WO2023282078A1 - タービン静翼およびガスタービン - Google Patents
タービン静翼およびガスタービン Download PDFInfo
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- WO2023282078A1 WO2023282078A1 PCT/JP2022/025110 JP2022025110W WO2023282078A1 WO 2023282078 A1 WO2023282078 A1 WO 2023282078A1 JP 2022025110 W JP2022025110 W JP 2022025110W WO 2023282078 A1 WO2023282078 A1 WO 2023282078A1
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- Prior art keywords
- cooling
- cooling hole
- opening
- cavity
- blade
- Prior art date
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- 238000001816 cooling Methods 0.000 claims abstract description 834
- 239000000567 combustion gas Substances 0.000 claims abstract description 113
- 238000011144 upstream manufacturing Methods 0.000 claims abstract description 42
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/182—Transpiration cooling
- F01D5/183—Blade walls being porous
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- a gas turbine mixes combustion of compressed air and fuel to generate high-temperature combustion gas.
- Turbine stator vanes that form a part of the gas turbine are arranged in the generated hot combustion gas, so they may be thermally damaged by the hot combustion gas.
- the turbine stator blade receives part of the compressed air from the outside as cooling air to cool the blade body and the shroud.
- An example of a cooling structure using cooling air for turbine stationary blades is shown in Patent Document 1.
- Patent Literature 1 discloses an example in which cooling holes necessary for the high temperature region and the low temperature region of the blade body and the shroud are arranged in each region to perform proper cooling.
- the present disclosure applies a more appropriate cooling means to the suction surface side leading edge region of the shroud, which has a particularly high heat load, among the shrouds of the turbine stator blades, and is capable of further reducing the amount of cooling air. Intended to provide wings.
- At least one embodiment according to the present disclosure is a turbine stator vane comprising a blade body, a shroud formed at an end portion of the blade body in a blade height direction, and a fillet portion joining the blade body and the shroud.
- the shroud includes a bottom plate in contact with the combustion gas flow path, a peripheral wall extending in the blade height direction along the peripheral edge of the bottom plate, and a recess forming a space surrounded by the peripheral wall and the bottom plate, wherein the peripheral wall includes a leading edge end extending to the leading edge side of the wing body and a suction side end extending from the leading edge on the suction side of the wing body to the trailing edge, and the shroud is formed in the suction side leading edge region of the shroud and includes a plurality of the cooling holes formed in the bottom plate, said plurality of cooling holes having a first end connected to an inlet opening formed in said bottom plate; a second end connected to an outlet opening formed in the gas path surface of the bottom plate
- an appropriate cooling structure is formed in the suction side leading edge region of the shroud to evenly cool the gas path side of the bottom plate. Also, the amount of cooling air is reduced, improving the efficiency of the gas turbine.
- FIG. 1 is a configuration diagram of a gas turbine in one embodiment according to the present disclosure.
- 2 is a perspective view of a gas turbine stator vane in one embodiment according to the present disclosure;
- FIG. 3 is a plan view of an embodiment shroud according to the present disclosure;
- FIG. 4 is a cross-sectional view of the shroud along line AA of FIG. 3.
- FIG. 5 shows a planar cross-section of the gas path surface of the shroud along line BB of FIG.
- FIG. 6 shows a plan cross-section of another embodiment of the gas path surface of the shroud along line BB of FIG.
- FIG. 7 is a detail view showing part of a planar cross-section of the gas path surface of the shroud shown in FIG. 6;
- 8A and 8B are a plan view and a cross-sectional view of a cooling hole showing the details of the portion C in FIG.
- FIG. 9 is a flow chart showing a cooling method for turbine stator blades.
- FIG. 1 is a schematic configuration diagram showing a gas turbine 1 of an embodiment to which a turbine stator blade 24 is applied.
- a gas turbine 1 includes a compressor 2 for generating compressed air, a combustor 4 for generating combustion gas G using the compressed air and fuel, and a combustion a turbine 6 that is rotationally driven by the gas G.
- a generator (not shown) is connected to the turbine 6 so that rotational energy of the turbine 6 is used to generate power.
- the compressor 2 is provided in a compressor casing 10 and an inlet side of the compressor casing 10, and is provided so as to pass through both the compressor casing 10 and a turbine casing 22, which will be described later, and an intake chamber 12 for taking in air. and various blades arranged in the compressor casing 10 .
- the various vanes are an inlet guide vane 14 provided on the intake chamber 12 side, a plurality of compressor stator vanes 16 fixed on the compressor casing 10 side, and axially alternate with respect to the compressor stator vanes 16. a plurality of compressor rotor blades 18 implanted in the rotor 8 in an array.
- the compressor 2 may include other components such as an air bleed chamber (not shown).
- air taken from the intake chamber 12 passes through a plurality of compressor stator blades 16 and a plurality of compressor rotor blades 18 and is compressed to generate compressed air.
- Compressed air is sent axially downstream from the compressor 2 to a combustor 4 .
- the combustor 4 is arranged inside the casing 20 . As shown in FIG. 1 , a plurality of combustors 4 are annularly arranged around a rotor 8 in a casing 20 .
- the combustor 4 is supplied with fuel and compressed air generated by the compressor 2 , and combusts the fuel to generate a high-temperature, high-pressure combustion gas G, which is a working fluid for the turbine 6 .
- the generated combustion gas G is sent from the combustor 4 to the turbine 6 on the downstream side in the axial direction.
- the turbine 6 includes a turbine casing (casing) 22 and various turbine blades arranged within the turbine casing 22 .
- the various turbine blades are composed of a plurality of turbine stator vanes 24 fixed on the turbine casing 22 side and a plurality of turbines implanted in the rotor 8 so as to be alternately arranged in the axial direction with respect to the turbine stator vanes 24.
- the rotor 8 extends in the axial direction, and the combustion gas G discharged from the turbine casing 22 is discharged to the exhaust casing 28 on the downstream side in the axial direction.
- the left side of the drawing is the axial upstream side
- the right side of the drawing is the axial downstream side.
- a radial direction means a direction perpendicular to the rotor 8 .
- the circumferential direction it represents the rotation direction of the rotor 8 .
- the radial direction may also be referred to as the wing height direction.
- the turbine rotor blades 24 are configured to generate rotational driving force from the high-temperature, high-pressure combustion gas G flowing inside the turbine casing 22 together with the turbine stator blades 24 . This rotational driving force is transmitted to the rotor 8 to drive a generator (not shown) connected to the rotor 8 .
- An exhaust chamber 29 is connected to an axially downstream side of the turbine casing 22 via an exhaust casing 28 .
- the combustion gas G after driving the turbine 6 is discharged to the outside through the exhaust vehicle chamber 28 and the exhaust chamber 29 .
- FIG. 2 shows a perspective view of the turbine stator vane 24 .
- the stationary blade 24 of the turbine 6 has a blade body 40 extending in the blade height direction and shrouds 60 on both outer and inner ends of the blade body 40 in the blade height direction.
- the shroud 60 includes an outer shroud 60a formed on the outer side of the wing body 40 in the wing height direction, and an inner shroud 60b formed on the inner side of the wing body 40 in the wing height direction.
- the blade body 40 is arranged in a combustion gas flow path 47 through which the combustion gas G flows.
- the outer shroud 60 a defines the outer position in the blade height direction of the combustion gas flow path 47 annularly formed around the rotor 8 .
- the inner shroud 60b defines the inner position of the annular combustion gas flow path 47 in the blade height direction.
- a hook 76 for supporting the turbine stator blade 24 in the turbine casing 22 is provided on the outer shroud 60 a of the stator blade 40 on the trailing edge 43 side of the blade body 40 .
- the hook 76 of the turbine stationary blade 24 is provided on the peripheral wall 62 on the trailing edge 43 side of the outer shroud 60a.
- the wing body 40 extends in the wing height direction, connects to the outer shroud 60a via a fillet portion 46 on the outer side in the wing height direction, and connects to the outer shroud 60a on the inner side in the wing height direction. It connects to the inner shroud 60b via the portion 46.
- the blade body 40 forms the turbine stationary blade 24 together with the outer shroud 60a and the inner shroud 60b.
- FIG. 3 shows a plane cross section of the outer shroud 60a viewed from the outside in the blade height direction, which is on the opposite side of the combustion gas flow path 47.
- the outer shroud 60a side will be described as an example.
- the wing body 40 connected to the outer shroud 60a via the fillet portion 46 forms a wing shape.
- Airfoil 40 has a leading edge 42 at an axially upstream end and a trailing edge 43 at an axially downstream end.
- the blade body 40 has, of the circumferentially facing surfaces of the blade surface 41, a suction surface 44 forming a convex surface and a pressure surface 45 forming a concave surface.
- the suction side 44 and the pressure side 45 join at the leading edge 42 and the trailing edge 43 and together form a single airfoil 40 .
- the side of the pressure surface 45 of the wing body 40 may be referred to as the ventral side
- the side of the suction surface 44 of the wing body 40 may be referred to as the dorsal side.
- the wing body 40 extends in the wing height direction and has a wing body cavity 51 (first cavity) through which the cooling air Ac flows in the internal space of the wing body 40 .
- the blade cavity 51 extends in the blade height direction from the outer shroud 60a to the inner shroud 60b, and a plurality of internal spaces are continuously formed between the leading edge 42 and the trailing edge 43.
- three wing-body cavities 51 (a wing-body leading edge cavity 52, a wing-body intermediate cavity 53, an example of the arrangement of the wing body trailing edge cavity 54) is shown as an example.
- the blade cavity 51 has a plurality of blade partition ribs 49 connected at one end to the inner wall 62a of the blade wall 40b on the suction surface 44 side and at the other end to the inner wall 62a of the blade wall 40b on the pressure surface 45 side. divided into internal spaces.
- the wing body cavity 51 is composed of a wing body leading edge cavity 52 disposed on the leading edge 42 side of the wing body 40 via the wing body partitioning rib 49 and a wing body leading edge cavity 52 is subdivided into an airfoil mid-cavity 53 located axially downstream and adjacent thereto.
- the wing body cavity 51 is adjacent to the wing body intermediate cavity 53 via the wing body partitioning rib 49 and the axially downstream side of the wing body intermediate cavity 53. It is divided into wing body trailing edge cavities 54 located therein.
- Each of the blade cavities 51 does not communicate with each other and opens to either the outer shroud 60a or the inner shroud 60b, and the blade end 40a of the other blade cavity 51 is provided with a lid 56 or the like. , is blocked. All airfoil cavities 51 are supplied with cooling air Ac from either outer shroud 60 a or inner shroud 60 b to cool airfoil 40 and discharge airfoil 41 into combustion gas flow path 47 .
- the blade cavity 51 communicates with each other to form a serpentine flow path, and cooling air Ac is supplied from one opening 56a of the blade leading edge cavity 52 in the blade height direction. It may flow through the body trailing edge cavity 54 and exit into the combustion gas flow path 47 through cooling passages (not shown) formed in the trailing edge 43 .
- FIG. 4 shows a cross section of the wing body leading edge cavity 52 of the wing body 40 and the outer shroud 60a around the wing body leading edge cavity 52 along line AA in FIG.
- the outer shroud 60a includes a bottom plate 69 that forms the bottom surface of the outer shroud 60a, and is formed around the entire outer periphery of the bottom plate 69.
- a peripheral wall 62 erected in the height direction, partition ribs 73 dividing a recess 75 formed by the bottom plate 69 and the peripheral wall 62 into a plurality of cavities 80, and the cavities 80 (recesses 75) are separated from each other on the outer side in the blade height direction.
- It is composed of a collision plate 85 that divides into a cavity 82 (third cavity) and an inner cavity 83 (fourth cavity) on the inner side in the blade height direction.
- a collision plate 85 arranged in the cavity 80 has a plurality of through holes 86 that communicate the outer cavity 82 and the inner cavity 83 .
- the outer cavity 82 forms part of the recess 75 and forms one space with the outer shroud 60a.
- the inner cavity 83 is arranged inside the outer cavity 82 in the blade height direction with the recess 75 divided into a plurality of spaces in the blade height direction by the collision plate 85 with the collision plate 85 interposed therebetween.
- the peripheral wall 62 is arranged to face a front edge end 64 formed on the axially upstream side of the front edge 42 and axially downstream of the front edge end 64 .
- a suction side end 66 formed at the end of the circumferential blade body 40 on the side of the suction side 44 and circumferentially opposed to the suction side end 66 and a pressure surface side end portion 67 formed at the end portion of the blade body 40 on the pressure surface 45 side.
- the bottom plate 69 has an outer surface (gas path surface) 71 in contact with the combustion gas G inside the combustion gas flow path 47 in the blade height direction, and a counterflow on the side opposite to the outer surface (gas path surface) 71 in the blade height direction. and an inner surface (counter-flow surface) 70 facing outward in the blade height direction on the roadside.
- the bottom plate 69 has a plurality of cooling holes 89, the details of which will be described later.
- the cooling hole 89 penetrates the bottom plate 69 in the blade height direction and communicates with the combustion gas flow path 47 facing the inner cavity 83 and the outer surface 71 via the cooling hole 89 .
- the outer edge of the blade body 40 in the blade height direction (the inner side in the blade height direction in the case of the inner shroud 60b) extends from the inner surface 70 of the bottom plate 69 of the outer shroud 60a to the outer side or inner side in the blade height direction. has a wing body end 40a that slightly protrudes into the
- the region of the outer shroud 60 a on the suction surface 44 side and on the front edge 42 side protrudes from the inner surface 70 of the bottom plate 69 to the opposite side of the flow path, which is opposite to the outer surface (gas path surface) 71 .
- a plurality of projecting partition ribs 73 are provided.
- the partition rib 73 is a leading edge partition rib 73 a that connects the leading edge end portion 64 and the blade body end portion 40 a on the leading edge 42 side of the blade body 40 formed in the recess 75 of the shroud 60 .
- a suction surface side intermediate partition rib 73 b that connects the blade body end portion 40 a of the blade body 40 and the suction side end portion 66 .
- the inner cavity 83 communicates with the outer cavity 82 via the through hole 86 of the impingement plate 85 on the outer side in the blade height direction, and communicates with the outer cavity 82 via the cooling hole 89 of the bottom plate 69 on the inner side in the blade height direction. It communicates with the gas flow path 47 .
- the configuration of the inner shroud 60b is substantially the same as the configuration of the outer shroud 60a described above. That is, the structure shown in FIGS. 3 and 4 is an example of the outer shroud 60a, but the structure shown in FIGS. 3 and 4 can also be applied to the structure of the inner shroud 60b. Therefore, the names and symbols of the components of the inner shroud 60b may be the same as the description of the components of the outer shroud 60a, unless otherwise specified. In the following description using FIGS. 4 to 8 as well, the description relating to the outer shroud 60a is also applicable to the inner shroud 60b, unless otherwise specified. In the case of the inner shroud 60b, the outer side in the blade height direction of the outer shroud 60a should be read as the inner side in the blade height direction, and the inner side in the blade height direction should be read as the outer side in the blade height direction.
- the region forming the combustion gas flow path 47 sandwiched between the shrouds 60 at both ends of the turbine stator blade 24 in the blade height direction is a region where the high-temperature combustion gas G flowing into the turbine stator blade 24 from the upstream side in the axial direction passes through the blade.
- gas path surface 71 of shroud 60 As it flows along surface 41 and gas path surface 71, gas path surface 71 of shroud 60 is superheated.
- the gas path surface 71 on the negative pressure surface 44 side of the leading edge 42 tends to overheat remarkably because the flow velocity of the combustion gas G is faster than that on the positive pressure surface 45 side. Therefore, a cooling means for suppressing thermal damage from the combustion gas G to the shroud 60 is required.
- shroud 60 including an outer shroud 60a and an inner shroud 60b will be described. Therefore, shroud 60 is applicable to both outer shroud 60a and inner shroud 60b unless otherwise specified.
- FIGS. 5, 6 and 7 show plan cross-sections of the leading edge 42 side of the suction surface 44 when the outer shroud 60a is viewed from the side of the gas path surface (outer surface) 71 on the inner side in the blade height direction.
- 4 is a sectional view along line BB of FIG.
- the cooling structure of this embodiment includes an impingement plate 85 having a plurality of through holes 86, a bottom plate 69 having a plurality of cooling holes 89, and an outer cavity 82 formed outside the impingement plate 85 in the blade height direction. and an inner cavity 83 formed inside the impingement plate 85 in the blade height direction.
- the shroud 60 allows the cooling air Ac supplied from the outer cavity 82 through the through holes 86 formed in the impingement plate 85 to blow into the inner cavity 83 and onto the inner surface 70 of the bottom plate 69 .
- a cooling structure combining a film cooling structure for cooling the outer surface (gas path surface) 71 of the bottom plate 69 is formed. 3, 4, 5 and 9, a cooling structure combining impingement cooling and film cooling of the suction side leading edge cavity 81 will be specifically described below.
- a plurality of cooling holes 89 are arranged along the blade surface 41 of the blade body 40 so as to surround the blade surface 41 in the outer surface (gas path surface) 71 of the suction side leading edge cavity 81 of the shroud 60 .
- a plurality of cooling hole rows 90 having a plurality of cooling holes 89 surround the outer periphery of the blade surface 41 of the blade body cavity 51 of the blade body 40 on the suction side 44 side. , along the curved surface of the blade surface 41 at predetermined intervals.
- the plurality of cooling hole rows 90 are formed so as to gradually change the inclination with respect to the axial direction as they go toward the downstream side in the axial direction.
- Cooling hole rows 90 (91, 92, 93, 94) shown in FIG. and a fourth cooling hole array 94 .
- Each respective cooling hole row 91 , 92 , 93 , 94 each comprises a plurality of cooling holes 89 .
- the reference numerals of the cooling holes 89 forming the third cooling hole row 93 and the fourth cooling hole row 94 are the most airfoil. Only the cooling holes 89 closest to the surface 41 and the cooling holes 89 farthest from the blade surface 41 are indicated with reference numerals, and the reference numerals of the other cooling holes 89 are omitted.
- each of the cooling hole rows 91, 92, 93, and 94 is arranged from the blade surface 41 side of the blade body 40 to the leading edge end 64 or It is composed of a plurality of cooling holes 89 arranged at predetermined intervals toward the suction surface side end portion 66 .
- the direction in which the cooling hole 89 extends is the same as the direction in which the cooling hole center line FL extends. match.
- the combustion gas G flowing into the gas path surface 71 on the leading edge 42 side of the turbine stationary blade 24 from the upstream side in the axial direction flows along the blade surface 41 of the blade body 40 toward the suction surface 44 side and the pressure surface 45 .
- flow on the side A blade surface 41 on the negative pressure surface 44 side of the blade body 40 forms a convex curved surface, and the shape of the blade surface 41 changes toward the downstream side in the axial direction. Therefore, the direction of flow of the combustion gas G flowing along the blade surface 41 changes as the curved surface of the blade surface 41 of the blade body 40 changes.
- the cooling air Ac discharged from the cooling holes 89 of the bottom plate 69 of the shroud 60 into the combustion gas flow path 47 is directed along the flow of the combustion gas G whose flow direction changes so as not to disturb the flow of the combustion gas G. It is desirable to discharge in the direction. Therefore, the plurality of cooling holes 89 forming the plurality of cooling hole rows 90 are arranged so as to gradually change their inclination with respect to the axial direction along with the change in the flow direction of the combustion gas G along with the axial downstream side. That is, the inclination of the cooling hole center lines FL of the plurality of cooling holes 89 forming the plurality of cooling hole rows 90 with respect to the axial line AL gradually decreases toward the downstream side in the axial direction.
- each of the cooling hole rows 91, 92, 93, and 94 shown in FIG. toward the leading edge end 64 or the suction side end 66, in the direction away from the blade surface 41, the plurality of cooling holes 89 forming the same cooling hole row 90 are arranged at the same intervals and at the same distance.
- a configuration that extends while maintaining an inclination with respect to the axial line AL is desirable.
- the direction in which the groups of the cooling hole rows 91, 92, 93, and 94 extend is parallel to the direction in which the isobar IBL of the combustion gas G, which will be described later, extends.
- the cooling hole centerline FL of the cooling hole 89 described above is the inlet of the plurality of cooling holes 89 forming each of the cooling hole rows 91 , 92 , 93 , 94 forming the cooling hole row 90 . It is indicated by a straight solid line connecting the center of the opening 89a and the center of the outlet opening 89b.
- a plurality of cooling holes 89 forming each of the cooling hole rows 91, 92, 93, 94 are arranged from positions approaching the blade surface 41 of the plurality of cooling holes 89 in which the respective cooling hole rows 91, 92, 93, 94 are arranged.
- first opening centerline OL1 which is a dashed line connecting the centers of the outlet openings 89b of the cooling holes 89 adjacent to each other.
- the plurality of cooling holes 89 that form the same cooling hole row 90 are arranged from positions approaching the blade surface 41 of the plurality of cooling holes 89 in which the respective cooling hole rows 91, 92, 93, and 94 are arranged.
- second opening centerline OL2 shown by a dashed line connecting the centers of the inlet openings 89a of the cooling holes 89 adjacent to each other.
- the first opening centerline OL1 and the second opening centerline OL2 are collectively referred to as the opening centerline OL.
- the structure of the cooling hole 89 is shown in FIG. 8 as details of the C section of the cooling hole shown in FIG. 8, the cooling hole 89 formed in the bottom plate 69 has an inlet opening 89a that opens to the inner surface 70 and an outlet opening 89b that opens to the outer surface (gas path surface) 71. As shown in FIG. An outlet opening 89b is formed at a position on the side of the trailing edge 43 on the downstream side in the axial direction from the position of the inlet opening 89a.
- the inclination of the cooling hole 89 with respect to the inner surface 70 or the outer surface (gas path surface) 71 of the bottom plate 69 is the same.
- the length of the line FL is also the same.
- the cooling hole row 90 is the cooling hole 89 closest to the blade surface 41 with reference to the position of the cooling hole 89 closest to the blade surface 41 . , toward the leading edge end 64 or the suction side end 66 in a direction away from the blade surface 41 .
- Each cooling hole row 91, 92, 93, 94 consisting of a plurality of cooling holes 89 is regarded as one group of cooling holes 89 extending while maintaining the same spacing and the same inclination with respect to the axial line AL. be able to.
- the cooling hole center lines FL of the plurality of cooling holes 89 forming the same cooling hole rows 91, 92, 93, 94 are parallel to each other and the same within the same cooling hole rows 91, 92, 93, 94. , and the inclination with respect to the same axial line AL.
- the first opening center line OL1 and the second opening center line OL2 of the plurality of cooling holes 89 forming the same cooling hole rows 91, 92, 93, and 94 are formed parallel to each other and are aligned with the cooling hole center line FL. It extends with the same inclination.
- the inclination of the cooling hole center line FL with respect to the first opening center line OL1 is preferably maintained at the same inclination in the same cooling hole rows 91, 92, 93, and 94 at any position in the axial direction. .
- each cooling hole row As shown in FIG. 5, when comparing the plurality of cooling hole rows 90 (91, 92, 93, 94) arranged from the axial upstream side to the downstream side, each cooling hole row
- the direction in which the groups of the plurality of cooling holes 89 forming the 91, 92, 93, and 94 extend coincides with the direction in which the first opening centerline OL1 and the second opening centerline OL2 extend, and extends toward the downstream side in the axial direction.
- the inclination with respect to the axial direction increases and the inclination with respect to the axial line AL decreases.
- the cooling hole center lines FL of the cooling holes 89 of the cooling hole array 90 are compared, the cooling hole center lines FL of the groups of the plurality of cooling holes 89 forming the respective cooling hole arrays 91, 92, 93, and 94 extend.
- the direction coincides with the direction in which the cooling hole center line FL of each cooling hole 89 extends, and as it goes axially downstream, the inclination with respect to the axial direction becomes smaller, and the inclination with respect to the axial direction line AL becomes smaller.
- first opening center line OL1 and the second opening center line OL2 of each of the cooling hole rows 91, 92, 93, and 94 also tend toward the downstream side in the axial direction, and the inclination with respect to the axial direction increases. slope becomes smaller.
- the first cooling hole row 91 arranged on the most upstream side in the axial direction is directed toward the leading edge end 64 or the suction side end 66 with reference to the cooling hole 91a closest to the blade surface 41. It is composed of five cooling holes 91a, 91b, 91c, 91d, and 91e having the same spacing and the same inclination with respect to the axial direction of the cooling hole center line FL.
- the second cooling hole row 92 arranged adjacent to the first cooling hole row 91 on the downstream side in the axial direction is located at the suction surface side end portion with reference to the cooling hole 92 a closest to the blade surface 41 .
- first cooling hole array 91 is arranged parallel to an isobar IBL1 of the combustion gas G, which will be described later, and the first opening center line OL1 of the second cooling hole array 92 is aligned with the combustion gas G. It is arranged parallel to the isobar line IBL2.
- the first opening center line OL1 of the second cooling hole row 92 is axially offset from the first opening center line OL1 of the first cooling hole row 91.
- the inclination increases and the inclination with respect to the axial line AL decreases.
- the cooling hole center line FL of the second cooling hole array 92 has a greater inclination with respect to the axial direction than the cooling hole center line FL of the first cooling hole array 91, and has a smaller inclination with respect to the axial direction line AL.
- the isobar IBL of the combustion gas G which will be described later, is axially downstream, approaches the suction surface side end portion 66, has a large inclination with respect to the axial direction, and has a small inclination with respect to the axial direction line AL.
- the opening centerline (first opening centerline OL1) of each of the cooling hole rows 91, 92, 93, and 94 be arranged parallel to the constant pressure line IBL of the combustion gas G.
- the opening center line OL and the cooling hole center line FL which are the directions in which the respective cooling hole rows 91, 92, 93, and 94 extend, change along with the change in the inclination of the isobar IBL of the combustion gas G with respect to the axial line AL. It is desirable to change the inclination of the opening centerline (first opening centerline OL1) of the cooling hole rows 91, 92, 93, 94 with respect to the axial line AL. That is, the opening center line OL and the cooling hole center line FL of each of the cooling hole rows 91, 92, 93, and 94 are directed downstream in the axial direction, and the inclination with respect to the axial line AL gradually decreases.
- the inclination or angle of the opening centerline OL (the first opening centerline OL1, the second opening centerline OL2) or the cooling hole centerline FL of the plurality of cooling holes 89 forming the cooling hole row 90 with respect to the axial line AL is an axial line AL that passes through the leading edge 42 and extends in the axial direction.
- the center line OL or the cooling hole center line FL is viewed, it means the inclination or angle formed by the axial direction line AL and the opening center line OL or the cooling hole center line FL in the counterclockwise direction.
- the number and arrangement of the plurality of cooling holes 89 forming each cooling hole row 90 are selected in consideration of the metal temperature of the gas path surface 71 of the shroud 60 and the like.
- the embodiment shown in FIG. 5 has four cooling hole rows 90 (a first cooling hole row 91, a second cooling hole row 92, a third cooling hole row 93, and a fourth cooling hole row) in the suction side leading edge cavity 81. 94) are arranged at a predetermined interval in the downstream direction from the upstream side in the axial direction.
- the number of cooling hole rows 90 is not limited to four, and may be three or less, or may be five or more.
- the number of cooling holes 89 may be five or more, or may be four or less.
- the number of cooling holes 89 in the third cooling hole row 93 and the fourth cooling hole row 94 may be three or more.
- FIG. 5 shows part of the pressure distribution of the combustion gas G flowing through the gas path surface 71 of the leading edge 42 of the shroud 60 on the negative pressure surface 44 side.
- An isobar IBL of the pressure (static pressure) of the combustion gas G is indicated by a dashed line.
- the pressure of the combustion gas G flowing into the turbine stationary blade 24 decreases while flowing through the combustion gas passages 47 on the suction surface 44 side and the pressure surface 45 side from the leading edge 42 to the trailing edge 43 .
- the isobar IBL of the combustion gas G has, for example, the blade surface 41 on the suction surface 44 side of the turbine stator blade 24 as a starting point Xa, and the blade surface 41 on the pressure surface 45 side of the turbine stator blade 24 (not shown) adjacent in the circumferential direction. is drawn as a gentle curve with the end point at .
- the isobar IBL means a curve connecting positions where the pressure (static pressure) of the combustion gas G flowing through the combustion gas flow path 47 shows the same pressure.
- An isobar IBL1 shown in FIG. 5 as an example of the isobar IBL of the combustion gas G connects a starting point Xa on the blade surface 41 of the blade body 40 and an intermediate point Xb located on the end surface of the suction surface side end portion 66, and is indicated by a dashed line. indicated by the gentle curve shown.
- the isobar IBL1 indicates part of the entire length of the isobar, and although not shown, is a curved line extending from the intermediate point Xb to the blade surface 41 of the adjacent turbine stator blade 24 on the pressure surface 45 side.
- the pressure (static pressure) of the combustion gas G decreases toward the downstream side in the axial direction of the gas path surface 71 .
- the isobar IBL1 from the starting point Xa to the intermediate point Xb extends axially downstream, separates from the blade surface 41, approaches the suction surface side end portion 66, has a large inclination with respect to the axial direction, and extends along the axial line AL. becomes smaller.
- the pressure (static pressure) of the isobar IBL2 is lower than that of the isobar IBL1. Further, the flow of the combustion gas G on the gas path surface 71 moves axially downstream and approaches the suction surface side end portion 66, and the axial distance between the isobars IBL1 and IBL2 increases.
- the tendency of the axial interval of the isobars IBL to widen is that the axial interval near the starting point Xa of the blade surface 41 is small, the axial interval gradually widens as the distance from the blade surface 41 increases, and the axial interval increases in the vicinity of the intermediate point Xb. widest.
- the inclination of the isobar IBL with respect to the axial direction varies greatly in the vicinity of the blade surface 41 , but varies slightly away from the blade surface 41 and up to the intermediate point Xb of the suction surface side end portion 66 .
- the first cooling hole row 91 arranged closest to the leading edge end 64 on the most upstream side in the axial direction among the plurality of cooling hole rows 90 is taken as an example.
- the relationship between the gas G and the isobar IBL will be described.
- the first cooling hole row 91 is composed of a group of five cooling holes 89 (91a, 91b, 91c, 91d, and 91e), and extends from a position close to the blade surface 41 toward the suction surface side end 66 at equal intervals. are arrayed.
- An example of the constant pressure line IBL of the combustion gas G in the vicinity of the first cooling hole array 91 is the constant pressure line IBL1.
- the isobar IBL1 is formed by drawing a gentle curve from a starting point Xa on the blade surface 41 on the suction surface 44 side of the leading edge 42 side of the blade body 40 to an intermediate point Xb on the end surface of the suction surface side end portion 66. .
- the arrangement of the plurality of cooling holes 89 of the first cooling hole row 91 is such that the first opening center line OL1 connecting the outlet openings 89b of the plurality of cooling holes 89 of the first cooling hole row 91 is substantially parallel to the isobar IBL1.
- the opening center line OL (first opening center line OL1) of the cooling hole 89 must be strictly parallel to the isobar IBL1.
- a curved line is desirable.
- the cooling holes 89 are formed by machining or electric discharge machining, it is desirable to arrange the plurality of cooling holes 89 such that the first opening center line OL1 is straight from the viewpoint of simplification of the machining work. .
- the first cooling device located near the isobar IBL1 extending from the starting point Xa on the blade surface 41 on the leading edge 42 side of the blade body 40 to the intermediate point Xb on the suction surface side end portion 66.
- the first opening centerline OL1 of the plurality of cooling holes 89 of the hole row 91 is the cooling hole 91a arranged closest to the blade surface 41 side and the adjacent cooling hole 91a in the direction from the blade surface 41 to the suction surface side end portion 66.
- the cooling hole 91a closest to the blade surface 41 and the adjacent cooling hole 91b are selected in the above description, a combination of other two adjacent cooling holes 89 of the same cooling hole row 90 may be selected. That is, the first cooling hole OL1 determined by the cooling holes 91d and the cooling holes 91e, which are a combination of the other cooling holes 89 forming the same first cooling hole row 91, is parallel to the isobar IBL1.
- the arrangement of the cooling holes 89 in the hole array 91 may be selected. Simply selecting the linear first opening centerline OL1 based on the outlet openings 89b of two adjacent cooling holes 89 of the same cooling hole row 90 improves the cooling performance of the shroud 60 and reduces the processing work.
- the two adjacent cooling holes 89 used when selecting the second opening center line OL2 are desirably a combination of the two adjacent cooling holes 89 used when selecting the first opening center line OL1.
- the arrangement of the plurality of cooling holes 89 of the cooling hole array 90 is selected so that the metal temperature, thermal stress, etc. of the bottom plate 69 forming the shroud 60 are within allowable values.
- the cooling structure of the shroud 60 consists of a combination of impingement cooling by the impingement plate 85 and film cooling by the cooling holes 89 of the bottom plate 69. Thermal damage from the combustion gas G is suppressed. As shown in FIG.
- the cooling air Ac supplied to the shroud 60 from the outside is supplied to the outer cavity 82 and supplied to the inner cavity 83 through the through holes 86 formed in the impingement plate 85 .
- the cooling air Ac is decompressed while passing through the through holes 86 of the impingement plate 85 .
- the cooling air Ac forms a jet in the course of flowing into the inner cavity 83 from the through-hole 86 and collides with the inner surface 70 of the floor plate 69 to impingement-cool (collision-cool) the inner surface 70 .
- the cooling air Ac after impingement cooling of the inner surface 70 film-cools the gas path surface 71 in the process of being discharged from the cooling holes 89 formed in the bottom plate 69 to the combustion gas flow path 47 on the side of the gas path surface 71 .
- a characteristic factor that influences the cooling of the shroud 60 by the arrangement of the cooling holes 89 of the cooling hole row 90 arranged in the suction side leading edge cavity 81 is film cooling by the cooling holes 89 .
- the combustion gas G that has flowed into the combustion gas flow path 47 of the turbine stationary blade 24 flows down the gas path surface 71 of the shroud 60 in the axial direction downstream, and the pressure ( static pressure) decreases.
- the amount of cooling air discharged from the inner cavity 83 of the shroud 60 into the combustion gas passage 47 through the cooling holes 89 is the difference in pressure between the inlet opening 89a and the outlet opening 89b of the cooling hole 89, that is, the cooling hole It depends on the differential pressure between the inner cavity 83 of 89 and the combustion gas flow path 47 .
- the amount of cooling air flowing through the cooling holes 89 of the cooling hole array 90 varies due to the difference in the pressure drop of the combustion gas G while the combustion gas G flows through the gas path surface 71 .
- the same pressure is maintained in the inner cavity 83 to which the inlet opening 89a on the upstream side of the cooling hole 89 connects as long as it is in the same space.
- the pressure of the combustion gas G on the side of the gas path surface 71 connected to the outlet opening 89b on the downstream side of the cooling hole 89 decreases toward the downstream side in the axial direction. Therefore, depending on the arrangement of the plurality of cooling holes 89 in the cooling hole row 90, a difference in differential pressure (pressure difference) occurs between the cooling holes 89 among the plurality of cooling holes 89 forming the same cooling hole row 90. Variation in the amount of cooling air discharged can occur. Variations in the amount of cooling air in the plurality of cooling holes 89 forming the cooling hole array 90 cause non-uniform film cooling and non-uniform metal temperature distribution of the bottom plate 69 .
- the first opening center line OL1 of the plurality of cooling holes 89 forming the same cooling hole row 90 is aligned with the isobar IBL of the combustion gas G near each of the cooling hole rows 91, 92, 93, and 94. It is desirable to select the arrangement of the plurality of cooling holes 89 of the same cooling hole row 90 so that they are generally parallel. If the arrangement of the plurality of cooling holes 89 of the same cooling hole row 90 is set so that the first opening center line OL1 of the cooling hole row 90 and the isobar IBL of the combustion gas G are substantially parallel, the same cooling hole row The plurality of cooling holes 89 that make up 90 can maintain the same differential pressure.
- the amount of cooling air discharged from the plurality of cooling holes 89 of the same cooling hole row 90 to the gas path surface 71 is made uniform.
- Film cooling on the downstream side in the axial direction from the positions of the plurality of cooling holes 89 of the cooling hole array 90 is made uniform.
- the temperature distribution of the gas path surface 71 of the shroud 60 is leveled, thermal damage to the bottom plate 69 is suppressed, and thermal stress caused by uneven temperature distribution of the bottom plate 69 is reduced.
- the pressure (static pressure) of the combustion gas G decreases axially downstream, but the axial interval between isobars IBL of the combustion gas G tends to increase axially downstream. . Therefore, the axial distance between the first opening center lines OL1 of the cooling hole rows 91, 92, 93, and 94 arranged in parallel with the isobar IBL also gradually increases toward the downstream in the axial direction. As a result, the gas path surface 71 on the downstream side in the axial direction from the plurality of cooling holes 89 of each of the cooling hole rows 91, 92, 93, 94 is uniformly cooled.
- the constant pressure line IBL of the combustion gas G moves toward the downstream side in the axial direction, approaches the suction surface side end portion 66, and increases in inclination with respect to the axial direction. Therefore, the axial inclination of the linear first opening center lines OL1 of the plurality of cooling hole arrays 90 is also directed toward the axial downstream side, and the inclination with respect to the axial direction is large in accordance with the change of the constant pressure line IBL.
- the slope with respect to AL becomes smaller gradually. As a result, as shown in FIG.
- the first opening center line OL1 extending toward the front edge 42 on the side opposite to the suction surface end portion 66 in the circumferential direction is directed downstream in the axial direction and has a smaller inclination with respect to the axial line AL.
- a circular front edge region 42a (first region) indicated by a dashed line inscribed in the outer edge 46a of the fillet portion 46 formed axially upstream of the position of the front edge 42 with respect to the position of the front edge 42 is formed.
- the first opening centerlines OL1 of the plurality of cooling hole rows 90 pass through the leading edge region 42a (first region).
- a plurality of cooling hole rows 90 (91, 92, 93, 94) composed of a plurality of cooling holes 89 formed in the suction side leading edge cavity 81 are centered around the leading edge 42.
- the first opening center line OL1 of at least one of the plurality of cooling hole rows 90 configured by the plurality of cooling holes 89 formed in the suction side leading edge cavity 81 is aligned with the leading edge cavity 81.
- the constant pressure line IBL of the combustion gas G has a parallel positional relationship with the first opening center line OL1 of the cooling hole array 90 as a characteristic factor that affects the arrangement of the cooling hole array 90 of the present embodiment.
- the combustion gas G flowing on the gas path surface 71 on the suction surface 44 side of the shroud 60 on the leading edge 42 side flows along the blade surface 41 having a convex curved surface.
- the region where the plurality of cooling holes 89 formed in the suction side leading edge cavity 81 are arranged extends from the upstream side to the downstream side in the axial direction, and the blade surface 41 of the blade body 40 extends toward the suction side end portion 66 . , and the inclination of the curved surface of the blade surface 41 with respect to the axial line AL gradually decreases.
- the cooling hole center line FL is arranged in a direction inclined toward the blade surface 41 from the direction orthogonal to the opening center line OL with respect to the direction in which the opening center line OL of the plurality of cooling holes 89 extends. ing.
- the cooling hole center lines FL of the same cooling hole rows 90 are also axially aligned.
- the inclination with respect to the axial line AL decreases toward the downstream side.
- the inclination or angle formed by the cooling hole center line FL of the cooling hole 89 of each of the cooling hole rows 91, 92, 93, and 94 with the opening center line OL (first opening center line OL1) may be any position in the axial direction. It is desirable to maintain the same inclination or angle.
- the inclination of the cooling hole center line FL of the same cooling hole row 90 with respect to the opening center line OL is not maintained, and the cooling hole center line FL is excessively inclined toward the blade surface 41 depending on the position of the cooling hole row 90 in the axial direction. In this case, the flow of cooling air Ac discharged from the cooling holes 89 disturbs the flow of the combustion gas G.
- the positional relationship between the first opening center line OL1 and the second opening center line OL2 of the cooling hole row 90 will be described by taking the first cooling hole row 91 as an example.
- the cooling hole center lines FL of the plurality of cooling holes 89 forming the same cooling hole row 90 have the same length and the same inclination. Therefore, as shown in FIG. 5, if the first opening center line OL1 of the first cooling hole row 91 is a straight line starting from the leading edge region (first region) 42a, then the same cooling hole row 90 can A second opening center line OL2 extending toward the front edge 42 connecting the inlet openings 89a of the cooling holes 89 is also formed in a straight line.
- the second opening centerline OL2 of the same first cooling hole array 91 is an upstream leading edge region located at a predetermined position axially upstream of the position of the leading edge 42 on the axial line AL passing through the leading edge 42. (Second region) is formed by a straight line starting from 42b.
- the upstream-side leading edge region (second region) 42b is on the axial direction line AL on the upstream side in the axial direction from the position of the leading edge 42, and is on the axis of the cooling hole center line FL of the first cooling hole row 91. It refers to an area formed in a circular shape with the same radius as the leading edge area 46a, centered at a position at a distance corresponding to the directional length, and indicated by a dashed line.
- the arrangement of the cooling holes 89 and their functions, actions, and effects have been described with a focus on the first cooling hole row 91.
- the selection of arrangement can also be set in the same manner as in the case of the first cooling hole row 91 described above.
- the opening center lines OL of the other cooling hole rows 90 change in inclination with respect to the axial line AL as they move toward the downstream side in the axial direction. Therefore, among the opening centerlines OL of all the cooling hole rows 90, the first opening centerline OL1 of at least one of the cooling hole rows 90 starts from the leading edge region (first region) 42a and extends from the second opening centerline OL1.
- the OL2 extends in the direction of the leading edge end portion 64 or the suction surface side end portion 66 from the upstream leading edge region (second region) 42b.
- FIG. 6 shows a plan cross-section of this embodiment of shroud 60 and is a plan view taken along line BB of FIG.
- FIG. 7 is a detailed view showing a portion of the plan view of this embodiment of the shroud 60 shown in FIG.
- the cooling structure of this embodiment relates to an embodiment in which the arrangement of the cooling holes 89 is changed from the structure of the first embodiment of the plurality of cooling holes 89 of the cooling hole row 90 formed in the shroud 60 described above.
- the cooling structure that constitutes the present embodiment differs from the first embodiment in that the arrangement of the plurality of cooling holes 89 that constitute the film cooling structure is different. It has a different configuration.
- the impingement cooling structure shown in FIGS. 3 and 4 is also applied to this embodiment.
- the cooling hole array 95 of this embodiment shown in FIG. It consists of columns 99 .
- Each respective cooling hole row 96 , 97 , 98 , 99 each comprises a plurality of cooling holes 89 .
- the arrangement of the plurality of cooling holes 89 of the plurality of cooling hole rows 95 (96, 97, 98, 99) according to this embodiment is indicated by solid lines, and for comparison, the first embodiment described below is shown.
- the arrangement of the plurality of cooling holes 89 of the plurality of cooling hole rows 90a (91, 92, 93, 94), which is a modification of the form, is indicated by dashed lines.
- the number of cooling hole rows constituting the plurality of cooling hole rows 95 arranged on the gas path surface 71 of the suction side leading edge cavity 81 of the shroud 60 and the respective cooling hole rows 96, 97, 98, 99 is the same as in the first embodiment.
- the plurality of cooling holes 89 indicated by solid lines in the plurality of cooling hole rows 90 are aligned with the first opening centers of the respective cooling hole rows 91, 92, 93, 94.
- the arrangement of the cooling holes 89 is selected so as to be substantially parallel to the isobar IBL1 of the combustion gas G near the line OL1.
- the high-temperature portion of the gas path surface 71 of the shroud 60 spreads more than in the first embodiment, and it is desired to strengthen cooling to a position closer to the blade surface 41.
- the extending direction of the opening center lines OL (the first opening center line OL1 and the second opening center line OL2) of the plurality of cooling holes 89 forming the cooling hole row 90 of the first embodiment is maintained.
- the groups of the plurality of cooling holes 89 of each of the cooling hole rows 91, 92, 93, 94 may be desired to be arranged closer to the blade surface 41 than in the first embodiment.
- the arrangement of the plurality of cooling holes 89 of the cooling hole row 90 of the first embodiment is further brought closer to the blade surface 41 in the arrangement of the cooling holes 89 of the cooling hole row 90a. be.
- the cooling holes 89 may be machined or drilled through the bottom plate 69 from the gas path surface 71 side toward the inner cavity 83 side by machining or electrical discharge machining.
- the cooling holes 89 may be machined or drilled through the bottom plate 69 from the gas path surface 71 side toward the inner cavity 83 side by machining or electrical discharge machining.
- the wing body 40 becomes an obstacle, making it difficult to machine the cooling holes 89 .
- the extending direction of the cooling holes 89 is slightly changed so that the inclination of the cooling hole 89 with respect to the axial direction of the cooling hole center line FL is reduced. Correction may be desirable.
- the modified cooling hole array 90a is a virtual cooling hole array.
- the arrangement of the cooling holes 89 shown in FIG. 6 is different from the arrangement in which the plurality of cooling holes 89 of the cooling hole row 90a, which is a modified example of the first embodiment, is indicated by broken lines, and the arrangement of the cooling hole rows 95 (96) of the present embodiment. , 97, 98, 99) are shown in comparison with the placement of a plurality of cooling holes 89 shown in solid lines.
- Cooling hole rows 90a (91, 92, 93, 94), which are modifications of the first embodiment shown in FIGS. 6 and 7, constitute the respective cooling hole rows 91, 92, 93, 94 of the first embodiment.
- the number of the plurality of cooling holes 89, the direction in which each group of the cooling hole rows 91, 92, 93, and 94 extends, the interval between the cooling holes 89 in the direction in which the cooling hole row 90 extends, and the inclination of the cooling hole center line FL in the axial direction is maintained, and each group of cooling holes 89 of each of the cooling hole rows 91, 92, 93, and 94 of the first embodiment is moved toward the blade surface 41 side.
- the position and extension of the opening centerline OL (first opening centerline OL1, second opening centerline OL2) of each cooling hole row 90a (91, 92, 93, 94) constituting the modification of the first embodiment The direction is the same as in the first embodiment. Further, the inclination of the cooling hole center line FL of the plurality of cooling holes 89 of each cooling hole row 90a (91, 92, 93, 94) with respect to the axial direction and the cooling hole row 90a (91, 92, 93, 94) constituting the modified example 94) are the same as in the first embodiment, as are the intervals of the cooling holes 89 in the direction in which each group extends and the inclination of the cooling hole center line FL with respect to the opening center line OL.
- the concept of changing the arrangement of the cooling holes 89 of the cooling hole row 90a, which is the modified example of the first embodiment, to the arrangement of the cooling holes 89 of the cooling hole row 95 of the present embodiment will be described. do.
- the cooling holes 89 (91aa, 92aa, 93aa, 94a) closest to the blade surface 41 of each cooling hole row 90a (91, 92, 93, 94) showing the modification of the first embodiment are In order to avoid interference with the blade body 40 when drilling the cooling holes 89, it is desirable to correct the inclination of the cooling holes 89 with respect to the axial direction.
- the fourth cooling hole row 94 is arranged on the most downstream side in the axial direction among the cooling hole rows 90a, and the inclination of the cooling hole center line FL with respect to the axial line AL is equal to that of the other cooling holes on the upstream side in the axial direction. 89 (91aa, 92aa, 93aa), and the possibility of interference with the wing body 40 is small. Therefore, the arrangement of the cooling holes 94a of the modified example is maintained without changing the inclination of the cooling holes 94a closest to the blade surface 41 of the fourth cooling hole row 94.
- the cooling hole 89 closest to the blade surface 41 of the other cooling hole rows 90a (91, 92, 93) of the modified example is designed to avoid interference with the blade body 40 during machining.
- the cooling hole 91aa of the first cooling hole row 91, the cooling hole 92aa of the second cooling hole row 92, and the cooling hole 93aa of the third cooling hole 93 of 90a are changed in inclination with respect to the axial direction.
- the arrangement of the cooling holes 89 after changing the position of the cooling holes 89 closest to the blade surface 41 in such a procedure is the closest to each of the cooling hole rows 95 (96, 97, 98, 99) of the present embodiment.
- Cooling holes 89 (96a, 97a, 98a, 99a) are brought closer to the blade surface 41.
- FIG. The cooling holes 99a of the fourth cooling hole row 99 of the present embodiment are arranged in the same manner as the cooling holes 94a of the fourth cooling hole row 94 of the cooling hole row 90a of the modified example of the first embodiment. no.
- the configuration of the fourth cooling hole row 99 of the present embodiment shown in FIG. 6 is the same as the configuration of the fourth cooling hole row 94 of the cooling hole row 90a of the modified example. Only the cooling holes 99a closest to the blade surface 41 of the embodiment and the cooling holes 99c furthest from the blade surface 41 are shown, and the reference numerals of the cooling holes 89 of the modified example are omitted.
- the cooling hole rows 96, 97, 98, 99a The location of another cooling hole 89 to be located away from the blade surface 41 is selected.
- the cooling holes 89 constituting each of the cooling hole rows 96, 97, 98, and 99 are arranged based on the cooling holes 89 (96a, 97a, 98a, and 99a) closest to the blade surface 41 after the change in arrangement, It has the same inclination with respect to the axial direction as the cooling holes 89 (96a, 97a, 98a, 99a), and has the same spacing and the same cooling hole center line FL as the cooling holes 89 of the cooling hole row 90a of the modified example of the first embodiment. They are slanted and spaced and formed in a direction away from the blade surface 41 toward the leading edge end 64 or the suction side end 66 .
- the directions in which the cooling hole rows 96, 97, 98, and 99 extend are the directions in which the cooling hole rows 91, 92, 93, and 94 in the first embodiment extend, that is, the cooling holes in the modification.
- Each cooling of the first embodiment is not set in the same direction as the direction in which the opening center lines OL (first opening center line OL1, second opening center line OL2) of the hole row 90a (91, 92, 93, 94) extend. It is preferable that the arrangement be arranged upstream of the hole rows 91, 92, 93, and 94 in the axial direction, with a large inclination with respect to the axial direction and with a large inclination angle with respect to the axial line AL.
- the opening center lines OL (first opening center line OL1, second opening center line OL2) of the cooling holes 89 of the respective cooling hole rows 96, 97, 98, and 99 of the present embodiment are compared with the respective cooling hole rows of the first embodiment.
- the inclination of the cooling hole centerline FL with respect to the opening centerline OL is greater than the inclination of the cooling hole centerline FL of the first embodiment. This is because the cooling air flow discharged from the excessively inclined cooling holes 89 disturbs the flow of the combustion gas G flowing along the blade surface 41 . .
- the arrangement of the cooling holes 89 of the respective cooling hole rows 96, 97, 98 and 99 of the present embodiment is changed from the position of the cooling holes 89 of the respective cooling hole rows 91, 92, 93 and 94 of the first embodiment to the axial direction.
- the constant pressure line IBL of the combustion gas G in the vicinity of the opening center line OL of the cooling hole row 90 of the first embodiment is The parallel relationship between the opening center line OL and the constant pressure line IBL is somewhat lost as the distance increases axially upstream from the extending direction.
- the opening center line OL is formed substantially parallel to another isobar line IBL on the upstream side in the axial direction of the isobar line IBL, fluctuations in the amount of cooling air discharged from the cooling holes 89 for each cooling hole row are suppressed to be small. be done.
- the arrangement of the cooling holes 89 of the cooling hole rows 95 (96, 97, 98, 99 (94)) of the present embodiment is selected.
- the fourth cooling hole array 99 has the same arrangement as the fourth cooling hole array 94 of the modified example of the first embodiment, and does not need to be changed.
- the opening centerline OL of the cooling hole array 95 of the present embodiment is indicated by the first opening centerline OL1 and the second opening centerline OL2 of the cooling hole arrays 96 and 97 in FIG.
- the opening centerlines OL of the cooling hole rows 98 and 99 only the first opening centerline OL1 is shown in FIG.
- the second opening centerline OL2 of the cooling hole rows 98, 99 like the other cooling hole rows, is parallel to the first opening centerline OL1, connects the centers of the inlet openings 89a of the cooling holes 89, and has an intermediate leading edge region. It can be considered as a straight line starting from 42d and extending to the suction surface side end portion 66 .
- FIG. 7 shows a combination of a first cooling hole row 96 and a second cooling hole row 97 in the cooling hole row 95 of this embodiment shown in FIG. 9 is a detailed view showing a comparison of the arrangement of cooling holes 89 by extracting combinations of a first cooling hole row 91 and a second cooling hole row 92.
- FIG. 9 shows a detailed view showing a comparison of the arrangement of cooling holes 89 by extracting combinations of a first cooling hole row 91 and a second cooling hole row 92.
- the first cooling hole row 91 of the cooling hole row 90a of the modified example of the first embodiment is composed of a plurality of cooling holes 89 (91aa, 91bb, 91cc, 91dd, 91ee), and the second cooling hole row 92 is composed of a plurality of cooling holes 89 (92aa, 92bb, 92cc, 92dd, 92ee).
- the first cooling hole row 96 of the present embodiment is composed of a plurality of cooling holes 89 (96a, 96b, 96c, 96d, 96e), and the second cooling hole row 97 is composed of a plurality of cooling holes 89 (97a, 97b, 97c, 97d, 97e).
- the cooling holes 89 (91aa, 91bb, 91cc, 91dd, 91ee) of the first cooling hole row 91 of the cooling hole row 90a, which is a modification of the first embodiment, as an example, specific changes in the arrangement of the cooling holes 89 are described below. explain the way of thinking. As described above, it is the cooling hole 91aa closest to the blade surface 41 that needs to avoid interference with the blade body 40 when the cooling hole 89 is drilled. As shown in FIG. 7, in order to avoid interference with the blade body 40 during drilling of the cooling hole 91aa, the cooling hole 91aa is inclined with respect to the axial direction about the position of the outlet opening 89b of the cooling hole 91aa.
- the position of the new cooling hole 89 after the change corresponds to the position of the cooling hole 96a indicated by the solid line closest to the blade surface of the first cooling hole row 96 of the cooling hole row 95 of this embodiment.
- the arrangement of the group of the plurality of cooling holes 89 forming the first cooling hole row 96 in the present embodiment is based on the position of the cooling hole 96a closest to the blade surface 41, which has been changed based on the arrangement correction method described above. , from the blade surface 41 side toward the leading edge end portion 64 while maintaining the same inclination with respect to the axial direction as the cooling holes 96a and the same intervals between the cooling holes 89 as in the first embodiment.
- the direction in which the first cooling hole array 96 extends is the direction away from the isobar IBL1 on the upstream side in the axial direction from the direction in which the isobar IBL1 of the combustion gas G extends.
- the first opening center line OL1 is formed substantially parallel to the isobar line IBL3 on the upstream side in the axial direction of the isobar line IBL1.
- the inclination (angle) of the cooling hole center line FL of the first cooling hole row 96 with respect to the opening center line OL (first opening center line OL1) is It is desirable that the inclination of FL is the same with respect to the opening centerline OL (first opening centerline OL1).
- the direction in which the first cooling hole row 96 of the present embodiment extends is not the same as the direction in which the first opening center line OL1 of the first cooling hole row 91 of the cooling hole row 90a of the modified example extends.
- the arrangement is upstream of the cooling hole row 91 in the axial direction and in a direction in which the inclination with respect to the axial direction increases, and the opening center line OL of the cooling hole center line FL of the first cooling hole row 91 of the first embodiment
- the reason why the inclination of the cooling hole center line FL of the cooling hole 89 with respect to the opening center line OL1) is the same is that the inclination of the cooling hole center line FL of the cooling hole 89 with respect to the opening center line OL is kept the same, and the cooling hole 89 is not excessively inclined toward the blade surface 41 side. This is to avoid disturbing the flow of the combustion gas G by the flow of cooling air discharged from the cooling holes 89 that have been formed.
- the number of cooling holes 89 (96a, 96b, 96c, 96d, 96e) forming the first cooling hole row 96 of this embodiment is the same as in the first embodiment.
- the group of cooling holes 89 forming the first cooling hole array 96 in this embodiment is arranged in a direction in which the inclination with respect to the axial direction is greater than that of the first cooling hole array 91 in the first embodiment. It is formed on the side approaching the upstream leading edge end 64 .
- the idea of changing the arrangement of the cooling holes 89 of the second cooling hole row 92 arranged axially downstream and adjacent to the first cooling hole row 91 of the modification of the first embodiment also applies to the first cooling hole row 91. It is similar to the row of holes 91 . It is necessary to avoid interference with the blade body 40 when drilling the cooling holes 89 (92aa, 92bb, 92cc, 92dd, 92ee) of the second cooling hole row 92 of the modified cooling hole row 90a. , are the cooling holes 92aa closest to the blade surface 41 . As shown in FIG.
- the cooling hole 92aa is tilted with respect to the axial direction about the position of the outlet opening 89b of the cooling hole 92aa.
- the position of the new cooling hole 89 after the change corresponds to the position of the cooling hole 97a indicated by the solid line closest to the blade surface of the second cooling hole row 97 of this embodiment.
- the arrangement of the cooling holes 89 constituting the second cooling hole row 97 in the present embodiment is based on the positions of the cooling holes 97a set as described above, in the direction from the blade surface 41 side to the suction surface side end portion 66.
- the same inclination with respect to the axial direction as the cooling holes 97a and the same intervals between the cooling holes 89 as in the first embodiment are maintained.
- the number of cooling holes 89 (97a, 97b, 97c, 97d, 97e) forming the second cooling hole row 97 is the same as in the first embodiment.
- the second cooling hole array 97 in the present embodiment is arranged in a direction in which the inclination with respect to the axial direction is greater than that of the second cooling hole array 92 in the first embodiment.
- the inclination of the cooling hole center line FL with respect to the opening center line OL is the same as in the first embodiment. It is desirable that the cooling hole center line FL of the second cooling hole row 92 has the same inclination with respect to the opening center line OL (first opening center line OL1).
- the cooling holes 89 of the third cooling hole row 98 and the fourth cooling hole row 99 of the present embodiment The concept of selecting the arrangement is also the same as the above-described concept. However, the arrangement of the fourth cooling hole array 99 of the present embodiment maintains the same arrangement as the fourth cooling hole array 94 of the modified example, and does not need to be modified. Note that the number of cooling holes 89 and the number of cooling hole rows constituting each of the cooling hole rows 96, 97, 98, and 99 in this embodiment may differ from those in the first embodiment depending on the operating conditions of the gas turbine. may
- the opening center line OL ( It is desirable that the inclinations with respect to the first opening center line OL1 and the second opening center line OL2 be the same at any position in the axial direction. If the inclination of the cooling hole center line FL with respect to the opening center line OL is changed due to the difference in the position of the cooling hole row 95 in the axial direction, the cooling hole center line FL may be excessively inclined toward the blade surface 41 side, or may be inclined to the side opposite to the blade surface 41 side. This is because the cooling air Ac discharged from the cooling holes 89 disturbs the flow of the combustion gas G, which is not desirable.
- the arrangement of the cooling holes 89 of the cooling hole row 95 of the present embodiment is based on the arrangement of the cooling holes 89 of the cooling hole row 90a of the modified example of the first embodiment, and each cooling hole row 90a of the modified example
- Each cooling hole row 90a (91, 92, 93 , 94) are rotated counterclockwise to select the arrangement of each of the cooling hole rows 96, 97, 98 and 99 of the present embodiment.
- the counterclockwise rotation angle becomes smaller toward the downstream side in the axial direction of the cooling hole row 95.
- the air passing through the exit opening 89b or the entrance opening 89a of the cooling hole 89 closest to the blade surface 41 is passed through.
- the opening centerlines OL (first opening centerline OL1, second opening centerline OL2) of each of the cooling hole rows 96, 97, 98, 99 of the modification are different from each of the cooling hole rows 90a (91, 92, 93, 94 ) with respect to the axial direction and with respect to the axial line AL.
- the opening center line OL of each of the cooling hole rows 96, 97, 98, and 99 intersects the axial line AL on the side of the leading edge 42 of the blade body 40 circumferentially opposite to the suction surface side end 66 in the extending direction.
- points Y3 and Y4 where the opening center line OL (first opening center line OL1, second opening center line OL2) of each cooling hole row 90a (91, 92, 93, 94) of the modified example intersects the axial direction line AL. Further, the point Y3 coincides with the leading edge 42. As shown in FIG.
- the positions where the opening center lines OL of the respective cooling hole rows 91, 92, 93, 94 of the first embodiment intersect with the axial line AL correspond to the respective cooling hole rows 90a (91, 92, 93, 94), the opening center lines OL (the first opening center line OL1, the second opening center line OL2) coincide with the points Y3, Y4 at which the axial line AL intersects.
- Points Y1 and Y2 at positions where the opening center lines OL (first opening center line OL1, second opening center line OL2) of the cooling holes 89 of the hole rows 96, 97, 98, and 99 intersect the axial line AL are It is arranged closer to the trailing edge 43 than the position where the opening center lines OL of the cooling hole array 90 of the first embodiment intersect.
- a point Y3 at which the first opening center line OL1 of the cooling hole row 90 of the first embodiment intersects the axial line AL coincides with the position of the leading edge 42, so the cooling hole row of the present embodiment
- a point Y1 at which the first opening center line OL1 of 95 intersects the axial line AL is located closer to the trailing edge 43 than the leading edge 42 is.
- the point Y1 where the first opening center lines OL1 of at least two of the first opening center lines OL1 of the cooling hole rows 95 of the present embodiment intersect the axial line AL is closer to the trailing edge 43 than the leading edge 42. located in the downstream leading edge region 42 c (third region) in the side wing body leading edge cavity 52 . Therefore, the first opening centerline OL1 of the cooling hole row 95 of the present embodiment extends from the downstream leading edge region 42c axially downstream of the leading edge 42 to at least two adjacent holes forming the cooling hole row 95. It is formed by a straight line connecting the centers of the outlet openings 89b of the cooling holes 89 and extending to the front edge end 64 or the suction surface side end 66 .
- the downstream leading edge region 42c means a circular region arranged on the axial line AL and having the same radius as the leading edge region 42a.
- the second opening centerline OL2 of the cooling hole row 95 is arranged axially upstream of the first opening centerline OL1 and separated from the first opening centerline OL1 by the length of the cooling hole 89.
- the point Y2 where the second opening center lines OL2 of at least two of the second opening center lines OL2 of the cooling hole arrays 95 intersect the axial line AL is It is located in the intermediate leading edge region 42 d (fourth region) in the wing body leading edge cavity 52 on the leading edge 42 side from the position of the point YI that intersects the line AL.
- the intermediate leading edge region 42d is a circular region arranged on the axial line AL and having the same radius as the leading edge region 42a. placed in between.
- the second opening centerlines OL2 of at least two of the cooling hole rows 95 are formed in a circle formed at a position upstream in the axial direction by the length of the cooling holes 89 from the center position of the downstream leading edge region 42c. Starting from the intermediate leading edge region 42d of the shape, connecting the centers of the inlet openings 89a of at least two adjacent cooling holes 89 forming the cooling hole row 95 in parallel with the first opening centerline OL1, the leading edge end 64 Alternatively, it is formed by a straight line extending to the suction surface side end portion 66 . At least two adjacent cooling holes 89 forming the second opening centerline OL2 are preferably the same combination of cooling holes 89 used when selecting the first opening centerline OL1.
- the positions of the points Y1 and Y2 which are the center positions where the downstream leading edge region 42c and the intermediate leading edge region 42d are arranged, are different from the arrangement of the cooling hole row 90a of the modified example of the first embodiment. It varies depending on the inclination angle ⁇ of the cooling hole center line FL when changing to the hole row 95 .
- the group of the plurality of cooling holes 89 is positioned closer to the blade surface 41 than the cooling structure of the cooling hole array 90 of the first embodiment. to suppress the occurrence of thermal damage and thermal stress on the gas path surface 71 of the shroud 60, and the gas path surface 71 is properly cooled. Also, the amount of cooling air is reduced and the efficiency of the gas turbine is improved.
- the method of cooling the suction surface side leading edge cavity 81 of the blade 40 of the turbine stationary blade 24 includes step S1 of supplying cooling air Ac to the outer cavity 82 of the shroud 60, A step S2 of reducing the pressure in the through hole 86 of the plate 85 and supplying the cooling air Ac to the inner cavity 83, a step S3 of impingement cooling the bottom plate 69 with the cooling air, and film-cooling the gas path surface 71 of the bottom plate 69 with the cooling air. and a step S4 of performing.
- step S1 of supplying cooling air Ac to the outer cavity 82 of the suction side leading edge cavity 81 of the shroud 60 the cooling air Ac is supplied to the shroud 60 from the casing 20 or the turbine casing 22 outside the turbine stator vanes 24. (S1).
- step S2 of reducing the pressure of the cooling air Ac through the through holes 86 of the impingement plate 85 the pressure in the inner cavity 83 is reduced in the process of discharging the cooling air Ac into the inner cavity 83 through the plurality of through holes 86 formed in the impingement plate 85. (S2).
- step S3 of impingement cooling the bottom plate 69 with the cooling air Ac the cooling air Ac ejected into the inner cavity 83 through the plurality of through holes 86 of the impingement plate 85 collides with the inner surface 70 of the bottom plate 69, The surface 70 is impingement cooled (impingement cooled) (S3).
- the cooling air Ac after the impingement cooling of the inner surface 70 of the bottom plate 69 is supplied to the plurality of cooling holes 89 formed in the bottom plate 69 .
- the gas path surface 71 of the bottom plate 69 of the shroud 60 is film-cooled in the process of discharging the combustion gas from the outlet opening 89b to the combustion gas flow path 47 (S4).
- the first opening center lines OL1 of the cooling hole rows 90 and 95 of the plurality of cooling holes 89 are arranged in parallel along the constant pressure line IBL of the combustion gas G.
- the inner cavity 83 connected to the upstream side of each group of the plurality of cooling holes 89 constituting the cooling hole rows 90 and 95 through the inlet opening 89a and the combustion gas flow path connected through the downstream outlet opening 89b. 47 becomes substantially the same, and the amount of cooling air discharged from each group of the plurality of cooling holes 89 constituting the cooling hole rows 90 and 95 is equalized to the same flow rate. be done.
- the first opening center lines OL1 of the cooling hole rows 90 and 95 of the plurality of cooling holes 89 formed in the bottom plate 69 are arranged along the constant pressure line IBL of the combustion gas G. are arranged in parallel with each other to stabilize internal pressure fluctuations in the inner cavity 83 .
- the first opening center lines OL1 of the cooling hole rows 90 and 95 of the plurality of cooling holes 89 are arranged in parallel along the isobar IBL of the combustion gas G, so that the plurality of cooling holes of the cooling hole rows 90 and 95
- the arrangement of the cooling holes 89 is selected so that the differential pressure (pressure difference) between the inner cavity 83 to which the upstream side of the 89 is connected and the combustion gas flow path 47 to which the downstream side is connected are substantially the same.
- the amount of cooling air discharged from the plurality of cooling holes 89 of the cooling hole rows 90, 95 is made uniform. Therefore, an excessive amount of cooling air is prevented from being discharged from the cooling holes 89, and the amount of cooling air can be reduced.
- the amount of cooling air discharged from the cooling holes 89 of the cooling hole rows 90 and 95 is made uniform, the metal temperature distribution of the bottom plate 69 is made uniform, and the occurrence of thermal stress in the bottom plate 69 of the shroud 60 is suppressed. be.
- expressions that express shapes such as squares and cylinders do not only represent shapes such as squares and cylinders in a geometrically strict sense, but also include irregularities and chamfers to the extent that the same effect can be obtained.
- the shape including the part etc. shall also be represented.
- the expressions “comprising”, “comprising”, “having”, “including”, or “having” one component are not exclusive expressions excluding the presence of other components.
- a turbine stator vane includes a blade body, a shroud formed at an end portion of the blade body in a blade height direction, and a fillet portion joining the blade body and the shroud.
- the shroud includes a bottom plate in contact with a combustion gas flow path, a peripheral wall extending in the blade height direction along the peripheral edge of the bottom plate, and a space surrounded by the peripheral wall and the bottom plate.
- the peripheral wall includes a leading edge end portion extending toward the leading edge side of the wing body and a suction side end portion extending from the leading edge to the trailing edge on the suction side side of the wing body.
- said shroud comprising a plurality of said cooling holes formed in a suction side leading edge region of said shroud and formed in said bottom plate, said plurality of cooling holes having first ends formed in said bottom plate connected to an inlet opening, a second end connected to an outlet opening formed in the gas path surface of the bottom plate and axially downstream of the inlet opening, the leading edge circumferentially from the surface of the wing body;
- the plurality of cooling holes are arranged at predetermined intervals toward the end portion or the suction surface side end portion, and maintain the same inclination with respect to the axial direction of the center line of the cooling holes connecting the inlet opening and the outlet opening.
- a set of cooling holes in which a first linear opening centerline connecting the centers of the outlet openings and a second linear opening centerline connecting the centers of the inlet openings of the cooling holes are formed parallel to each other.
- a plurality of the cooling hole rows are arranged along the blade surface from the upstream side to the downstream side in the axial direction, and the inclination of the cooling hole center line of the cooling holes of the plurality of cooling hole rows is , and becomes smaller toward the downstream side in the axial direction.
- a plurality of rows of cooling holes are arranged along the blade surface in the leading edge region on the suction side of the shroud, and the axial direction of the cooling hole centerlines of the plurality of rows of cooling holes becomes smaller toward the downstream side in the axial direction.
- the combustion gas flowing on the gas path surface flows axially downstream along the blade surface, and the inclination of the isobar of the combustion gas with respect to the axial direction decreases along the blade surface toward the axial downstream side. Therefore, the gradient of the isobar with respect to the axial direction becomes smaller, and the gradient of the cooling hole center line of each cooling hole row also becomes smaller toward the downstream side in the axial direction along the blade surface.
- the amount of cooling air discharged from the cooling holes of each cooling hole row is made uniform, the gas path surface is properly cooled, and the amount of cooling air is also reduced. Also, the flow of cooling air discharged from the cooling holes is also discharged along the flow direction of the combustion gas, so that the combustion gas flow is not disturbed. Therefore, the influence on the aerodynamic performance of the gas turbine is suppressed.
- the shroud includes a first region formed in a circular shape in contact with the outer edge of the fillet portion centered on the front edge of the blade body, and the first an opening centerline extending from the first region as a starting point;
- the first opening centerlines of the plurality of cooling holes forming the cooling hole row extend from the first region, they are substantially parallel to the isobar of the combustion gas. The amount of cooling air formed and discharged from the row of cooling holes is uniformed.
- the shroud is arranged in a first cavity formed inside the blade body, and is axially downstream of the leading edge on the axial line of the blade body. a third region having a size corresponding to a circular region inscribed in the outer edge of the fillet portion centered on the leading edge of the wing body; The first opening centerlines of the two cooling hole rows extend from the third region.
- the cooling structure is formed by arranging the cooling holes so that the inclination of the cooling holes approaches the inclination of the blade surface. Since the first opening centerlines of at least two cooling hole rows extend from the third region, the first opening centerlines of the respective cooling hole rows are formed substantially parallel to the combustion gas isobar. , the amount of cooling air discharged from the row of cooling holes is made uniform. Also, machining of the cooling holes becomes easier.
- the shroud is formed in a circular shape having the same radius as the first region on an axial line axially upstream of the leading edge of the blade body. Equipped with 2 areas, The second opening centerline extends from the second region.
- the second opening centerlines of the plurality of cooling holes forming the cooling hole row are formed on the upstream side in the axial direction in parallel with the first opening centerline. Since the center line extends from the second region as a starting point, the second opening center line is also formed substantially parallel to the isobar of the combustion gas, and the amount of cooling air discharged from the cooling hole array is made uniform.
- the shroud is arranged in the first cavity and is axially downstream from the leading edge on the axial line of the blade body and from the third region.
- a fourth region is arranged on the upstream side in the axial direction and is formed in a circular shape having the same radius as the third region, and the second opening centerlines of at least two of the cooling hole rows are aligned with each other. , extending from the fourth region.
- the second opening centerlines of the plurality of cooling holes forming the cooling hole row are formed on the upstream side in the axial direction in parallel with the first opening centerline. Since the center line extends from the fourth region as a starting point, the second opening center line is also formed substantially parallel to the isobar of the combustion gas, and the amount of cooling air discharged from the cooling hole array is uniformed.
- the first opening centerline or the second opening centerline is at least adjacent to the direction in which the first opening centerline or the second opening centerline extends. It is formed by two cooling holes.
- the first opening center line or the second opening center line of the row of cooling holes is at least adjacent to the extending direction of the first opening center line or the second opening center line. Since it is formed by two cooling holes, machining of the cooling holes is facilitated.
- the cooling hole centerline is inclined toward the blade surface from a direction perpendicular to the first opening centerline or the second opening centerline.
- the cooling hole centerline of the cooling hole is inclined toward the blade surface side from the direction orthogonal to the first opening centerline or the second opening centerline.
- the cooling air exhausted from the exhaust does not disturb the combustion gas flow across the gas path surface.
- the inclination of the cooling hole center line of the cooling hole row with respect to the first opening center line is the same at any position in the axial direction of the cooling hole row. is maintained.
- the inclination of the cooling hole centerline of the cooling hole row with respect to the first opening centerline is maintained at any position in the axial direction. Therefore, the cooling air discharged from the cooling holes does not disturb the flow of the combustion gas flowing on the gas path surface.
- the first opening centerlines of the plurality of cooling hole rows are oriented in the axial downstream direction and arranged adjacent to each other in the axial direction. is increased in axial distance from the first opening centerline.
- the interval between isobars of the combustion gas in the second cavity expands in the axial downstream direction.
- the first opening centerline of each cooling hole row is arranged parallel to the isobar of the combustion gas. Therefore, the distance between the center lines of the first openings of the cooling hole row increases as the cooling air goes downstream in the axial direction, and the gas path surface from which the cooling air is discharged is uniformly cooled.
- the plurality of cooling holes in the row of cooling holes maintains the same spacing in the direction in which the first opening centerline or the second opening centerline extends. are placed.
- the cooling holes forming the row of cooling holes are arranged at the same intervals in the direction in which the first opening center line or the second opening center line extends. Therefore, the gas path surface through which the cooling air is discharged is uniformly cooled.
- the groups of the plurality of cooling holes forming the plurality of rows of cooling holes have starting points in at least one of the first region to the fourth region. radially toward the front edge or the suction side end.
- the group of the plurality of cooling holes forming the plurality of rows of cooling holes is arranged at the leading edge starting from at least one of the first to fourth regions. It extends radially toward the end or the end on the negative pressure side.
- the groups of cooling holes forming the cooling hole array spread radially along with the inclination of the blade surface, so that the gas path surface is uniformly cooled and the discharged cooling air flow does not disturb the combustion gas flow. .
- either the first opening centerline or the second opening centerline of the plurality of cooling hole rows lies within the first region to the fourth region. starting from at least one region of , and spreading radially toward the front edge end or the suction surface side end.
- either the first opening center line or the second opening center line of the plurality of cooling hole rows is in at least one of the first to fourth regions. radiating toward the front edge or the suction side end.
- the shroud includes a leading edge partition rib that connects the blade body and the leading edge end, and a blade body and the suction surface side end that connect the blade body and the suction surface side end.
- the second cavity is divided into a third cavity formed outside in the blade height direction and a fourth cavity formed inside the third cavity, and the third cavity and the fourth cavity are communicated. and an impingement plate with a plurality of through holes.
- the shroud includes: a leading edge partition rib connecting the blade body and the leading edge end; and a suction side partition rib connecting the blade body and the suction side end. and a second cavity defined by the outer wall surface of the blade, the leading edge partition rib, and the suction surface side partition rib. Furthermore, the shroud divides the second cavity into a third cavity formed outside in the blade height direction and a fourth cavity formed inside the third cavity. 4 includes an impingement plate with a plurality of through holes communicating with the cavities. As a result, the cooling air supplied to the inner shroud through the impingement plate effectively cools the bottom plate through a combination of impingement cooling of the inner surface of the bottom plate and film cooling of the gas path surface by the cooling holes in the bottom plate. .
- the shroud includes an outer shroud formed at an outer end portion of the blade body in the blade height direction, and a an inner shroud formed on the inner end.
- a gas turbine according to a fifteenth aspect comprises: a turbine stator blade according to any one of claims 1 to 13; Equipped with a vessel and
- a turbine stator blade cooling method includes a blade body, and a shroud formed at an end portion of the blade body in the blade height direction, the shroud forming a combustion gas flow path.
- a peripheral wall formed in the blade height direction along the peripheral edge of the bottom plate; a recess forming a space surrounded by the peripheral wall and the bottom plate; a second cavity formed in the leading edge region on the suction surface side, and a third cavity formed outside the second cavity in the blade height direction.
- a cooling hole array having a plurality of cooling holes communicating with the fourth cavity through inlet openings formed in the surface thereof and communicating with the combustion gas flow path through outlet openings formed in the gas path surface of the bottom plate; a cooling method for a turbine stator blade, comprising supplying cooling air from the outside to the third cavity; reducing the pressure of cooling air in the fourth cavity supplied from the third cavity to the fourth cavity through holes; impingement cooling the inner surface of the bottom plate with the cooling air; discharging the cooling air into the combustion gas flow path from a plurality of the cooling holes forming the cooling hole row formed in the bottom plate and having a first opening centerline arranged parallel to the isobar of the combustion gas; and C. film cooling the gas path surface.
- the shroud includes the second cavity having the impingement plate in the suction surface side region of the shroud, and the externally supplied cooling air passes through the impingement plate.
- a vacuum is applied through the holes to impingement cool the inner surface of the bottom plate.
- the first opening centerline connecting the outlet openings of the cooling holes forming the cooling hole row is arranged parallel to the isobar of the combustion gas flow, the pressure at the outlet opening of the cooling holes forming the cooling hole row is The same pressure is maintained, and internal pressure fluctuations in the fourth cavity connected to the upstream side of the cooling hole are suppressed. Therefore, the amount of cooling air discharged from the cooling holes is stabilized, the gas path surface is properly cooled, and the amount of cooling air is reduced.
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Abstract
Description
本願は、2021年7月7日に日本国特許庁に出願された特願2021-112476号に基づき優先権を主張し、その内容をここに援用する。
前記複数の冷却孔は、第1端が前記底板に形成された入口開口に接続し、
第2端が前記底板のガスパス面に形成されて前記入口開口より軸方向下流側に形成された出口開口に接続し、前記翼体の翼面から周方向の前記前縁端部又は前記負圧面側端部に向けて所定間隔をあけて配置され、前記入口開口と前記出口開口を結ぶ冷却孔中心線の軸方向に対する傾きが同一に維持され、前記複数の冷却孔の前記出口開口の中心を結ぶ直線状の第1開口中心線と、前記冷却孔の前記入口開口の中心を結ぶ直線状の第2開口中心線と、が互いに平行に形成された一組の冷却孔列を形成し、前記冷却孔列が、軸方向上流側から下流側に向けて前記翼面に沿って複数配置され、前記複数の冷却孔列の前記冷却孔の前記冷却孔中心線の傾きが、軸方向下流側に向かうと共に小さくなる。
タービン静翼が適用されるガスタービンの構成について、図1を参照して説明する。なお、図1は、タービン静翼24が適用される一実施形態のガスタービン1を示す概略構成図である。
圧縮機2は、圧縮機車室10と、圧縮機車室10の入口側に設けられ、空気を取り込むための吸気室12と、圧縮機車室10及び後述するタービン車室22を共に貫通するように設けられたロータ8と、圧縮機車室10内に配置された各種の翼と、を備える。各種の翼は、吸気室12側に設けられた入口案内翼14と、圧縮機車室10側に固定された複数の圧縮機静翼16と、圧縮機静翼16に対して軸方向に交互に配列されるようにロータ8に植設された複数の圧縮機動翼18と、を含む。なお、圧縮機2は、不図示の抽気室等の他の構成要素を備えていてもよい。このような圧縮機2において、吸気室12から取り込まれた空気は、複数の圧縮機静翼16及び複数の圧縮機動翼18を通過して圧縮されることで圧縮空気が生成される。圧縮空気は圧縮機2から軸方向下流側の燃焼器4に送られる。
タービン6において、ロータ8は、軸方向に延在し、タービン車室22から排出された燃焼ガスGは、軸方向の下流側の排気車室28に排出される。図1では、図示の左側が軸方向上流側であり、図示の右側が軸方向下流側である。また、以下の説明では、単に径方向と記載した場合、ロータ8に直交する方向を表す。また、周方向と記載した場合、ロータ8の回転方向を表す。径方向は、翼高さ方向と呼ぶ場合もある。
図2は、タービン静翼24の斜視図を示す。図2に示すように、タービン6の静翼24は、翼高さ方向に延びる翼体40と、翼体40の翼高さ方向の外側及び内側の両端にシュラウド60を有する。シュラウド60は、翼体40の翼高さ方向の外側に形成されている外側シュラウド60aと、翼体40の翼高さ方向の内側に形成されている内側シュラウド60bと、からなる。翼体40は、燃焼ガスGが流れる燃焼ガス流路47内に配置されている。外側シュラウド60aは、ロータ8廻りに環状に形成された燃焼ガス流路47の翼高さ方向の外側の位置を画定している。内側シュラウド60bは、環状の燃焼ガス流路47の翼高さ方向の内側の位置を画定している。
本実施形態におけるシュラウド60の負圧面側前縁キャビティ81廻りの冷却構造は、図3、図4及び図5に示される。なお、図5、図6及び図7は、外側シュラウド60aを翼高さ方向の内側のガスパス面(外表面)71側から見た負圧面44側の前縁42側の平面断面を示し、図4のB-B線に沿った断面図である。
本実施形態の冷却構造は、複数の貫通孔86を備えた衝突板85と、複数の冷却孔89を備えた底板69と、衝突板85の翼高さ方向の外側に形成された外側キャビティ82と、衝突板85の翼高さ方向の内側に形成された内側キャビティ83と、から構成される。これらの構成の組合せにより、シュラウド60は、衝突板85に形成された貫通孔86を介して外側キャビティ82から供給された冷却空気Acが、内側キャビティ83に噴出して底板69の内表面70に衝突し、内表面70をインピンジメント冷却(衝突冷却)するインピンジメント冷却構造と、インピンジメント冷却後の冷却空気Acが底板69に形成された冷却孔89を介して燃焼ガス流路47に排出する過程で、底板69の外表面(ガスパス面)71を冷却するフィルム冷却構造と、を組み合わせた冷却構造が形成される。
図3、図4、図5及び図9に基づき、負圧面側前縁キャビティ81のインピンジメント冷却とフィルム冷却を組合わせた冷却構造について、以下に具体的に説明する。
図5に示す冷却孔列90(91、92、93、94)は、軸方向上流側から下流側に向けて、第1冷却孔列91、第2冷却孔列92、第3冷却孔列93及び第4冷却孔列94から構成されている。それぞれの各冷却孔列91、92、93、94は、それぞれが複数の冷却孔89を備える。なお、各冷却孔列91、92、93、94を構成する複数の冷却孔89の内で、第3冷却孔列93及び第4冷却孔列94を構成する冷却孔89の符号は、最も翼面41に接近する冷却孔89と最も翼面41から離れた冷却孔89のみに符号を表示し、他の冷却孔89の符号の表示は省略している。
すなわち、後述する燃焼ガスGの等圧線IBLは、軸方向下流側に向かい、且つ、負圧面側端部66に接近すると共に、軸方向に対する傾斜が大きく、軸方向線ALに対する傾きが小さくなる。一方、各冷却孔列91、92、93、94の開口中心線(第1開口中心線OL1)は、燃焼ガスGの等圧線IBLに平行に配置することが望ましい。従って、各冷却孔列91、92、93、94の延在する方向である開口中心線OL及び冷却孔中心線FLは、燃焼ガスGの等圧線IBLの軸方向線ALに対する傾きの変化と共に、各冷却孔列91、92、93、94の開口中心線(第1開口中心線OL1)の軸方向線ALに対する傾きを変えることが望ましい。すなわち、各冷却孔列91、92、93、94の開口中心線OL及び冷却孔中心線FLは、軸方向下流側に向かうと共に、軸方向線ALに対する傾きは次第に小さくなる。ここで、冷却孔列90を構成する複数の冷却孔89の開口中心線OL(第1開口中心線OL1、第2開口中心線OL2)又は冷却孔中心線FLの軸方向線ALに対する傾き又は角度とは、前縁42を通り軸方向に延伸する軸方向線ALに対して、開口中心線OL又は冷却孔中心線FLと軸方向線ALとが交差する位置より軸方向下流側の位置から開口中心線OL又は冷却孔中心線FLを見た場合、反時計廻りの方向に軸方向線ALと開口中心線OL又は冷却孔中心線FLがなす傾き又は角度を意味する。
第3冷却孔列93及び第4冷却孔列94の冷却孔89の数は、3つ以上を配置してもよい。
ここで、等圧線IBLとは、燃焼ガス流路47を流れる燃焼ガスGの圧力(静圧)が同じ圧力を示す位置を繋ぐ曲線を意味する。
燃焼ガスGがガスパス面71を流れる過程における燃焼ガスGの圧力降下の違いにより、冷却孔列90の冷却孔89を流れる冷却空気量に違いが生ずる。冷却孔89の上流側の入口開口89aが接続する内側キャビティ83は、同一の空間内である限り、同一の圧力が維持される。一方、冷却孔89の下流側の出口開口89bが接続するガスパス面71側の燃焼ガスGの圧力は、軸方向下流側に向かうと共に低下する。従って、冷却孔列90の複数の冷却孔89の配置によっては、同一の冷却孔列90を構成する複数の冷却孔89の中でも、冷却孔89の差圧(圧力差)の違いが発生し、排出する冷却空気量のばらつきを生ずる可能性がある。冷却孔列90を構成する複数の冷却孔89の冷却空気量のばらつきは、不均一なフィルム冷却を生じ、底板69の不均一なメタル温度分布を生ずる原因になる。この点を改善するため、同一の冷却孔列90を構成する複数の冷却孔89の第1開口中心線OL1が、各冷却孔列91、92、93、94近傍の燃焼ガスGの等圧線IBLに大略平行になるように、同一の冷却孔列90の複数の冷却孔89の配置を選定することが望ましい。同一の冷却孔列90の複数の冷却孔89の配置を、冷却孔列90の第1開口中心線OL1と燃焼ガスGの等圧線IBLが大略平行となるように設定すれば、同一の冷却孔列90を構成する複数の冷却孔89は同一の差圧を維持することできる。同一の冷却孔列90の複数の冷却孔89の差圧を同一とすれば、同一の冷却孔列90の複数の冷却孔89からガスパス面71に排出される冷却空気量が均一化され、同一の冷却孔列90の複数の冷却孔89の位置から軸方向下流側のフィルム冷却が均一化される。その結果、シュラウド60のガスパス面71の温度分布が平準化され、底板69の熱損傷が抑制され、底板69の不均一な温度分布により生ずる熱応力が低減される。
図5に示すように、シュラウド60の前縁42側の負圧面44側のガスパス面71を流れる燃焼ガスGは、凸状の曲面を有する翼面41に沿って流れる。負圧面側前縁キャビティ81に形成されている複数の冷却孔89が配置されている領域は、軸方向上流側から下流側に向かうと共に、翼体40の翼面41が負圧面側端部66に接近し、翼面41の曲面の軸方向線ALに対する傾きが次第に小さくなる領域である。この領域においては、複数の冷却孔89の開口中心線OLが延びる方向に対して、冷却孔中心線FLは、開口中心線OLに対して直交する方向より翼面41側に傾く方向に配置されている。 また、複数の冷却孔列90の開口中心線OLは、軸方向下流側に向かうと共に、軸方向線ALに対する傾きが小さくなるので、同一の冷却孔列90の冷却孔中心線FLも、軸方向下流側に向かうと共に軸方向線ALに対する傾きが小さくなる。なお、各冷却孔列91、92、93、94の冷却孔89の冷却孔中心線FLが開口中心線OL(第1開口中心線OL1)となす傾き又は角度は、軸方向のいずれの位置でも同一の傾き又は角度に維持されることが望ましい。同一の冷却孔列90の冷却孔中心線FLの開口中心線OLに対する傾きが維持されず、冷却孔列90の軸方向の位置によって、冷却孔中心線FLが翼面41側へ過度に傾斜する場合は、冷却孔89から排出される冷却空気Acの流れが、燃焼ガスGの流れを乱すことになる。
また、同一の第1冷却孔列91の第2開口中心線OL2は、前縁42を通る軸方向線AL上の前縁42の位置より軸方向上流側の所定位置にある上流側前縁領域(第2領域)42bを起点とする直線で形成される。ここで、上流側前縁領域(第2領域)42bとは、前縁42の位置より軸方向上流側の軸方向線AL上にあり、第1冷却孔列91の冷却孔中心線FLの軸方向長さに相当する距離にある位置を中心に、前縁領域46aと同じ半径の破線で示す円状に形成された領域を言う。
以下の説明は、シュラウド60の負圧面側前縁キャビティ81廻りの冷却構造の第2実施形態に係り、図6及び図7を参照しながら説明する。図6は、シュラウド60の本実施形態の平面断面を示し、図4のB-B線に沿った平面図である。図7は、図6に示すシュラウド60の本実施形態の平面図の一部を示す詳細図である。
本実施形態の冷却構造は、前述のシュラウド60に形成された冷却孔列90の複数の冷却孔89の第1実施形態の構造に対して、冷却孔89の配置を変えた実施形態に関する。本実施形態を構成する冷却構造は、第1実施形態におけるインピンジメント冷却構造とフィルム冷却構造の組合せに対して、フィルム冷却構造を構成する複数の冷却孔89の配置の考え方が、第1実施形態と異なる構成である。なお、図3及び図4に示すインピンジメント冷却構造は、本実施形態にも適用される。
図6では、本実施形態に係る複数の冷却孔列95(96、97、98、99)の複数の冷却孔89の配置を実線で示すと共に、比較のために、下記に説明する第1実施形態の変形例である複数の冷却孔列90a(91、92、93、94)の複数の冷却孔89の配置を破線で示している。
本実施形態においても、シュラウド60の負圧面側前縁キャビティ81のガスパス面71に配置された複数の冷却孔列95を構成する冷却孔列の数及び各冷却孔列96、97、98、99を構成する冷却孔89の数は、第1実施形態と同じ構成である。
ここで、下流側前縁領域42cとは、軸方向線AL上に配置され、前縁領域42aと同一の半径を有する円状の領域を意味する。
なお、下流側前縁領域42c及び中間前縁領域42dが配置される中心位置である点Y1及びY2の位置は、第1実施形態の変形例の冷却孔列90aの配置を本実施形態の冷却孔列95に変更する際の冷却孔中心線FLの傾き角αによって変動する。
上述の第1実施形態及び第2実施形態に示すタービン静翼24の冷却方法の手順について、図9に基づき説明する。
図9に示すように、タービン静翼24の翼体40の負圧面側前縁キャビティ81の冷却方法は、シュラウド60の外側キャビティ82に冷却空気Acを供給する工程S1と、冷却空気Acを衝突板85の貫通孔86で減圧し、内側キャビティ83に冷却空気Acを供給する工程S2と、冷却空気で底板69をインピンジメント冷却する工程S3と、冷却空気で底板69のガスパス面71をフィルム冷却する工程S4と、を含んでいる。
例えば、四角形状や円筒形状等の形状を表す表現は、幾何学的に厳密な意味での四角形状や円筒形状等の形状を表すのみならず、同じ効果が得られる範囲で、凹凸部や面取り部等を含む形状も表すものとする。一方、一の構成要素を「備える」、「具える」、「具備する」、「含む」、又は、「有する」という表現は、他の構成要素の存在を除外する排他的な表現ではない。
(1)第1の態様に係るタービン静翼は、翼体と、前記翼体の翼高さ方向の端部に形成されたシュラウドと、前記翼体と前記シュラウドを接合するフィレット部と、を備えるタービン静翼であって、前記シュラウドは、燃焼ガス流路に接する底板と、前記底板の周縁に沿って前記翼高さ方向に延びる周壁と、前記周壁と前記底板に囲まれた空間を形成する凹部と、を含み、前記周壁は、前記翼体の前縁側に延在する前縁端部と、前記翼体の負圧面側の前縁から後縁に延びる負圧面側端部と、を含み、前記シュラウドは、前記シュラウドの負圧面側前縁領域に形成され、前記底板に形成された複数の前記冷却孔を備え、前記複数の冷却孔は、第1端が前記底板に形成された入口開口に接続し、第2端が前記底板のガスパス面に形成されて前記入口開口より軸方向下流側に形成された出口開口に接続し、前記翼体の翼面から周方向の前記前縁端部又は前記負圧面側端部に向けて所定間隔をあけて配置され、前記入口開口と前記出口開口を結ぶ冷却孔中心線の軸方向に対する傾きが同一に維持され、前記複数の冷却孔の前記出口開口の中心を結ぶ直線状の第1開口中心線と、前記冷却孔の前記入口開口の中心を結ぶ直線状の第2開口中心線と、が互いに平行に形成された一組の冷却孔列を形成し、前記冷却孔列が、軸方向上流側から下流側に向けて前記翼面に沿って複数配置され、前記複数の冷却孔列の前記冷却孔の前記冷却孔中心線の傾きが、軸方向下流側に向かうと共に小さくなる。
従って、等圧線の軸方向に対する傾きが小さくなると共に、各冷却孔列の冷却孔中心線の傾きも翼面に沿って軸方向下流側に向けて小さくなり、各冷却孔列は、燃焼ガスの等圧線に平行に形成されている。従って、各冷却孔列の冷却孔から排出される冷却空気量が均一化され、ガスパス面が適正に冷却され、冷却空気量も低減される。
また、冷却孔から排出される冷却空気の流れも燃焼ガスの流れ方向に沿って排出され、燃焼ガス流を乱さない。従って、ガスタービンの空力性能への影響が抑制される。
前記第2開口中心線が、前記第2領域を起点に延伸する。
2 圧縮機
4 燃焼器
6 タービン
8 ロータ
10 圧縮機車室
12 吸気室
14 入口案内翼
16 圧縮機静翼
18 圧縮機動翼
20 ケーシング
22 タービン車室
24 タービン静翼
26 タービン動翼
28 排気車室
29 排気室
40 翼体
40a 翼体端部
40b 翼壁
41 翼面
42 前縁
42a 前縁領域(第1領域)
42b 上流側前縁領域(第2領域)
42c 下流側前縁領域(第3領域)
42d 中間前縁領域(第4領域)
43 後縁
44 負圧面
45 正圧面
46 フィレット部
46a 外縁
47 燃焼ガス流路
49 翼体仕切リブ
51 翼体キャビティ(第1キャビティ)
52 翼体前縁キャビティ
53 翼体中間キャビティ
54 翼体後縁キャビティ
56 蓋
56a 開口
60 シュラウド(外側シュラウド60a、内側シュラウド60b)
62 周壁
62a 内壁
64 前縁端部
65 後縁端部
66 負圧面側端部
67 正圧面側端部
69 底板
70 内表面
71 外表面(ガスパス面)
73 仕切リブ
73a 前縁仕切リブ
73b 負圧面側中間仕切リブ
75 凹部
76 フック
80 キャビティ
81 負圧面側前縁キャビティ(第2キャビティ)
82 外側キャビティ(第3キャビティ)
83 内側キャビティ(第4キャビティ)
85 衝突板
86 貫通孔
89 冷却孔
89a 入口開口
89b 出口開口
90 冷却孔列(第1冷却孔列91(91a~91e)、第2冷却孔列92(92a~92e)、第3冷却孔列93(93a~93c)、第4冷却孔列94(94a~94c))
90a 冷却孔列(変形例)
95 冷却孔列(第1冷却孔列96(96a~96e)、第2冷却孔列97(97a~97e)、第3冷却孔列98(98a~98c)、第4冷却孔列99(99a~99c))
G 燃焼ガス
Ac 冷却空気
AL 軸方向線
FL 冷却孔中心線
OL 開口中心線
OL1 第1開口中心線
OL2 第2開口中心線
IBL、IBL1、IBL2、IBL3 等圧線
Xa 起点
Xb 中間点
Claims (16)
- 翼体と、
前記翼体の翼高さ方向の端部に形成されたシュラウドと、
前記翼体と前記シュラウドを接合するフィレット部と、
を備えるタービン静翼であって、
前記シュラウドは、
燃焼ガス流路に接する底板と、
前記底板の周縁に沿って前記翼高さ方向に延びる周壁と、
前記周壁と前記底板に囲まれた空間を形成する凹部と、
を含み、
前記周壁は、
前記翼体の前縁側に延在する前縁端部と、
前記翼体の負圧面側の前縁から後縁に延びる負圧面側端部と、
を含み、
前記シュラウドは、
前記シュラウドの負圧面側前縁領域に形成され、前記底板に形成された複数の冷却孔を備え、
前記複数の冷却孔は、
第1端が前記底板に形成された入口開口に接続し、
第2端が前記底板のガスパス面に形成されて前記入口開口より軸方向下流側に形成された出口開口に接続し、
前記翼体の翼面から周方向の前記前縁端部又は前記負圧面側端部に向けて所定間隔をあけて配置され、
前記入口開口と前記出口開口を結ぶ冷却孔中心線の軸方向に対する傾きが同一に維持され、
前記複数の冷却孔の前記出口開口の中心を結ぶ直線状の第1開口中心線と、前記冷却孔の前記入口開口の中心を結ぶ直線状の第2開口中心線と、が互いに平行に形成された一組の冷却孔列を構成し、
前記冷却孔列が、軸方向上流側から下流側に向けて前記翼面に沿って複数配置され、
前記複数の冷却孔列の前記冷却孔の前記冷却孔中心線の傾きが、軸方向下流側に向かうと共に小さくなる
タービン静翼。 - 前記シュラウドは、
前記翼体の前記前縁を中心に前記フィレット部の外縁に内接し円状に形成された第1領域を備え、
前記第1開口中心線が、前記第1領域を起点に延伸する、
請求項1に記載のタービン静翼。 - 前記シュラウドは、
前記翼体の内部に形成された第1キャビティ内に配置され、前記翼体の軸方向線上の前記前縁より軸方向下流側に配置され、前記翼体の前記前縁を中心に前記フィレット部の外縁に内接する円状に形成された領域に相当する大きさの第3領域を備え、
前記冷却孔列の内、少なくとも2つの前記冷却孔列の前記第1開口中心線が、前記第3領域を起点に延伸する、
請求項1に記載のタービン静翼。 - 前記シュラウドは、
前記翼体の前記前縁より軸方向上流側の軸方向線上の前記第1領域と同じ半径の円状に形成された第2領域を備え、
前記第2開口中心線が、前記第2領域を起点に延伸する、
請求項2に記載のタービン静翼。 - 前記シュラウドは、
前記第1キャビティ内に配置され、前記翼体の前記軸方向線上の前記前縁より軸方向下流側で前記第3領域より軸方向上流側に配置され、前記第3領域と同じ半径の円状に形成された第4領域を備え、
前記冷却孔列の内、少なくとも2つの前記冷却孔列の前記第2開口中心線が、前記第4領域を起点に延伸する、
請求項3に記載のタービン静翼。 - 前記第1開口中心線又は前記第2開口中心線は、前記第1開口中心線又は前記第2開口中心線が延伸する方向に隣接する少なくとも2つの冷却孔により形成されている、
請求項1から5のいずれか一項に記載のタービン静翼。 - 前記冷却孔中心線は、前記第1開口中心線又は前記第2開口中心線と直交する方向より前記翼面の側に傾いている、
請求項1から5のいずれか一項に記載のタービン静翼。 - 前記冷却孔列の前記冷却孔中心線の前記第1開口中心線に対する傾きは、軸方向のいずれの位置の前記冷却孔列においても、同一の傾きが維持される、
請求項1から5のいずれか一項に記載のタービン静翼。 - 前記複数の冷却孔列の前記第1開口中心線は、軸方向下流方向に向かうと共に、軸方向に隣接して配置された前記冷却孔列の前記第1開口中心線との軸方向の間隔が拡大する
請求項1から5のいずれか一項に記載のタービン静翼。 - 前記冷却孔列の複数の前記冷却孔は、前記第1開口中心線又は前記第2開口中心線が延伸する方向に同一の間隔を維持して配置されている、
請求項1~5の何れか一項に記載のタービン静翼。 - 前記複数の冷却孔列を構成する複数の前記冷却孔の群は、前記第1領域から前記第4領域の内の少なくとも一つの領域を起点に
前記前縁端部又は前記負圧面側端部に向けて放射状に延伸する、
請求項6に記載のタービン静翼。 - 前記複数の冷却孔列の前記第1開口中心線又は前記第2開口中心線のいずれかが、前記第1領域から前記第4領域の内の少なくとも一つの領域を起点に前記前縁端部又は前記負圧面側端部に向けて放射状に延伸する、
請求項6に記載のタービン静翼。 - 前記シュラウドは、
前記翼体と、前記前縁端部を接続する前縁仕切リブと、前記翼体と前記負圧面側端部を接続する負圧面側仕切リブと、により前記凹部が区分けされ、
前記翼体の外壁面と、前記前縁仕切リブと、前記負圧面側仕切リブとに囲まれて形成された第2キャビティを含み、
前記第2キャビティを前記翼高さ方向の外側に形成される第3キャビティと前記第3キャビティの内側に形成される第4キャビティと、に区分けされ、
前記第3キャビティと前記第4キャビティとを連通する複数の貫通孔を備えた衝突板と、
を含む、
請求項1~5のいずれか一項に記載のタービン静翼。 - 前記シュラウドは、
前記翼体の前記翼高さ方向の外側の端部に形成された外側シュラウドと、
前記翼体の前記翼高さ方向の内側の端部に形成された内側シュラウドと、
からなる請求項1~5のいずれか一項に記載のタービン静翼。 - 請求項1から5のいずれか一項に記載のタービン静翼と、
前記タービン静翼が設けられる燃焼ガス流路を流れる燃焼ガスを生成する燃焼器と、
を備えるガスタービン。 - 翼体と、
前記翼体の翼高さ方向の端部に形成されたシュラウドと、
を備え、
前記シュラウドは、
燃焼ガス流路に接する底板と、
前記底板の周縁に沿って前記翼高さ方向に形成される周壁と、
前記周壁と前記底板に囲まれた空間を形成する凹部と、
前記底板と前記翼体と前記周壁を接続する複数の仕切リブと、により前記凹部を区分けし、前記負圧面側前縁領域に形成された第2キャビティと、
前記第2キャビティを前記翼高さ方向の外側に形成される第3キャビティと前記第3キャビティの内側に形成される第4キャビティとに区分けし、前記第3キャビティと前記第4キャビティとを連通する複数の貫通孔を備えた衝突板と、
を備え、
前記底板の内表面に形成された入口開口を介して前記第4キャビティに連通し、前記底板のガスパス面に形成された出口開口を介して燃焼ガス流路に連通する複数の冷却孔を有する冷却孔列を備えたタービン静翼の冷却方法であって、
外部から前記第3キャビティに冷却空気を供給する工程と、
前記冷却空気が、前記負圧面前縁キャビティに配置された前記衝突板に形成された前記貫通孔を介して、前記第3キャビティから前記第4キャビティに供給され、前記第4キャビティの冷却空気の圧力を減圧する工程と、
前記冷却空気が前記底板の内表面をインピンジメント冷却する工程と、
前記底板に形成され、燃焼ガスの等圧線に平行に配置された第1開口中心線を備えた前記冷却孔列を構成する複数の前記冷却孔から前記冷却空気を前記燃焼ガス流路に排出し、前記ガスパス面をフィルム冷却する工程と、
を含む、
タービン静翼の冷却方法。
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Publication number | Priority date | Publication date | Assignee | Title |
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JP2008286157A (ja) * | 2007-05-21 | 2008-11-27 | Mitsubishi Heavy Ind Ltd | タービン静翼 |
US20120034075A1 (en) * | 2010-08-09 | 2012-02-09 | Johan Hsu | Cooling arrangement for a turbine component |
JP2018091227A (ja) * | 2016-12-02 | 2018-06-14 | 三菱重工業株式会社 | 静翼セグメント、これを備えるガスタービン及びガスタービン設備 |
JP2018096376A (ja) * | 2016-12-08 | 2018-06-21 | ドゥサン ヘヴィー インダストリーズ アンド コンストラクション カンパニー リミテッド | ベーンの冷却構造 |
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JP4898731B2 (ja) * | 2008-03-26 | 2012-03-21 | 三菱重工業株式会社 | ガスタービン冷却構造およびこれを備えたガスタービン |
US10337404B2 (en) | 2010-03-08 | 2019-07-02 | General Electric Company | Preferential cooling of gas turbine nozzles |
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JP2008286157A (ja) * | 2007-05-21 | 2008-11-27 | Mitsubishi Heavy Ind Ltd | タービン静翼 |
US20120034075A1 (en) * | 2010-08-09 | 2012-02-09 | Johan Hsu | Cooling arrangement for a turbine component |
JP2018091227A (ja) * | 2016-12-02 | 2018-06-14 | 三菱重工業株式会社 | 静翼セグメント、これを備えるガスタービン及びガスタービン設備 |
JP2018096376A (ja) * | 2016-12-08 | 2018-06-21 | ドゥサン ヘヴィー インダストリーズ アンド コンストラクション カンパニー リミテッド | ベーンの冷却構造 |
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