment. In other words, the impact cooling effect of the blade body 51 in the first embodiment is higher than that in this modified example.

[0144] As described above, in the first embodiment, the opening side of the first blade air passage and the second blade air passage in the first blade height side Dh1 and the second blade height side Dh2 can be the second blade height side Dh2, and in this modified embodiment, it can be the first blade height side Dh1. Furthermore, in the first embodiment, the cylinder height opening side Dih of the second insert can face the second blade height side Dh2, and in this modified embodiment, it can face the first blade height side Dh1.

[0145] Furthermore, this modified example is a modification of the first embodiment, but the second embodiment may also be configured with the same structure as this modified example.

[0146] "The third variation of the stationary blade"

[0147] The following is for reference. Figure 11 A third variation of the first embodiment of the stationary blade according to the present invention will be described.

[0148] In this modified example, the stationary blade 50d is a stationary blade in which an impact plate 78 is added to both the outer shield 60o and the inner shield 60i of the stationary blade 50 in the first embodiment.

[0149] The impact plate 78 inside the outer shroud 60° divides the cavity 72 of the outer shroud 60° into two spaces along the blade height direction Dh. Multiple impact holes 79 are formed in the impact plate 78, extending along the blade height direction Dh.

[0150] The impact plate 78 inside the inner shroud 60i divides the cavity 72 of the inner shroud 60i into two spaces along the blade height direction Dh. Multiple impact holes 79 are formed in the impact plate 78, extending along the blade height direction Dh.

[0151] Cooling air Ac flowing into the cavity 72 of the outer shroud 60o is ejected from the plurality of impact holes 79 of the impact plate 78 and collides with the gas path opposite surface 65 of the outer shroud 60o, thus subjecting it to impact cooling. Similar to the first embodiment, a portion of the cooling air Ac impact-cooling the gas path opposite surface 65 flows into the front blade air passage 80f from the opening 80fo. And, similar to the first embodiment, another portion of the cooling air Ac impact-cooling the gas path opposite surface 65 flows into the rear blade air passage 80b from the opening 80bo.

[0152] Cooling air Ac flowing into the cavity 72 of the inner shroud 60i is ejected from the plurality of impact holes 79 of the impact plate 78 and collides with the gas path opposite surface 65 of the inner shroud 60i, thus subjecting it to impact cooling. Similar to the first embodiment, a portion of the cooling air Ac that impact-cools the gas path opposite surface 65 flows into the first insert 90. Also similar to the first embodiment, the cooling air Ac flowing into the first insert 90 impact-cools the first channel demarcation surface 81p, and then impact-cools the second channel demarcation surface 85p.

[0153] As described above, in this modified example, the cooling air Ac flowing into the cavity 72 of the inner shroud 60i can perform triple impact cooling on the interior of the stationary blade 50d. Therefore, in this modified example, compared with the first embodiment or its various modifications, the stationary blade 50d can be cooled more effectively while reducing the amount of cooling air Ac used.

[0154] Furthermore, this modified example is a modification of the first embodiment, but similarly to this modified example, an impact plate 78 may be added to the second embodiment, the first modified example, and the second modified example.

[0155] Other variations of the stationary blade

[0156] In the above embodiments and modifications, the first side of the blade height, Dh1, is the radially inner side, Dri, and the second side of the blade height, Dh2, is the radially outer side, Dro. However, it is permissible for the first side of the blade height, Dhl, to be the radially outer side, Dro, and the second side of the blade height, Dh2, to be the radially inner side, Dri.

[0157] The stationary blades in the above embodiments and modifications have two blade air passages serving as intermediate blade air passages 80m, with one designated as the first blade air passage and the other as the second blade air passage. However, the stationary blade may have three or more blade air passages serving as intermediate blade air passages 80m, with one designated as the first blade air passage and the other as the second blade air passage. Furthermore, the first and second blade air passages need not be passages between the front blade air passage 80f and the rear blade air passage 80b. For example, the first blade air passage may be one of the intermediate blade air passages 80m, and the second blade air passage may be the rear blade air passage 80b.

[0158] In all the above embodiments and variations, the stationary blades are stationary blades constituting the primary stationary blade row 46. However, the stationary blades may be stationary blades constituting a stationary blade row that is located further downstream of the axis than the primary stationary blade row 46.

[0159] The embodiments and modifications of the present invention have been described in detail above, but the present invention is not limited to the above embodiments and modifications. Various additions, modifications, substitutions, and partial deletions can be made without departing from the conceptual idea and spirit of the present invention derived from the content specified in the technical solutions and their equivalents.

[0160] Postscript

[0161] The stationary blades in the above embodiments and variations can be understood as follows.

[0162] (1) In the first method, the stationary blades are installed on the gas turbine 10.

[0163] The stationary blade includes: blade bodies 51, 51a, and 51c, with a leaf-shaped cross-section extending along a blade height direction Dh having a directional component perpendicular to the cross-section; first inserts 90, 90a, 90b, and 90c, and second inserts 95, 95a, 95b, and 95c, which are cylindrical, extend along a cylindrical height direction Dih, and are disposed within the blade bodies 51, 51a, and 51c such that the cylindrical height direction Dih faces the blade height direction Dh; and end caps 100, 100a, and 100c. The blade bodies 51, 51a, and 51c have a plurality of blade air channels 80 extending along the blade height direction Dh within the blade bodies 51, 51a, and 51c. The first blade air channels 81, 81a, 81c and the second blade air channels 85, 85a, 85c of the plurality of blade air channels 80 are all end openings on one side of the blade height direction Dh, namely the blade height side, either the first side Dh1 or the second side Dh2. The first inserts 90, 90a, 90b, 90c and the second inserts 95, 95a, 95b, 95c each have a cylindrical outer peripheral plate portion 91, 96 extending along the cylinder height direction Dih, and a sealing plate portion 93, 98 that closes one end of the outer peripheral plate portion 91, 96 on the cylinder height direction Dih, namely the cylinder height sealing side Dih1. Multiple impact holes 92, 97 are formed on the outer peripheral plate portions 91, 96, penetrating from the inside to the outside of the cylindrical outer peripheral plate portions 91, 96. The outer peripheral plates 91 and 96 have openings on the other side of the cylinder height direction Dih, namely the cylinder height opening side Dih2. The outer peripheral plates 91 of the first inserts 90, 90a, 90b, and 90c are arranged in the first blade air channels 81, 81a, and 81c such that there is a gap between the outer peripheral plates 91 of the first inserts 90 and the first channel defining surfaces 81p of the blade bodies 51, 51a, and 51c that define the first blade air channels 81, and cooling air Ac flows into the outer peripheral plates 91 from the openings of the first inserts 90, 90a, 90b, and 90c. The outer peripheral plate portions 96 of the second inserts 95, 95a, 95b, and 95c are arranged such that the cylinder height opening side Dih2 of the second inserts 95, 95a, 95b, and 95c faces the blade height side. There is a gap between the outer peripheral plate portions 96 of the second inserts 95, 95a, 95b, and 95c and the second channel defining surface 85p of the blade bodies 51, 51a, and 51c that defines the second blade air channel 85. Cooling air Ac flows into the second blade air channel 85, 85a, and 85c through the openings of the second inserts 95, 95a, 95b, and 95c.The end caps 100, 100a, and 100c are disposed on one side of the blade height of the blade body 51 such that cooling air Ac ejected from the plurality of impact holes 92 of the first inserts 90, 90a, 90b, and 90c into the space between the outer peripheral plate portion 91 of the first inserts 90, 90a, 90b, and 90c and the first channel demarcation surface 81p is guided through the opening of the first blade air channel 81 into the second inserts 95, 95a, 95b, and 95c. They also cover the opening of the first blade air channel 81 and the opening of the second inserts 95, 95a, 95b, and 95c.

[0164] In this method, cooling air Ac flowing into the first inserts 90, 90a, 90b, and 90c disposed within the first blade air passages 81, 81a, and 81c impinges on the first passage marking surface 81p. Furthermore, at least a portion of this cooling air Ac flows into the second inserts 95, 95a, 95b, and 95c disposed within the second blade air passages 85, 85a, and 85c. The cooling air Ac flowing into the second inserts 95, 95a, 95b, and 95c impinges on the second passage marking surface 85p. Therefore, in this method, compared to the case where cooling air Ac flowing into one insert impinges on the blade body and is then immediately ejected into the combustion gas flow path, the stationary blades can be cooled more effectively, thus reducing the amount of cooling air Ac used.

[0165] (2) The stationary blade in the second method is the same as the stationary blade in the first method.

[0166] The outer surfaces, i.e., the leaf surfaces, of the blade bodies 51, 51a, and 51c have first leaf surface portions 54f and 55f that are positioned back-to-back with the first channel demarcation surface 81p, and second leaf surface portions 54s and 55s that are positioned back-to-back with the second channel demarcation surface 85p. The plurality of impact holes 92 are formed in the portion of the outer peripheral plate portion 91 of the first inserts 90, 90a, 90b, and 90c opposite to the first leaf surface portions 54f and 55f. The plurality of impact holes 97 are formed in the portion of the outer peripheral plate portion 96 of the second inserts 95, 95a, 95b, and 95c opposite to the second leaf surface portions 54s and 55s.

[0167] In this method, the blade surface exposed to the combustion gases can be effectively cooled.

[0168] (3) The stationary blade in the third method is the same as the stationary blade in the second method.

[0169] Multiple nozzles 87ns and 87ps are formed in the blade bodies 51, 51a, and 51c, extending from the second channel demarcation surface 85p to the second blade surfaces 54s and 55s. The positions of the second blade surfaces 54s and 55s are such that, during the operation of the gas turbine 10, the pressure on the outer side of the blade bodies 51, 51a, and 51c along the second blade surfaces 54s and 55s is lower than the pressure on the outer side of the blade bodies 51, 51a, and 51c along the first blade surfaces 54f and 55f.

[0170] (4) The stationary blade in the fourth method is the same as the stationary blade in the third method.

[0171] The blade bodies 51 and 51c have a leading edge 52 extending along the blade height direction Dh, a trailing edge 53 extending along the blade height direction Dh, and a positive pressure surface 55 and a negative pressure surface 54 extending along the blade height direction Dh and connecting the leading edge 52 and the trailing edge 53. The first leaf surfaces 54f and 55f are part of one of the positive pressure surface 55 and the negative pressure surface 54. The second leaf surfaces 54s and 55s are located on the side closer to the trailing edge 53 than the first leaf surfaces 54f and 55f.

[0172] (5) The stationary blade in the fifth method is the same as the stationary blade in the third method.

[0173] The blade body 51a has a leading edge 52 extending along the blade height direction Dh, a trailing edge 53 extending along the blade height direction Dh, and a positive pressure surface 55 and a negative pressure surface 54 extending along the blade height direction Dh and connecting the leading edge 52 and the trailing edge 53. The first blade portion 55f is a part of the positive pressure surface 55. The second blade portion 54s is a part of the negative pressure surface 54.

[0174] (6) The stationary blade in the sixth embodiment is in any one of the stationary blades in the first to fifth embodiments.

[0175] In the first blade air channels 81 and 81a, the ends of the first blade height side Dh1 and the second blade height side Dh2 of the first blade air channels 81 and 81a are open. In the second blade air channels 85 and 85a, the ends of the first blade height side Dh1 of the second blade air channels 85 and 85a are closed, and the ends of the second blade height side Dh2 are open. The first inserts 90 and 90a have flange portions 94 that extend from the end of the outer peripheral plate portion 91 of the first inserts 90 and 90a at the cylinder height opening side Dih2 toward the outer peripheral side of the outer peripheral plate portion 91 of the first inserts 90 and 90a, and extend to the first channel defining surface 81p to connect with the blade body 51.

[0176] The second inserts 95 and 95a have flanges 99 that extend from the end of the outer peripheral plate portion 96 of the second inserts 95 and 95a at the cylindrical height opening side Dih2 towards the outer peripheral side of the outer peripheral plate portion 96, and extend to the second channel defining surface 85p to connect with the blade body 51. The outer peripheral plate portions 91 of the first inserts 90 and 90a are disposed within the first blade air channels 81 and 81a such that the cylindrical height opening side Dih2 of the first inserts 90 and 90a faces the first blade height side Dh1. The outer peripheral plate portions 96 of the second inserts 95 and 95a are disposed within the second blade air channels 85 and 85a such that the cylindrical height opening side Dih2 of the second inserts 95 and 95a faces the second blade height side Dh2.

[0177] In this method, the structure of each insert is not complicated, and it can improve the impact cooling effect of the blade body 51.

[0178] (7) The stationary blade in the seventh embodiment further comprises, in any one of the first to sixth embodiments, the following:

[0179] The first guide member 110, within the first blade air channels 81, 81a, 81c, allows the first inserts 90, 90a, 90b, 90c to move in the height direction Dih of the cylinder, and restricts the displacement of the first inserts 90, 90a, 90b, 90c in the direction of expansion of the cross section; and the second guide member 115, within the second blade air channels 85, 85a, 85c, allows the second inserts 95, 95a, 95b, 95c to move in the height direction Dih of the cylinder, and restricts the displacement of the second inserts 95, 95a, 95b, 95c in the direction of expansion of the cross section.

[0180] In this method, even when the outer peripheral plate portion 91 of the first inserts 90, 90a, 90b, 90c and the first channel defining surface 81p differ in thermal deformation due to temperature difference while driving the gas turbine 10, the distance between the outer peripheral plate portion 91 of the first inserts 90, 90a, 90b, 90c and the first channel defining surface 81p can be kept approximately constant, thereby achieving the target impact cooling effect. Furthermore, in this method, even when the outer peripheral plate portion 96 of the second inserts 95, 95a, 95b, 95c and the second channel defining surface 85p differs in thermal deformation due to temperature difference while driving the gas turbine 10, the distance between the outer peripheral plate portion 96 of the second inserts 95, 95a, 95b, 95c and the second channel defining surface 85p can be kept approximately constant, thereby achieving the target impact cooling effect.

[0181] (8) The stationary blade in the eighth embodiment is the same as the stationary blade in the seventh embodiment.

[0182] The first guide member 110 includes a first groove member 111 having a first groove 112 extending along the cylinder height direction Dih, and a first protruding member 113 entering the first groove 112 and movable relative to the first groove 112 along the cylinder height direction Dih. One of the first groove member 111 and the first protruding member 113 is fixed to the first inserts 90, 90a, and the other is fixed to the first channel marking surface 81p. The second guide member 115 includes a second groove member 116 having a second groove 117 extending along the cylinder height direction Dih, and a second protruding member 118 entering the second groove 117 and movable relative to the second groove 117 along the cylinder height direction Dih. One of the second groove member 116 and the second protruding member 118 is fixed to the second inserts 95, 95a, and the other is fixed to the second channel marking surface 85p.

[0183] (9) The stationary blade in the ninth embodiment further comprises, in the case of the stationary blade in the sixth embodiment,:

[0184] A first guide member 110, within the first blade air channels 81, 81a, allows the first inserts 90, 90a to move in the cylinder height direction Dih, and restricts the displacement of the first inserts 90, 90a in the direction of cross-sectional expansion; and a second guide member 115, within the second blade air channels 85, 85a, allows the second inserts 95, 95a to move in the cylinder height direction Dih, and restricts the displacement of the second inserts 95, 95a in the direction of cross-sectional expansion. The first guide member 110 includes a first groove member 111 having a first groove 112 extending along the cylinder height direction Dih, and a first protrusion member 113 entering the first groove 112 and movable relative to the first groove 112 along the cylinder height direction Dih. One of the first groove component 111 and the first protruding component 113 is fixed to the outer peripheral plate portion 91 of the first inserts 90, 90a, and the other component is fixed to the first channel demarcation surface 81p of the blade bodies 51, 51a. The second guide 115 includes a second groove component 116 having a second groove 117 extending along the cylinder height direction Dih, and a second protruding component 118 entering the second groove 117 and movable relative to the second groove 117 along the cylinder height direction Dih. One of the second groove component 116 and the second protruding component 118 is fixed to the sealing plate portion 98 of the second inserts 95, 95a, and the other component is fixed to the portion of the blade bodies 51, 51a closed by the end of the second blade air channel 85, 85a on the first side Dh1 of the blade height.

[0185] (10) The stationary blade in the 10th embodiment further comprises:

[0186] A first shield 60i is disposed at the end of the blade body 51, 51a, 51c on the first side of blade height Dh1; a second shield 60o is disposed at the end of the blade body 51, 51a, 51c on the second side of blade height Dh2; and an impact plate 78 having a plurality of impact holes 79. The first shield 60i has: a shield body 61 having a gas path surface 64 facing the second side of blade height Dh2 and a gas path opposite surface 65 facing the side opposite to the gas path surface 64; and a peripheral wall 71 disposed along the periphery of the shield body 61 and protruding from the gas path opposite surface 65 toward the first side of blade height Dh1. The impact plate 78 is formed by the shield body 61 and the peripheral wall 71, and divides the cavity 72 in the recessed portion facing the second side of the blade height Dh2 into a space of the first side of the blade height Dh1 and a space of the second side of the blade height Dh2, and is fixed to the first shield 60i in such a way that the plurality of impact holes 79 of the impact plate 78 extend along the blade height direction Dh.

[0187] In this method, the cooling air Ac flowing into the stationary blades can perform three-stage impact cooling on the interior of the stationary blades. Therefore, this method can effectively cool the stationary blades while reducing the amount of cooling air Ac used.

[0188] The gas turbine in the above embodiments can be understood, for example, as follows.

[0189] (11) The gas turbine in the 11th embodiment has a stationary blade of any one of the 1st to 10th embodiments, a rotor 41 that rotates about the axis Ar, and a housing 45 covering the outer periphery of the rotor 41.

[0190] The stationary blade is fixed to the inner circumferential surface of the housing 45.

[0191] Industrial availability

[0192] According to one aspect of the present invention, the stationary blades can be effectively cooled, thereby improving durability and reducing the amount of cooling air used.

[0193] Symbol Explanation

[0194] 10-Gas turbine, 11-Gas turbine rotor, 15-Gas turbine casing, 16-Intermediate casing, 20-Compressor, 21-Compressor rotor, 22-Rotor shaft, 23-Moving blade row, 23a-Moving blade, 25-Compressor casing, 26-Stationary blade row, 26a-Stationary blade, 30-Burner, 40-Turbine, 41-Turbine rotor, 42-Rotor shaft, 43-Moving blade row, 43a-Moving blade, 45-Turbine casing, 45a-Outer casing, 45b-Inner casing, 45c-Divider ring, 46-Stationary blade row, 46a-Stationary blade, 49-Combustion gas flow path, 50, 50a, 50b, 50c, 50d-Stationary blade, 51, 51a, 51c-Blade body, 52-Leading edge 53-Trail edge, 54-Negative pressure surface, 54f-First blade section on the negative pressure side, 54s-Second blade section on the negative pressure side, 55-Positive pressure surface, 55f-First blade section on the positive pressure side, 55s-Second blade section on the positive pressure side, 60o-Outer shroud, 60i-Inner shroud, 61-Shroud body, 62f-Front end face, 62b-Rear end face, 63n-Negative pressure side end face, 63p-Positive pressure side end face, 64-Gas path surface, 65-Opposite surface of gas path, 71-Peripheral wall, 71f-Front peripheral wall, 71b-Rear peripheral wall, 71n-Negative pressure side peripheral wall, 71p-Positive pressure side peripheral wall, 72-Cavity, 76-Cage, 78-Impact plate, 79-Impact hole, 80-Blade air passage, 80f-Front blade air passage, 80 fa - Front ejector hole, 80fo - Opening, 80b - Rear blade air passage, 80ba - Rear ejector hole, 80bo - Opening, 80m - Middle blade air passage, 81, 81a, 81c - First blade air passage, 81p - First passage marking surface, 82f - First opening (or simply opening), 82s - Second opening, 83nf - First ejector hole on the negative pressure side, 83pf - First ejector hole on the positive pressure side, 84 - Sealing flange, 85, 85a, 85c - Second blade air passage, 85p - Second passage marking surface, 86, 86c - Opening, 87ns - Second ejector hole on the negative pressure side, 87ps - Second ejector hole on the positive pressure side, 88 - Sealing flange, 90, 90a, 90b, 90c - 1st insert, 90° - insert opening, 91 - outer peripheral plate, 92 - impact hole, 93 - sealing plate, 94, 94b, 94c - flange, 95, 95a, 95b, 95c - 2nd insert, 95° - insert opening, 96 - outer peripheral plate, 97 - impact hole, 98 - sealing plate, 99 - flange, 100, 100a, 100c - end cap, 101, 101a - top plate, 102 - outer peripheral plate, 110 - 1st guide, 111 - 1st groove component, 112 - 1st groove, 113 - 1st protrusion component, 115 - 2nd guide, 116 - 2nd groove component, 117 - 2nd groove, 118 - 2nd protrusion component, A - air, Ac - cooling air, F - fuelG - Combustion gas, Ar - Axis, CL - Arc, C1 - First cavity inside the blade, C2 - Second cavity inside the blade, Da - Axis direction, Dau - Upstream side of the axis, Dad - Downstream side of the axis, Dc - Circumferential, Dcp - Circumferential positive pressure side, Dcn - Circumferential negative pressure side, Dr - Radial, Dri - Inner radial side, Dro - Outer radial side, Dh - Blade height direction, Dh1 - First side of blade height, Dh2 - Second side of blade height, Dih - Cylinder height direction, Dih1 - Sealed side of cylinder height, Dih2 - Open side of cylinder height.

Claims

1. A stationary blade disposed on a gas turbine, the stationary blade comprising: The blade body has a leaf-shaped cross-section and extends along the blade height direction, which has a directional component perpendicular to the cross-section. The first and second inserts are cylindrical, extending along the height direction of the cylinder, and are disposed within the blade body such that the height direction of the cylinder faces the height direction of the blade; and End cap, The blade body has: a leading edge extending along the blade height direction, a trailing edge extending along the blade height direction, a positive pressure surface and a negative pressure surface extending along the blade height direction and connecting the leading edge and the trailing edge, and a plurality of blade air channels extending along the blade height direction within the blade body. The front blade air channel, the first blade air channel, and the second blade air channel among the plurality of blade air channels are all end openings on one side of the blade height direction, namely the first side or the second side of the blade height. The front blade air passage is located on the side closest to the leading edge within the blade body and among the plurality of blade air passages. The first blade air passage and the second blade air passage are located within the blade body on a side closer to the trailing edge than the air passage of the front blade. Both the first and second inserts have a cylindrical outer peripheral plate portion extending along the height direction of the cylinder, and a sealing plate portion that closes one end of the outer peripheral plate portion along the height direction of the cylinder, i.e., the cylinder height sealing side. Multiple impact holes are formed in the outer peripheral plate portion, extending from the inside to the outside of the cylindrical outer peripheral plate portion. The outer peripheral plate portion has an opening on the other side in the cylinder height direction, namely the cylinder height opening side. The outer peripheral plate portion of the first insert has a gap between the outer peripheral plate portion of the first insert and the first channel defining surface of the blade body defining the air channel of the first blade, and is disposed within the air channel of the first blade in such a way that cooling air flows into the outer peripheral plate portion from the opening of the first insert. The outer peripheral plate of the second insert is positioned such that the opening side of the second insert at the cylinder height faces the side at the blade height. A gap exists between the outer peripheral plate of the second insert and the second channel defining surface of the blade body that defines the air channel of the second blade. Cooling air is arranged within the air channel of the second blade such that it flows in from the opening of the second insert. The end cap is positioned on one side of the blade body at the blade height such that cooling air ejected from the plurality of impact holes of the first insert into the space between the outer peripheral plate of the first insert and the first channel demarcation surface is guided through the opening of the first blade air channel into the second insert. It covers the opening of the first blade air channel and the opening of the second insert, but does not cover the opening of the front blade air channel. In the first blade air passage, the end of the first blade air passage on the first side of the blade height and the end on the second side of the blade height are open. In the second blade air channel, the end of the second blade air channel on the first side of the blade height is closed, and the end on the second side of the blade height is open.

2. The stationary blade according to claim 1, wherein, The outer surface of the leaf body, i.e., the leaf surface, has a first leaf surface that is back-to-back with the first channel delineation surface and a second leaf surface that is back-to-back with the second channel delineation surface. The plurality of impact holes are formed in the outer peripheral plate portion of the first insert, opposite to the first leaf surface portion. The plurality of impact holes are formed in the portion of the outer peripheral plate of the second insert that is opposite to the second leaf surface.

3. The stationary blade according to claim 2, wherein, Multiple ejection holes are formed in the blade body, extending from the second channel demarcation surface to the second blade surface. The position of the second blade section in the blade surface is the position where, during the driving of the gas turbine, the pressure on the outer side of the blade body and along the second blade section is lower than the pressure on the outer side of the blade body and along the first blade section.

4. The stationary blade according to claim 3, wherein, The first leaf surface is a part of one of the positive pressure surface and the negative pressure surface. The second leaf surface is located on the side of the leaf surface that is closer to the trailing edge than the first leaf surface.

5. The stationary blade according to claim 3, wherein, The first leaf section is part of the positive pressure surface. The second leaf section is part of the negative pressure surface.

6. The stationary blade according to any one of claims 1 to 5, wherein, The first insert has a flange portion that extends from the end of the outer peripheral plate portion of the first insert at the cylinder height opening side toward the outer peripheral side of the outer peripheral plate portion of the first insert, and extends to the first channel defining surface to connect with the blade body. The second insert has a flange that extends from the end of the outer peripheral plate portion of the second insert at the cylinder height opening side toward the outer peripheral side of the outer peripheral plate portion of the second insert, and extends to the second channel defining surface to connect with the blade body. The outer peripheral plate portion of the first insert is disposed within the air passage of the first blade such that the opening side of the first insert at the cylinder height faces the first side at the blade height. The outer peripheral plate portion of the second insert is disposed within the air passage of the second blade such that the cylinder height opening side of the second insert faces the blade height second side.

7. The stationary blade according to any one of claims 1 to 5, further comprising: The first guide member, within the air passage of the first blade, allows displacement of the first insert in the direction of the cylinder height and restricts displacement of the first insert in the direction of expansion of the cross-section; and The second guide, within the air passage of the second blade, allows the second insert to move in the direction of the cylinder height and restricts the displacement of the second insert in the direction of expansion of the cross section.

8. The stationary blade according to claim 7, wherein, The first guide member includes a first groove member having a first groove extending along the height direction of the cylinder and a first protrusion member entering the first groove and movable relative to the first groove along the height direction of the cylinder. One of the first groove component and the first protruding component is fixed to the first insert, and the other component is fixed to the first channel defining surface. The second guide member includes a second groove member having a second groove extending along the height direction of the cylinder and a second protrusion member entering the second groove and movable relative to the second groove along the height direction of the cylinder. One of the second groove component and the second convex component is fixed to the second insert, and the other component is fixed to the second channel demarcation surface.

9. The stationary blade according to claim 6, further comprising: The first guide member, within the air passage of the first blade, allows displacement of the first insert in the direction of the cylinder height and restricts displacement of the first insert in the direction of expansion of the cross-section; and The second guide member, within the air passage of the second blade, allows the second insert to move in the direction of the cylinder height, and restricts the displacement of the second insert in the direction of expansion of the cross-section. The first guide member includes a first groove member having a first groove extending along the height direction of the cylinder and a first protrusion member entering the first groove and movable relative to the first groove along the height direction of the cylinder. One of the first groove component and the first protrusion component is fixed to the outer peripheral plate portion of the first insert, and the other component is fixed to the first channel marking surface of the blade body. The second guide member includes a second groove member having a second groove extending along the height direction of the cylinder and a second protrusion member entering the second groove and movable relative to the second groove along the height direction of the cylinder. One of the second groove component and the second protruding component is fixed to the sealing plate portion of the second insert, and the other component is fixed to the portion of the blade body closed by the end of the blade height first side in the air channel of the second blade.

10. The stationary blade according to any one of claims 1 to 5, further comprising: The first protective cover is disposed at the end of the blade body on the first side of the blade height; A second protective cover is disposed at the end of the blade body on the second side of the blade height; and The impact plate has multiple impact holes. The first protective cover has: The shield body has a gas path surface facing the second side of the blade height and a gas path opposite surface facing the side opposite to the gas path surface; and A peripheral wall is provided along the periphery of the main body of the shield, and protrudes from the side opposite to the gas path to the first side of the blade height. The impact plate is formed by the shield body and the peripheral wall, and divides the cavity in the recessed portion facing the second side of the blade height into a space on the first side of the blade height and a space on the second side of the blade height, and is fixed to the first shield in such a way that the plurality of impact holes of the impact plate extend along the blade height direction.

11. A gas turbine comprising: The stationary blade according to any one of claims 1 to 10; The rotor rotates about its axis. The housing covers the outer periphery of the rotor. The stationary blade is fixed to the inner circumferential surface of the housing.

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