Stationary blade and gas turbine equipped with same

Abstract

This stator blade comprises a blade body having a cross-sectional shape that forms a blade profile. The blade body includes: a trailing end space and an adjacent space that are located between a leading edge and a trailing edge; and a plurality of trailing end cooling passages that penetrate from the trailing end space to the trailing edge. The adjacent space is located further on the leading edge side than the trailing end space. The edge of the trailing end space on the leading edge side is open and communicates with the trailing end space. A plurality of divider ribs, which are aligned in the blade height direction and divide the trailing end space in the blade height direction, and a plurality of pins are arranged in the trailing end space. The plurality of pins all both joined to a positive pressure-side inner wall surface and a negative pressure-side inner wall surface that define the trailing end space. Among the plurality of divider ribs, at least one divider rib forms an extending divider rib which extends to the interior of the adjacent space and which is joined to an inner wall surface demarcating the adjacent space.

Description

[Technical Field]

[0001] The present invention relates to a stator vane and a gas turbine equipped with the same. This application claims priority based on Japanese Patent Application No. 2022-089017, filed on May 31, 2022, the contents of which are incorporated herein by reference. [Background technology]

[0002] A gas turbine includes a compressor that compresses air to generate compressed air, a combustor that combusts fuel in the compressed air to generate combustion gas, and a turbine driven by the combustion gas. The turbine includes a turbine rotor that rotates about an axis, a turbine casing that covers the rotor, and multiple stator blade rows. The turbine rotor has a rotor shaft that is centered on the axis and multiple rotor blade rows attached to the rotor shaft. The multiple rotor blade rows are aligned in the axial direction along which the axis extends. Each rotor blade row has multiple rotor blades aligned in the circumferential direction about the axis. The multiple stator blade rows are aligned in the axial direction and attached to the inner periphery of the turbine casing. Each of the multiple stator blade rows is arranged axially upstream of one of the multiple rotor blade rows. Each stator blade row has multiple stator blades aligned in the circumferential direction about the axis.

[0003] The stator vane has a blade body extending radially relative to the axis to form an airfoil shape, an inner shroud provided radially inside the blade body, and an outer shroud provided radially outside the blade body. The blade body of the stator vane is disposed in a combustion gas flow path through which combustion gas passes. The inner shroud defines the radially inner edge of the combustion gas flow path, and the outer shroud defines the radially outer edge of the combustion gas flow path.

[0004] The stationary blades of a gas turbine are exposed to high-temperature combustion gases, and therefore are generally cooled by air or the like.

[0005] For example, the blade body of a vane described in Patent Document 1 below has multiple cooling air spaces formed therein through which cooling air passes. Each of the multiple cooling air spaces extends in the blade height direction, which is the radial direction relative to the axis. Among the multiple cooling air spaces, a trailing end space located closest to the trailing edge forms multiple aft-end cooling passages extending to the trailing edge of the blade body. This aft-end space is provided with multiple pins and multiple ribs that partition the aft-end space in the blade height direction. The multiple pins protrude from the pressure side inner surface or the suction side inner surface that defines the aft-end space. The multiple ribs also protrude from the pressure side inner surface or the suction side inner surface that defines the aft-end space. Furthermore, a cylindrical insert is inserted into an adjacent space of the multiple cooling air spaces that is in contact with the leading edge of the aft-end space. This cylindrical insert has through holes formed therein that allow cooling air to be ejected from the inner circumferential side toward the outer circumferential side.

[0006] For example, the blade body of a vane described in Patent Document 2 below also has multiple cooling air spaces through which cooling air passes. Each of the multiple cooling air spaces extends in the blade height direction, which is the radial direction relative to the axis. Of the multiple cooling air spaces, a trailing end space located closest to the trailing edge has multiple pins arranged therein. The multiple pins are joined to the pressure side inner surface and the suction side inner surface that define the aft end space. Also, of the multiple cooling air spaces, a cylindrical insert is inserted into an adjacent space that contacts the leading edge side edge of the aft end space. This cylindrical insert has through holes formed therein that allow cooling air to be ejected from the inner peripheral side toward the outer peripheral side. [Prior art documents] [Patent documents]

[0007] [Patent Document 1] Japanese Patent Application Laid-Open No. 10-306705 Figure 5 [Patent Document 2] Patent No. 6353131 Summary of the Invention [Problem to be solved by the invention]

[0008] In the techniques described in Patent Documents 1 and 2, by providing a plurality of pins in the aft end space, it is possible to efficiently exchange heat between the wall surfaces that define the aft end space and the cooling air in the aft end space. Also, as in the technique described in Patent Document 2, by connecting the pressure side inner surface and the suction side inner surface that define the aft end space with a plurality of pins in the aft end space, it is possible to increase the rigidity of the portion of the stator vane that includes the aft end space.

[0009] In the techniques described in Patent Documents 1 and 2, a cylindrical insert is inserted into the adjacent space adjacent to the leading edge of the rear end space. Therefore, this The pressure side inner surface and the suction side inner surface that define the adjacent space are not connected by a pin, etc. Therefore, the rigidity of the portion of the stator vane around the adjacent space is lower than the rigidity of the portion of the stator vane around the aft end space.

[0010] During operation of a gas turbine, the pressure inside the cooling air space of the blade is higher than the pressure outside the blade. Therefore, due to the pressure difference between the inside and outside of the blade, a force is applied to the blade that causes the blade surface to bulge outward. The phenomenon in which the blade surface bulges due to this force is called bulging.

[0011] Bulging is likely to occur in the low-rigidity portions of the vane body, which not only reduces the aerodynamic performance of the vane but also its durability.

[0012] Therefore, an object of the present disclosure is to provide a technology that can improve the bulging strength of a stator vane and suppress a decrease in the aerodynamic performance and durability of the stator vane. [Means for solving the problem]

[0013] In order to achieve the above object, one aspect of the invention relates to a stator blade, A gas turbine includes a stator vane having a blade body with an airfoil-shaped cross section extending in a blade height direction having a component perpendicular to the cross section. The blade body has leading and trailing edges extending in the blade height direction, pressure and suction surfaces extending in the blade height direction and connecting the leading and trailing edges, an aft-end space and an adjacent space located between the leading and trailing edges and between the pressure and suction surfaces, and a plurality of aft-end cooling passages penetrating from the aft-end space to the trailing edge. The adjacent space is located closer to the leading edge than the aft-end space. The edge of the aft-end space on the leading edge side is open and communicates with the aft-end space. Both the adjacent space and the aft-end space are defined by inner wall surfaces. The inner wall surface of the adjacent space and the inner wall surface of the aft end space each have a pressure-side inner wall surface that extends along the pressure surface and a suction-side inner wall surface that extends along the suction surface and is spaced from the pressure-side inner wall surface toward the suction surface. The pressure-side inner wall surface of the adjacent space is connected to the pressure-side inner wall surface of the aft end space. The suction-side inner wall surface of the adjacent space is connected to the suction-side inner wall surface of the aft end space. A plurality of partition ribs and a plurality of pins are arranged in the blade height direction and divide the aft end space in the blade height direction within the aft end space. All of the pins are joined to the pressure-side inner wall surface of the aft end space and the suction-side inner wall surface of the aft end space. At least one of the plurality of partition ribs extends into the adjacent space and forms an extended partition rib joined to the inner wall surface that defines the adjacent space. The portion of the extension partition rib within the adjacent space has a portion where the amount of protrusion from the inner wall surface gradually decreases toward the leading edge. The engine further includes a cylindrical insert disposed in the adjacent space. The insert has a plurality of impingement holes formed therein that penetrate from the inner periphery to the outer periphery.

[0014] In this aspect, the pressure side inner wall surface and the suction side inner wall surface that define the aft end space are joined by a plurality of pins. As a result, the rigidity around the aft end space within the blade body is higher than the rigidity around the adjacent space within the blade body. In other words, the rigidity around the adjacent space within the blade body is lower than the rigidity around the aft end space within the blade body. Bulging is likely to occur in areas of low rigidity within the blade body. When this bulging occurs, not only does the aerodynamic performance of the stator vane deteriorate, but its durability also deteriorates. In particular, high stress occurs due to deformation caused by bulging near the boundary between the low rigidity area within the blade body and the high rigidity area within the blade body. In other words, high stress occurs due to deformation caused by bulging near the boundary between the adjacent space and the aft end space.

[0015] Therefore, in this aspect, at least one of the partition ribs arranged in the rear end space is extended into the adjacent space to increase the rigidity near the boundary between the adjacent space and the rear end space, thereby suppressing the occurrence of bulging and reducing deformation near the boundary between the adjacent space and the rear end space.

[0016] Therefore, in this aspect, the bulging strength of the stator blade is improved, and it is possible to suppress a decrease in the aerodynamic performance and durability of the stator blade due to the occurrence of the bulging phenomenon.

[0017] In order to achieve the above object, a gas turbine according to one aspect of the invention comprises: The turbine includes the stator vane according to the above aspect, a rotor that rotates about an axis, and a casing that covers an outer circumferential side of the rotor. The stator vane is fixed to an inner circumferential surface of the casing. [Effects of the Invention]

[0018] According to one aspect of the present disclosure, the bulging strength of the stator vane can be improved, thereby suppressing deterioration in the aerodynamic performance and durability of the stator vane. [Brief explanation of the drawings]

[0019] [Figure 1] 1 is a schematic cross-sectional view of a gas turbine in one embodiment according to the present disclosure. [Figure 2] FIG. 1 is a perspective view of a stator vane in an embodiment according to the present disclosure. [Figure 3] 3 is a cross-sectional view taken along line III-III in FIG. 2 (a longitudinal cross-sectional view of a main part of a stator blade). [Figure 4] 4 is a cross-sectional view (transverse cross-sectional view of the wing body) taken along line IV-IV in FIG. 3. [Figure 5] FIG. 5 is an enlarged view of the V portion in FIG. 4 (a cross-sectional view of the main part of the wing body). [Figure 6] FIG. 10 is a longitudinal cross-sectional view of a main portion of a vane in a modified example of an embodiment according to the present disclosure. [Figure 7] FIG. 10 is a cross-sectional view of a main portion of a wing body according to another modified example of an embodiment of the present disclosure. DETAILED DESCRIPTION OF THE INVENTION

[0020] Hereinafter, embodiments of a stator vane according to the present disclosure and a gas turbine including the stator vane will be described in detail with reference to the drawings.

[0021] "Gas Turbine Embodiment" An embodiment of a gas turbine will be described with reference to FIG.

[0022] As shown in FIG. 1, the gas turbine 10 of this embodiment includes a compressor 20 that compresses air A, a combustor 30 that burns fuel F in the air A compressed by the compressor 20 to generate combustion gas G, and a turbine 40 that is driven by the combustion gas G.

[0023] The compressor 20 has a compressor rotor 21 that rotates about an axis Ar, a compressor casing 25 that covers the compressor rotor 21, and a plurality of stator blade rows 26. The turbine 40 has a turbine rotor 41 that rotates about the axis Ar, a turbine casing 45 that covers the turbine rotor 41, and a plurality of stator blade rows 46. Note that, hereinafter, the direction in which the axis Ar extends will be referred to as the axial direction Da, the circumferential direction about the axis Ar will be simply referred to as the circumferential direction Dc, and the direction perpendicular to the axis Ar will be referred to as the radial direction Dr. Furthermore, one side of the axial direction Da will be referred to as the axial upstream side Dau, and the opposite side will be referred to as the axial downstream side Dad. Furthermore, the side of the radial direction Dr that approaches the axis Ar will be referred to as the radially inner side Dri, and the opposite side will be referred to as the radially outer side Dro.

[0024] The compressor 20 is disposed on the axial upstream side Dau with respect to the turbine 40 .

[0025] 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. To this gas turbine rotor 11, for example, a rotor of a generator GEN is connected. The gas turbine 10 further includes an intermediate casing 16. This intermediate casing 16 is arranged between the compressor casing 25 and the turbine casing 45 in the axial direction Da. The compressor casing 25, the intermediate casing 16, and the turbine casing 45 are connected to each other to form the gas turbine casing 15.

[0026] The compressor rotor 21 has a rotor shaft 22 extending in the axial direction Da around the axis Ar, and a plurality of rotor blade rows 23 attached to the rotor shaft 22. The plurality of rotor blade rows 23 are aligned in the axial direction Da. Each rotor blade row 23 is made up of a plurality of rotor blades aligned in the circumferential direction Dc. One of the plurality of stator blade rows 26 is arranged on the axial downstream side Dad of each of the plurality of rotor blade rows 23. Each stator blade row 26 is provided inside the compressor casing 25. Each stator blade row 26 is made up of a plurality of stator blades aligned in the circumferential direction Dc.

[0027] The turbine rotor 41 has a rotor shaft 42 that extends in the axial direction Da centered on the axis Ar, and a plurality of rotor blade rows 43 attached to the rotor shaft 42. The plurality of rotor blade rows 43 are aligned in the axial direction Da. Each rotor blade row 43 is made up of a plurality of rotor blades aligned in the circumferential direction Dc. One of the plurality of stator blade rows 46 is arranged on the axial upstream side Dau of each of the plurality of rotor blade rows. Each stator blade row 46 is provided inside the turbine casing 45. Each stator blade row 46 is made up of a plurality of stator blades aligned in the circumferential direction Dc.

[0028] The combustor 30 is attached to the intermediate casing 16 .

[0029] The compressor 20 compresses air A to generate compressed air. This compressed air flows into the combustor 30. Fuel F is supplied to the combustor 30. In the combustor 30, the fuel F is burned in the compressed air to generate high-temperature, high-pressure combustion gas G. This combustion gas G is sent from the combustor 30 to an annular combustion gas flow path 49 in the turbine casing 45. The combustion gas G rotates the turbine rotor 41 while flowing through the combustion gas flow path 49 toward the axial downstream side Dad. The rotation of this turbine rotor 41 rotates the rotor of the generator GEN connected to the gas turbine rotor 11. As a result, the generator GEN generates electricity.

[0030] Hereinafter, an embodiment and modifications thereof relating to the stator blades that constitute the first stage stator blade row 46 in the turbine 40 will be described.

[0031] "Embodiment of Stator Blade" An embodiment of the stator vane will be described with reference to Figs. 2 to 5. Fig. 2 is a perspective view of the stator vane in this embodiment. Fig. 3 is a cross-sectional view taken along line III-III in Fig. 2 (longitudinal cross-sectional view of the essential parts of the stator vane). Fig. 4 is a cross-sectional view taken along line IV-IV in Fig. 3 (transverse cross-sectional view of the blade body). Fig. 5 is an enlarged view of part V in Fig. 4 (transverse cross-sectional view of the essential parts of the blade body).

[0032] As shown in Figures 2 to 4, the stator vane 50 of this embodiment has a blade body 51, an inner shroud 80i, an outer shroud 80o, an inner impingement plate 88i, an outer impingement plate 88o, a first insert 68A, a second insert 68B, and a third insert 68C.

[0033] The blade body 51 has an airfoil-shaped cross section and extends in a blade height direction Dh having a directional component perpendicular to the cross section. The outer shroud 80o is provided at one end of the blade body 51 in the blade height direction Dh. The inner shroud 80i is provided at the other end of the blade body 51 in the blade height direction Dh. The blade body 51, the inner shroud 80i, and the outer shroud 80o are integrally formed by casting or the like.

[0034] When the stator vane 50 is attached to the turbine casing 45, the blade height direction Dh becomes the radial direction Dr. Furthermore, a blade height first side Dh1, which is one side of the blade height direction Dh, becomes the radial outer side Dro, and a blade height second side Dh2, which is the other side of the blade height direction Dh, becomes the radial inner side Dri. Therefore, the outer shroud 80o is provided on the radial outer side Dro of the blade body 51, and the inner shroud 80i is provided on the radial inner side Dri of the blade body 51. Therefore, in this embodiment, the blade height direction Dh may be referred to as the radial direction Dr, the blade height first side Dh1 as the radial outer side Dro, and the blade height second side Dh2 as the radial inner side Dri.

[0035] As shown in Figures 2 to 4, the blade surface, which is the outer surface of the blade body 51, has a leading edge 52, a trailing edge 53, a suction surface 54 which is a convex surface, and a pressure surface 55 which is a concave surface. The suction surface 54 and the pressure surface 55 are surfaces that connect the leading edge 52 and the trailing edge 53. The leading edge 52, the trailing edge 53, the suction surface 54, and the pressure surface 55 all extend in the radial direction Dr, which is the blade height direction Dh. When the stator blade 50 is attached to the turbine casing 45, the leading edge 52 is located on the axial upstream side Dau with respect to the trailing edge 53. Furthermore, when the stator blade 50 is attached to the turbine casing 45, the suction surface 54 faces one side of the circumferential direction Dc. Ki, positiveThe pressure surface 55 faces the other side in the circumferential direction Dc. The blade body 51 is disposed in the combustion gas flow path 49 of the turbine 40 described with reference to FIG.

[0036] The blade body 51 has a plurality of cooling air spaces 60 extending in the blade height direction Dh (radial direction Dr) within the blade body 51. The plurality of cooling air spaces 60 are aligned along the camber line CL of the blade body 51 from the axial upstream side Dau to the axial downstream side Dad. Of the plurality of cooling air spaces 60, the cooling air space 60 on the axially most upstream side Dau is referred to as a first space 60A, the cooling air space 60 adjacent to the axial downstream side Dad of this first space 60A is referred to as a second space 60B, the cooling air space 60 adjacent to the axial downstream side Dad of this second space 60B is referred to as a third space 60C, and the cooling air space 60 adjacent to the axial downstream side Dad of this third space 60C is referred to as a fourth space 60D. The first space 60A and the second space 60B are separated by a first partition wall 57 extending in a direction substantially perpendicular to the camber line CL. The second space 60B and the third space 60C are separated by a second partition wall 58 that extends in a direction substantially perpendicular to the camber line CL. A first insert 68A is disposed in the first space 60A, a second insert 68B is disposed in the second space 60B, and a third insert 68C is disposed in the third space 60C.

[0037] The inner shroud 80i defines the edge of the radially inner side Dri of the annular combustion gas flow path 49. The outer shroud 80o defines the edge of the radially outer side Dro of the annular combustion gas flow path 49.

[0038] The inner shroud 80i includes a shroud body 81i, a peripheral wall 84i, and a retainer 86i.

[0039] The shroud body 81i is a rectangular plate-shaped member that extends in a direction including a directional component perpendicular to the radial direction Dr, which is the blade height direction Dh. The shroud body 81i has a gas path surface 82i and a counter-gas path surface 83i. The gas path surface 82i faces the radially outer side Dro, which is the blade height first side Dh1, and is the surface that comes into contact with the combustion gas G. The counter-gas path surface 83i faces the radially inner side Dri, which is the blade height second side Dh2. The counter-gas path surface 83i and the gas path surface 82i are in a back-to-back relationship.

[0040] The peripheral wall 84i is a wall that protrudes from the shroud main body 81i toward the radially inward direction Dri along the outer peripheral edge of the shroud main body 81i. The shroud main body 81i and the peripheral wall 84i form a cavity 85i in the inner shroud 80i that is recessed toward the radially outward direction Dro.

[0041] The retainer 86i is formed on the radially inner side Dri of the peripheral wall 84i. This retainer 86i is connected to the end of the radially outer side Dro of an inner cover (not shown) fixed to the gas turbine casing 15, and serves to support the radially inner side Dri of this stator blade 50 on the inner cover.

[0042] The outer shroud 80o has basically the same configuration as the inner shroud 80i. Therefore, like the inner shroud 80i, the outer shroud 80o also has a shroud main body 81o and a peripheral wall 84o. However, the outer shroud 80o does not have a portion corresponding to the retainer 86i of the inner shroud 80i. Like the shroud main body 81i of the inner shroud 80i, the shroud main body 81o of the outer shroud 80o is a rectangular plate-shaped member and has a gas path surface 82o and a counter-gas path surface 83o. The gas path surface 82o of the outer shroud 80o faces the radially inner side Dri, which is the blade height second side Dh2, and is the surface that comes into contact with the combustion gas G. The counter-gas path surface 83o of the outer shroud 80o faces the radially outer side Dro, which is the blade height first side Dh1.

[0043] The peripheral wall 84o is a wall that protrudes radially outward Dro from the shroud body 81o along the outer peripheral edge of the shroud body 81o. The shroud body 81o and the peripheral wall 84o form a cavity 85o in the outer shroud 80o that is recessed radially inward Dri. A portion of the peripheral wall 84o serves to attach the stator vane 50 to the inner circumferential side of the turbine casing 45.

[0044] The inner impingement plate 88i divides the cavity 85i of the inner shroud 80i into two spaces in the blade height direction Dh. A plurality of impingement holes 89 penetrating the inner impingement plate 88i in the blade height direction Dh are formed.

[0045] The cooling air Ac that has flowed into the cavity 85i of the inner shroud 80i is ejected radially outward Dro from multiple impingement holes 89 in the inner impingement plate 88i and collides with the anti-gas path surface 83i of the inner shroud 80i, thereby impinging and cooling this surface. The cooling air Ac that has impinge-cooled the anti-gas path surface 83i is ejected into the combustion gas flow path 49, for example, through a passage not shown, and film-cools the gas path surface 82i, etc.

[0046] The outer impingement plate 88o divides the cavity 85o of the outer shroud 80o into two spaces in the blade height direction Dh. A plurality of impingement holes 89 penetrating the outer impingement plate 88o in the blade height direction Dh are formed in the outer impingement plate 88o.

[0047] The cooling air Ac that has flowed into the cavity 85o of the outer shroud 80o is ejected radially inward Dri from multiple impingement holes 89 in the outer impingement plate 88o and collides with the anti-gas path surface 83o of the outer shroud 80o, thereby impinging and cooling this surface. After impingement cooling the anti-gas path surface 83o, the cooling air Ac is ejected into the combustion gas flow path 49, for example, via a passage not shown, and performs film cooling on the gas path surface 82o, etc.

[0048] As shown in Figures 3 and 4, the third space 60C is closed at the radially inner end Dri on the blade height second side Dh2 and open at the radially outer end Dro on the blade height first side Dh1. The radially inner end Dri of the blade body 51 forms a part of the anti-gas path surface 83i of the inner shroud 80i, and the radially outer end Dro of the blade body 51 forms a part of the anti-gas path surface 83o of the outer shroud 80o. Therefore, the opening 61C of the third space 60C opens at the anti-gas path surface 83o of the outer shroud 80o. The blade body 51 is formed with a plurality of third blade surface cooling passages 67C that penetrate from the inner wall surface 62C that defines the third space 60C to the blade surface of the blade body 51.

[0049] 3 and 4, the first space 60A and the second space 60B are closed at the radially inner end Dri on the blade height second side Dh2 and open at the radially outer end Dro on the blade height first side Dh1. The openings of the first space 60A and the second space 60B are open on the anti-gas path surface 83o of the outer shroud 80o, similar to the opening 61C of the third space 60C. The blade body 51 is formed with a plurality of first blade surface cooling passages 67A that penetrate from the inner wall surface 62A that defines the first space 60A to the blade surface of the blade body 51. Furthermore, the blade body 51 is formed with a plurality of second blade surface cooling passages 67B that penetrate from the inner wall surface 62B that defines the second space 60B to the blade surface of the blade body 51.

[0050] As shown in FIGS. 3 and 4 , the third insert 68C disposed in the third space 60C is cylindrical and extends in the radial direction Dr. The radially inner end Dri of the third insert 68C is closed, and the radially outer end Dro of the third insert 68C is open. Almost the entire third insert 68C is located within the third space 60C, but the radially outer portion Dro of the third insert 68C protrudes from the third space 60C toward the radially outer portion Dro, and the end of the radially outer portion Dro of the third insert 68C is located radially outer than the outer impingement plate 88o. Therefore, cooling air Ac can flow into the third insert 68C through the opening of the third insert 68C. The cylindrical third insert 68C is formed with a plurality of impingement holes 69 penetrating from the inner circumferential side to the outer circumferential side. For this reason, the cooling air Ac that has flowed into the third insert 68C is ejected from the multiple impingement holes 69 and collides with the inner wall surface 62C that defines the third space 60C, thereby impingement cooling this area. A portion of the cooling air Ac that has impingement cooled the inner wall surface 62C that defines the third space 60C is ejected into the combustion gas flow path 49 via the multiple third blade surface cooling passages 67C described above, thereby film cooling the blade surface.

[0051] The first insert 68A disposed in the first space 60A and the second insert 68B disposed in the second space 60B have substantially the same configuration as the third insert 68C described with reference to Figures 3 and 4. That is, like the third insert 68C, the first insert 68A and the second insert 68B are cylindrical and extend in the radial direction Dr. The ends of the radially inner side Dri of the first insert 68A and the second insert 68B are closed, and the ends of the radially outer side Dro of the first insert 68A and the second insert 68B are open. Almost the entire first insert 68A is located within the first space 60A, but the radially outer side Dro portion of the first insert 68A is First space 60AThe first insert 68A protrudes radially outward Dro from the first insert 68A, and the end of the radially outward Dro of the first insert 68A is located radially outward Dro of the outer impingement plate 88o. Therefore, cooling air Ac can flow into the first insert 68A through the opening of the first insert 68A. The cylindrical first insert 68A is also formed with a plurality of impingement holes 69 penetrating from the inner circumferential side to the outer circumferential side. Therefore, the cooling air Ac that has flowed into the first insert 68A is ejected from the plurality of impingement holes 69 and collides with the inner wall surface 62A that defines the first space 60A, thereby impinging and cooling this surface. The cooling air Ac that has impinged-cooled the inner wall surface 62A that defines the first space 60A is ejected into the combustion gas flow path 49 via the plurality of first blade surface cooling passages 67A described above, thereby film-cooling the blade surface. Furthermore, almost the entire second insert 68B is located within the second space 60B, but a portion of the second insert 68B on the radially outer side Dro protrudes from the second space 60B toward the radially outer side Dro, and the end of the second insert 68B on the radially outer side Dro is located radially outer than the outer impingement plate 88o. Therefore, cooling air Ac can flow into the second insert 68B through the opening of the second insert 68B. The cylindrical second insert 68B also has multiple impingement holes 69 penetrating from the inner circumferential side to the outer circumferential side. Therefore, the cooling air Ac that flows into the second insert 68B is ejected from the multiple impingement holes 69 and impinges on the inner wall surface 62B that defines the second space 60B, thereby impinging and cooling the inner wall surface 62B that defines the second space 60B. The cooling air Ac that has impinged-cooled the inner wall surface 62B that defines the second space 60B is ejected into the combustion gas flow path 49 via the multiple second blade surface cooling passages 67B described above, thereby film-cooling the blade surface.

[0052] The fourth space 60D is located on the axially most downstream side Dad of the multiple cooling air spaces 60. Therefore, hereinafter, this fourth space 60D will be referred to as the rear end space 60D. Furthermore, the third space 60C is adjacent to the rear end space 60D on the axially upstream side Dau. Therefore, hereinafter, this third space 60C will be referred to as the adjacent space 60C.

[0053] The aft end space 60D is closed at a radially inner end Dri, which is the blade height second side Dh2, and at a radially outer end Dro, which is the blade height first side Dh1. The axial upstream edge Dau of the aft end space 60D (the edge on the leading edge 52 side) is open and communicates with the adjacent space 60C. The inner wall surface 62D defining the aft end space 60D has a blade height first side inner wall surface 64D, a blade height second side inner wall surface 65D, a pressure side inner wall surface 63Dp, and a suction side inner wall surface 63Dn. The blade height first side inner wall surface 64D faces the blade height second side Dh2 and defines the edge of the blade height first side Dh1 of the aft end space 60D. The blade height second side inner wall surface 65D faces the blade height first side Dh1 and defines the edge of the blade height second side Dh2 of the aft end space 60D. The pressure side inner wall surface 63Dp faces the suction surface 54 and widens along the pressure surface 55 to define the edge of the aft end space 60D on the pressure surface 55 side. An edge of the pressure side inner wall surface 63Dp on the blade height first side Dh1 is connected to the blade height first side inner wall surface 64D. An edge of the pressure side inner wall surface 63Dp on the blade height second side Dh2 is connected to the blade height second side inner wall surface 65D. The suction side inner wall surface 63Dn faces the pressure surface 55 and widens along the suction surface 54, and is spaced away from the pressure side inner wall surface 63Dp toward the suction surface 54 to define the edge of the aft end space 60D on the suction surface 54 side. An edge of the suction side inner wall surface 63Dn on the blade height first side Dh1 is connected to the blade height first side inner wall surface 64D. An edge of the suction side inner wall surface 63Dn on the second blade height side Dh2 is connected to the second blade height side inner wall surface 65D. Furthermore, an edge of the suction side inner wall surface 63Dn on the downstream axial side Dad is connected to an edge of the pressure side inner wall surface 63Dp on the downstream axial side Dad.

[0054] A plurality of rear end cooling passages 67D are formed in the blade body 51, penetrating from the rear end space 60D to the combustion gas flow path. The rear end cooling passages 67D penetrate from the boundary between the axially downstream edge Dad of the suction side inner wall surface 63Dn and the axially downstream edge Dad of the pressure side inner wall surface 63Dp to the trailing edge 53 of the blade body 51. The multiple rear end cooling passages 67D are aligned in the blade height direction Dh.

[0055] In the rear end space 60D, a plurality of partition ribs 71 that are aligned in the blade height direction Dh and that partition the rear end space 60D in the blade height direction Dh, and a plurality of cylindrical or polygonal pillar-shaped pins 72 are arranged.

[0056] The partition ribs 71 extend in a direction substantially perpendicular to the blade height direction Dh and are joined to the pressure side inner wall surface 63Dp and the suction side inner wall surface 63Dn. The pins 72 extend in a direction substantially perpendicular to the camber line CL and are joined to the pressure side inner wall surface 63Dp and the suction side inner wall surface 63Dn.

[0057] Of the multiple partition ribs 71, at least one partition rib 71 forms an extended partition rib 71a that extends into the adjacent space 60C. Specifically, the extended partition rib 71a is disposed at a position that is 30 to 70% of the dimension in the blade height direction Dh of the rear end space 60D from the blade height second inner wall surface 65D that defines the rear end space 60D. In other words, the extended partition rib 71a is disposed near the center of the blade body 51 in the blade height direction Dh.

[0058] The inner wall surface 62C defining the adjacent space 60C (third space 60C) includes a blade height second-side inner wall surface 65C, a pressure side inner wall surface 63Cp, a suction side inner wall surface 63Cn, and a second partition wall surface 66C that faces the axial downstream side Dad of the second partition wall 58. The blade height second-side inner wall surface 65C faces the blade height first side Dh1 and defines the edge of the blade height second side Dh2 of the adjacent space 60C. The edge of the axial downstream side Dad of the blade height second-side inner wall surface 65C is connected to the edge of the axial upstream side Dau of the blade height second-side inner wall surface 65D that defines the aft end space 60D. The pressure side inner wall surface 63Cp faces the suction surface 54 and extends along the pressure surface 55 to define the edge of the aft end space 60D on the pressure surface 55 side. An edge of the pressure side inner wall surface 63Cp on the second blade height side Dh2 is connected to the second blade height side inner wall surface 65C. An edge of the pressure side inner wall surface 63Cp on the upstream axial side Dau is connected to the second partition wall surface 66C. An edge of the pressure side inner wall surface 63Cp on the downstream axial side Dad is connected to an edge of the pressure side inner wall surface 63Dp on the upstream axial side Dau that defines the rear end space 60D. The suction side inner wall surface 63Cn faces the pressure surface 55 and is connected to the suction surface Along 54The suction side inner wall surface 63Cn extends in a direction perpendicular to the blade height direction and is spaced from the pressure side inner wall surface 63Cp toward the suction side 54, defining the edge of the adjacent space 60C on the suction side 54 side. The edge of the suction side inner wall surface 63Cn on the second blade height side Dh2 is connected to the second blade height side inner wall surface 65C. The edge of the axial upstream side Dau of the suction side inner wall surface 63Cn is connected to the second partition wall surface 66C. The edge of the axial downstream side Dad of the suction side inner wall surface 63Cn is connected to the edge of the axial upstream side Dau of the suction side inner wall surface 63Dn that defines the rear end space 60D.

[0059] A portion of the extended partition rib 71a present within the adjacent space 60C is joined to the pressure-side inner wall surface 63Dp and the suction-side inner wall surface 63Cn of the inner wall surface 62C that defines the adjacent space 60C. As shown in Fig. 5, the extension dimension L of the extended partition rib 71a extending from the axial upstream-side edge Dau of the aft end space 60D (the edge on the leading edge 52 side) into the adjacent space 60C is smaller than twice the boundary width W, which is the distance between the pressure-side inner wall surface 63Dp and the suction-side inner wall surface 63Dn at the edge on the leading edge 52 side of the aft end space 60D. The edge on the leading edge 52 side of the aft end space 60D is the boundary between the adjacent space 60C and the aft end space 60D, and is also the opening 61D on the leading edge 52 side of the aft end space 60D. In addition, the edge of the rear end space 60D on the side of the leading edge 52 is the position of the edge of the pin 72 closest to the leading edge 52 among the multiple pins 72 in this embodiment.

[0060] Another portion of the cooling air Ac, which is ejected from the third insert 68C arranged in the adjacent space 60C that is the third space 60C and impingement-cools the inner wall surface 62C that defines the adjacent space 60C, flows into the aft end space 60D through the opening 61D of the aft end space 60D. As the cooling air Ac flows into the aft end space 60D, it convectively cools the partition ribs 71, the pins 72, and the inner wall surface 62D that defines the aft end space 60D. The cooling air Ac flows into the aft end cooling passages 67D. As the cooling air Ac flows into the aft end cooling passages 67D, it convectively cools the surfaces that define the aft end space 60D. The cooling air Ac is ejected from the trailing edge 53 of the blade-body 51 into the combustion gas flow path 49.

[0061] As described above, the pressure-side inner wall surface 63Dp and the suction-side inner wall surface 63Dn, which define the aft-end space 60D, are joined by a plurality of pins 72 and partition ribs 71. Meanwhile, because the third insert 68C is inserted into the adjacent space 60C adjacent to the aft-end space 60D, the pressure-side inner wall surface 63Cp and the suction-side inner wall surface 63Cn, which define the adjacent space 60C, are not joined by pins or the like. Therefore, the rigidity around the adjacent space 60C in the blade body 51 is lower than the rigidity around the aft-end space 60D in the blade body 51. As described in the "Problem to be Solved by the Invention" section, portions of the blade body 51 with low rigidity are prone to bulging, a creep deformation in the form of a bulging blade surface, due to the pressure difference between the inside and outside of the blade body 51 during gas turbine operation. When bulging occurs, the blade surface in this low-rigidity portion deforms as shown by the dashed two-dot line in FIG. 4 . When this bulging phenomenon occurs, not only does the aerodynamic performance of the stator vane 50 deteriorate, but the durability of the stator vane 50 also deteriorates. In particular, high stress occurs due to deformation caused by the bulging phenomenon near the boundary between the low rigidity portion of the wing-body 51 and the high rigidity portion of the wing-body 51. In other words, high stress occurs due to deformation caused by the bulging phenomenon near the boundary between the adjacent space 60C and the aft-end space 60D. Furthermore, the amount of deformation caused by the bulging phenomenon becomes large around the adjacent space 60C in the wing-body 51, near the center in the wing height direction Dh of the wing-body 51.

[0062] Therefore, in this embodiment, of the multiple partition ribs 71 arranged in the aft end space 60D, the multiple partition ribs 71 arranged near the center in the blade height direction Dh of the blade body 51 are extended into the adjacent space 60C to increase the rigidity near the boundary between the adjacent space 60C and the aft end space 60D and near the center in the blade height direction Dh of the blade body 51. As a result, in this embodiment, the occurrence of bulging is suppressed and deformation near the boundary between the adjacent space 60C and the aft end space 60D and near the center in the blade height direction Dh of the blade body 51 is suppressed.

[0063] Therefore, in this embodiment, the bulging strength of the stator blade 50 is improved, and it is possible to suppress a decrease in the aerodynamic performance and durability of the stator blade 50 due to the occurrence of the bulging phenomenon.

[0064] In this embodiment, as described above, the extension dimension L of the extended partition rib 71a extending from the edge of the aft end space 60D on the leading edge 52 side into the adjacent space 60C is smaller than twice the boundary width W, which is the distance between the pressure side inner wall surface 63Dp of the aft end space 60D and the suction side inner wall surface 63Dn of the aft end space 60D at the edge of the aft end space 60D on the leading edge 52 side. However, the extension dimension L of the extended partition rib 71a may be larger than twice the boundary width W. In this case, the bulging strength of the blade body 51 is increased compared to when the extension dimension L of the extended partition rib 71a is twice the boundary width W, but the increase in bulging strength is smaller than the increase in the extension dimension L. Furthermore, because this stator vane 50 is formed by casting, increasing the extension dimension L of the extended partition rib 71a makes casting correspondingly more difficult. Therefore, in this embodiment, the extension dimension L of the extended partition rib 71a is smaller than twice the boundary width W.

[0065] "First variant of the stationary blade" A first modified embodiment of the stationary vane will be described with reference to FIG.

[0066] In the stator vane 50 of the embodiment, as explained using Figure 3, among the multiple partition ribs 71, the multiple partition ribs 71 arranged at a position 30 to 70% of the dimension in the blade height direction Dh of the aft end space 60D from the blade height second side inner wall surface 65D that defines the aft end space 60D form extended partition ribs 71a.

[0067] 6, in the stator vane 50a of this modification, all of the partition ribs 71 form extended partition ribs 71a. Therefore, in this modification, the overall rigidity of the blade body 51 in the blade height direction Dh near the boundary between the adjacent space 60C and the aft-end space 60D can be increased.

[0068] "Second variant of the stationary blade" A second modified embodiment of the stationary vane will be described with reference to FIG.

[0069] In the stator vane 50 of the above embodiment, as explained using Figure 5, the portion of the extension partition rib 71a that exists within the adjacent space 60C is joined to the positive pressure side inner wall surface 63Cp and the negative pressure side inner wall surface 63Cn of the inner wall surface 62C that defines this adjacent space 60C.

[0070] As shown in Figure 7, in the stator vane 50b of this modified example, the portion of the extended partition rib 71b that exists within the adjacent space 60C is joined only to the negative pressure side inner wall surface 63Cn of the inner wall surface 62C that defines this adjacent space 60C, and is not joined to the positive pressure side inner wall surface 63Cp.

[0071] The static pressure acting on the pressure-side inner wall surface 63Cp defining the adjacent space 60C from within the adjacent space 60C is equal to the static pressure acting on the suction-side inner wall surface 63Cn defining the adjacent space 60C. Meanwhile, the flow velocity of the combustion gas G flowing along the suction surface 54 outside the blade-body 51 is higher than the flow velocity of the combustion gas G flowing along the pressure surface 55 outside the blade-body 51. Therefore, the static pressure acting on the suction surface 54 from outside the blade-body 51 is lower than the static pressure acting on the pressure surface 55 from outside the blade-body 51. Therefore, the pressure difference between the pressure in the adjacent space 60C and the pressure in the region along the suction surface 54 outside the blade-body 51 is greater than the pressure difference between the pressure in the adjacent space 60C and the pressure in the region along the pressure surface 55 outside the blade-body 51. Therefore, even if bulging occurs around the adjacent space 60C, the amount of deformation due to the bulging phenomenon is greater on the suction surface 54 side than on the pressure surface 55 side.

[0072] Therefore, in this modified example, the portion of the extension partition rib 71b that exists within the adjacent space 60C is joined only to the negative pressure side inner wall surface 63Cn of the inner wall surface 62C that defines this adjacent space 60C, thereby increasing the rigidity only on the negative pressure surface 54 side near the boundary between the adjacent space 60C and the rear end space 60D.

[0073] In this modified example, the space occupied by the extended partition rib 71b within the adjacent space 60C is smaller than in the above embodiment, thereby improving the ease of inserting the third insert 68C into the adjacent space 60C and the freedom of layout of the third insert 68C within the adjacent space 60C.

[0074] This modification is a modification of the stator vane 50 in the above embodiment. However, this modification may be applied to the stator vane 50a in the first modification.

[0075] "Other Variations of Stator Blades" Each of the stator vanes 50, 50a, 50b in the above embodiment and each modified example has four spaces, from the first space 60A to the fourth space 60D. However, the stator vane may have more spaces. Furthermore, each of the stator vanes 50, 50a, 50b in the above embodiment and each modified example has inserts arranged in all spaces except for the aft-end space 60D, which is the fourth space 60D. However, it is not necessary for inserts to be arranged in all spaces except for the aft-end space 60D.

[0076] The stator vanes 50, 50a, 50b in the above-described embodiment and each modified example are all stator vanes that constitute the first-stage stator vane row 46. However, the stator vanes may also be stator vanes that constitute the stator vane row 46 on the axially downstream side Dad of the first-stage stator vane row 46.

[0077] Furthermore, the present disclosure is not limited to the embodiment and modifications described above. Various additions, modifications, substitutions, partial deletions, etc. are possible within the scope that does not deviate from the conceptual idea and intent of the present invention derived from the content defined in the claims and their equivalents.

[0078] "Addendum" The stationary blades in the above-described embodiment and each of the modified examples can be understood, for example, as follows.

[0079] (1) The stationary blade in the first aspect is The gas turbine 10 includes stator blades 50, 50a, and 50b, each of which has a cross section shaped like an airfoil and has a blade body 51 extending in a blade height direction Dh having a directional component perpendicular to the cross section. The blade body 51 has a leading edge 52 and a trailing edge 53 extending in the blade height direction Dh, a pressure surface 55 and a suction surface 54 extending in the blade height direction Dh and connecting the leading edge 52 and the trailing edge 53, an aft-end space 60D and an adjacent space 60C located between the leading edge 52 and the trailing edge 53 and between the pressure surface 55 and the suction surface 54, and a plurality of aft-end cooling passages 67D penetrating from the aft-end space 60D to the trailing edge 53. The adjacent space 60C is located closer to the leading edge 52 than the aft-end space 60D. An edge of the aft-end space 60D on the leading edge 52 side is open and communicates with the aft-end space 60D. The adjacent space 60C and the aft-end space 60D are both defined by inner wall surfaces 62C, 62D. The inner wall surface 62C of the adjacent space 60C and the inner wall surface 62D of the rear end space 60D each have a pressure side inner wall surface 63Cp, 63Dp that extends along the pressure surface 55, and a suction side inner wall surface 63Cn, 63Dn that extends along the suction surface 54 and is spaced away from the pressure side inner wall surface 63Cp, 63Dp toward the suction surface 54. The pressure side inner wall surface 63Cp of the adjacent space 60C is connected to the pressure side inner wall surface 63Dp of the rear end space 60D. The suction side inner wall surface 63Cn of the adjacent space 60C is connected to the suction side inner wall surface 63Dn of the rear end space 60D. A plurality of partition ribs 71 and a plurality of pins 72 are arranged in the rear end space 60D, and are aligned in the blade height direction Dh to divide the rear end space 60D in the blade height direction Dh. Each of the pins 72 is joined to the pressure side inner wall surface 63Dp of the rear end space 60D and the suction side inner wall surface 63Dn of the rear end space 60D. At least one of the plurality of partition ribs 71 extends into the adjacent space 60C and forms an extended partition rib 71a, 71b joined to the inner wall surface 62C that defines the adjacent space 60C.

[0080] In this embodiment, the pressure side inner wall surface 63Dp and the suction side inner wall surface 63Dn that define the aft end space 60D are joined by multiple pins 72. Therefore, the rigidity around the aft end space 60D in the blade-body 51 is higher than the rigidity around the adjacent space 60C in the blade-body 51. In other words, the rigidity around the adjacent space 60C in the blade-body 51 is lower than the rigidity around the aft end space 60D in the blade-body 51. Bulging is likely to occur in low-rigidity portions of the blade-body 51. When this bulging occurs, not only does the aerodynamic performance of the stator vane 50 deteriorate, but the durability of the stator vane 50 also deteriorates. In particular, high stress occurs due to deformation caused by bulging near the boundary between the low-rigidity portion of the blade-body 51 and the high-rigidity portion of the blade-body 51. In other words, high stress occurs due to deformation caused by bulging near the boundary between the adjacent space 60C and the aft end space 60D.

[0081] Therefore, in this embodiment, at least one of the partition ribs 71 arranged in the rear end space 60D is extended into the adjacent space 60C to increase the rigidity near the boundary between the adjacent space 60C and the rear end space 60D. As a result, in this embodiment, the occurrence of the bulging phenomenon is suppressed, and deformation near the boundary between the adjacent space 60C and the rear end space 60D is suppressed.

[0082] Therefore, in this embodiment, the bulging strength of the stator blades 50, 50a, 50b is improved, and it is possible to suppress a decrease in the aerodynamic performance and durability of the stator blades 50, 50a, 50b due to the occurrence of the bulging phenomenon.

[0083] (2) The stationary blade in the second aspect is In the stator vane 50 described in the first embodiment, the extended partition rib 71a is positioned at a position 30 to 70% of the dimension of the aft end space 60D in the blade height direction Dh from one end of the aft end space 60D in the blade height direction Dh.

[0084] The amount of deformation due to the bulging phenomenon increases around the adjacent space 60C in the blade body 51 and near the center in the blade height direction Dh of the blade body 51. Therefore, in this embodiment, among the multiple partition ribs 71, the partition rib 71 located at a position 30 to 70% of the dimension of the aft end space 60D in the blade height direction Dh from one end of the aft end space 60D in the blade height direction Dh, in other words, the partition rib 71 located in the center of the blade body 51 in the blade height direction Dh, is designated as the extended partition rib 71a. As a result, in this embodiment, deformation near the boundary between the adjacent space 60C and the aft end space 60D and near the center in the blade height direction Dh of the blade body 51 can be suppressed.

[0085] (3) The stationary blade in the third aspect is In the vane 50a in the first embodiment or the second embodiment, all of the plurality of partition ribs 71 are the extension partition ribs 71a and 71b.

[0086] In this embodiment, the overall rigidity of the wing body 51 in the wing height direction Dh near the boundary between the adjacent space 60C and the trailing end space 60D can be increased.

[0087] (4) The stationary blade in the fourth aspect is In the stator vanes 50, 50a, 50b in any one of the first to third embodiments, the extension dimension L of the extension partition ribs 71a, 71b extending from the edge of the rear end space 60D on the leading edge 52 side into the adjacent space 60C is smaller than twice the boundary width W, which is the distance between the positive pressure side inner wall surface 63Dp and the negative pressure side inner wall surface 63Dn at the edge of the rear end space 60D on the leading edge 52 side.

[0088] The extension dimension L of the extended partition ribs 71a, 71b may be greater than twice the boundary width W. In this case, the bulging strength of the blade body 51 is increased compared to when the extension dimension L of the extended partition ribs 71a, 71b is twice the boundary width W, but the increase in bulging strength is smaller than the increase in the extension dimension L. Furthermore, since the stator vanes 50, 50a, 50b are formed by casting, increasing the extension dimension L of the extended partition ribs 71a, 71b makes casting correspondingly more difficult. Therefore, in this embodiment, the increase in bulging strength is weighed against the difficulty of casting, and the extension dimension L of the extended partition ribs 71a, 71b is set to be less than twice the boundary width W.

[0089] (5) The stationary blade in the fifth aspect is In the vane 50b in any one of the first to fourth embodiments, the extension partition rib 71b is joined to the negative pressure side inner wall surface 63Dn of the adjacent space 60C and is not joined to the positive pressure side inner wall surface 63Dp of the adjacent space 60C.

[0090] The static pressure acting on the pressure-side inner wall surface 63Cp defining the adjacent space 60C from within the adjacent space 60C is equal to the static pressure acting on the suction-side inner wall surface 63Cn defining the adjacent space 60C. Meanwhile, the flow velocity of the combustion gas G flowing along the suction surface 54 outside the blade-body 51 is higher than the flow velocity of the combustion gas G flowing along the pressure surface 55 outside the blade-body 51. Therefore, the static pressure acting on the suction surface 54 from outside the blade-body 51 is lower than the static pressure acting on the pressure surface 55 from outside the blade-body 51. Therefore, the pressure difference between the pressure in the adjacent space 60C and the pressure in the region along the suction surface 54 outside the blade-body 51 is greater than the pressure difference between the pressure in the adjacent space 60C and the pressure in the region along the pressure surface 55 outside the blade-body 51. Therefore, even if bulging occurs around the adjacent space 60C, the amount of deformation due to the bulging phenomenon is greater on the suction surface 54 side than on the pressure surface 55 side.

[0091] Therefore, in this embodiment, the portion of the extension partition rib 71b that exists within the adjacent space 60C is joined only to the negative pressure side inner wall surface 63Cn of the inner wall surface 62C that defines this adjacent space 60C, thereby increasing the rigidity only on the negative pressure surface 54 side near the boundary between the adjacent space 60C and the rear end space 60D.

[0092] (6) The stator blade in the sixth aspect is The vane 50, 50a, 50b according to any one of the first to fifth aspects further includes a cylindrical insert 68C arranged in the adjacent space 60C. The insert 68C has a plurality of impingement holes 69 formed therein, penetrating from the inner circumferential side to the outer circumferential side.

[0093] In this embodiment, the cooling air Ac that has flowed into the insert 68C is ejected from the impingement holes 69 and collides with the inner wall surface 62C that defines the adjacent space 60C, thereby impinging and cooling this area. Therefore, in this embodiment, the blade surface along the inner wall surface 62C that defines the adjacent space 60C can be efficiently cooled.

[0094] The gas turbine in the above embodiment can be understood as follows, for example. (7) A gas turbine according to a seventh aspect includes: The turbine includes a stator vane 50, 50a, 50b according to any one of the first to sixth aspects, a rotor 41 that rotates about an axis Ar, and a casing 45 that covers the outer circumferential side of the rotor 41. The stator vanes 50, 50a, 50b are fixed to the inner circumferential surface of the casing 45. [Industrial Applicability]

[0095] According to one aspect of the present disclosure, the bulging strength of the stator vane can be improved, thereby suppressing deterioration in the aerodynamic performance and durability of the stator vane. [Explanation of symbols]

[0096] 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 25: Compressor casing 26: Stator blade row 30: Combustor 40: Turbine 41: Turbine rotor 42: Rotor shaft 43: Moving blade row 45: Turbine casing 46: Stator blade row 49: Combustion gas flow path 50,50a,50b: Stator blade 51: Wing body 52: Leading edge 53: Trailing edge 54: Negative pressure surface 55: Pressure surface 57:First bulkhead 58:Second bulkhead 60: Cooling air space 60A: First space 62A: Inner wall 67A: First wing surface cooling passage 68A: First insert 69; Impingement foramen 60B:Second space 62B: Inner wall 67B:Second wing surface cooling passage 68B: Second insert 60C: Third space (adjacent space) 61C:Aperture 62C: Inner wall 63Cp: Pressure side inner wall 63Cn: Negative pressure side inner wall 65C: Second inner wall of blade height 66C:Second bulkhead surface 67C: Third wing surface cooling passage 68C: Third insert 60D: Fourth space (rear end space) 61D:Aperture 62D: Inner wall 63Dp: Pressure side inner wall 63Dn: Negative pressure side inner wall 64D: First inner wall of blade height 65D: Second inner wall of blade height 67D: Rear end cooling passage 71: Partition rib 71a, 71b: Extension partition rib 72: Pin 80i: Inner shroud 80o: Outer shroud 81i, 81o: Shroud body 82i, 82o: Gas path surface 83i, 83o: Anti-gas path surface 84i,84o: Peripheral wall 85i, 85o: Cavity 86i: Retainer 88i: Medial impingement plate 88o: Lateral impingement plate 89: Impingement hole A: Air Ac: Cooling air F:Fuel G: Combustion gas Ar: Axis line CL: Camber line Da: Axial direction Dau: Axis upstream side Dad: Downstream of the axis Dc: Circumferential direction Dr: Radial direction Dri: Radial inner direction Dro: Radial outer side Dh: Wing height direction Dh1: First wing height Dh2: Wing height second side L: Extension dimension W: Border width

Claims

1. In a stationary blade provided in a gas turbine, The cross section has an airfoil shape and includes a wing body extending in a wing height direction having a directional component perpendicular to the cross section, the blade body has a leading edge and a trailing edge extending in the blade height direction, a pressure surface and a suction surface extending in the blade height direction and connecting the leading edge and the trailing edge, an aft-end space and an adjacent space located between the leading edge and the trailing edge and between the pressure surface and the suction surface, and a plurality of aft-end cooling passages penetrating from the aft-end space to the trailing edge, the adjacent space is located closer to the leading edge than the rear end space, an edge of the rear end space on the front edge side is open and communicates with the rear end space; the adjacent space and the rear end space are both defined by an inner wall surface, the inner wall surface of the adjacent space and the inner wall surface of the rear end space each have a pressure-side inner wall surface that extends along the pressure surface, and a suction-side inner wall surface that extends along the suction surface and is spaced from the pressure-side inner wall surface toward the suction surface, the pressure side inner wall surface of the adjacent space and the pressure side inner wall surface of the rear end space are connected to each other, the negative pressure side inner wall surface of the adjacent space and the negative pressure side inner wall surface of the rear end space are connected to each other, a plurality of partition ribs and a plurality of pins are arranged in the rear end space and are aligned in the blade height direction to partition the rear end space in the blade height direction; each of the plurality of pins is joined to the positive pressure side inner wall surface of the rear end space and the negative pressure side inner wall surface of the rear end space; At least one of the plurality of partition ribs extends into the adjacent space and forms an extended partition rib joined to the inner wall surface that defines the adjacent space, a portion of the extension partition rib within the adjacent space having a portion whose protrusion from the inner wall surface gradually decreases toward the leading edge, further comprising a cylindrical insert disposed within the adjacent space; The insert has a plurality of impingement holes formed therein, the impingement holes penetrating from the inner circumferential side to the outer circumferential side. Static wing.

2. In the vane described in claim 1, In the adjacent space, a pin protruding from the positive pressure side inner wall surface of the adjacent space and a pin protruding from the negative pressure side inner wall surface of the adjacent space are not arranged. Static wing.

3. The vane according to claim 1, The extension partition rib is disposed at a position that is 30 to 70% of the dimension of the rear end space in the blade height direction from one end of the rear end space in the blade height direction. Static wing.

4. The vane according to claim 1 or 3, All of the plurality of partition ribs are the extension partition ribs. Static wing.

5. The vane according to claim 1 or 3, an extension dimension of the extension partition rib extending from the leading edge side edge of the aft end space into the adjacent space is smaller than twice a boundary width which is a distance between the pressure side inner wall surface and the suction side inner wall surface at the leading edge side edge of the aft end space; Static wing.

6. The vane according to claim 1 or 3, the extension partition rib is joined to the negative pressure side inner wall surface of the adjacent space and is not joined to the positive pressure side inner wall surface of the adjacent space; Static wing.

7. The vane according to claim 1 or 3; a rotor that rotates around an axis; a casing that covers the outer periphery of the rotor; Equipped with The stator vane is fixed to an inner circumferential surface of the casing. Gas turbine.

Images