Compressor stator vane, compressor having the same, and gas turbine facility

Abstract

To suppress a generation of a boundary layer formed along a negative pressure face of a compressor stator vane.SOLUTION: A compressor stator vane includes: a vane body with a cross section forming a vane form; and a first shroud provided at a first side end of a vane height of the vane body. The vane body and the first shroud are connected in the vane body and the first shroud, and a cavity is formed which opens on a first opposite gas path face and a first side peripheral face. A plurality of suction holes having an inlet opening that opens on a negative pressure face and an outlet opening that opens on an inner face defining the cavity are formed in the vane body. In a region of a predefined width of the negative pressure face in a front-rear direction in which a front edge and a rear edge are aligned, and a region from the first side end of the vane height to a second side end of the vane height of the negative pressure face, an opening forming region is formed. The inlet opening of each of the plurality of suction holes that align in a vane height direction and the front-rear direction is formed in the opening forming region.SELECTED DRAWING: Figure 3

Description

[Technical Field]

[0001] The present disclosure relates to a compressor stator vane, a compressor including the same, and gas turbine equipment including the compressor. [Background technology]

[0002] A gas turbine includes a compressor capable of compressing air to generate compressed air, a combustor capable of burning fuel in the compressed air to generate combustion gas, and a turbine capable of being driven by the combustion gas. The compressor includes a rotor rotating about an axis, a casing covering the rotor, and multiple stator blade rows. The rotor has a rotor shaft extending in an axial direction about the axis, and multiple rotor blade rows attached to the rotor shaft. The multiple rotor blade rows are arranged at intervals from each other in the axial direction. Each of the multiple rotor blade rows has a plurality of rotor blades arranged in a circumferential direction about the axis. Multiple stator blade rows are provided inside the casing. Each of the multiple stator blade rows is arranged axially downstream of one of the multiple rotor blade rows. Each of the multiple stator blade rows has a plurality of stator blades arranged in a circumferential direction about the axis.

[0003] The following Patent Documents 1 and 2 disclose compressor stator vanes.

[0004] The stator vane disclosed in Patent Document 1 has a hollow portion (cavity) formed in the vane that penetrates in the radial direction relative to the axis. A cooling medium such as cooling air is supplied to the rotor shaft from outside the casing through the hollow portion (cavity) in the vane and the casing. The technology disclosed in Patent Document 1 suppresses a decrease in creep strength of the stator vane and the rotor shaft by supplying cooling air to the stator vane and the rotor shaft.

[0005] The stator vane disclosed in Patent Document 2 has a gap formed that penetrates from the pressure surface to the suction surface of the stator vane. During operation of the compressor, air leaks from the pressure surface to the suction surface through the gap. The technology disclosed in Patent Document 2 aims to improve compression efficiency by suppressing separation of the boundary layer formed along the suction surface through the air leakage from the pressure surface to the suction surface. [Prior art documents] [Patent documents]

[0006] [Patent Document 1] Japanese Patent Application Publication No. 11-315800 [Patent Document 2] Japanese Patent Application Laid-Open No. 2013-100784 Summary of the Invention [Problem to be solved by the invention]

[0007] The present disclosure aims to provide a technology that can suppress the development of a boundary layer formed along the suction surface of a compressor stator vane, thereby expanding the operating range of the compressor and improving the efficiency of the compressor. [Means for solving the problem]

[0008] In order to achieve the above object, a compressor stator vane according to one aspect of the invention comprises: The present invention comprises a blade body having an airfoil-shaped cross section and extending in a blade height direction including a directional component perpendicular to the cross section, a first shroud provided at an end of the blade body on the first blade height side out of a first blade height side and a second blade height side in the blade height direction, and a second shroud provided at an end of the blade body on the second blade height side. The blade body has a leading edge, a trailing edge, a pressure side connecting the leading edge and the trailing edge, and a suction side connecting the leading edge and the trailing edge and in a back-to-back relationship with the pressure side. The first shroud has a first gas path surface facing the second blade height side and extending from the end of the blade body on the first blade height side in a direction including a directional component perpendicular to the blade height direction, a first counter-gas path surface facing the first blade height side and in a back-to-back relationship with the first gas path surface, and a first side peripheral surface connecting an edge of the first gas path surface to an edge of the first counter-gas path surface. The second shroud has a second gas path surface facing the first blade height side and extending from the end of the blade body on the second blade height side in a direction including a directional component perpendicular to the blade height direction, and a second counter-gas path surface facing the second blade height side and back-to-back with the second gas path surface. A cavity is formed in the blade body and the first shroud, connecting within the blade body and the first shroud and opening at the first counter-gas path surface or the first peripheral surface. The blade body is formed with a plurality of suction holes, each having an inlet opening at the suction surface and an outlet opening at an inner surface defining the cavity, penetrating from the suction surface to the inner surface defining the cavity. An opening formation region is formed in the suction surface, the region having a predetermined width in the fore-aft direction where the leading edge and the trailing edge are aligned, and extending from the end of the suction surface on the first blade height side to the end of the second blade height side. The opening formation region has an inlet opening for each of the plurality of suction holes aligned in the blade height direction and the fore-aft direction.

[0009] In order to achieve the above object, there is provided a compressor according to one aspect of the invention, comprising: The compressor includes a compressor rotor rotatable about an axis, a compressor casing covering the compressor rotor, and a plurality of stator vane rows lined up in the axial direction along which the axis extends. The compressor rotor has a rotor shaft extending in the axial direction about the axis, and a plurality of rotor blade rows lined up in the axial direction and attached to the rotor shaft. Each of the plurality of stator vane rows is disposed downstream in the axial direction of any one of the plurality of rotor blade rows and attached to the compressor casing. Each of the plurality of stator vane rows has a plurality of stator vanes lined up in the circumferential direction about the axis. Each of the plurality of stator vane rows has a plurality of stator vanes lined up in the circumferential direction about the axis. Each of the plurality of stator vane rows has a plurality of stator vanes that are compressor stator vanes according to the one aspect. The fore-aft direction is the axial direction. The blade height direction is a radial direction relative to the axis. The first blade height side is the radially outer side of a radially inner side and a radially outer side in the radial direction. The second blade height side is the radially inner side.

[0010] In order to achieve the above object, one aspect of the invention is a gas turbine facility comprising: a gas turbine including the compressor, a combustor capable of burning fuel in air compressed by the compressor to generate combustion gas, and a turbine capable of being driven by the combustion gas; and a cooling device; The compressor casing is cylindrical about the axis and includes one or more blade rings that hold some of the multiple stator vane rows, and a casing body that is arranged outer circumferentially of the one or more blade rings and to which the one or more blade rings are attached. Of the one or more blade rings, the blade ring that holds at least one stator vane row has a blade ring bleed passage that penetrates from its inner circumferential side to its outer circumferential side and communicates with the cavities of each of the multiple stator vanes in the at least one stator vane row, allowing air to flow in from the cavities. The casing body has a body bleed passage that penetrates from its inner circumferential side to its outer circumferential side, allowing air to flow in from the blade ring bleed passage and to be exhausted to the outer circumferential side of the casing body. The turbine includes a turbine rotor that is rotatable about the axis, a turbine casing that covers the turbine rotor, and multiple stator vane rows that are arranged in the axial direction and arranged inner circumferentially of the turbine casing. The cooling device includes a bleed line connected to the main bleed air flow path of the compressor casing, a cooler capable of cooling air from the bleed line, a boost compressor capable of compressing the air cooled by the cooler, and a cooling air line capable of guiding the air cooled by the cooler and compressed by the boost compressor to at least one of the plurality of stator blade rows of the turbine. [Effects of the Invention]

[0011] According to one aspect of the present disclosure, it is possible to suppress the development of a boundary layer formed along the suction surface of a compressor stator vane, thereby expanding the operating range of the compressor and improving the efficiency of the compressor. [Brief explanation of the drawings]

[0012] [Figure 1] 1 is a schematic cross-sectional view of a gas turbine facility according to an embodiment of the present disclosure; [Figure 2] 1 is a cross-sectional view of a main portion of a gas turbine in an embodiment according to the present disclosure. FIG. [Figure 3] FIG. 2 is a side view of the stator blade in the first embodiment according to the present disclosure. [Figure 4] FIG. 4 is a cross-sectional view taken along line IV-IV in FIG. [Figure 5] FIG. 4 is a cross-sectional view taken along line VV in FIG. [Figure 6] FIG. 2 is a cross-sectional view of a main portion of a wing body according to the first embodiment of the present disclosure. [Figure 7] 10 is a graph showing the relationship between the incidence angle and pressure loss when the central position in the axial direction of the opening formation region is changed. [Figure 8] 10 is a graph showing the relationship between incidence angle and pressure loss when the width of the blade-body cavity in the axial direction is changed. [Figure 9] FIG. 4 is a side view of a stator blade in a second embodiment according to the present disclosure. [Figure 10] 10 is a graph showing the relationship between the incidence angle and pressure loss when the axial center position in the opening formation region and the opening density in the inner region are changed. [Figure 11] FIG. 10 is a side view of a stator vane in a third embodiment according to the present disclosure. [Figure 12] FIG. 10 is a side view of a stator vane in a fourth embodiment according to the present disclosure. [Figure 13] 10 is a graph showing the relationship between the incidence angle and pressure loss when the shape of each region in the opening formation region and the opening density of each region are changed. [Figure 14] FIG. 10 is a side view of a stator vane in a fifth embodiment according to the present disclosure. [Figure 15] 15 is a cross-sectional view taken along line XV-XV in FIG. 14. [Figure 16] 16 is a cross-sectional view taken along line XVI-XVI in FIG. 14. [Figure 17] 10 is a graph showing the relationship between the incidence angle and pressure loss when the presence or absence of suction holes in the outer shroud and the inner shroud is changed. DETAILED DESCRIPTION OF THE INVENTION

[0013] Various embodiments and modifications of the present disclosure will be described in detail below with reference to the drawings.

[0014] "Embodiment of gas turbine facility" An embodiment of a gas turbine facility will be described with reference to FIGS.

[0015] 1, the gas turbine facility includes a gas turbine 10 and a cooling device 16. The gas turbine 10 includes a compressor 40 capable of compressing air A to generate compressed air, a plurality of combustors 20 capable of burning fuel F in the compressed air to generate combustion gas G, and a turbine 30 capable of being driven by the combustion gas G.

[0016] The compressor 40 is a multi-stage axial flow compressor. The compressor 40 includes a compressor rotor 41 rotatable about an axis Ar, a compressor casing 45 enclosing the compressor rotor 41, and multiple stator vane rows 48. The turbine 30 includes a turbine rotor 31 rotatable about an axis Ar, a turbine casing 35 enclosing the turbine rotor 31, and multiple stator vane rows 38. Hereinafter, the direction in which the axis Ar extends is referred to as the axial direction Da, one side of the axial direction Da is referred to as the axial upstream side Dau, and the other side is referred to as the axial downstream side Dad. The radial direction relative to the axis Ar is simply referred to as the radial direction Dr, and the side of the radial direction Dr approaching the axis Ar is referred to as the radial inner side Dri, and the side away from the axis Ar is referred to as the radial outer side Dro. The circumferential direction centered on the axis Ar is simply referred to as the circumferential direction Dc.

[0017] The compressor 40 is disposed on the axial upstream side Dau with respect to the turbine 30. The compressor rotor 41 and the turbine rotor 31 are positioned on the same axis Ar and are connected to each other to form the gas turbine rotor 11. For example, a rotor of a generator GEN is connected to this gas turbine rotor 11. The gas turbine 10 further includes an intermediate casing 14 disposed between the compressor casing 45 and the turbine casing 35. Compressed air from the compressor 40 flows into this intermediate casing 14. The multiple combustors 20 are attached to the intermediate casing 14 and aligned in the circumferential direction Dc. The compressor casing 45, the intermediate casing 14, and the turbine casing 35 are connected to each other to form the gas turbine casing 15.

[0018] The compressor rotor 41 has a rotor shaft 42 that extends in the axial direction Da around 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 48 is arranged on the axial downstream side Dad of each of the plurality of rotor blade rows 43. Each stator blade row 48 is provided inside the compressor casing 45. Each stator blade row 48 is made up of a plurality of stator blades aligned in the circumferential direction Dc.

[0019] The turbine rotor 31 has a rotor shaft 32 extending in the axial direction Da centered on the axis Ar, and a plurality of rotor blade rows 33 attached to the rotor shaft 32. The plurality of rotor blade rows 33 are aligned in the axial direction Da. Each rotor blade row 33 is made up of a plurality of rotor blades aligned in the circumferential direction Dc. One of a plurality of stator blade rows 38 is arranged on the axial upstream side Dau of each of the plurality of rotor blade rows 33. Each stator blade row 38 is provided inside the turbine casing 35. Each stator blade row 38 is made up of a plurality of stator blades aligned in the circumferential direction Dc.

[0020] The cooling device 16 has an extraction line 17a, a cooler 18, a cooling air line 17b, and a boost compressor 19. One end of the extraction line 17a is connected to a compressor casing 45. Air inside the compressor casing 45 can flow into this extraction line 17a. The cooler 18 can cool the air from the extraction line 17a. The cooling air line 17b is connected to a discharge port of the boost compressor 19. This cooling air line 17b can guide the air cooled by the cooler 18 and compressed by the boost compressor 19 to at least one of the multiple stator blade rows 38 of the turbine 30.

[0021] As shown in Fig. 2, the compressor casing 45 has a plurality of blade rings 47, 47a and a casing main body 46. The plurality of blade rings 47, 47a are cylindrical and centered on the axis Ar. The plurality of blade rings 47, 47a are aligned in the axial direction Da. Each of the plurality of blade rings 47, 47a holds one or more stator blade rows 48, 48a.

[0022] Each of the multiple stator blades 50, 50a constituting the stator blade rows 48, 48a includes a blade body 51, a first shroud 61o, and a second shroud 61i. The blade body 51 has an airfoil-shaped cross section and extends in a blade height direction Dr, which includes a component perpendicular to the cross section. The blade body 51 includes a leading edge 51L, a trailing edge 51T, a pressure surface 52p connecting the leading edge 51L and the trailing edge 51T, and a suction surface 52n connecting the leading edge 51L and the trailing edge 51T and facing back-to-back with the pressure surface 52p. The first shroud 61o is provided at the end of the blade height first side Dro of the blade body 51 in the blade height direction Dr. The second shroud 61i is provided at the end of the blade height second side Dri of the blade body 51. The first shroud 61o has a first gas path surface 62o that faces the blade height second side Dri and extends from an end of the blade height first side Dro of the blade body 51 in a direction including a directional component perpendicular to the blade height direction Dr, a first counter-gas path surface 63o that faces the blade height first side Dro and is back-to-back with the first gas path surface 62o, and a first side peripheral surface 64o that connects the edge of the first gas path surface 62o with the edge of the first counter-gas path surface 63o. The second shroud 61i has a second gas path surface 62i that faces the blade height first side Dro and extends from an end of the blade height second side Dri of the blade body 51 in a direction including a directional component perpendicular to the blade height direction Dr, and a second counter-gas path surface 63i that faces the blade height second side Dri and is back-to-back with the second gas path surface 62i.

[0023] The blade rings 47, 47a have a gas path surface 47p facing the radially inward direction Dri and defining the outer edge of the annular compressed air flow path through which air flows, and a blade groove 47g recessed from the gas path surface 47p toward the radially outward direction Dro. The first shroud 61o of the stator vane 50, 50a is fitted into the blade groove 47g. Therefore, when the stator vane 50, 50a is attached to the compressor casing 45, the blade height direction Dr becomes the radial direction Dr. Furthermore, the blade height first side Dro becomes the radially outward direction Dro, and the blade height second side Dri becomes the radially inward direction Dri. Furthermore, the longitudinal direction Da in which the leading edge 51L and the trailing edge 51T of the blade body 51 are aligned becomes the axial direction Da. Furthermore, the side in the fore-aft direction Da where the leading edge 51L is located relative to the trailing edge 51T is the axial upstream side Dau, and the side in the fore-aft direction Da where the trailing edge 51T is located relative to the leading edge 51L is the axial downstream side Dad. Therefore, hereinafter, the blade height direction Dr will be referred to as the radial direction Dr, the blade height first side Dro will be referred to as the radially outer side Dro, the blade height second side Dri will be referred to as the radially inner side Dri, the fore-aft direction Da will be referred to as the axial direction Da, the side of the leading edge 51L in the fore-aft direction Da will be referred to as the axial upstream side Dau, and the side of the trailing edge 51T in the fore-aft direction Da will be referred to as the axial downstream side Dad. Furthermore, the side in the circumferential direction Dc where the pressure surface 52p is located relative to the suction surface 52n will be referred to as the circumferential pressure side Dcp, and the side in the circumferential direction Dc where the suction surface 52n is located relative to the pressure surface 52p will be referred to as the circumferential suction side Dcn. Furthermore, the first shroud 61o is referred to as the outer shroud 61o, the first gas path surface 62o of the first shroud 61o is referred to as the outer gas path surface 62o, and the first counter-gas path surface 63o of the first shroud 61o is referred to as the outer counter-gas path surface 63o. Furthermore, the second shroud 61i is referred to as the inner shroud 61i, the second gas path surface 62i of the second shroud 61i is referred to as the inner gas path surface 62i, and the second counter-gas path surface 63i of the second shroud 61i is referred to as the inner counter-gas path surface 63i.

[0024] "First embodiment of compressor vane" A first embodiment of the compressor vane will be described below.

[0025] As shown in FIG. 2, the compressor stator vane 50a in this embodiment is a stator vane that constitutes one of the stator vane rows 48a among the plurality of stator vane rows 48, 48a.

[0026] As shown in FIGS. 3 to 5, the stator vane 50a has a cavity 70 formed within the inner shroud 61i, the blade body 51, and the outer shroud 61o. The side peripheral surface (first side peripheral surface) 64o of the outer shroud 61o has a leading end surface 64f facing the axial upstream side Dau, a trailing end surface 64b facing the axial downstream side Dad and in a back-to-back relationship with the leading end surface 64f, and a pair of side end surfaces 64s facing the circumferential direction Dc. The cavity 70 includes an inner cavity 73 within the inner shroud 61i, a blade-body cavity 72 within the blade body 51, and an outer cavity 71 within the outer shroud 61o. The inner cavity 73 is connected to the blade-body cavity 72. The blade-body cavity 72 is connected to the outer cavity 71. The outer cavity 71 opens at the leading end surface 64f of the outer shroud 61o.

[0027] As shown in Figures 3 and 4, the blade body 51 is formed with a plurality of suction holes 55. Each suction hole 55 has an inlet opening 55i that opens at the suction surface 52n of the blade body 51 and an outlet opening 55o that opens at a suction-side inner surface 72p, which is the inner surface of the blade-body cavity 72 that is back-to-back with the suction surface 52n. Thus, each suction hole 55 penetrates from the suction surface 52n to the suction-side inner surface 72p. A portion of the air flowing along the suction surface 52n of the blade body 51 flows into the cavity 70 through the plurality of suction holes 55. As shown in Figure 2, the blade ring 47a that holds the stator vane row 48a has a blade ring bleed passage 47e that penetrates from the inner periphery to the outer periphery and communicates with the cavity 70 for each of the plurality of stator vanes 50a of the stator vane row 48a. The blade ring bleed air passage 47e is connected to the opening of the cavity 70 of each of the multiple stator vanes 50a in the stator vane row 48a, allowing air to flow in from the cavity 70. The casing main body 46, which is arranged on the outer circumferential side of the multiple blade rings 47, 47a, has a main bleed air passage 46e that penetrates from the inner circumferential side to the outer circumferential side. Air flows into this main bleed air passage 46e from the blade ring bleed air passage 47a and can be discharged to the outer circumferential side of the casing main body 46. The bleed air line 17a described using Figure 1 is connected to this main bleed air passage 46e. Therefore, a portion of the air flowing along the negative pressure surface 52n of the blade body 51 flows into the cooling device 16 via the cavity 70 of the stator vane 50a, the blade ring bleed air passage 47e of the blade ring 47a, and the main body bleed air passage 46e of the casing main body 46, and is cooled and pressurized in this cooling device 16, after which it is sent to one of the multiple stator vane rows 38 of the turbine 30 and cools that stator vane row 38.

[0028] An area of ​​the negative pressure surface 52n with a predetermined width in the axial direction Da from the end of the radially outer side Dro of the negative pressure surface 52n to the end of the radially inner side Dri is an opening formation area 53. In this embodiment, the width in the axial direction Da of this opening formation area 53 is the same at any position in the radial direction Dr. In this opening formation area 53, inlet openings 55i are formed for each of the multiple suction holes 55 aligned in the radial direction Dr and the axial direction Da.

[0029] As shown in FIG. 6 , the suction hole 55 is inclined with respect to the suction surface 52n so as to gradually extend toward the axial downstream side Dad from the inlet opening 55i toward the outlet opening 55o. The angle α of the direction in which the suction hole 55 having the inlet opening 55i extends with respect to the suction surface 52n is preferably 20° or greater and 70° or less. In this embodiment, this angle α is 30°. The cross-sectional shape of the suction hole 55 on a plane perpendicular to the direction in which the suction hole 55 extends is circular. Therefore, the shapes of the inlet opening 55i and the outlet opening 55o are elliptical. Air flows along the suction surface 52n from the leading edge 51L to the trailing edge 51T. As described above, the extension direction of the suction hole 55 in this embodiment is inclined with respect to the plane in which the inlet opening 55i is formed. Therefore, in this embodiment, some of the air flowing along the suction surface 52n is more likely to flow into the cavity 70 through the suction hole 55.

[0030] The suction hole 55 has a minimum inner diameter d between the inlet opening 55i and the outlet opening 55o, and gradually increases in diameter from the portion with the minimum inner diameter d toward the inlet opening 55i, and also gradually increases in diameter from the portion with the minimum inner diameter d toward the outlet opening 55o. In this embodiment, some of the air flowing along the negative pressure surface 52n is likely to flow into the suction hole 55 through the inlet opening 55i. Furthermore, in this embodiment, the air that has flowed into the suction hole 55 is likely to flow into the cavity 70 from the outlet opening 55o.

[0031] The ratio (d / L) of the hole length L of suction hole 55 to the minimum inner diameter d of suction hole 55 is preferably 2 or less. Furthermore, the ratio (A2 / A1) of the area (A2) of outlet opening 55o to the cross-sectional area A1 of suction hole 55 at the position of the minimum inner diameter d is preferably 1.5 or less. Note that the area (A2) of outlet opening 55o here is the area of ​​outlet opening 55o in a direction perpendicular to the direction in which suction hole 55 extends.

[0032] Here, as shown in Figure 4, the dimension of the blade body 51 in the axial direction (front-rear direction) Da is defined as Cx. The dimension that is a% of this Cx is defined as a%Cx. The minimum inner diameter d of the suction hole 55 is preferably 0.8%Cx or more and 3.0%Cx or less. In this embodiment, the minimum inner diameter d of the suction hole 55 is, for example, 1.0%Cx. Furthermore, the central axis distance in the axial direction Da between two inlet openings 55i adjacent to each other in the axial direction Da, and the central axis distance in the radial direction Dr between two inlet openings 55i adjacent to each other in the radial direction Dr, are preferably, for example, 1.5% or more and 7.0% or less.

[0033] As described above, when the suction holes 55 are formed, part of the air flowing along the negative pressure surface 52n is more likely to flow into the cavity 70 via the suction holes 55.

[0034] An air boundary layer is formed along the suction surface 52n of the stator vane 50a. When this boundary layer develops, air resistance to the suction surface 52n increases, reducing the efficiency of the compressor 40. In this embodiment, a portion of the air flowing along the suction surface 52n flows into the cavity 70 of the stator vane 50a through the multiple suction holes 55 and is exhausted from the opening of this cavity 70. Therefore, in this embodiment, the development of the boundary layer is suppressed, the operating range of the compressor 40 is expanded, and the efficiency of the compressor 40 can be improved.

[0035] The inventors have used CFD (Computational Fluid Dynamics) analysis to determine the relationship between the incidence angle θ and pressure loss when the center position RC in the axial direction Da of the opening formation region 53 is set to the following position, as shown in Fig. 7. Here, the incidence angle θ is the difference between the flow angle β and the blade angle κ at the leading edge 51L, as shown in the following equation. θ=β-κ 4, the flow angle β here is the angle between the air flow direction and a tangent line TL to the camber line CaL at the leading edge 51L. Also, the blade angle κ at the leading edge 51L is the angle between the tangent line TL to the camber line CaL at the leading edge 51L and a chord line ChL.

[0036] The center position RC of the opening formation region 53 is 30% Cx from the leading edge 51L (short dashed line in Figure 7). The center position RC of the opening formation region 53 is 40% Cx from the leading edge 51L (the two-dot chain line in FIG. 7). The center position RC of the opening formation region 53 is at a position 50% Cx from the leading edge 51L (first embodiment, dashed line in FIG. 7). The center position RC of the opening formation region 53 is 60% Cx from the leading edge 51L (long dashed line in Figure 7). In any of the above cases, the width of the opening formation region 53 in the axial direction Da is 20% Cx. For reference, Fig. 7 also shows a case where no suction hole 55 is formed on the negative pressure surface 52n (thick solid line in Fig. 7).

[0037] As a result of the CFD analysis, it was found that when suction holes 55 are formed on suction surface 52n, the pressure loss is reduced at any incidence angle θ compared to when suction holes 55 are not formed on suction surface 52n (thick solid line in FIG. 7). This is because the thickness of the boundary layer formed along suction surface 52n is thinner.

[0038] In particular, it was found that the pressure loss was lower than in other examples when the center position RC in the axial direction Da of the opening formation region 53 was located at 50% Cx from the leading edge 51L (dash-dotted line in FIG. 7) and when the center position RC in the axial direction Da of the opening formation region 53 was located at 60% Cx from the leading edge 51L (long dashed line in FIG. 7). From this, it was found that the center position RC in the axial direction Da of the opening formation region 53 is preferably located within a range of 45% Cx to 65% Cx from the leading edge 51L, which range includes the positions of 50% Cx from the leading edge 51L and 60% Cx from the leading edge 51L. Note that in this embodiment, the center position RC in the axial direction Da of the opening formation region 53 is located at 50% Cx from the leading edge 51L.

[0039] When the center position RC of the opening formation region 53 in the axial direction Da is located at 50% Cx from the leading edge 51L, and when the center position RC of the opening formation region 53 in the axial direction Da is located at 60% Cx from the leading edge 51L, there is an incidence angle θ1 at which the pressure loss begins to increase sharply. This is thought to be because when the incidence angle θ becomes more positive than this incidence angle θ1, a separation phenomenon occurs in which air separates from the suction surface 52n.

[0040] In the above example, the width of the opening formation region 53 in the axial direction Da is 20% Cx, but it has been found that the same tendency occurs when this width is set to 30% Cx or 40% Cx. From this, it can be seen that the position of the end of the opening formation region 53 on the axial upstream side Dau is at a position Dad on the axial downstream side of the position 30% Cx from the leading edge 51L.

[0041] Furthermore, the inventors have determined by CFD analysis the relationship between the incidence angle θ and pressure loss when the width of the blade-body cavity 72 in the axial direction Da is set to the following width, as shown in FIG. The width W of the wing-body cavity 72 is 35%Cx (dashed line in Figure 8). The width W of the blade cavity 72 is 65%Cx (first embodiment, dashed line in FIG. 8). When the width W of the blade-body cavity 72 is 35% Cx, the position of the end of the axial upstream side Dau of the blade-body cavity 72 is 30% Cx from the leading edge 51L, and the position of the end of the axial downstream side Dad of the blade-body cavity 72 is 65% Cx from the leading edge 51L. When the width W of the blade-body cavity 72 is 65% Cx, the position of the end of the axial upstream side Dau of the blade-body cavity 72 is 15% Cx from the leading edge 51L, and the position of the end of the axial downstream side Dad of the blade-body cavity 72 is 80% Cx from the leading edge 51L.

[0042] As a result of the CFD analysis, it was found that the pressure loss is lower when the width of the blade-body cavity 72 in the axial direction Da is 65% Cx (dash-dotted line in Figure 8) than when it is 35% Cx (dashed line in Figure 8). This is thought to be because the resistance to the air flowing through the cavity 70 is reduced by increasing the width of the blade-body cavity 72 in the axial direction Da. It was also found that the incidence angle θ1 at which the pressure loss begins to increase sharply is shifted to the (+) side when the width of the blade-body cavity 72 in the axial direction Da is 65% Cx (dash-dotted line in Figure 8) compared to when it is 35% Cx (dashed line in Figure 8). This is also thought to be because the resistance to the air flowing through the blade-body cavity 72 is reduced by increasing the width of the blade-body cavity 72 in the axial direction Da. In this way, when the incidence angle θ1 at which the pressure loss begins to increase rapidly shifts to the (+) side, the range of operating conditions of the compressor 40 can be widened.

[0043] Therefore, in this embodiment, based on the above findings, the width of the blade-body cavity 72 in the axial direction Da is set to 65% Cx (dashed line in Figure 8). Note that the width of the blade-body cavity 72 in the axial direction Da is preferably 60% Cx or more. Furthermore, it is preferable that the position of the end of the axial upstream side Dau of the blade-body cavity 72 is axially upstream Dau of the position 20% Cx of the blade body 51 from the leading edge 51L, and the position of the axial downstream side Dad of the blade-body cavity 72 is axially downstream Dad of the position 70% Cw from the leading edge 51L.

[0044] 5, the inner surface defining the cavity 70 has a plurality of partial inner surfaces that are connected to one another. Among the plurality of partial inner surfaces, the surfaces 76 at the corners of two adjacent partial inner surfaces are curved surfaces with a radius r of 3.5% Cx or more.

[0045] When air flowing along one partial inner surface passes through a corner and flows along another partial inner surface adjacent to the partial inner surface, turbulence such as a vortex occurs in the region along the other partial inner surface. Such turbulence increases the resistance of the air flowing through cavity 70. Therefore, in this embodiment, the surface 76 of the corner is curved with a radius r of 3.5% Cx or more, thereby reducing the turbulence and lowering the resistance of the air flowing through cavity 70.

[0046] As described above, in this embodiment, the resistance of the air flowing inside the cavity 70 is reduced, so that the air flows through the cavity 70 more easily.

[0047] Furthermore, in this embodiment, the air in the cavity 70 of the stator vane 50a is forcibly sucked in by the boost compressor 19 of the cooling device 16, making it easier for some of the air flowing along the negative pressure surface 52n to flow into the cavity 70.

[0048] Therefore, in this embodiment, from the above viewpoint as well, it is possible to suppress the development of the boundary layer and improve the efficiency of the compressor 40.

[0049] "Second embodiment of compressor vane" A second embodiment of the compressor vane will be described below.

[0050] 9, the configuration of the stator vane 50b in this embodiment is basically the same as the configuration of the stator vane 50a in the first embodiment. However, in this embodiment, the total areas of the inlet openings 55i differ between the multiple regions in the opening formation region 53.

[0051] In this embodiment, as in the first embodiment, an area having a predetermined width in the axial direction Da from the end of the radially outer side Dro of the negative pressure surface 52n to the end of the radially inner side Dri is the opening formation area 53. In this embodiment, the width in the axial direction Da of this opening formation area 53 is the same at any position in the radial direction Dr. In this opening formation area 53, inlet openings 55i are formed for each of the plurality of suction holes 55 aligned in the radial direction Dr and the axial direction Da.

[0052] The opening formation region 53 includes a first side region RO, an intermediate region RM, and a second side region RI. The length of the first side region RO in the blade height direction (radial direction) Dr, the length of the intermediate region RM in the blade height direction Dr, and the length of the second side region RI in the blade height direction Dr are all the same. The first side region RO is a region including an end of the blade height first side (radially outer side) Dro of the suction surface 52n, and is hereinafter referred to as the outer region RO. The intermediate region RM is a region including an intermediate position in the blade height direction (radial direction) Dr on the suction surface 52n, and extends from an end of the blade height second side (radially inner side) Dri of the first side region (outer region) RO to the blade height second side (radially inner side) Dri. The second side region RI is a region extending from an end of the blade height second side (radially inner side) Dri of the intermediate region RM to an end of the blade height second side (radially inner side) Dri of the suction surface 52n, and is hereinafter referred to as the inner region RI.

[0053] In this embodiment, the density of the inlet openings 55i in the middle region RM is the same as the density of the inlet openings 55i in the outer region RO. In this embodiment, the density of the inlet openings 55i in the inner region RI is higher than the density of the inlet openings 55i in the middle region RM and the density of the inlet openings 55i in the outer region RO. Thus, in this embodiment, the total area of ​​the inlet openings 55i in the inner region RI is larger than the total area of ​​the inlet openings 55i in the middle region RM.

[0054] The inventors used CFD analysis to determine the relationship between the incidence angle θ and pressure loss when the center position RC in the axial direction Da in the opening formation region 53 and the opening density in the inner region RI are set as follows, as shown in Figure 10. The center position RC of the aperture formation region 53 is at a position 50% Cx from the leading edge 51L, and the aperture density of the inner region RI is not high (first embodiment, dashed line in FIG. 10). The center position RC of the aperture formation region 53 is 50% Cx from the leading edge 51L, and the aperture density of the inner region RI is high (Ih) (second embodiment, dashed line in FIG. 10). In the above, "the opening density of the inner region RI is not high" means that the density of the entrance openings 55i in the inner region RI is the same as the density of the entrance openings 55i in the intermediate region RM and the density of the entrance openings 55i in the outer region RO. In any of the above cases, the width of the opening formation region 53 in the axial direction Da is 20% Cx. The pressure loss for the incidence angle θ indicated by the dashed-dotted line in Fig. 10 is the pressure loss under the same conditions as when the pressure loss for the incidence angle θ indicated by the dashed-dotted line in Fig. 7 was determined, and is therefore the same as the pressure loss for the incidence angle θ indicated by the dashed-dotted line in Fig. 7.

[0055] As a result of the CFD analysis, it was found that when the density of the inlet openings 55i of the inner region RI is increased (dashed line in Figure 10), the pressure loss decreases and the incidence angle θ1' at which the pressure loss begins to increase rapidly shifts to the (+) side compared to when the density of the inlet openings 55i of the inner region RI is not increased (dotted line in Figure 10).

[0056] When a boundary layer is likely to develop around the inner region RI in the negative pressure surface 52n, by increasing the density of the inlet openings 55i of the inner region RI as described above, the development of the boundary layer can be suppressed, the pressure loss can be kept low, and the efficiency of the compressor 40 can be improved.

[0057] Depending on the operating conditions of the compressor 40 and the number of stages of the stator vane row 48a, a boundary layer may be likely to develop around the outer region RO in the suction surface 52n. In this case, by increasing the density of the inlet openings 55i in the outer region RO, the development of the boundary layer can be suppressed, reducing pressure loss and improving the efficiency of the compressor 40. Depending on the operating conditions of the compressor 40 and the number of stages of the stator vane row 48a, a boundary layer may be likely to develop around the inner region RI and outer region RO in the suction surface 52n. In this case, by increasing the density of the inlet openings 55i in the inner region RI and outer region RO, the development of the boundary layer can be suppressed, reducing pressure loss and improving the efficiency of the compressor 40.

[0058] "Third and fourth embodiments of compressor vane" Hereinafter, a third embodiment and a fourth embodiment of the compressor vane will be described.

[0059] 11 and 12, the configurations of the stator vanes 50c and 50d in the third and fourth embodiments are basically the same as the configuration of the stator vane 50a in the first embodiment. However, in the third and fourth embodiments, the shape of the opening formation region 53 and the total area of ​​the inlet openings 55i among the multiple regions in the opening formation region 53 are different.

[0060] 11, in the stator vane 50c of the third embodiment, as in the first embodiment, a region within a predetermined width in the axial direction Da from the end of the radially outer side Dro of the suction surface 52n to the end of the radially inner side Dri is an opening formation region 53. A center position RC of this opening formation region 53 is located at a position 50% Cx from the leading edge 51L.

[0061] The opening formation region 53 in the third embodiment includes a first side region RO (outer region RO), a middle region RM, and a second side region RI (inner region RI), similar to the second embodiment.

[0062] In the third embodiment, the width in the axial direction Da of the outer region RO and the width in the axial direction Da of the region on the first blade height side (radially outer side) Dro of the middle region RM are the same at any position in the radial direction Dr, e.g., 10% Cx. On the other hand, the width in the axial direction Da of the region on the second blade height side (radially inner side) Dri of the middle region RM increases toward the radially inner side Dri. The width in the axial direction Da of the inner region RI also increases toward the radially inner side Dri. Therefore, the shape of the inner region RI is an isosceles trapezoid, in other words, a pyramidal shape. The width in the axial direction Da of the inner region RI at the edge on the radially outer side Dro is the same as the width in the axial direction Da of the middle region RM at the edge on the radially inner side Dri. The width in the axial direction Da of the inner region RI at the edge on the radially inner side Dri is, e.g., 40% Cx. The position of the end of the axial upstream side Dau in this opening formation region 53 is on the radially inner side Dri of the inner region RI and at the edge of the axial upstream side Dau, 30% Cx from the leading edge 51L.

[0063] In the third embodiment, the density of the inlet openings 55i in the middle region RM is the same as the density of the inlet openings 55i in the outer region RO. In the third embodiment, the density of the inlet openings 55i in the inner region RI is higher than the density of the inlet openings 55i in the middle region RM and the density of the inlet openings 55i in the outer region RO. Furthermore, in the inner region RI, the number of inlet openings 55i gradually increases toward the radially inner side Dri. Therefore, the number of inlet openings 55i in the inner region RI is greater than the number of inlet openings 55i in the middle region RM and the number of inlet openings 55i in the outer region RO. Therefore, in the third embodiment, the total area of ​​the inlet openings 55i in the inner region RI is greater than the total area of ​​the inlet openings 55i in the middle region RM and the total area of ​​the inlet openings 55i in the outer region RO.

[0064] 12, in the stator vane 50d of the fourth embodiment, as in the first embodiment, a region within a predetermined width in the axial direction Da from the end of the radially outer side Dro of the suction surface 52n to the end of the radially inner side Dri is an opening formation region 53. A center position RC of this opening formation region 53 is located at a position 50% Cx from the leading edge 51L.

[0065] The opening formation region 53 in the fourth embodiment includes a first side region RO (outer region RO), a middle region RM, and a second side region RI (inner region RI), similar to the second and third embodiments.

[0066] In the fourth embodiment, the width in the axial direction Da of the intermediate region RM is the same at any position in the radial direction Dr, for example, 10% Cx. On the other hand, the width in the axial direction Da of the outer region RO gradually increases toward the radially outer side Dro. Therefore, the shape of the outer region RO is an isosceles trapezoid, in other words, an inverted pyramid. The width in the axial direction Da of the outer region RO at the radially inner edge Dri is the same as the width in the axial direction Da of the intermediate region RM. On the other hand, the width in the axial direction Da of the outer region RO at the radially outer edge Dro is, for example, 40% Cx. Furthermore, the width in the axial direction Da of the inner region RI increases toward the radially inner side Dri. Therefore, the shape of the inner region RI is an isosceles trapezoid, in other words, a pyramid. The width in the axial direction Da of the inner region RI at the radially outer edge Dro is the same as the width in the axial direction Da of the intermediate region RM. Meanwhile, the width in the axial direction Da at the edge of the radially inner side Dri of the inner region RI is, for example, 40% Cx. The position of the end of the axial upstream side Dau in the opening formation region 53 is the position of the edge of the axially upstream side Dau on the radially inner side Dri of the inner region RI, and also the position of the edge of the axially upstream side Dau on the radially outer side Dro of the outer region RO. This position is 30% Cx from the leading edge 51L.

[0067] In the fourth embodiment, the density of the inlet openings 55i in the outer region RO is higher than the density of the inlet openings 55i in the middle region RM. Furthermore, in the outer region RO, the number of inlet openings 55i gradually increases toward the radially outer side Dro. Therefore, the number of inlet openings 55i in the outer region RO is greater than the number of inlet openings 55i in the middle region RM. Also, in the fourth embodiment, the density of the inlet openings 55i in the inner region RI is higher than the density of the inlet openings 55i in the middle region RM. Furthermore, in the inner region RI, the number of inlet openings 55i gradually increases toward the radially inner side Dri. Therefore, the number of inlet openings 55i in the inner region RI is greater than the number of inlet openings 55i in the middle region RM. Therefore, in the fourth embodiment, the total area of ​​the inlet openings 55i in the inner region RI and the total area of ​​the inlet openings 55i in the outer region RO are greater than the total area of ​​the inlet openings 55i in the middle region RM.

[0068] The inventors have used CFD analysis to determine the relationship between the incidence angle θ and pressure loss when the shape of each region in the opening formation region 53 and the opening density of each region are as follows, as shown in FIG. The center position RC of the aperture formation region 53 is at a position 50% Cx from the leading edge 51L, and the aperture density of each region is the same (first embodiment, dashed line in FIG. 13). The center position RC of the aperture formation region 53 is 50% Cx from the leading edge 51L, the shape of the inner region RI is pyramidal, and the aperture density of this inner region RI is not high (Ip) (short dashed line in Figure 13). The center position RC of the aperture formation region 53 is located at 50% Cx from the leading edge 51L, the shape of the inner region RI is pyramidal, and the aperture density of this inner region RI is high (Iph) (third embodiment, two-dot chain line in Figure 13). The center position RC of the aperture formation region 53 is 50% Cx from the leading edge 51L, the shapes of the inner region RI and the outer region RO are pyramidal, and the aperture density of the inner region RI and the outer region RO is not high (Ip-Op) (thin solid line in Figure 13). The center position RC of the aperture formation region 53 is located at 50% Cx from the leading edge 51L, the shapes of the inner region RI and the outer region RO are pyramidal, and the aperture density of the inner region RI and the outer region RO is high (Iph-Oph) (fourth embodiment, long dashed line in FIG. 13). In the above, "the opening density in the aa region is not high" means that the density of the entrance openings 55i in the aa region is the same as the density of the entrance openings 55i in the intermediate region RM.

[0069] As a result of the CFD analysis, it was found that when the shape of the inner region RI and / or the outer region RO is made pyramidal and the number of inlet openings 55i in these regions is increased (short dashed line, two-dot chain line, thin solid line, long dashed line in Figure 13), the incidence angles θ1', θ" at which pressure loss begins to increase rapidly are shifted to the (+) side compared to when the width of the opening formation region 53 in the axial direction Da is constant at every position in the radial direction Dr (dash-dotted line in Figure 13). In particular, it was found that when the shape of the inner region RI and the outer region RO is made pyramidal and the density of the inlet openings 55i in these regions is increased (long dashed line in Figure 13c), the incidence angle θ" at which pressure loss begins to increase rapidly is shifted to the (+) side compared to when the shape of the inner region RI and the outer region RO is made pyramidal and the density of the inlet openings 55i in these regions is not high (thin solid line).

[0070] When a boundary layer is likely to develop around the inner region RI in the suction surface 52n, by making the number of inlet openings 55i in the inner region RI greater than the number of inlet openings 55i in the intermediate region RM as in the third embodiment, it is possible to suppress the development of the boundary layer, keep pressure loss low, and improve the efficiency of the compressor 40. In particular, by making the number of inlet openings 55i in the inner region RI greater than the number of inlet openings 55i in the intermediate region RM and increasing the density of the inlet openings 55i in the inner region RI greater than the density of the inlet openings 55i in the intermediate region RM as in the third embodiment, it is possible to further suppress the development of the boundary layer, keep pressure loss low, and improve the efficiency of the compressor 40.

[0071] In addition, when a boundary layer is likely to develop around the inner region RI in the negative pressure surface 52n, it is sufficient to make the number of inlet openings 55i in the inner region RI greater than the number of inlet openings 55i in the intermediate region RM, and it is not necessary to increase the density of the inlet openings 55i in the inner region RI greater than the density of the inlet openings 55i in the intermediate region RM, as in the third embodiment.

[0072] Furthermore, if a boundary layer is likely to develop around the outer region RO in the suction surface 52n, the outer region RO may be formed in a pyramidal shape, and the number of inlet openings 55i in the outer region RO may be made greater than the number of inlet openings 55i in the intermediate region RM. In this case as well, the density of the inlet openings 55i in the outer region RO may be made greater than the density of the inlet openings 55i in the intermediate region RM.

[0073] When a boundary layer is likely to develop around the inner region RI and the outer region RO on the negative pressure surface 52n, it is sufficient to make the number of inlet openings 55i in the inner region RI and the outer region RO greater than the number of inlet openings 55i in the intermediate region RM, and it is not necessary to increase the density of the inlet openings 55i in the inner region RI and the outer region RO greater than the density of the inlet openings 55i in the intermediate region RM, as in the fourth embodiment.

[0074] "Fifth embodiment of compressor vane" Hereinafter, a fifth embodiment of the compressor vane will be described.

[0075] 14 to 16, the configuration of the stator vane 50e in the fifth embodiment is basically the same as the configuration of the stator vane 50a in the first embodiment. However, in the fifth embodiment, a plurality of suction holes 66 are formed in the outer shroud 61o and the inner shroud 61i.

[0076] The suction holes 66 of the outer shroud 61o have an inlet opening 66i that opens in the gas path surface 62o of the outer shroud 61o and an outlet opening 66o that opens in an outer inner surface 71p that is back-to-back with the gas path surface 62o and is an inner surface that defines the outer cavity 71. Thus, the suction holes 66 penetrate from the gas path surface 62o to the outer inner surface 71p that defines a portion of the outer cavity 71. The suction holes 66 of the inner shroud 61i have an inlet opening 66i that opens in the gas path surface 62i of the inner shroud 61i and an outlet opening 66o that opens in an inner inner surface 73p that is back-to-back with the gas path surface 62i and is an inner surface that defines the inner cavity 73. Thus, the suction holes 66 penetrate from the gas path surface 62i to the inner inner surface 73p that defines a portion of the inner cavity 73.

[0077] In the present embodiment, an opening formation region 65o is formed in the gas path surface 62o of the outer shroud 61o by a region along the suction surface 52n on the circumferential suction side Dcn with respect to the blade body 51. Inlet openings 66i are formed in the opening formation region 65o for each of the plurality of suction holes 66 aligned in the circumferential direction Dc and the axial direction Da.

[0078] In the present embodiment, an opening formation region 65i is formed in the gas path surface 62i of the inner shroud 61i by a region along the suction surface 52n on the circumferential suction side Dcn with respect to the blade body 51. Inlet openings 66i are formed in the opening formation region 65i for each of the plurality of suction holes 66 aligned in the circumferential direction Dc and the axial direction Da.

[0079] It is preferable that the axial upstream end Dau of the opening formation region 65o in the gas path surface 62o of the outer shroud 61o and the axial upstream end Dau of the opening formation region 65i in the gas path surface 62i of the inner shroud 61i are located closer to the trailing edge 51T than a position that is 30% Cx from the leading edge 51L. In the present embodiment, the axial upstream end Dau of the opening formation region 65o in the gas path surface 62o of the outer shroud 61o and the axial upstream end Dau of the opening formation region 65i in the gas path surface 62i of the inner shroud 61i are located at a position that is 40% Cx from the leading edge 51L, similar to the opening formation region 53 in the suction surface 52n in the first embodiment.

[0080] The suction holes 66 of the outer shroud 61o and the suction holes 66 of the inner shroud 61i are inclined with respect to the gas path surfaces 62o, 62i so as to gradually extend toward the axial downstream side Dad from their inlet openings 66i toward their outlet openings 66o, similar to the suction holes 55 of the blade body 51 described with reference to Fig. 6. The angle α of the direction in which the suction holes 66 having the inlet openings 66i extend with respect to the gas path surfaces 62o, 62i is preferably 20° or more and 70° or less. In this embodiment, this angle α is 30°.

[0081] Like the suction holes 55 of the blade body 51, the suction holes 66 of the outer shroud 61o and the suction holes 66 of the inner shroud 61i have a minimum inner diameter d in the portion between the inlet opening 66i and the outlet opening 66o, and gradually increase in diameter from the portion of minimum inner diameter d toward the inlet opening 66i, and also gradually increase in diameter from the portion of minimum inner diameter d toward the outlet opening 66o.

[0082] As with the suction holes 55 of the blade body 51, the suction holes 66 of the outer shroud 61o and the suction holes 66 of the inner shroud 61i preferably have a ratio (d / L) of the hole length L of the suction holes 66 to the minimum inner diameter d of 2 or less. Also, the ratio (A2 / A1) of the area (A2) of the outlet opening 66o to the cross-sectional area A1 of the suction holes 66 at the position of the minimum inner diameter d is preferably 1.5 or less.

[0083] As shown in FIG. 17, the inventors have performed a CFD analysis to determine the relationship between the incidence angle θ and pressure loss when the presence or absence of suction holes 66 in the outer shroud 61o and the inner shroud 61i is as follows. The center position RC of the opening formation region 53 on the suction surface 52n is at a position 50% Cx from the leading edge 51L, and no suction holes 66 are formed in the outer shroud 61o and the inner shroud 61i (first embodiment, dashed line in FIG. 17). The suction holes 66 are formed in the outer shroud 61o and the inner shroud 61i at a position where the center position RC of the opening formation region 53 is 50% Cx from the leading edge 51L (+IE+OE) (fifth embodiment, dashed line in FIG. 17).

[0084] As a result of the CFD analysis, it was found that when suction holes 66 are formed in the outer shroud 61o and the inner shroud 61i (dashed line in Figure 17), the incidence angle θ1' at which the pressure loss begins to increase sharply shifts to the negative side compared to when suction holes 66 are not formed in the outer shroud 61o and the inner shroud 61i (dotted line in Figure 17).

[0085] Therefore, in this embodiment, within a wide range of the incidence angle θ, it is possible to suppress the development of the boundary layer, thereby keeping the pressure loss low and improving the efficiency of the compressor 40.

[0086] Although this embodiment is an example in which the suction holes 66 are formed in the outer shroud 61o and the inner shroud 61i of the stator vane 50a in the first embodiment, the suction holes 66 may be formed in the outer shroud 61o and the inner shroud 61i of the stator vanes 50b, 50c, and 50d in all of the examples described above. In this case, too, the same effects as those of this embodiment can be obtained.

[0087] In addition, in the present embodiment, the suction holes 66 are formed in both the outer shroud 61o and the inner shroud 61i of the stator vane 50e. However, if a boundary layer is likely to develop around the region of the radially inner side Dri on the suction surface 52n, the suction holes 66 may be formed only in the inner shroud 61i of the inner shroud 61i and the outer shroud 61o of the stator vanes 50a, 50b, 50c, 50d, and 50e in all the examples described above, including the present embodiment. In addition, if a boundary layer is likely to develop around the region of the radially outer side Dro on the suction surface 52n, the suction holes 66 may be formed only in the outer shroud 61o of the inner shroud 61i and the outer shroud 61o of the stator vanes 50a, 50b, 50c, 50d, and 50e in all the examples described above, including the present embodiment.

[0088] "Variations" In the above example, the entrance openings 55i, 66i and the exit openings 55o, 66o are elliptical in shape. However, the entrance openings 55i, 66i and the exit openings 55o, 66o are not limited to elliptical shapes and may be rectangular, for example.

[0089] In the above example, the cavity 70 opens at the front end surface 64f of the outer shroud 61o. However, the cavity 70 may open at any surface other than the gas path surface 62o of the outer shroud 61o, for example, at the outer opposite gas path surface 63o of the outer shroud 61o.

[0090] In the above example, the suction holes 55, 66 are formed in the plurality of stator vanes 50a, 50b, 50c, 50d, 50e that constitute some of the stator vane rows 48a out of the plurality of stator vane rows 48, 48a. However, for example, the suction holes 55, 66 may be formed not only in one stator vane row 48a but also in the plurality of stator vanes that constitute all of the stator vane rows 48 downstream of this one stator vane row 48a. Furthermore, the suction holes 55, 66 may be formed in the plurality of stator vanes that constitute all of the stator vane rows 48, 48a.

[0091] The compressor 40 in the above example is the compressor of the gas turbine 10. However, the compressor does not have to be the compressor 40 of the gas turbine 10 as long as the compressor is a multi-stage axial compressor.

[0092] Furthermore, the present disclosure is not limited to the embodiment and modifications described above, and various additions, modifications, substitutions, partial deletions, etc. are possible within the scope of the conceptual idea and spirit of the present invention derived from the content defined in the claims and their equivalents.

[0093] "Addendum" The compressor stator vanes 50a, 50b, 50c, 50d, and 50e in the above-described embodiment and modified examples can be understood, for example, as follows. (1) The compressor stator vanes 50a, 50b, 50c, 50d, and 50e in the first embodiment are The blade body 51 has a blade-shaped cross section and extends in a blade height direction Dr including a directional component perpendicular to the cross section, a first shroud 61o provided at an end of the blade height first side Dro of a blade height first side Dro and a blade height second side Dri in the blade height direction Dr of the blade body 51, and a second shroud 61i provided at the end of the blade height second side Dri of the blade body 51. The blade body 51 has a leading edge 51L, a trailing edge 51T, a pressure surface 52p connecting the leading edge 51L and the trailing edge 51T, and a suction surface 52n connecting the leading edge 51L and the trailing edge 51T and facing back to back with the pressure surface 52p. The first shroud 61o has a first gas path surface 62o that faces the blade height second side Dri and extends in a direction including a directional component perpendicular to the blade height direction Dr from an end of the blade height first side Dro of the blade body 51, a first counter-gas path surface 63o that faces the blade height first side Dro and is back-to-back with the first gas path surface 62o, and a first side peripheral surface 64o that connects an edge of the first gas path surface 62o and an edge of the first counter-gas path surface 63o. The second shroud 61i has a second gas path surface 62i that faces the blade height first side Dro and extends in a direction including a directional component perpendicular to the blade height direction Dr from an end of the blade height second side Dri of the blade body 51 A cavity 70 is formed in the blade body 51 and the first shroud 61o, which is continuous within the blade body 51 and the first shroud 61o and opens at the first anti-gas path surface 63o or the first side circumferential surface 64o. The blade body 51 is formed with a plurality of suction holes 55, each having an inlet opening 55i opening at the suction surface 52n and an outlet opening 55o opening at an inner surface that defines the cavity 70, and penetrating from the suction surface 52n to the inner surface that defines the cavity 70. In the suction surface 52n, an area of ​​a predetermined width in the fore-aft direction Da where the leading edge 51L and the trailing edge 51T are aligned, and an area from an end of the first blade height side Dro to an end of the second blade height side Dri of the suction surface 52n, forms an opening formation region 53. In the opening formation region 53, the inlet openings 55i are formed for each of the plurality of suction holes 55 aligned in the blade height direction Dr and the front-rear direction Da.

[0094] An air boundary layer is formed along the suction surface 52n of each of the stator vanes 50a, 50b, 50c, 50d, and 50e. When this boundary layer develops, air resistance to the suction surface 52n increases, reducing the efficiency of the compressor 40. In this embodiment, a portion of the air flowing along the suction surface 52n flows into the cavity 70 of each of the stator vanes 50a, 50b, 50c, 50d, and 50e through the multiple suction holes 55 and is exhausted from the opening of the cavity 70. Therefore, this embodiment can suppress the development of the boundary layer, expand the operating range of the compressor, and improve the compressor efficiency. In particular, in this embodiment, the inlet openings 55i are formed for each of the multiple suction holes 55 aligned in the blade height direction Dr and the longitudinal direction Da throughout the entire opening formation region 53 where the boundary layer is likely to develop. Therefore, the development of the boundary layer can be effectively suppressed while limiting the number of suction holes 55.

[0095] (2) The compressor stator vanes 50b, 50c, and 50d in the second embodiment are In the compressor stator vane 50b, 50c, 50d according to the first aspect, the opening formation region 53 has: a first side region RO including an end of the blade height first side Dro of the suction surface 52n; an intermediate region RM including an intermediate position in the blade height direction Dr on the suction surface 52n and extending from an end of the blade height second side Dri of the first side region RO to the blade height second side Dri; and a second side region RI extending from the end of the blade height second side Dri of the intermediate region RM to the end of the blade height second side Dri of the suction surface 52n. A total area of ​​the inlet openings 55i in at least one of the first side region RO and the second side region RI is larger than a total area of ​​the inlet openings 55i in the intermediate region RM.

[0096] Depending on the position of the stator vane in the compressor and the operating conditions of the compressor, a boundary layer may be likely to develop around the first region RO of the suction surface 52n, a boundary layer may be likely to develop around the second region RI of the suction surface 52n, or a boundary layer may be likely to develop around the first region RO and the second region RI of the suction surface 52n. Therefore, when a boundary layer is likely to develop around the first region RO of the suction surface 52n, the total area of ​​the inlet openings 55i in the first region RO can be made larger than the total area of ​​the inlet openings 55i in the intermediate region RM, thereby effectively suppressing the development of the boundary layer and keeping pressure loss low. Also, when a boundary layer is likely to develop around the second region RI of the suction surface 52n, the total area of ​​the inlet openings 55i in the second region RI can be made larger than the total area of ​​the inlet openings 55i in the intermediate region RM, thereby effectively suppressing the development of the boundary layer and keeping pressure loss low. Furthermore, when a boundary layer is likely to develop around the first side region RO and the second side region RI on the negative pressure surface 52n, the development of the boundary layer can be effectively suppressed and pressure loss can be kept low by making the total area of ​​the inlet openings 55i in the first side region RO and the total area of ​​the inlet openings 55i in the second side region RI larger than the total area of ​​the inlet openings 55i in the intermediate region RM.

[0097] (3) The compressor stator vanes 50b, 50c, and 50d in the third embodiment are In the compressor stator vanes 50b, 50c, 50d in the second aspect, the number of the inlet openings 55i in the at least one side region is greater than the number of the inlet openings 55i in the intermediate region RM, and the density of the inlet openings 55i in the at least one side region is higher than the density of the inlet openings 55i in the intermediate region RM.

[0098] By making the number of inlet openings 55i in at least one side region greater than the number of inlet openings 55i in the intermediate region RM, the total area of ​​the inlet openings 55i in at least one side region can be made greater than the total area of ​​the inlet openings 55i in the intermediate region RM. Also, by making the density of the inlet openings 55i in at least one side region greater than the density of the inlet openings 55i in the intermediate region RM, the total area of ​​the inlet openings 55i in at least one side region can be made greater than the total area of ​​the inlet openings 55i in the intermediate region RM.

[0099] (4) The compressor stator vanes 50c and 50d in the fourth aspect are In the compressor stator vanes 50c, 50d according to the second aspect, the width in the front-to-rear direction Da in the at least one side region gradually increases with increasing distance from the intermediate region RM in the blade height direction Dr. The maximum width in the front-to-rear direction Da in the at least one side region is wider than the maximum width in the front-to-rear direction Da in the intermediate region RM. The number of the inlet openings 55i in the at least one side region gradually increases with increasing distance from the intermediate region RM in the blade height direction Dr and is greater than the number of the inlet openings 55i in the intermediate region RM. The density of the inlet openings 55i in the at least one side region is higher than the density of the inlet openings 55i in the intermediate region RM.

[0100] By making the maximum width in the front-rear direction Da in at least one side region wider than the maximum width in the front-rear direction Da in the intermediate region RM and by making the number of inlet openings 55i in at least one side region greater than the number of inlet openings 55i in the intermediate region RM, in this embodiment, the total area of ​​the inlet openings 55i in at least one side region can be made greater than the total area of ​​the inlet openings 55i in the intermediate region RM. Therefore, in this embodiment, when a boundary layer is likely to develop in at least one of the portions on the first blade height side Dro and the second blade height side Dri of the suction surface 52n, the development of the boundary layer in at least one of the portions on the first blade height side Dro and the second blade height side Dri can be effectively suppressed.

[0101] (5) The compressor stator vane 50d in the fifth aspect is In the compressor stator vane 50d according to any one of the second to fourth aspects, the at least one side region includes the first side region RO and the second side region RI.

[0102] (6) The compressor stator vanes 50a, 50b, 50c, 50d, and 50e in the sixth aspect are In the compressor stator vanes 50a, 50b, 50c, 50d, and 50e in any one of the first to fifth embodiments, the center position RC in the longitudinal direction Da of the opening formation region 53 is a position within a range of 45% to 65% of the width of the blade body 51 in the longitudinal direction Da from the leading edge 51L.

[0103] On the suction surface 52n, the center position RC in the longitudinal direction Da of the region where the boundary layer is likely to develop is a position within a range from the leading edge 51L of 45% to 65% of the width in the longitudinal direction Da of the blade body 51. In this embodiment, the center position RC of the opening formation region 53 is at the center position RC of the region where the boundary layer is likely to develop, so that the development of the boundary layer can be effectively suppressed while keeping the number of suction holes 55 small.

[0104] (7) The compressor stator vanes 50a, 50b, 50c, 50d, and 50e in the seventh aspect are In the compressor stator vanes 50a, 50b, 50c, 50d, and 50e in the sixth aspect, the position of the end of the opening formation region 53 on the side of the leading edge 51L in the longitudinal direction Da is closer to the trailing edge 51T than a position that is 30% of the width of the blade body 51 in the longitudinal direction Da from the leading edge 51L.

[0105] On the suction surface 52n, the position of the end on the leading edge 51L side in the longitudinal direction Da of the region where a boundary layer is likely to develop is closer to the trailing edge 51T than a position that is 30% of the width of the wing-body 51 in the longitudinal direction Da from the leading edge 51L. In this embodiment, the position of the end on the leading edge 51L side of the opening formation region 53 is closer to the trailing edge 51T than a position that is 30% of the width of the wing-body 51 in the longitudinal direction Da from the leading edge 51L, so that the development of a boundary layer can be effectively suppressed while keeping the number of suction holes 55 small.

[0106] (8) The compressor stator vane 50e in the eighth aspect is In the compressor stator vane 50e according to any one of the first to seventh embodiments, at least one of the first shroud 61o and the second shroud 61i has an inlet opening 66i that opens in a gas path surface 62o, 62i of the at least one shroud and an outlet opening 55o that opens on the inner surface that defines the cavity 70. A plurality of suction holes 66 are formed that penetrate from the gas path surface 62o, 62i to the inner surface that defines the cavity 70. A side of the pressure surface 52p on which the suction surface 52n exists is a suction side Dcn. In the gas path surface 62o, 62i of the at least one shroud, a region on the suction side Dcn and along the suction surface 52n with respect to the blade body 51 forms an opening formation region 65o, 65i. The inlet openings 66i are formed in the opening formation regions 65o, 65i in the gas path surfaces 62o, 62i of the at least one shroud, for each of the plurality of suction holes 66 formed in the at least one shroud.

[0107] In this embodiment, when a boundary layer is likely to develop in at least one of the blade height first side Dro portion and the blade height second side Dri portion of the negative pressure surface 52n, the development of the boundary layer in at least one of the blade height first side Dro portion and the blade height second side Dri portion can be effectively suppressed.

[0108] (9) The compressor stator vane 50e in the ninth aspect is In the compressor stator vane 50e of the eighth aspect, the end of the opening formation region 65o, 65i in the gas path surface 62o, 62i of at least one of the shrouds on the side of the leading edge 51L in the longitudinal direction Da is closer to the trailing edge 51T than a position that is 30% of the width of the blade body 51 in the longitudinal direction Da from the leading edge 51L.

[0109] On the suction surface 52n, the position of the end on the leading edge 51L side in the longitudinal direction Da of the region where a boundary layer is likely to develop is closer to the trailing edge 51T than a position that is 30% of the width of the blade-body 51 in the longitudinal direction Da from the leading edge 51L. In this embodiment, the positions of the ends on the leading edge 51L side of the opening formation regions 65o, 65i are closer to the trailing edge 51T than a position that is 30% of the width of the blade-body 51 in the longitudinal direction Da from the leading edge 51L. Therefore, in this embodiment, the development of a boundary layer can be effectively suppressed while keeping the number of suction holes 66 small.

[0110] (10) The compressor stator vanes 50a, 50b, 50c, 50d, and 50e in the tenth aspect are In the compressor stator vane 50a, 50b, 50c, 50d, 50e according to any one of the first to ninth embodiments, each of the plurality of suction holes 55, 66 is inclined with respect to a plane on which the inlet openings 55i, 66i are formed so as to gradually extend from the leading edge 51L toward the trailing edge 51T in the longitudinal direction Da as it moves from the inlet openings 55i, 66i to the outlet openings 55o, 66o. The angle of the direction in which the plurality of suction holes 55, 66 extend with respect to the plane on which the inlet openings 55i, 66i are formed is 20° or more and 70° or less. Each of the multiple suction holes 55, 66 has a minimum inner diameter d in the portion between the inlet opening 55i, 66i and the outlet opening 55o, 66o, and gradually increases in diameter from the portion with the minimum inner diameter d toward the inlet opening 55i, 66i, and also gradually increases in diameter from the portion with the minimum inner diameter d toward the outlet opening 55o, 66o.

[0111] Air flows from the leading edge 51L side to the trailing edge 51T side along the surface on which the inlet openings 55i, 66i are formed. The suction holes 55, 66 in this embodiment are inclined with respect to the surface on which the inlet openings 55i, 66i are formed so as to gradually extend from the leading edge 51L side to the trailing edge 51T side as they move from the inlet openings 55i, 66i toward the outlet openings 55o, 66o. Therefore, in this embodiment, some of the air flowing along the surface on which the inlet openings 55i, 66i are formed easily flows into the cavity 70 through the suction holes 55, 66. Furthermore, in this embodiment, the diameter gradually increases from the portion of the minimum inner diameter d toward the inlet openings 55i, 66i, so that some of the air flowing along the surface on which the inlet openings 55i, 66i are formed easily flows into the suction holes 55, 66 through the inlet openings 55i, 66i. In addition, in this embodiment, the diameter gradually increases from the portion with the minimum inner diameter d toward the outlet openings 55o, 66o, so that the air that has flowed into the suction holes 55, 66 can easily flow into the cavity 70 from the outlet openings 55o, 66o.

[0112] (11) The compressor stator vanes 50a, 50b, 50c, 50d, and 50e in an eleventh aspect are In the compressor stator vanes 50a, 50b, 50c, 50d, and 50e according to the tenth aspect, the ratio of the hole length of each of the plurality of suction holes 55, 66 to the minimum inner diameter d of each of the plurality of suction holes 55, 66 is 2 or less.

[0113] In this embodiment, air flows easily through the suction holes 55 and 66 .

[0114] (12) The compressor stator vanes 50a, 50b, 50c, 50d, and 50e in a twelfth aspect are In the compressor stator vane 50a, 50b, 50c, 50d, 50e according to the tenth or eleventh aspect, a ratio (A2 / A1) of an area A2 of the outlet opening 55o, 66o to a cross-sectional area A1 of the suction hole 55, 66 at the position of the minimum inner diameter d is 1.5 or less. The area of ​​the outlet opening 55o, 66o is an area in a direction perpendicular to a direction in which the suction hole 55, 66 having the outlet opening 55o, 66o extends.

[0115] (13) The compressor stator vanes 50a, 50b, 50c, 50d, and 50e in a thirteenth aspect are In the compressor stator vanes 50a, 50b, 50c, 50d, and 50e in any one of the first to twelfth embodiments, the minimum inner diameter d of each of the plurality of suction holes 55, 66 is 0.8% or more and 3.0% or less of the width Da of the blade body 51 in the fore-and-aft direction.

[0116] (14) The compressor stator vanes 50a, 50b, 50c, 50d, and 50e in a fourteenth aspect are In the compressor stator vanes 50a, 50b, 50c, 50d, 50e in any one of the first to thirteenth embodiments, the central axis distance between two adjacent suction holes 55, 66 among the plurality of suction holes 55, 66 is 1.5% or more and 7.0% or less of the width of the blade body 51 in the fore-and-aft direction Da.

[0117] (15) The compressor stator vanes 50a, 50b, 50c, 50d, and 50e in a fifteenth aspect are In the compressor stator vane 50a, 50b, 50c, 50d, 50e according to any one of the first to fourteenth aspects, the inner surface defining the cavity 70 has a plurality of partial inner surfaces that are connected to one another. Among the plurality of partial inner surfaces, surfaces 76 at corners of two adjacent partial inner surfaces are curved surfaces with a radius r that is 3.5% or more of the width of the blade body 51 in the longitudinal direction Da.

[0118] When air flowing along one partial inner surface passes through a corner and flows along another partial inner surface adjacent to the partial inner surface, turbulence such as a vortex occurs in the region along the other partial surface. When turbulence occurs, the resistance of the air flowing through the cavity 70 increases. Therefore, in this embodiment, the surface 76 of the corner is curved with a radius r that is 3.5% or more of the width of the wing body 51 in the longitudinal direction Da, thereby reducing turbulence and lowering the resistance of the air flowing through the cavity 70.

[0119] (16) The compressor stator vanes 50a, 50b, 50c, 50d, and 50e in a sixteenth aspect are In the compressor stator vane 50a, 50b, 50c, 50d, 50e according to any one of the first to fifteenth aspects, the width in the longitudinal direction Da of a blade-body cavity 72, which is a portion of the cavity 70 formed in the blade body 51, is 60% or more of the width of the blade body 51 in the longitudinal direction Da. The position of the end of the blade-body cavity 72 on the leading edge 51L side is closer to the leading edge 51L than a position that is 20% of the width of the blade body 51 in the longitudinal direction Da from the leading edge 51L. The position of the end of the blade-body cavity 72 on the trailing edge 51T side is closer to the trailing edge 51T than a position that is 70% of the width of the blade body 51 in the longitudinal direction Da from the leading edge 51L.

[0120] The resistance of the air flowing through the cavity 70 can be reduced.

[0121] The compressor 40 in the above embodiment and modified examples can be understood, for example, as follows. (17) In a seventeenth aspect, the compressor 40 is The compressor includes a compressor rotor 41 rotatable about an axis Ar, a compressor casing 45 covering the compressor rotor 41, and a plurality of stator vane rows 48, 48a arranged in an axial direction Da along which the axis Ar extends. The compressor rotor 41 includes a rotor shaft 42 extending in the axial direction Da around the axis Ar, and a plurality of moving blade rows 43 attached to the rotor shaft 42 and arranged in the axial direction Da. Each of the plurality of stator vane rows 48, 48a is disposed on the axial downstream side Dad of one of the plurality of moving blade rows 43 in the axial direction Da and attached to the compressor casing 45. Each of the plurality of stator vane rows 48, 48a has a plurality of stator vanes arranged in a circumferential direction Dc about the axis Ar. Of the plurality of stator vane rows 48, 48a, at least one stator vane row 48a has each of the plurality of stator vanes 50a, 50b, 50c, 50d, 50e according to any one of the first to sixteenth embodiments. The longitudinal direction Da is the axial direction Da. The blade height direction Dr is the radial direction Dr relative to the axis Ar. The blade height first side Dro is the radially outer side Dro of the radially inner side Dri and the radially outer side Dro in the radial direction Dr. The blade height second side Dri is the radially inner side Dri.

[0122] (18) In an eighteenth aspect, the compressor 40 is In the compressor 40 of the seventeenth aspect, the compressor casing 45 has a cylindrical shape centered on the axis Ar and includes one or more blade rings 47, 47a that hold part of the multiple stator vane rows 48, 48a, and a casing body 46 that is arranged on the outer circumferential side of the one or more blade rings 47, 47a and to which the one or more blade rings 47, 47a are attached. Of the one or more blade rings 47, 47a, the blade ring 47a that holds at least one stator vane row 48a has a blade ring bleed flow passage 47e that penetrates from an inner circumferential side to an outer circumferential side and communicates with the cavity 70 of each of the multiple stator vanes 50a, 50b, 50c, 50d, 50e that the at least one stator vane row 48a has, and into which air from the cavity 70 can flow. The casing body 46 has a body bleed air passage 46e that penetrates from the inner peripheral side to the outer peripheral side, receives air from the blade ring bleed air passage 47e, and can exhaust the air to the outer peripheral side of the casing body 46.

[0123] The gas turbine facilities in the above-described embodiments and modifications can be understood, for example, as follows. (19) A gas turbine facility according to a nineteenth aspect includes: The gas turbine 10 includes the compressor 40 of the eighteenth aspect, a combustor 20 capable of generating combustion gas by burning fuel in air compressed by the compressor 40, and a turbine 30 that can be driven by the combustion gas, and a cooling device 16. The turbine 30 includes a turbine rotor 31 that can rotate about the axis Ar, a turbine casing 35 that covers the turbine rotor 31, and a plurality of stator vane rows 38 that are aligned in the axial direction Da and arranged on the inner peripheral side of the turbine casing 35. The cooling device 16 includes an extraction line 17a connected to the main extraction air flow path 46e of the compressor casing 45, a cooler 18 capable of cooling the air from the extraction line 17a, a boost compressor 19 capable of compressing the air cooled by the cooler 18, and a cooling air line 17b capable of guiding the air cooled by the cooler and compressed by the boost compressor 19 to at least one of the plurality of stator blade rows 38 of the turbine 30.

[0124] In this embodiment, the air in the cavity 70 of the stator vanes 50a, 50b, 50c, 50d, and 50e is forcibly sucked in by the boost compressor 19 of the cooling device 16, so that some of the air flowing along the negative pressure surface 52n is more likely to flow into the cavity 70. [Explanation of symbols]

[0125] 10: Gas turbine 11: Gas turbine rotor 14: Intermediate casing 15: Gas turbine casing 16: Cooling device 17a: Bleed line 17b: Cooling air line 18:Cooler 19: Boost compressor 20: Combustor 30: Turbine 31: Turbine rotor 32: Rotor shaft 33: Moving blade row 35: Turbine casing 38: Stator blade row 40: Compressor 41: Compressor rotor 42: Rotor shaft 43: Moving blade row 45: Compressor casing 46: Casing body 46e: Main body bleed flow passage 47,47a: Wing ring 47e: Blade ring bleed channel 47p: Gaspath surface 47g: Wing groove 48,48a: Stator blade row 50, 50a, 50b, 50c, 50d, 50e: Stator vanes (compressor vanes) 51: Wing body 51L: Leading edge 51T: Trailing edge 52p: Positive pressure side 52n: Negative pressure side 53;Aperture formation area 55: Suction hole 55i: Entrance opening 55o: Exit opening 61o: Outer shroud (first shroud) 62o: Outer gas path surface (first gas path surface, or simply gas path surface) 63o: Outer anti-gas path surface (first anti-gas path surface) 64o: Side circumferential surface (first side circumferential surface) 64f: Front end surface 64b: Rear end surface 64s: Side end surface 65o;Aperture forming area 66: Suction hole 66i: Entrance opening 66o:Exit opening 61i: Inner shroud (second shroud) 62i: Inner gas path surface (second gas path surface, or simply gas path surface) 63i: Inner anti-gas path surface (second anti-gas path surface) 64i: Side circumferential surface (second side circumferential surface) 65i;Aperture formation area 70: Hollow 71; outer cavity 71p: Outer inner surface 72: Wing body cavity 72p: Negative pressure side inner surface 73:Inner cavity 73p: Inside 76: Corner surface A: Air G: Combustion gas F:Fuel CaL: Camber line ChL: Codeline TL: Tangent β: Flow angle κ: wing angle θ: Incidence angle RO: Outer area (first side area) RM: intermediate area RI: Inner area (second side area) Ar: Axis line Da: Axial direction (back and forth direction) Dau: Upstream side of the axis (leading edge side) Dad: Downstream side of axis (trailing edge side) Dc: Circumferential direction Dcn: Circumferential suction side Dcp: Circumferential pressure side Dr: Radial direction (blade height direction) Dro: Radial outer side (first side of blade height) Dri: Radial inner side (second blade height side)

Claims

1. A wing body having a cross section that forms an airfoil shape and extends in a wing height direction that includes a directional component perpendicular to the cross section; a first shroud provided at an end of the blade height first side of the blade body in the blade height direction; and a second shroud provided at an end of the blade body on the second blade height side; Equipped with the blade body has a leading edge, a trailing edge, a pressure side connecting the leading edge and the trailing edge, and a suction side connecting the leading edge and the trailing edge and being back-to-back with the pressure side, the first shroud has a first gas path surface facing the second blade height side and extending from an end of the blade body on the first blade height side in a direction including a directional component perpendicular to the blade height direction, a first counter-gas path surface facing the first blade height side and facing back-to-back with the first gas path surface, and a first side peripheral surface connecting an edge of the first gas path surface and an edge of the first counter-gas path surface, The second shroud has a second gas path surface facing the first blade height side and extending in a direction including a directional component perpendicular to the blade height direction from an end of the blade body on the second blade height side, and a second counter gas path surface facing the second blade height side and facing back to back with the second gas path surface, a cavity is formed in the blade body and the first shroud, the cavity being continuous within the blade body and the first shroud and opening at the first anti-gas path surface or the first side circumferential surface; a plurality of suction holes are formed in the blade body, each having an inlet opening that opens on the suction surface and an outlet opening that opens on an inner surface that defines the cavity, the suction holes penetrating from the suction surface to the inner surface that defines the cavity; an area of ​​a predetermined width in the longitudinal direction in which the leading edge and the trailing edge are aligned on the suction surface and which extends from an end of the suction surface on the first blade height side to an end of the suction surface on the second blade height side forms an opening formation area; In the opening formation region, the inlet openings are formed for the plurality of suction holes arranged in the blade height direction and the front-rear direction. Compressor stator vanes.

2. The compressor vane according to claim 1, the opening formation region has: a first side region including an end of the suction surface on the first blade height side; an intermediate region including an intermediate position in the blade height direction on the suction surface and extending from the end of the first side region on the second blade height side to the second blade height side; and a second side region extending from the end of the intermediate region on the second blade height side to the end of the suction surface on the second blade height side, a total area of ​​the inlet openings in at least one of the first side region and the second side region is greater than a total area of ​​the inlet openings in the intermediate region; Compressor stator vanes.

3. The compressor vane according to claim 2, the number of the inlet openings in the at least one side region is greater than the number of the inlet openings in the middle region, and the density of the inlet openings in the at least one side region is greater than the density of the inlet openings in the middle region; Compressor stator vanes.

4. The compressor vane according to claim 2, a width in the front-rear direction of the at least one side region gradually increases as the width increases away from the intermediate region in the wing height direction; a maximum width in the front-rear direction of the at least one side region is greater than a maximum width in the front-rear direction of the intermediate region; the number of the inlet openings in the at least one side region gradually increases as the blade moves away from the intermediate region in the blade height direction, the number of the inlet openings in the at least one side region is greater than the number of the inlet openings in the intermediate region, and the density of the inlet openings in the at least one side region is higher than the density of the inlet openings in the intermediate region; Compressor stator vanes.

5. The compressor vane according to claim 2, The at least one side region includes the first side region and the second side region. Compressor stator vanes.

6. The compressor vane according to claim 1, The center position of the opening formation region in the longitudinal direction is a position within a range of 45% to 65% of the width of the wing body in the longitudinal direction from the leading edge. Compressor stator vanes.

7. The compressor vane according to claim 6, The position of the end of the opening forming region on the leading edge side in the longitudinal direction is on the trailing edge side of a position that is 30% of the width of the wing body in the longitudinal direction from the leading edge. Compressor stator vanes.

8. The compressor vane according to claim 1, at least one of the first shroud and the second shroud has an inlet opening that opens in a gas path surface of the at least one shroud and an outlet opening that opens on the inner surface that defines the cavity, and a plurality of suction holes are formed that penetrate from the gas path surface to the inner surface that defines the cavity; a negative pressure side is a side of the positive pressure side where the negative pressure surface is located, a region of the gas path surface of the at least one shroud on the suction side of the blade body and along the suction surface forms an opening forming region; the inlet openings are formed in the opening formation region in the gas path surface of the at least one shroud for each of the plurality of suction holes formed in the at least one shroud. Compressor stator vanes.

9. The compressor vane according to claim 8, an end of the gas path surface of the at least one shroud on the side of the leading edge in the longitudinal direction in the opening formation region is located on the trailing edge side of a position that is 30% of the width of the airfoil in the longitudinal direction from the leading edge, Compressor stator vanes.

10. The compressor vane according to claim 1, each of the plurality of suction holes is inclined with respect to a plane on which the inlet opening is formed so as to gradually extend from the front edge side to the rear edge side in the front-rear direction as it moves from the inlet opening to the outlet opening; an angle of the direction in which the plurality of suction holes extend relative to a plane on which the inlet opening is formed being equal to or greater than 20° and equal to or less than 70°; each of the plurality of suction holes has a minimum inner diameter in a portion between the inlet opening and the outlet opening, and gradually increases in diameter from the minimum inner diameter portion toward the inlet opening, and also gradually increases in diameter from the minimum inner diameter portion toward the outlet opening; Compressor stator vanes.

11. The compressor vane according to claim 10, a ratio of the hole length of each of the plurality of suction holes to the minimum inner diameter of each of the plurality of suction holes is 2 or less; Compressor stator vanes.

12. The compressor vane according to claim 10, a ratio of an area of ​​the outlet opening to a cross-sectional area of ​​the suction hole at the position of the minimum inner diameter is 1.5 or less; The area of ​​the outlet opening is an area in a direction perpendicular to the direction in which the suction hole having the outlet opening extends. Compressor stator vanes.

13. The compressor vane according to claim 1, The minimum inner diameter of each of the plurality of suction holes is 0.8% or more and 3.0% or less of the width of the wing body in the front-to-rear direction. Compressor stator vanes.

14. The compressor vane according to claim 1, a distance between the central axes of two adjacent suction holes among the plurality of suction holes is 1.5% or more and 7.0% or less of the width of the wing body in the longitudinal direction; Compressor stator vanes.

15. The compressor vane according to claim 1, the inner surface defining the cavity has a plurality of partial inner surfaces that are connected to one another; Among the plurality of partial inner surfaces, the surfaces of the corners of two adjacent partial inner surfaces are curved surfaces with a radius of 3.5% or more of the width of the wing body in the longitudinal direction. Compressor stator vanes.

16. The compressor vane according to claim 1, a width in the front-to-rear direction of a wing body cavity, which is a portion of the cavity formed in the wing body, is 60% or more of a width in the front-to-rear direction of the wing body, the position of the leading edge side end of the wing-body cavity is on the leading edge side of a position that is 20% of the width of the wing-body in the longitudinal direction from the leading edge, The position of the end of the wing-body cavity on the trailing edge side is on the trailing edge side of a position that is 70% of the width of the wing-body in the longitudinal direction from the leading edge. Compressor stator vanes.

17. a compressor rotor rotatable about an axis; a compressor casing that covers the compressor rotor; a plurality of stator blade rows arranged in an axial direction in which the axis extends; Equipped with the compressor rotor has a rotor shaft extending in the axial direction about the axis line, and a plurality of rotor blade rows attached to the rotor shaft and aligned in the axial direction, each of the plurality of stator blade rows is disposed downstream of any one of the plurality of rotor blade rows in the axial direction and attached to the compressor casing; Each of the plurality of stator blade rows has a plurality of stator blades arranged in a circumferential direction with respect to the axis, each of the plurality of stator vanes included in at least one stator vane row among the plurality of stator vane rows is the compressor stator vane according to any one of claims 1 to 16, the front-rear direction is the axial direction, the blade height direction is a radial direction relative to the axis, The first blade height side is the radially outer side of the radially inner side and the radially outer side in the radial direction, The blade height second side is the radially inner side, Compressor.

18. 18. The compressor according to claim 17, The compressor casing has a cylindrical shape centered on the axis, and includes one or more blade rings that hold a portion of the plurality of stator blade rows, and a casing body that is disposed on the outer circumferential side of the one or more blade rings and to which the one or more blade rings are attached; and Among the one or more blade rings, a blade ring that holds the at least one stator vane row has a blade ring bleed flow passage that penetrates from an inner peripheral side to an outer peripheral side, communicates with the cavity of each of the plurality of stator vanes of the at least one stator vane row, and allows air from the cavity to flow in, the casing body has a main body bleed flow passage that penetrates from an inner peripheral side to an outer peripheral side, receives air from the blade ring bleed flow passage, and is capable of discharging the air to the outer peripheral side of the casing body. Compressor.

19. a gas turbine including the compressor according to claim 18, a combustor capable of burning fuel in air compressed by the compressor to generate combustion gas, and a turbine capable of being driven by the combustion gas; A cooling device; Equipped with The turbine is a turbine rotor rotatable about the axis; a turbine casing that covers the turbine rotor; a plurality of stator blade rows arranged in the axial direction and disposed on an inner peripheral side of the turbine casing; and The cooling device is a bleed line connected to the main body bleed flow path of the compressor casing; a cooler capable of cooling air from the extraction line; a boost compressor capable of compressing the air cooled by the cooler; a cooling air line capable of guiding the air cooled by the cooler and compressed by the boost compressor to at least one stator blade row of the plurality of stator blade rows of the turbine; having Gas turbine equipment.

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