WO2016002265A1 - 静翼、これを備えているガスタービン、静翼の製造方法、及び静翼の改造方法 - Google Patents
静翼、これを備えているガスタービン、静翼の製造方法、及び静翼の改造方法 Download PDFInfo
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- WO2016002265A1 WO2016002265A1 PCT/JP2015/058172 JP2015058172W WO2016002265A1 WO 2016002265 A1 WO2016002265 A1 WO 2016002265A1 JP 2015058172 W JP2015058172 W JP 2015058172W WO 2016002265 A1 WO2016002265 A1 WO 2016002265A1
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- WIPO (PCT)
- Prior art keywords
- retainer
- shroud
- inner shroud
- axial direction
- radially
- Prior art date
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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
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
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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
- 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
- F01D5/186—Film cooling
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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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
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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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/246—Fastening of diaphragms or stator-rings
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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
- 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
- F01D5/187—Convection cooling
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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
- 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
- F01D5/187—Convection cooling
- F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
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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
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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
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
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- 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
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- 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
- F02C7/16—Cooling of plants characterised by cooling medium
- F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
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- 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
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- 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
- F05D2230/00—Manufacture
- F05D2230/10—Manufacture by removing material
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- 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
- F05D2230/00—Manufacture
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/21—Manufacture essentially without removing material by casting
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- 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
- F05D2230/00—Manufacture
- F05D2230/80—Repairing, retrofitting or upgrading methods
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- 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
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- 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
- F05D2240/80—Platforms for stationary or moving blades
- F05D2240/81—Cooled platforms
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- 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
- F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
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- 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
- F05D2260/202—Heat transfer, e.g. cooling by film cooling
-
- 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
- F05D2260/30—Retaining components in desired mutual position
Definitions
- the present invention relates to a stationary blade, a gas turbine including the stationary blade, a method for manufacturing the stationary blade, and a method for modifying the stationary blade.
- the stationary blade includes a blade body extending in a radial direction with respect to an axis, an outer shroud formed on a radially outer side of the blade body, an inner shroud formed on a radially inner side of the blade body, and a radial direction from the inner shroud.
- a support rail (or retainer) that protrudes inward and extends in the circumferential direction.
- the radially outer surface of the inner shroud that is, the surface facing the outer shroud is a surface in contact with the combustion gas. For this reason, in order to protect the inner shroud from high-temperature combustion gas, it is necessary to cool the inner shroud with a cooling medium such as air. For this reason, a cooling air passage through which air passes is formed in the inner shroud described in Patent Document 1, and a through hole is formed in the support rail.
- an object of the present invention is to provide a technique capable of suppressing thermal stress and enhancing durability.
- a stationary blade as one aspect according to the invention for achieving the above object is as follows: A stationary blade disposed upstream of a moving blade of a turbine rotor rotating about an axis in an axial direction in which the axis extends, and a blade extending in a radial direction with respect to the axis, and a radial direction of the blade An outer shroud formed on the outer side, an inner shroud formed on the radially inner side of the blade body and forming a combustion gas passage through which combustion gas flows between the outer shroud and the axial direction of the inner shroud A retainer that protrudes inward in the radial direction from the inner shroud and extends in the circumferential direction around the axis at a position between the upstream edge and the downstream edge in the axial direction, and The retainer is formed with an opening penetrating in the axial direction and defining a space through which air flows, and the circumferential width of the opening is the retainer in the axial direction. There wider than the
- the opening area of the retainer is larger than the opening area of the support rail (or retainer) in the stationary blade described in Patent Document 1. For this reason, the rigidity of the retainer of the stationary blade is lower than the support rail (or retainer) of the stationary blade described in Patent Document 1. Further, in the stator blade, the width of the retainer opening in the circumferential direction is wider than the circumferential width of the blade body at the radially inner end of the blade body at the position where the retainer exists in the axial direction. For this reason, it can be avoided that the position where the retainer is provided in the inner shroud and the position where the blade body is provided in the inner shroud overlap in the circumferential direction. Therefore, in the stationary blade, the rigidity around the inner shroud is lower than that of the stationary blade described in Patent Document 1. Therefore, in the stationary blade, the thermal stress generated in the inner shroud can be suppressed.
- the inner shroud extends in the axial direction and the circumferential direction, and an inner shroud body whose outer surface in the radial direction is in contact with the combustion gas, and an outer peripheral edge of the inner shroud body.
- a circumferential wall protruding radially inward from the inner shroud body, and the inner shroud is formed with a recess recessed toward the radially outer side by the inner shroud body and the circumferential wall.
- the inside is divided into a radially inner region and an inner cavity which is a radially outer region, and includes a collision plate in which a plurality of air holes are formed, and the radially inner edge of the opening is The radially outer edge of the collision plate is located on the radially inner side with respect to the radially inner surface of the collision plate, and the radially outer edge of the opening is located on the radially outer side with respect to the radially outer surface of the collision plate. It may be location.
- the stator blade can impingement cool the portion of the inner surface of the inner shroud body in the radial direction where the retainer is present in the axial direction. For this reason, in the said stationary blade, the part in which a retainer exists in an axial direction can be cooled effectively. Particularly, in the stationary blade, since the circumferential width of the opening is wider than the circumferential width of the blade body at the position where the retainer is present in the axial direction, the collision plate can be arranged including the inside of the opening. For this reason, in the said stationary blade, the range which can impinge cool with the air which passed the several air of the collision board in the position where a retainer exists in an axial direction can be expanded rather than the stationary blade of patent document 1. FIG. Therefore, in the stationary blade, the thermal stress generated in the inner shroud can be further suppressed.
- an edge on one side in the circumferential direction of the opening is formed on the radially inner end of the blade body at a position where the retainer exists in the axial direction.
- the blade on the radially inner end of the blade body at the position where the retainer exists in the axial direction is located on the one side of the outer surface of the one side, and the edge on the other side in the circumferential direction of the opening You may be located in the said other side rather than the outer surface of the said other side of a body.
- the surface facing the radially outer side of the inner peripheral surface of the opening penetrating the retainer in the axial direction is the upstream side. You may incline gradually toward the said radial direction outer side as it goes to the said downstream from the side.
- the surface facing the radially outer side of the inner peripheral surface of the opening is gradually inclined toward the radially outer side from the upstream side toward the downstream side. For this reason, in the stationary blade, the collision plate can be easily attached and detached by inclining the collision plate with respect to the radially inner surface of the inner shroud body.
- the collision plate is inserted into the opening and spreads on the upstream side and the downstream side with respect to the retainer. It may be formed of a single porous plate.
- the single porous plate forming the collision plate includes a porous plate located on the upstream side and a porous plate located on the downstream side.
- the plate may be joined and integrated.
- the portion is disposed on the downstream side with respect to the retainer, and the portion of the opening of the concave portion that is on the downstream side of the retainer You may provide the sealing board which plugs up.
- the peripheral wall of the inner shroud has a pair of side peripheral walls facing each other with a space therebetween in the circumferential direction, An edge on one side in the circumferential direction of the opening is located in a surface on the inner cavity side in the side circumferential wall on the one side of the pair of side circumferential walls, and an edge on the other side in the circumferential direction of the opening is In the pair of the side peripheral walls, the other side peripheral wall may be positioned in a plane on the inner cavity side.
- the retainer has a larger opening area, the retainer has lower rigidity, and an impact plate is disposed including the inside of the opening, so that the axial retainer in the radially inner region of the inner shroud is arranged.
- the range in which impingement cooling at the position can be expanded in the circumferential direction. For this reason, in the said stationary blade, the thermal stress which generate
- substantially the entire circumferential direction of the portion where the retainer exists in the axial direction in the radially inner surface of the inner shroud main body can be cooled almost uniformly. Therefore, in the said stationary blade, the thermal stress which generate
- the inner shroud is formed with a downstream end surface facing the downstream side, and the inner shroud includes the inner shroud.
- a cooling air ejection hole that penetrates the inner shroud from the cavity and opens at the downstream end surface of the inner shroud body may be formed.
- a plurality of the cooling air ejection holes arranged in the circumferential direction may be formed in the inner shroud.
- the inner shroud body has a cooling air jet that penetrates the inner shroud body from the inner cavity toward the radially outer side.
- a hole may be formed.
- a stationary blade as one aspect according to the invention for achieving the above object is as follows: Any of the above stationary blades, the turbine rotor, a turbine casing that rotatably covers the turbine rotor, and the stationary blades are fixed to an inner peripheral side, and fixed to the turbine casing, And a combustor that generates combustion gas.
- the gas turbine also includes the stationary blade described above, the durability of the stationary blade can be improved.
- the retainer is formed with an opening that penetrates in the axial direction and defines a space through which air flows.
- the retainer in which the opening wider than the circumferential width of the wing body at the radially inner end of the wing body at a position where the retainer exists in the direction, the wing, and the outer shroud;
- the inner shroud is integrally formed by casting.
- a method for remodeling a stationary blade as one aspect according to the invention for achieving the above object is as follows: A stationary blade disposed upstream of a moving blade of a turbine rotor that rotates about an axis in an axial direction in which the axis extends, and a blade that extends in a radial direction with respect to the axis; An outer shroud formed radially outward, an inner shroud formed on the radially inner side of the blade body and forming a combustion gas flow path through which combustion gas flows between the outer shroud, and the inner shroud A retainer that protrudes inward in the radial direction from the inner shroud and extends in a circumferential direction around the axis at a position between the upstream edge in the axial direction and a downstream edge in the axial direction.
- the retainer is formed with an opening that penetrates in the axial direction and defines a space through which air flows. , So that wider than the circumferential width of the blade body in the radially inner end of the blade body at a position where the retainer is present in the axial direction, to process the retainer.
- the circumferential width of the opening before the processing is such that the blade body at the radially inner end of the blade body at a position where the retainer exists in the axial direction.
- the retainer may be ground to expand the opening.
- thermal stress generated in the inner shroud of the stationary blade can be suppressed. Therefore, according to one embodiment of the present invention, it is possible to increase the durability of the stationary blade.
- FIG. 7 is a sectional view taken along line VII-VII in FIG. 6.
- FIG. 7 is a sectional view taken along line VIII-VIII in FIG. 6. It is a principal part notched side view of the stationary blade in the comparative example which concerns on this invention.
- FIG. 10 is a sectional view taken along line XX in FIG. 9. It is a flowchart which shows the manufacturing method of the stationary blade in one Embodiment which concerns on this invention. It is a flowchart which shows the remodeling method of the stationary blade in one Embodiment which concerns on this invention. It is principal part sectional drawing of the stationary blade in the 1st modification of one Embodiment which concerns on this invention. It is a principal part notched side view of the stationary blade in the 2nd modification of one Embodiment which concerns on this invention.
- stator blade according to the present invention, an embodiment of a gas turbine including the stator blade, and various modifications of the stator blade will be described in detail with reference to the drawings.
- the gas turbine includes a compressor 10 that compresses air, a combustor 20 that burns fuel in the air compressed by the compressor 10 to generate combustion gas, and combustion. And a turbine 30 driven by gas.
- the compressor 10 includes a compressor rotor 11 that rotates about an axis Ar, a compressor casing 15 that rotatably covers the compressor rotor 11, and a plurality of stationary blade stages 14.
- the direction in which the axis Ar extends is the axial direction Da
- one side of the axial direction Da is the upstream side
- the other side is the downstream side.
- the circumferential direction around the axis Ar is simply referred to as the circumferential direction Dc
- the direction perpendicular to the axis Ar is referred to as the radial direction Dr.
- the compressor rotor 11 includes a rotor shaft 12 extending in the axial direction Da around the axis Ar, and a plurality of blade stages 13 attached to the rotor shaft 12.
- the plurality of blade stages 13 are arranged in the axial direction Da.
- Each blade stage 13 is composed of a plurality of blades arranged in the circumferential direction Dc.
- a stationary blade stage 14 is disposed on each upstream side of the plurality of blade stages 13.
- Each stationary blade stage 14 is provided inside the compressor casing 15.
- Each stationary blade stage 14 is configured by a plurality of stationary blades arranged in the circumferential direction Dc.
- the annular space between the radially outer peripheral side of the rotor shaft 12 and the radially inner peripheral side of the compressor casing 15 is a region where the stationary blade stage 14 and the moving blade stage 13 are arranged in the axial direction Da.
- An air compression flow path 19 that is compressed while air flows is formed.
- the turbine 30 includes a turbine rotor 31 that rotates about an axis Ar, a turbine casing 35 that rotatably covers the turbine rotor 31, and a plurality of stationary blade stages 34.
- the combustor 20 is fixed to a portion on the upstream side of the turbine casing 35.
- the turbine rotor 31 includes a rotor shaft 32 extending in the axial direction Da around the axis line Ar, and a plurality of blade stages 33 attached to the rotor shaft 32.
- the plurality of blade stages 33 are arranged in the axial direction Da.
- Each of the blade stages 33 is composed of a plurality of blades arranged in the circumferential direction Dc.
- a stationary blade stage 34 is arranged on each upstream side of the plurality of blade stages 33.
- Each stationary blade stage 34 is provided inside the turbine casing 35. As shown in FIG. 3, each stationary blade stage 34 includes a plurality of stationary blades 40 arranged in the circumferential direction Dc. An annular space between the outer peripheral side of the rotor shaft 32 and the inner peripheral side of the turbine casing 35 and in which the stationary blade stage 34 and the moving blade stage 33 are arranged in the axial direction Da is a combustor 20. The combustion gas flow path 39 through which the combustion gas G from the gas flows is formed.
- the combustor 20 includes a combustion cylinder (or tail cylinder) 21 that sends high-temperature and high-pressure combustion gas G into the combustion gas flow path 39 of the turbine 30, and a fuel injector 22 that injects fuel into the combustion cylinder 21 together with air.
- the fuel injector 22 has a plurality of nozzles 23 that inject fuel into the combustion cylinder 21. Each nozzle 23 is supplied with fuel from a fuel supply source via a fuel line.
- the compressor rotor 11 and the turbine rotor 31 are located on the same axis Ar and connected to each other to form the gas turbine rotor 1.
- the compressor casing 15 and the turbine casing 35 are connected to each other to form a gas turbine casing 5.
- the gas turbine is further arranged on the inner peripheral side of the gas turbine casing 5 between the air compression passage 19 of the compressor 10 and the combustion gas passage 39 of the turbine 30 in the axial direction Da.
- An inner cover 6 is provided to cover the outer peripheral side. The inner cover 6 extends in the axial direction Da to the position of the most upstream first stationary blade stage 34 f of the stationary blade stages 34 of the turbine 30.
- each of the plurality of stationary blades 40 constituting each stationary blade stage 34 of the turbine 30 is formed on a blade body 41 extending in the radial direction Dr and on the radially outer side of the blade body 41. It has an outer shroud 51 and an inner shroud 61 formed inside the wing body 41 in the radial direction. Between the inner shroud 61 and the outer shroud 51, a part of the combustion gas flow path 39 is formed.
- the plurality of stationary blades 40f constituting the most upstream first stationary blade stage 34f further includes a retainer 91 that protrudes radially inward from the inner shroud 61 and extends in the circumferential direction.
- the wing body 41 extends in the radial direction Dr and flows through the cooling air main flow path 42 through which cooling air flows.
- the wing body 41 passes through the wing body 41 from the cooling air main flow path 42 toward the upstream side and opens at the front edge of the wing body 41.
- a plurality of cooling air ejection holes 43 are formed.
- the blade body 41 may be formed with a plurality of cooling air ejection holes that penetrate the blade body 41 toward the downstream side from the cooling air main flow path 42 and open at the rear edge of the blade body 41.
- the outer shroud 51 includes a plate-shaped outer shroud body 52 that extends in the axial direction Da and the circumferential direction Dc, and a peripheral wall 55 that protrudes radially outward from the outer shroud body 52 along the outer peripheral edge of the outer shroud body 52.
- the peripheral wall 55 includes an upstream peripheral wall 56 and a downstream peripheral wall 57 that face each other in the axial direction Da, and a pair of side peripheral walls 58 that face each other in the circumferential direction Dc. Both the upstream peripheral wall 56 and the downstream peripheral wall 57 protrude outward in the radial direction from the pair of side peripheral walls 58 with respect to the outer shroud main body 52 to form a hook portion.
- the upstream peripheral wall 56 and the downstream peripheral wall 57 forming the hook portion serve to attach the stationary blade 40 to the inner peripheral side of the turbine casing 35.
- the outer shroud 51 is formed with a recess 54 that is recessed radially inward by the outer shroud body 52 and the peripheral wall 55.
- the cooling air main flow path 42 of the wing body 41 is opened in the recess 54. Therefore, air from the radially outer side of the outer shroud 51 flows into the cooling air main flow path 42 of the wing body 41.
- the air that has flowed into the cooling air main channel 42 is ejected into the combustion gas channel 39 from a plurality of cooling air ejection ports.
- the stationary blade 40 further includes a collision plate 59 that partitions the concave portion 54 of the outer shroud 51 into a radially inner region and a radially outer region.
- the collision plate 59 is formed with a plurality of air holes penetrating in the radial direction Dr.
- the inner shroud 61 has a plate-like inner shroud body 62 extending in the axial direction Da and the circumferential direction Dc, and a radial direction from the inner shroud body 62 along the outer peripheral edge of the inner shroud body 62. And a peripheral wall 71 protruding inward.
- the radially outer surface of the inner shroud body 62 forms a gas path surface 66 that comes into contact with the combustion gas.
- the inner shroud main body 62 is formed with an upstream end face 63 and a downstream end face 64 that face each other in the axial direction Da, and a pair of side end faces 65 that face each other in the circumferential direction Dc. As shown in FIG. 3, each of the pair of side end faces 65 is inclined so as to be gradually located on one side in the circumferential direction Dc from the upstream side toward the downstream side. For this reason, the inner shroud main body 62 has a parallelogram shape when viewed from the radially inner side toward the radially outer side.
- the peripheral wall 71 includes an upstream peripheral wall 73 and a downstream peripheral wall 74 that face each other in the axial direction Da, and a pair of side peripheral walls 75 that face each other in the circumferential direction Dc.
- the upstream peripheral wall 73 extends in the circumferential direction Dc along the upstream end surface 63 at a position slightly downstream from the upstream end surface 63 of the inner shroud main body 62.
- the downstream peripheral wall 74 extends in the circumferential direction Dc along the downstream end surface 64 at a position slightly upstream from the downstream end surface 64 of the inner shroud main body 62.
- the side peripheral wall 75 is formed along the side end surface 65 of the inner shroud body 62 between the upstream peripheral wall 73 and the downstream peripheral wall 74.
- the inner shroud 61 is formed with a recess 84 that is recessed radially outward by the inner shroud body 62 and the peripheral wall 71.
- the cooling air main flow path 42 of the blade body 41 opens in the recess 54 of the outer shroud 51 and also opens in the recess 84 of the inner shroud 61.
- the retainer 91 is positioned in the axial direction Da within the region where the wing body 41 is present, and from the one side peripheral wall 75 of the pair of side peripheral walls 75 of the inner shroud 61 in the circumferential direction Dc. It extends to the other side peripheral wall 75.
- the retainer 91 protrudes radially inward from any of the upstream peripheral wall 73, the downstream peripheral wall 74, and the side peripheral wall 75 that form the peripheral wall 71.
- the retainer 91 is in contact with the radially outer end 6a (see FIG. 6) on the downstream side of the inner cover 6, and the radially inner portion of the stationary blade 40f is connected to the radially outer end 6a on the downstream side of the inner cover 6 (FIG. 6). (See)) to support.
- the retainer 91 is formed with an opening 92 (hereinafter referred to as a retainer opening 92) that defines a space through which air passes through in the axial direction Da.
- the retainer opening 92 has a long rectangular shape in the circumferential direction Dc when viewed from the axial direction Da.
- the first inner peripheral surface 93 facing one side in the circumferential direction Dc is located on the recess 84 side of the side peripheral wall 75y on the other side in the circumferential direction Dc of the pair of side peripheral walls 75.
- the second inner peripheral surface 94 that is located in the plane and faces the other side in the circumferential direction Dc is located in the surface on the concave portion 84 side of the one side peripheral wall 75x of the pair of side peripheral walls 75.
- the edge 94e on one side in the circumferential direction Dc of the retainer opening 92 is located within the surface on the concave portion 84 side of the one side circumferential wall 75x of the pair of side circumferential walls 75, and the circumferential direction Dc of the retainer opening 92
- the other side edge 93e of the pair of side peripheral walls 75 is located in the surface of the other side peripheral wall 75y on the concave portion 84 side.
- one edge 94e in the circumferential direction Dc of the retainer opening 92 is one side than the outer surface 48 on one side of the wing body 41 at the radially inner end of the wing body 41 at the position where the retainer 91 is present in the axial direction Da.
- the edge 93e on the other side in the circumferential direction Dc of the retainer opening 92 is on the other side than the outer surface 47 on the other side of the blade body 41 at the radially inner end of the blade body 41 at the position where the retainer 91 is present in the axial direction Da.
- the width Wo of the retainer opening 92 in the circumferential direction Dc coincides with the width of the circumferential direction Dc in the recess 84 of the inner shroud 61, and the radially inner end of the wing body 41 at the position where the retainer 91 exists in the axial direction Da. Is wider than the width Ww of the wing body 41 in the circumferential direction Dc.
- the third inner peripheral surface 95 facing the radially inner side of the inner peripheral surface of the retainer opening 92 is included in the radially inner surface 67 of the inner shroud main body 62.
- the position of the surface 67 and the radial direction Dr coincide.
- the radially outer edge 95e of the retainer opening 92 is included in the radially inner surface 67 of the inner shroud main body 62, and the position of the surface 67 coincides with the radial direction Dr.
- the fourth inner peripheral surface 96 facing the radially outer side is inclined so as to gradually go radially outward from the upstream side toward the downstream side.
- the downstream side edge 96d of the fourth inner peripheral surface 96 has a position in the radial direction Dr that substantially coincides with a position of the radially inner surface of the side peripheral wall 75. Therefore, the upstream edge 96u of the fourth inner peripheral surface 96 is located on the radially inner side of the position of the radially inner surface of the side peripheral wall 75.
- the plurality of stationary blades 40f constituting the first stationary blade stage 34f further includes a collision plate 101 that divides the inside of the concave portion 84 into a radially inner region 85 and an inner cavity 86 that is a radially outer region, And a sealing plate 105 that closes a portion downstream of the retainer 91 in the opening of 84.
- the outer shroud 51, the wing body 41, the inner shroud 61, and the retainer 91 are integrally formed, and thereby, the stationary blade body MB (see FIG. 4) is configured. Therefore, the stationary blade 40f of the present embodiment includes the collision plate 101, the sealing plate 105, the stationary blade main body MB, and the collision plate 59 that partitions the concave portion 54 of the outer shroud 51.
- the collision plate 101 is inserted through the retainer opening 92 at a substantially intermediate position in the radial direction Dr within the recess 84. Therefore, the radially outer edge of the retainer opening 92 is positioned radially outward from the radially outer surface of the collision plate 101, and the radially inner edge of the retainer opening 92 is smaller than the radially inner surface of the collision plate 101. Is also located radially inward.
- the upstream edge of the collision plate 101 is in contact with the upstream peripheral wall 73 of the inner shroud 61, the downstream edge thereof is in contact with the downstream peripheral wall 74 of the inner shroud 61, and the side edge that is the end in the circumferential direction Dc is the side peripheral wall 75 of the inner shroud 61. Is in contact with The collision plate 101 has a plurality of air holes penetrating from the radially inner side toward the radially outer side.
- the sealing plate 105 is located on the downstream side of the retainer 91 and on the radially inner side of the collision plate 101.
- the sealing plate 105 has an upstream edge in contact with the fourth inner peripheral surface 96 of the retainer opening 92, a downstream edge in contact with the downstream peripheral wall 74 of the inner shroud 61, and a side edge that is an end in the circumferential direction Dc as an inner shroud. 61 is in contact with the side peripheral wall 75.
- the inner shroud 61 is formed with a plurality of first cooling air ejection holes 68 (see FIG. 6) that penetrate the inner shroud 61 from the inner cavity 86 toward the downstream side and open at the downstream end face 64 of the inner shroud body 62.
- the plurality of first cooling air ejection holes 68 are arranged in the circumferential direction Dc (see FIG. 3).
- the inner shroud body 62 has a plurality of second cooling air ejection holes 69 (see FIG. 5) that pass through the inner shroud body 62 radially outward from the inner cavity 86 and open at the gas path surface 66 of the inner shroud body 62. 6) is formed.
- Compressor 10 sucks outside air and compresses it to generate compressed air.
- a part of the compressed air generated by the compressor 10 is ejected into the combustion cylinder 21 via the fuel injector 22 of the combustor 20.
- fuel from the fuel injector 22 is injected into the combustion cylinder 21. This fuel burns in the compressed air in the combustion cylinder 21.
- combustion gas G is generated, and this combustion gas G flows from the combustion cylinder 21 into the combustion gas flow path 39 of the turbine 30.
- the turbine rotor 31 rotates when the combustion gas G passes through the combustion gas passage 39.
- the stationary blade 40f that forms part of the combustion gas passage 39 is exposed to high-temperature combustion gas. For this reason, the flow path and the hole through which cooling air flows are formed in the stationary blade 40f of this embodiment as mentioned above.
- a part of the compressed air generated by the compressor 10 flows into the concave portion 54 of the outer shroud 51 from the radially outer side of the stationary blade 40f.
- Part of the compressed air that has flowed into the recess 54 of the outer shroud 51 flows into the outer cavity between the collision plate 59 and the outer shroud body 52 through the plurality of air holes of the collision plate 59.
- the compressed air collides with the outer shroud body 52 and impingement cools the outer shroud body.
- the remaining part of the compressed air that has flowed into the recess 54 of the outer shroud 51 flows into the cooling air main flow path 42 of the blade body 41 and is jetted into the combustion gas flow path 39 from the plurality of cooling air ejection holes 43.
- the blade body 41 is further cooled in the process of being ejected from the plurality of cooling air ejection holes 43.
- the other part of the compressed air generated by the compressor 10 flows into the recess 84 of the inner shroud 61 from the radially inner side of the stationary blade 40f. More precisely, the compressed air flows from the portion of the opening of the recess 84 of the inner shroud 61 upstream of the retainer 91 into the radially inner region 85 in the recess 84. Further, the compressed air also flows from the retainer opening 92 into the radially inner region 85 in the recess 84.
- This compressed air cools the downstream portion of the inner shroud body 62 in the process of flowing through the plurality of first cooling air ejection holes 68.
- the stator blade 40c of the comparative example is basically different from the retainer 91 of the stator blade 40f of the present embodiment in the retainer 91c.
- the retainer 91c in the stationary blade 40c of the comparative example is formed so as to protrude radially inward from the radially inner surface of the inner shroud body 62c.
- a retainer opening 92c formed in the retainer 91c is formed at a position between the collision plate 101cb and the sealing plate 105 in the radial direction Dr. As shown in FIG. 10, the retainer opening 92c has a rectangular shape when viewed from the axial direction Da.
- the dimension of the retainer opening 92c in the radial direction Dr is smaller than the distance between the collision plate 101cb and the sealing plate 105 in the radial direction Dr. For this reason, the width of the retainer opening 92c in the radial direction Dr is much narrower than the width of the retainer opening 92 of the present embodiment in the radial direction Dr.
- the inner diameter dimension Woc which is the width in the circumferential direction Dc of the retainer opening 92c, is the width Ww in the circumferential direction Dc of the wing body 41 at the radially inner end of the wing body 41 at the position where the retainer 91c exists in the axial direction Da. Narrower. That is, the opening area of the retainer opening 92c of the comparative example is much smaller than the opening area of the retainer opening 92 of the present embodiment.
- the rigidity of the retainer 91c of the comparative example is greater than the rigidity of the retainer 91 of the present embodiment. Is also expensive.
- the position where the retainer 91c is provided in the inner shroud body 62c and the position where the wing body 41 is provided in the inner shroud body 62c overlap in the circumferential direction Dc.
- the rigidity around the inner shroud body 62c, particularly the rigidity around the position where the retainer 91c is provided in the inner shroud body 62c is increased.
- a temperature distribution is generated in the inner shroud body 62c, a high thermal stress is generated around the position where the retainer 91c is provided in the inner shroud 61c.
- the rigidity of the retainer 91 of the present embodiment is larger than the rigidity of the retainer 91c of the comparative example. Is also low.
- the position where the retainer 91 is provided in the inner shroud 61 and the position where the wing body 41 is provided in the inner shroud 61 are different in the circumferential direction Dc. Therefore, in the stationary blade 40f of this embodiment, the rigidity around the inner shroud main body 62 is lower than that of the comparative example. For this reason, in this embodiment, even if temperature distribution arises in the inner shroud main body 62, the thermal stress which generate
- the retainer 91c shown in the comparative example is provided from the inner shroud main body 62c to the inner side in the radial direction and over the entire width in the circumferential direction Dc of the inner shroud main body 62c. Therefore, the radially inner surface 67 at the position in the axial direction Da of the inner shroud main body 62c where the retainer 91c is present is an area where impingement cooling cannot be performed over the entire width in the circumferential direction Dc.
- the retainer opening 92 formed in the retainer 91 of the present embodiment has a width Ww in the circumferential direction Dc of the wing body 41 at the radially inner end of the wing body 41 at the position where the retainer 91 exists in the axial direction Da.
- the collision plate 101 can be disposed on the radially inner surface 67 of the inner shroud main body 62 over almost the entire region in the circumferential direction Dc where the retainer 91 is present in the axial direction Da. Therefore, impingement cooling is possible over the entire width in the circumferential direction Dc of the radially inner surface 67 of the inner shroud body 62 including the portion where the retainer 91 exists in the axial direction Da. Therefore, the inner shroud main body 62 of the present embodiment is substantially more uniformly cooled by compressed air than the comparative example, including the portion where the retainer 91 is present in the axial direction Da.
- the temperature difference in the inner shroud body 62 of the present embodiment can be made smaller than that in the comparative example. Therefore, in this embodiment, the thermal stress which generate
- the rigidity around the inner shroud main body 62 is lower than that in the comparative example, and the temperature difference in the inner shroud main body 62 is small, so that it occurs in the inner shroud main body 62 as compared with the comparative example. Thermal stress can be reduced. Therefore, in the present embodiment, the durability of the stationary blade 40f can be improved as compared with the comparative example.
- the recess 84c is divided into a radially inner region 85 and a radially outer cavity 86.
- a downstream collision plate 101cb that partitions the downstream portion into a radially inner region 85 and a radially outer cavity 86 is necessary.
- the width Wo of the retainer opening 92 in the circumferential direction Dc matches the width of the circumferential direction Dc in the recess 84 of the inner shroud 61, even if the collision plate 101 is formed by a single porous plate, By inserting this single perforated plate through the retainer opening 92, the concave portion 84 can be partitioned into a radially inner region 85 and a radially outer cavity 86.
- the manufacturing process (S10) of the stationary blade body MB, the manufacturing process (S20) of the collision plates 59 and 101, and the manufacturing process (S30) of the sealing plate 105 are performed individually.
- a mold and a core for casting the stationary blade body MB are manufactured (S11).
- the core is for forming the cooling air main flow path 42 and the like in the wing body 41.
- molten metal is poured into the one in which the core is incorporated in the mold, and an intermediate product of the stationary blade body MB is cast (S12).
- the outer shroud 51, the wing body 41, the inner shroud 61, and the retainer 91 are integrated.
- the retainer 91 is formed with the retainer opening 92 described above.
- the intermediate product is finished to complete the stationary blade body MB (S13).
- the finishing treatment includes polishing the surface of the intermediate product, applying a thermal barrier coating to the surface of the intermediate product, processing the various cooling air ejection holes 43, 68, and 69.
- a plate corresponding to the shape and size of the collision plates 59 and 101 is manufactured.
- a plurality of through holes are formed in the plate.
- finish processing is performed on the plate in which the plurality of through holes are formed, that is, the perforated plate, and the collision plates 59 and 101 are completed.
- the manufacturing process (S30) of the sealing plate 105 first, a plate corresponding to the shape and size of the sealing plate 105 is manufactured. Next, finishing processing is performed on the plate to complete the sealing plate 105.
- the retainer 91c of the comparative example is processed by a processing method such as grinding to expand the retainer opening 92c, and the shape and size of the retainer opening 92c are described above.
- the shape and size of the retainer opening 92 of the embodiment are matched (S10a).
- a collision plate and a sealing plate are separately manufactured (S20a, S30a).
- the stationary blade 40a of the present modification is obtained by changing the size of the retainer opening 92a of the above-described embodiment, and the other configuration is the same as that of the stationary blade 40f of the above-described embodiment.
- the width Woa in the circumferential direction Dc of the retainer opening 92a in the stationary blade 40a of the present modification is narrower than the width in the circumferential direction Dc in the recess 84a of the inner shroud 61a
- the retainer 91a in the axial direction Da is similar to the above embodiment. It is wider than the width Ww in the circumferential direction Dc of the wing body 41 at the radially inner end of the wing body 41 at the existing position.
- edge 94e on one side in the circumferential direction Dc of the retainer opening 92a is one side than the outer surface 48 on one side of the wing body 41 at the radially inner end of the wing body 41 at the position where the retainer 91a exists in the axial direction Da.
- the other edge 93e in the circumferential direction Dc of the retainer opening 92a is the other than the outer surface 47 on the other side of the wing body 41 at the radially inner end of the wing body 41 at the position where the retainer 91a exists in the axial direction Da.
- the width of the retainer opening 92a in the radial direction Dr is the same as that in the above embodiment.
- the rigidity of the retainer 91a of this modified example is that of the retainer 91c of the comparative example. Lower than.
- the position where the retainer 91a is provided in the inner shroud 61a and the position where the wing body 41 is provided in the inner shroud 61a are different in the circumferential direction Dc.
- the rigidity around the inner shroud body 62a is lower than that of the comparative example. Therefore, in this modification, even if temperature distribution arises in the inner shroud main body 62a, the thermal stress generated in the inner shroud main body 62a can be suppressed.
- the retainer opening 92a is formed wider in the circumferential direction Dc than the width Ww in the circumferential direction Dc of the wing body 41 at the radially inner end of the wing body 41 at the position where the retainer 91a exists in the axial direction Da.
- the inner shroud body 62 is formed from a position flush with the radially inner surface 67 of the inner shroud body 62 to a radially inner surface (downstream edge 96d) of the side peripheral wall 75.
- the thermal stress generated in the inner shroud main body 62a can be made smaller than in the comparative example, so that the durability of the stationary blade 40a can be improved as compared with the comparative example.
- the stationary blade 40b of this modification is a modification of the collision plate 101 of the above embodiment, and the other configuration is the same as the stationary blade 40f of the above embodiment.
- the collision plate 101 of the above embodiment uses a single porous plate as it is as a single collision plate 101.
- the two perforated plates 103a and 103b are joined and integrated together, and this is used as one impact plate 101a.
- one perforated plate 103a has a radially inner region 85 and a radially outer inner portion in the recess 84 of the inner shroud 61, the portion upstream of the retainer 91. It is an upstream perforated plate that partitions into the cavity 86.
- the remaining one perforated plate 103b is a part of the concave portion 84 of the inner shroud 61 on the upstream side of the retainer 91, a portion in the retainer opening 92, and the retainer.
- This is a downstream perforated plate that partitions a portion downstream of 91 into a radially inner region 85 and a radially outer cavity 86.
- This modification corresponds to the case where such labor is required.
- the downstream porous plate 103 b and the upstream porous plate 103 a are temporarily attached to the inner shroud 61.
- the downstream perforated plate 103b and the upstream perforated plate 103a are joined together by welding or the like, and both are integrated to form a single collision plate 101a.
- the single collision plate 101a is permanently attached to the inner shroud 61 as necessary.
- this modification is a modification of the collision board 101 of the said embodiment, also in the said 1st modification, like this modification, two porous plates are joined and both are integrated, This may be used as a single collision plate.
- the durability of the stationary blade can be improved.
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Abstract
Description
軸線を中心として回転するタービンロータの動翼に対して、前記軸線が延びる軸線方向における上流側に配置されている静翼において、前記軸線に対する径方向に延びる翼体と、前記翼体の径方向外側に形成されている外側シュラウドと、前記翼体の径方向内側に形成され、前記外側シュラウドとの間に燃焼ガスが流れる燃焼ガス流路を形成する内側シュラウドと、前記内側シュラウドの前記軸線方向における前記上流側の縁と前記軸線方向における下流側の縁との間の位置で、前記内側シュラウドから前記径方向内側に突出し且つ前記軸線を中心とする周方向に延びるリテーナと、を備え、前記リテーナには、前記軸線方向に貫通し、空気が流れる空間を画定する開口が形成され、前記開口の前記周方向の幅は、前記軸線方向で前記リテーナが存在する位置での前記翼体の径方向内側端における前記翼体の前記周方向の幅より広い。
以上のいずれかの静翼と、前記タービンロータと、前記タービンロータを回転可能に覆い、且つ前記静翼が内周側に固定されているタービン車室と、前記タービン車室に固定され、前記燃焼ガスを生成する燃焼器と、を備える。
軸線を中心として回転するタービンロータの動翼に対して、前記軸線が延びる軸線方向における上流側に配置されている静翼であって、前記軸線に対する径方向に延びる翼体と、前記翼体の径方向外側に形成されている外側シュラウドと、前記翼体の径方向内側に形成され、前記外側シュラウドとの間に燃焼ガスが流れる燃焼ガス流路を形成する内側シュラウドと、前記内側シュラウドの前記軸線方向における前記上流側の縁と前記軸線方向における下流側の縁との間の位置で、前記内側シュラウドから前記径方向内側に突出し且つ前記軸線を中心とした周方向に延びるリテーナと、を備え、前記リテーナには、前記軸線方向に貫通し、空気が流れる空間を画定する開口が形成されている静翼の製造方法において、前記周方向の幅が、前記軸線方向で前記リテーナが存在する位置での前記翼体の径方向内側端における前記翼体の前記周方向の幅より広い前記開口が形成されている前記リテーナと、前記翼と、前記外側シュラウドと、前記内側シュラウドと、を鋳造で一体形成する。
軸線を中心として回転するタービンロータの動翼に対して、前記軸線が延びる軸線方向における上流側に配置されている静翼であって、前記軸線に対する径方向に延びる翼体と、前記翼体の径方向外側に形成されている外側シュラウドと、前記翼体の径方向内側に形成され、前記外側シュラウドとの間に燃焼ガスが流れる燃焼ガス流路を形成する内側シュラウドと、前記内側シュラウドの前記軸線方向における前記上流側の縁と前記軸線方向における下流側の縁との間の位置で、前記内側シュラウドから前記径方向内側に突出し且つ前記軸線を中心とした周方向に延びるリテーナと、を備え、前記リテーナには、前記軸線方向に貫通し、空気が流れる空間を画定する開口が形成されている静翼の改造方法において、前記開口の前記周方向の幅が、前記軸線方向で前記リテーナが存在する位置での前記翼体の径方向内側端における前記翼体の前記周方向の幅より広くなるよう、前記リテーナを加工する。
本発明に係る静翼、これを備えるガスタービンの一実施形態について、図1~図12を参照して説明する。
上記実施形態の静翼40fの第一変形例について、図13を参照して説明する。
上記実施形態の静翼40fの第二変形例について、図14を参照して説明する。
Claims (14)
- 軸線を中心として回転するタービンロータの動翼に対して、前記軸線が延びる軸線方向における上流側に配置されている静翼において、
前記軸線に対する径方向に延びる翼体と、
前記翼体の径方向外側に形成されている外側シュラウドと、
前記翼体の径方向内側に形成され、前記外側シュラウドとの間に燃焼ガスが流れる燃焼ガス流路を形成する内側シュラウドと、
前記内側シュラウドの前記軸線方向における前記上流側の縁と前記軸線方向における下流側の縁との間の位置で、前記内側シュラウドから前記径方向内側に突出し且つ前記軸線を中心とする周方向に延びるリテーナと、
を備え、
前記リテーナには、前記軸線方向に貫通し、空気が流れる空間を画定する開口が形成され、
前記開口の前記周方向の幅は、前記軸線方向で前記リテーナが存在する位置での前記翼体の径方向内側端における前記翼体の前記周方向の幅より広い、
静翼。 - 請求項1に記載の静翼において、
前記内側シュラウドは、前記軸線方向及び前記周方向に広がり、前記径方向外側の面が前記燃焼ガスに接する内側シュラウド本体と、前記内側シュラウド本体の外周縁に沿って前記内側シュラウド本体から前記径方向内側に突出する周壁と、を有し、
前記内側シュラウドには、前記内側シュラウド本体と前記周壁とにより、前記径方向外側に向かって凹む凹部が形成され、
前記凹部内を前記径方向内側の領域と前記径方向外側の領域である内側キャビティとに仕切し、複数の空気孔が形成されている衝突板を備え、
前記開口の前記径方向内側の縁は、前記衝突板の前記径方向内側の面よりも前記径方向内側に位置し、前記開口の前記径方向外側の縁は、前記衝突板の前記径方向外側の面よりも前記径方向外側に位置する、
静翼。 - 請求項1又は2に記載の静翼において、
前記開口の前記周方向における一方側の縁は、前記軸線方向で前記リテーナが存在する位置での前記翼体の径方向内側端における前記翼体の前記一方側の外面よりも前記一方側に位置し、
前記開口の前記周方向における他方側の縁は、前記軸線方向で前記リテーナが存在する位置での前記翼体の径方向内側端における前記翼体の前記他方側の外面よりも前記他方側に位置する、
静翼。 - 請求項2に記載の静翼において、
前記衝突板は、前記開口に挿通され、前記リテーナを基準として前記上流側及び前記下流側に広がっている一枚の多孔板で形成されている、
静翼。 - 請求項4に記載の静翼において、
前記衝突板を形成する前記一枚の多孔板は、前記上流側に位置する多孔板と、前記下流側に位置する多孔板とが接合されて一体化されたものである、
静翼。 - 請求項2、4、5のいずれか一項に記載の静翼において、
前記リテーナを基準として前記下流側に配置され、前記凹部の開口のうち、前記リテーナよりも前記下流側の部分を塞ぐ封止板を備える、
静翼。 - 請求項2、4から6のいずれか一項に記載の静翼において、
前記内側シュラウドの前記周壁は、前記周方向で互いの間隔をあけて対向する一対の側周壁を有し、
前記開口の前記周方向における一方側の縁は、一対の前記側周壁のうち前記一方側の側周壁における前記内側キャビティ側の面内に位置し、前記開口の前記周方向における他方側の縁は、一対の前記側周壁うち前記他方側の側周壁における前記内側キャビティ側の面内に位置する、
静翼。 - 請求項2、4から7のいずれか一項に記載の静翼において、
前記内側シュラウド本体には、前記下流側を向く下流端面が形成されており、
前記内側シュラウドには、前記内側キャビティから前記内側シュラウドを貫通して、前記内側シュラウド本体の前記下流端面で開口する冷却空気噴出孔が形成されている、
静翼。 - 請求項8に記載の静翼において、
前記内側シュラウドには、前記周方向に並ぶ複数の前記冷却空気噴出孔が形成されている、
静翼。 - 請求項2、4から9のいずれか一項に記載の静翼において、
前記内側シュラウド本体には、前記内側キャビティから前記内側シュラウド本体を前記径方向外側に向かって貫通する冷却空気噴出孔が形成されている、
静翼。 - 請求項1から10のいずれか一項に記載の静翼と、
前記タービンロータと、
前記タービンロータを回転可能に覆い、且つ前記静翼が内周側に固定されているタービン車室と、
前記タービン車室に固定され、前記燃焼ガスを生成する燃焼器と、
を備えるガスタービン。 - 軸線を中心として回転するタービンロータの動翼に対して、前記軸線が延びる軸線方向における上流側に配置されている静翼であって、
前記軸線に対する径方向に延びる翼体と、前記翼体の径方向外側に形成されている外側シュラウドと、前記翼体の径方向内側に形成され、前記外側シュラウドとの間に燃焼ガスが流れる燃焼ガス流路を形成する内側シュラウドと、前記内側シュラウドの前記軸線方向における前記上流側の縁と前記軸線方向における下流側の縁との間の位置で、前記内側シュラウドから前記径方向内側に突出し且つ前記軸線を中心とした周方向に延びるリテーナと、を備え、
前記リテーナには、前記軸線方向に貫通し、空気が流れる空間を画定する開口が形成されている静翼の製造方法において、
前記周方向の幅が、前記軸線方向で前記リテーナが存在する位置での前記翼体の径方向内側端における前記翼体の前記周方向の幅より広い前記開口が形成されている前記リテーナと、前記翼体と、前記外側シュラウドと、前記内側シュラウドと、を鋳造で一体形成する、
静翼の製造方法。 - 軸線を中心として回転するタービンロータの動翼に対して、前記軸線が延びる軸線方向における上流側に配置されている静翼であって、
前記軸線に対する径方向に延びる翼体と、前記翼体の径方向外側に形成されている外側シュラウドと、前記翼体の径方向内側に形成され、前記外側シュラウドとの間に燃焼ガスが流れる燃焼ガス流路を形成する内側シュラウドと、前記内側シュラウドの前記軸線方向における前記上流側の縁と前記軸線方向における下流側の縁との間の位置で、前記内側シュラウドから前記径方向内側に突出し且つ前記軸線を中心とした周方向に延びるリテーナと、を備え、
前記リテーナには、前記軸線方向に貫通し、空気が流れる空間を画定する開口が形成されている静翼の改造方法において、
前記開口の前記周方向の幅が、前記軸線方向で前記リテーナが存在する位置での前記翼体の径方向内側端における前記翼体の前記周方向の幅より広くなるよう、前記リテーナを加工する、
静翼の改造方法。 - 請求項13に記載の静翼の改造方法において、
前記加工前における前記開口の前記周方向の幅は、前記軸線方向で前記リテーナが存在する位置での前記翼体の径方向内側端における前記翼体の前記周方向の幅より狭く、
前記リテーナを加工する際には、前記リテーナを研削して前記開口を拡張する、
静翼の改造方法。
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