WO2021193628A1 - タービン翼及びこのタービン翼を製造する方法 - Google Patents
タービン翼及びこのタービン翼を製造する方法 Download PDFInfo
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- WO2021193628A1 WO2021193628A1 PCT/JP2021/011983 JP2021011983W WO2021193628A1 WO 2021193628 A1 WO2021193628 A1 WO 2021193628A1 JP 2021011983 W JP2021011983 W JP 2021011983W WO 2021193628 A1 WO2021193628 A1 WO 2021193628A1
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- Prior art keywords
- pressure surface
- cooling passage
- negative pressure
- trailing edge
- partition member
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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
- 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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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/10—Cores; Manufacture or installation of cores
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/22—Moulds for peculiarly-shaped castings
- B22C9/24—Moulds for peculiarly-shaped castings for hollow articles
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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
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—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
- 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
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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
- F01D9/06—Fluid supply conduits to nozzles or the like
- F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
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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
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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
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
- F05D2240/122—Fluid guiding means, e.g. vanes related to the trailing edge of a stator vane
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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
- F05D2240/123—Fluid guiding means, e.g. vanes related to the pressure side of a stator vane
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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
- F05D2240/124—Fluid guiding means, e.g. vanes related to the suction side of a stator vane
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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
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
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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
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade
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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
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/305—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the pressure side of a rotor blade
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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
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/306—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the suction side of a rotor blade
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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
- F05D2250/00—Geometry
- F05D2250/20—Three-dimensional
- F05D2250/23—Three-dimensional prismatic
- F05D2250/231—Three-dimensional prismatic cylindrical
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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
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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
- F05D2260/221—Improvement of heat transfer
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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
- F05D2260/221—Improvement of heat transfer
- F05D2260/2212—Improvement of heat transfer by creating turbulence
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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
- F05D2260/221—Improvement of heat transfer
- F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
Definitions
- the present disclosure relates to turbine blades and methods of manufacturing the turbine blades.
- This application claims priority based on Japanese Patent Application No. 2020-53739 filed with the Japan Patent Office on March 25, 2020, the contents of which are incorporated herein by reference.
- the turbine blade exposed to a high temperature gas flow is cooled by flowing a cooling fluid through a cooling passage formed inside the turbine blade.
- the cooling passage of a turbine blade disclosed in Patent Document 1 is branched into a cooling passage on the negative pressure surface side and a cooling passage on the pressure surface side by a partition member, and both cooling passages are on the trailing edge side of the turbine blade. It has a structure that merges to form a merge cooling passage.
- At least one embodiment of the present disclosure is intended to provide a turbine blade capable of efficient cooling and a method for manufacturing the turbine blade.
- the turbine blade according to the present disclosure includes a blade-shaped portion including a front edge and a trailing edge, and a pressure surface and a negative pressure surface extending between them, and a cooling passage is provided inside the blade-shaped portion.
- the cooling passages are a first cooling passage located closer to the pressure surface than the negative pressure surface and a second cooling passage located closer to the negative pressure surface than the pressure surface.
- One end is opened at the confluence portion formed by connecting the end portion of the first cooling passage on the trailing edge side and the end portion of the second cooling passage on the trailing edge side, and the other end is at the trailing edge.
- the first cooling passage and the second cooling passage are separated by a partition member provided inside the blade-shaped portion, and the cooling passage includes the partition member of the partition member.
- a plurality of pressure surface sides in which one end is connected to the pressure surface side wall including the pressure surface and the other end is connected to the partition member in the first cooling passage only from the end portion on the trailing edge side to the front edge side.
- a plurality of negative pressure surface side pin fins are provided, one end of which is connected to the negative pressure surface side wall including the negative pressure surface and the other end of which is connected to the partition member.
- another turbine blade includes a blade-shaped portion including a front edge and a trailing edge, and a pressure surface and a negative pressure surface extending between them, and a cooling passage is formed inside the blade-shaped portion.
- the cooling passage includes a first cooling passage located closer to the pressure surface than the negative pressure surface, a second cooling passage located closer to the negative pressure surface than the pressure surface, and the above.
- a plurality of portions having one end opened at the confluence portion formed by connecting the end portion of the first cooling passage on the trailing edge side and the end portion of the second cooling passage on the trailing edge side and the other end opening at the trailing edge.
- the first cooling passage and the second cooling passage are separated by a partition member provided inside the airfoil portion, and the thickness of the side wall of the negative pressure surface including the negative pressure surface is determined.
- the front edge side of the partition member is larger than the front edge side end of the partition member, as compared to the trailing edge side of the partition member.
- the method for manufacturing a turbine blade according to the present disclosure includes a blade-shaped portion including a front edge and a trailing edge, and a pressure surface and a negative pressure surface extending between them, and a cooling passage is formed inside the blade-shaped portion.
- the cooling passages are a first cooling passage located closer to the pressure surface than the negative pressure surface and a first cooling passage located closer to the negative pressure surface than the pressure surface.
- One end is opened at the confluence portion formed by connecting the two cooling passages, the end portion of the first cooling passage on the trailing edge side, and the end portion of the second cooling passage on the trailing edge side, and at the trailing edge.
- the first cooling passage and the second cooling passage are separated by a partition member provided inside the airfoil portion, and the cooling passage includes the plurality of outflow passages whose other ends are open.
- the first cooling passage one end is connected to the side wall of the pressure surface including the pressure surface and the other end is connected to the partition member only on the front edge side of the partition member on the trailing edge side.
- a plurality of negative pressure surface side pin fins are provided, one end of which is connected to the negative pressure surface side wall including the negative pressure surface and the other end of which is connected to the partition member.
- the method includes a manufacturing step of manufacturing the turbine blade, and a processing step of processing the plurality of outflow passages with respect to the airfoil portion after the manufacturing step.
- the cooling passage is provided with pressure surface side pin fins and negative pressure surface side pin fins only from the trailing edge side end to the front edge side of the partition member, and the confluence and outflow passages are provided with pin fins. Therefore, when the outflow passage is processed for the airfoil portion after the airfoil portion is manufactured, the risk of damaging the pin fins can be reduced.
- Such pin fins improve the cooling capacity of turbine blades by disturbing the flow of cooling fluid in the cooling passage, but if the risk of damaging the pin fins is reduced, the cooling efficiency of turbine blades may be adversely affected. Since it is reduced, efficient cooling of turbine blades is possible.
- the pressure inside the airfoil is higher than the pressure outside the airfoil on the negative pressure surface side, pressure is applied to the side wall of the airfoil in the direction of expansion.
- the strength of the side wall of the negative pressure surface can be increased, and such a pressure can be withstood.
- the cooling capacity can be easily adjusted by adjusting the inner diameter of the outflow passage, so that the degree of freedom in designing the turbine blade can be increased.
- FIG. 1 It is a schematic block diagram of the gas turbine which used the turbine blade which concerns on one Embodiment of this disclosure. It is a figure which looked at the turbine blade which concerns on one Embodiment of this disclosure in the direction from a pressure plane toward a negative pressure plane. It is sectional drawing along the line III-III of FIG. It is sectional drawing which shows an example of the arrangement of the pressure surface side pin fin and the negative pressure surface side pin fin in the turbine blade which concerns on one Embodiment of this disclosure. It is sectional drawing of the turbine blade which concerns on one Embodiment of this disclosure, and the core used when manufacturing this turbine blade. It is the schematic of each step of the method of manufacturing the turbine blade which concerns on one Embodiment of this disclosure. It is an enlarged sectional view of a part inside the airfoil of a turbine blade which concerns on one Embodiment of this disclosure.
- the gas turbine 1 is rotationally driven by a compressor 2 for generating compressed air, a combustor 4 for generating combustion gas using compressed air and fuel, and a combustion gas. It is provided with a turbine 6 configured to be such. In the case of the gas turbine 1 for power generation, a generator (not shown) is connected to the turbine 6.
- the compressor 2 includes a plurality of stationary blades 16 fixed to the compressor cabin 10 side and a plurality of moving blades 18 attached to the rotor 8. Air taken in from the air intake 12 is sent to the compressor 2, and this air passes through a plurality of stationary blades 16 and a plurality of moving blades 18 and is compressed to achieve high temperature and high pressure. It becomes compressed air.
- the turbine 6 has a combustion gas flow path 28 formed in the turbine casing 22, and includes a plurality of stationary blades 24 and moving blades 26 provided in the combustion gas flow path 28.
- the stationary blades 24 are fixed to the turbine casing 22 side, and a plurality of stationary blades 24 arranged along the circumferential direction of the rotor 8 form a stationary blade row.
- the moving blades 26 are attached to the rotor 8, and a plurality of moving blades 26 arranged along the circumferential direction of the rotor 8 form a moving blade row.
- the stationary blade rows and the moving blade rows are arranged alternately in the axial direction of the rotor 8.
- the turbine blades of the present disclosure include both the moving blades 26 and the stationary blades 24 of the turbine 6.
- the turbine blade according to the embodiment of the present disclosure will be described as a stationary blade 24, but the moving blade 26 may be used.
- the stationary blade 24 includes an airfoil portion 34, and the airfoil portion 34 extends in the airfoil height direction (span direction), and outer shrouds provided at both ends in the airfoil height direction. It has 38 and an inner shroud 40.
- the airfoil portion 34 has a leading edge 42 and a trailing edge 44 extending along the blade height direction, and has a pressure surface 46 and a negative pressure surface 48 extending between the leading edge 42 and the trailing edge 44.
- a cooling passage 50 through which a cooling fluid (for example, air) for cooling the stationary blade 24 flows is formed inside the airfoil portion 34.
- a partition member 51 is provided inside the airfoil portion 34, that is, in the cooling passage 50, and a part of the cooling passage 50 is separated into a first cooling passage 52 and a second cooling passage 53.
- the first cooling passage 52 is located closer to the pressure surface 46 than the negative pressure surface 48
- the second cooling passage 53 is located closer to the negative pressure surface 48 than the pressure surface 46.
- the ends of the first cooling passage 52 and the second cooling passage 53 on the trailing edge 44 side are connected to each other to form a merging portion 54.
- the cooling passage 50 further includes a plurality of outflow passages 55, one end of which opens into the confluence 54 and the other end of which opens into the trailing edge 44.
- the outflow passage 55 may be a passage having an arbitrary cross-sectional shape such as a circle or a rectangle, or may be in the form of a slit.
- the first cooling passage 52 is provided with a plurality of pressure surface side pin fins 61 having one end connected to the pressure surface side wall 47 including the pressure surface 46 and the other end connected to the partition member 51.
- the second cooling passage 53 is provided with a plurality of negative pressure surface side pin fins 62 having one end connected to the negative pressure surface side wall 49 including the negative pressure surface 48 and the other end connected to the partition member 51. Such pin fins are not provided in the confluence 54 and the outflow passage 55.
- the end portion 51a on the trailing edge 44 side of the partition member 51 is located on the trailing edge 44 side of the pressure surface side pin fins 61.
- the most downstream pressure surface side pin fin 61a and the plurality of negative pressure surface side pin fins 62 located on the trailing edge 44 side of any of the most downstream negative pressure surface side pin fins 62a, or the most downstream pressure. It is flush with the side surface of the surface side pin fin 61a and the most downstream negative pressure surface side pin fin 62a, whichever is closer to the trailing edge 44 (both in the same case).
- the outflow passage 55 is a plurality of passages having a small inner diameter, that is, a so-called multi-hole, after casting the stationary blade 24, a machine is used from the trailing edge 44 to the merging portion 54.
- the outflow passage 55 may be formed by processing or the like. In such a case, in the stationary blade 24, since the pin fins are not provided in the merging portion 54 and the outflow passage 55, the possibility of damaging the pin fins when forming the outflow passage 55 can be reduced.
- Such pin fins improve the cooling efficiency of the vane 24 by disturbing the flow of the cooling fluid in the cooling passage 50, but may damage the pin fins. If it is reduced, the possibility of adversely affecting the cooling efficiency of the stationary blade 24 is reduced, so that the stationary blade 24 can be efficiently cooled.
- the merging portion 54 and the outflow passage 55 are not provided with pin fins, that is, the pressure surface side pin fins 61 and the negative pressure surface side only from the end portion 51a on the trailing edge 44 side of the partition member 51 to the leading edge 42 (see FIG. 2). If the pin fins 62 are provided, the following further restrictions can be added to the arrangement of the pressure surface side pin fins 61 and the negative pressure surface side pin fins 62. Next, some such limitations and the effects obtained from the limitations will be described.
- each of the plurality of pressure surface side pin fins 61 and one of the plurality of negative pressure surface side pin fins 62 can coincide with each other's center lines L1 and L2. With such an arrangement, it is possible to obtain an action effect in manufacturing the stationary blade 24. The effects of such actions will be described below.
- a core 70 in which the hollow portion of the stationary blade 24 is solid is usually required as shown in FIG. It becomes. Since the stationary blade 24 and the core 70 have a shape in which the hollow portion and the solid portion are inverted, the portions of the pressure surface side pin fin 61 and the negative pressure surface side pin fin 62 in the stationary blade 24 are hollow portions in the core 70. It becomes 71,72. In FIG. 5, the solid portion is hatched, and the hollow portion is outlined.
- each of the plurality of cavity portions 71 corresponding to the plurality of pressure surface side pin fins 61 and any of the plurality of cavity portions 72 corresponding to the portions of the plurality of negative pressure surface side pin fins 62 are centered on each other L1. ', L2' will match. Then, when the core 70 is inspected after manufacturing, if light is irradiated from one of the cavity portions 71 and 72 having the same center line, the light can be confirmed from the other cavity portion if there is no problem in each of the cavity portions 71 and 72. On the contrary, if there is a blockage in each of the cavity portions 71 and 72, light cannot be confirmed from the other cavity portion. Therefore, the inspection workability of the core 70 after manufacturing can be improved.
- the trailing edge 44 before the side edge 42 (see FIG. 2) toward the side, adjacent with the pitch P 2 between the pressure surface side pin fin 61 adjacent constant negative pressure surface between the side pin fins 62, 62 pitch P 2 'of the can to be constant.
- this form may be combined with the above-mentioned form in which the center lines L1 and L2 coincide with each other, or the center lines L1 and L2 may not coincide with each other.
- the cooling fluid flowing through each of the first cooling passage 52 and the second cooling passage 53 is disturbed by the pressure surface side pin fins 61 and the negative pressure surface side pin fins 62, so that the cooling efficiency of the stationary blade 24 can be improved. While the cooling fluid flows between adjacent pin fins, the turbulence of the cooling fluid flow subsides, and the flow is disturbed again by the next pin fin. Therefore, if the pitches between the adjacent pin fins are different, the cooling efficiency is partially poor or good, and the metal temperature distribution becomes non-uniform. On the other hand, if the pin fins are provided at an appropriate and constant pitch, it is possible to reduce the possibility that the cooling efficiency is partially poor or good.
- the center line L1 of each of the plurality of pressure surface side pin fins 61 and the center line L2 of any one of the plurality of negative pressure surface side pin fins 62 coincide with each other and are adjacent to each other.
- P 2 P 2 at a constant' a
- the end portion 51a and the most downstream pressure face of the partition member 51 Assuming that the pitch between the side pin fin 61a and the center line of the most downstream negative pressure surface side pin fin 62a is P 1 , 0.5P 2 ⁇ P 1 ⁇ 2P 2 may be set.
- the risk of damaging the pin fins is further reduced, so that the risk of adversely affecting the cooling efficiency of the stationary blade 24 can be further reduced, and the stationary blade 24 can be cooled more efficiently.
- the arrangement of the pressure surface side pin fin 61 and the negative pressure surface side pin fin 62 may be different.
- the outer diameter of the pressure surface side pin fin 61 and the outer diameter of the negative pressure surface side pin fin 62 may be different from each other, or from the trailing edge 44 (see FIG. 3) side toward the leading edge 42 (see FIG. 2).
- the pitch P 2 between the pressure surface side pin fin 61 adjacent, or made different from the pitch P 2 'between the negative adjacent pressure side pin fins 62 and 62 may be or adopting both of these features . According to such a configuration, when the required cooling load is different between the negative pressure surface 48 side and the pressure surface 46 side, it is possible to cope with each cooling load.
- the blade When the required cooling load is different between the negative pressure surface 48 side and the pressure surface 46 side, it is possible to deal with each cooling load other than the arrangement of the pressure surface side pin fin 61 and the negative pressure surface side pin fin 62.
- the blade when the cooling load on the pressure surface 46 side is larger than that on the negative pressure surface 48 side, the blade has a film hole 30 at which one end opens in the cooling passage 50 and the other end opens in the pressure surface 46. It can be provided on the shape portion 34.
- the opening 30b that opens into the cooling passage 50 of the film hole 30 is located on the front edge 42 side of the end portion 51b on the front edge 42 (see FIG. 2) side of the partition member 51, and is located on the pressure surface of the film hole 30.
- the opening 30a that opens to 46 is located on the trailing edge 44 side of the opening 30b.
- the thickness of the negative pressure surface side wall 49 is such that the end portion of the partition member 51 is larger than the end portion 51b on the leading edge 42 (see FIG. 2) side of the partition member 51 as compared with the trailing edge 44 side.
- the leading edge 42 side may be larger than 51b. That is, a transition region 49a, which is a region where the thickness of the negative pressure surface side wall 49 increases in the direction from the trailing edge 44 to the leading edge 42, is provided slightly on the leading edge 42 side of the end portion 51b of the partition member 51. May be good.
- the pressure inside the airfoil portion 34 is higher than the pressure outside the airfoil portion 34 on the negative pressure surface 48 side, so that pressure is applied to the side wall 49 of the negative pressure surface in the direction of expansion.
- the strength of the negative pressure surface side wall 49 can be increased, and it becomes possible to withstand such pressure.
- FIG. 6 is a schematic view of each step of the method for manufacturing the stationary blade 24.
- step (1) the ceramic material is injected into the space 84 defined by the two molds 81 and 82 via the supply path 83 to prepare the core precursor 85.
- step (2) the core precursor 85 is fired to prepare the core 70.
- step (3) the stationary blade 24 is cast by inserting the core 70 into the internal space 91 of the mold 90 and injecting a metal material into the internal space 91.
- the portion corresponding to the core 70 becomes a hollow portion such as the cooling passage 50 (see FIG. 3).
- step (4) the vane 24 is removed from the mold 90 and the core 70 is removed from the vane 24.
- step (5) a plurality of outflow passages 55 are formed from the trailing edge 44 to the merging portion 54 by machining or the like.
- steps (1) to (4) can be said to be production steps for producing the airfoil portion 34
- step (5) provides a plurality of outflow passages 55 with respect to the airfoil portion 34. It can be said that it is a processing step to process. If the stationary blade 24 is manufactured by a method including such a step, the cooling capacity of the stationary blade 24 can be easily adjusted by adjusting the inner diameter of the outflow passage 55, so that the design of the stationary blade 24 is free. The degree can be increased.
- the merging portion 54 is defined by an end portion 51a of the partition member 51 and a passage inner surface 54a facing the end portion 51a, and the end portion 51a of the partition member 51 and the passage inner surface 54a. It is preferable that each has a rounded shape (curved surface).
- the core used when casting a product having a hollow part inside has a form in which the solid part and the hollow part in the product are inverted. Therefore, the core 70 (see FIG. 6) used when casting the stationary blade 24 includes a solid portion having a shape corresponding to the confluence portion 54, which is a hollow portion in the stationary blade 24. If the end portion 51a of the partition member 51 is sharp, there may be a problem in the injection property of the metal material into the mold at the time of casting. On the other hand, if the inner surface 54a of the passage is sharp, there may be a problem in the injection property of the raw material of the core into the mold at the time of manufacturing the core 70.
- the merging portion 54 has the above configuration, all of the shapes are rounded, so that it is possible to avoid deterioration of the injectability of the metal material and the raw material of the core at the time of casting and at the time of manufacturing the core.
- the turbine blade is An airfoil portion (34) including a leading edge (42) and a trailing edge (44) and a pressure surface (46) and a negative pressure surface (48) extending between them is provided, and inside the airfoil portion (34).
- Turbine blades static blades 24, moving blades 26 on which a cooling passage (50) is formed.
- the cooling passage (50) is A first cooling passage (52) located closer to the pressure surface (46) than the negative pressure surface (48).
- a second cooling passage (53) located closer to the negative pressure surface (48) than the pressure surface (46).
- 54) includes a plurality of outflow passages (55) having one end open and the trailing edge (44) having the other end open.
- the first cooling passage (52) and the second cooling passage (53) are separated by a partition member (51) provided inside the airfoil portion (34). In the cooling passage (50), only from the end portion (51a) on the trailing edge (44) side of the partition member (51) to the leading edge (44) side.
- a plurality of pressure surface side pin fins having one end connected to the pressure surface side wall (47) including the pressure surface (46) and the other end connected to the partition member (51). (61) and in the second cooling passage (53), a plurality of negative pressure surface side pin fins having one end connected to the negative pressure surface side wall (49) including the negative pressure surface (48) and the other end connected to the partition member (51). (62) is provided.
- the cooling passage is provided with pressure surface side pin fins and negative pressure surface side pin fins only from the trailing edge side end to the front edge side of the partition member, and the confluence and outflow passages are provided with pin fins. Therefore, when the outflow passage is processed for the airfoil portion after the airfoil portion is manufactured, the risk of damaging the pin fins can be reduced.
- Such pin fins improve the cooling capacity of turbine blades by disturbing the flow of cooling fluid in the cooling passage, but if the risk of damaging the pin fins is reduced, the cooling efficiency of turbine blades may be adversely affected. Since it is reduced, efficient cooling of turbine blades is possible.
- the turbine blade according to another aspect is the turbine blade of [1].
- Each of the plurality of pressure surface side pin fins (61) and one of the plurality of negative pressure surface side pin fins (62) coincide with each other's center lines (L1, L2).
- each of the plurality of cavity portions corresponding to the plurality of pressure surface side pin fins and one of the plurality of cavity portions corresponding to the plurality of negative pressure surface side pin fin portions are The centerlines of each other will match.
- the inspection workability after manufacturing the core can be improved.
- the turbine blade according to still another aspect is the turbine blade of [1] or [2]. From the trailing edge (44) side to the leading edge (42) side, the pitch (P 2 ) between the adjacent pressure surface side pin fins (61, 61) is constant and the adjacent negative pressure surface side pin fins (62). , 62) The pitch (P 2 ') is constant.
- each cooling passage The cooling fluid flowing through each cooling passage is disturbed by the pin fins to improve the cooling efficiency of the turbine blades.
- the cooling fluid flows between the pin fins adjacent to each other in the direction in which the cooling fluid flows, the cooling fluid flows.
- the turbulence of the flow is settled, and the flow is disturbed again by the next pin fin. Therefore, if the pitches between the adjacent pin fins are different, the cooling efficiency is partially poor or good, and the metal temperature distribution becomes non-uniform.
- the pin fins are provided at an appropriate and constant pitch, it is possible to reduce the possibility that the cooling efficiency is partially poor or good.
- the turbine blade according to still another aspect is the turbine blade according to any one of [1] to [3].
- the end portion (51a) on the trailing edge (44) side of the partition member (51) is the most downstream pressure surface located on the trailing edge (44) side of the plurality of pressure surface side pin fins (61).
- the risk of damaging the pin fins is further reduced, so that the risk of adversely affecting the cooling efficiency of the turbine blades can be further reduced, and more efficient cooling of the turbine blades becomes possible.
- the turbine blade according to still another aspect is the turbine blade of [4].
- Each of the plurality of pressure surface side pin fins (61) and one of the plurality of negative pressure surface side pin fins (62) coincide with each other's center lines (L1, L2). From the trailing edge (44) side to the leading edge (42) side, the pitch (P 2 ) between the adjacent pressure surface side pin fins (61, 61) is constant, and the adjacent negative pressure surface side pin fins (62). , 62) The pitch (P 2 ') is constant, and both pitches are the same.
- the risk of damaging the pin fins is further reduced as compared with the configuration of the above [4], so that the risk of adversely affecting the cooling efficiency of the turbine blades can be further reduced, and more efficient cooling can be achieved. It will be possible.
- the turbine blade according to still another aspect is the turbine blade of [1].
- the outer diameter of the pressure surface side pin fin (61) and the outer diameter of the negative pressure surface side pin fin (62) are different from each other, or From the trailing edge (44) side to the leading edge (42) side, the pitch (P 2 ) between the adjacent pressure surface side pin fins (61, 61) and the adjacent negative pressure surface side pin fins (62, 62). The pitch between them (P 2 ') is different.
- the turbine blade according to still another aspect is the turbine blade according to any one of [1] to [6].
- the merging portion (54) is defined by the end portion (51a) on the trailing edge (44) side of the partition member (51) and the passage inner surface (54a) facing the end portion (51a).
- the end portion (51a) on the trailing edge (44) side of the partition member (51) and the passage inner surface (54a) each have a rounded shape.
- the turbine blade according to still another aspect is the turbine blade according to any one of [1] to [7].
- the thickness of the negative pressure surface side wall (49) is larger than that of the end portion (51b) of the partition member (51) on the leading edge (42) side as compared with the trailing edge (44) side of the partition member (51). ) Is larger on the leading edge (42) side than the end (51b) on the leading edge (42) side.
- the turbine blade according to one aspect is An airfoil portion (34) including a leading edge (42) and a trailing edge (44) and a pressure surface (46) and a negative pressure surface (48) extending between them is provided, and inside the airfoil portion (34).
- Turbine blades (static blades 24, moving blades 26) on which a cooling passage (50) is formed.
- the cooling passage (50) is A first cooling passage (52) located closer to the pressure surface (46) than the negative pressure surface (48).
- a second cooling passage (53) located closer to the negative pressure surface (48) than the pressure surface (46).
- 54) includes a plurality of outflow passages (55) having one end open and the trailing edge (44) having the other end open.
- the first cooling passage (52) and the second cooling passage (53) are separated by a partition member (51) provided inside the airfoil portion (34).
- the thickness of the negative pressure surface side wall (49) including the negative pressure surface (48) is larger than that of the end portion (51b) of the partition member (51) on the front edge (42) side as compared with the trailing edge (44) side.
- the front edge (42) side of the partition member (51) is larger than the end portion (51b) of the partition member (51) on the front edge (42) side.
- the pressure inside the airfoil is higher than the pressure outside the airfoil on the negative pressure surface side, pressure is applied to the side wall of the airfoil in the direction of expansion.
- the strength of the side wall of the negative pressure surface can be increased, and it becomes possible to withstand such pressure.
- the turbine blade according to still another aspect is the turbine blade according to any one of [1] to [9].
- a film hole (30) having one end opened in the cooling passage (50) and the other end opening in the pressure surface (46) is provided in the airfoil portion.
- the opening (30b) of the film hole (30) that opens into the cooling passage (50) is the leading edge (42) of the partition member (51) rather than the leading edge (42) side end (51b). ) Side.
- the cooling fluid is supplied to the pressure surface through the film holes to directly lower the temperature of the high-temperature gas flowing along the pressure surface for the first cooling.
- the cooling load of the cooling fluid flowing through the passage can be reduced. As a result, it is possible to eliminate the need to provide an additional configuration in the first cooling passage in order to improve the cooling load of the cooling fluid flowing through the first cooling passage.
- the method for manufacturing a turbine blade is An airfoil portion (34) including a leading edge (42) and a trailing edge (44) and a pressure surface (46) and a negative pressure surface (48) extending between them is provided, and inside the airfoil portion (34). It is a method of manufacturing a turbine blade (static blade 24, moving blade 26) in which a cooling passage (50) is formed.
- the cooling passage (50) is A first cooling passage (52) located closer to the pressure surface (46) than the negative pressure surface (48).
- a second cooling passage (53) located closer to the negative pressure surface (48) than the pressure surface (46).
- 54) includes a plurality of outflow passages (55) having one end open and the trailing edge (44) having the other end open.
- the first cooling passage (52) and the second cooling passage (53) are separated by a partition member (51) provided inside the airfoil portion (34).
- the cooling passage (50) is provided only on the leading edge (42) side of the partition member (51) on the trailing edge (44) side end (51a).
- a plurality of pressure surface side pin fins having one end connected to the pressure surface side wall (47) including the pressure surface (46) and the other end connected to the partition member (51).
- a plurality of negative pressure surface side pin fins having one end connected to the negative pressure surface side wall (49) including the negative pressure surface (48) and the other end connected to the partition member (51).
- the method is A manufacturing step for manufacturing the turbine blades (24, 26) and After the manufacturing step, a processing step of processing the plurality of outflow passages (55) with respect to the airfoil portion (34) is included.
- the cooling capacity can be easily adjusted by adjusting the inner diameter of the outflow passage, so that the degree of freedom in designing the turbine blade can be increased.
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Abstract
Description
本願は、2020年3月25日に日本国特許庁に出願された特願2020-53739号に基づき優先権を主張し、その内容をここに援用する。
図1に示されるように、ガスタービン1は、圧縮空気を生成するための圧縮機2と、圧縮空気及び燃料を用いて燃焼ガスを発生させるための燃焼器4と、燃焼ガスによって回転駆動されるように構成されたタービン6とを備えている。発電用のガスタービン1の場合、タービン6には不図示の発電機が連結されている。
本開示のタービン翼は、タービン6の動翼26及び静翼24のいずれも対象としている。以下では、本開示の一実施形態に係るタービン翼を静翼24として説明するが、動翼26であってもよい。
次に、静翼24を製造する方法を図6に基づいて説明する。図6は、静翼24を製造する方法の各ステップの概略図である。ステップ(1)において、2つの型81,82によって画定された空間84内に、供給経路83を介してセラミックス材料を注入し、コア前駆体85を作製する。ステップ(2)において、コア前駆体85を焼成して、コア70を作製する。ステップ(3)において、鋳型90の内部空間91内にコア70を入れ、内部空間91内に金属材料を注入することにより、静翼24が鋳造される。静翼24において、コア70に相当する部分が、冷却通路50(図3参照)のような空洞部分となる。ステップ(4)において、静翼24を鋳型90から取り出し、コア70を静翼24から取り除く。ステップ(5)において、後縁44から合流部54まで機械加工等で複数の流出通路55を形成する。
前縁(42)と後縁(44)とこれらの間を延びる圧力面(46)及び負圧面(48)とを含む翼形部(34)を備え、該翼形部(34)の内部に冷却通路(50)が形成されたタービン翼(静翼24,動翼26)であって、
前記冷却通路(50)は、
前記負圧面(48)よりも前記圧力面(46)に近い位置にある第1冷却通路(52)と、
前記圧力面(46)よりも前記負圧面(48)に近い位置にある第2冷却通路(53)と、
前記第1冷却通路(52)の前記後縁(44)側の端部と前記第2冷却通路(53)の前記後縁(44)側の端部とが接続されて構成された合流部(54)に一端が開口するとともに前記後縁(44)に他端が開口する複数の流出通路(55)と
を含み、
前記第1冷却通路(52)と前記第2冷却通路(53)とは、前記翼形部(34)の内部に設けられた仕切部材(51)によって分離され、
前記冷却通路(50)には、前記仕切部材(51)の前記後縁(44)側の端部(51a)から前記前縁(44)側にのみ、
前記第1冷却通路(52)において、前記圧力面(46)を含む圧力面側壁(47)に一端が接続されるとともに前記仕切部材(51)に他端が接続される複数の圧力面側ピンフィン(61)と、
前記第2冷却通路(53)において、前記負圧面(48)を含む負圧面側壁(49)に一端が接続されるとともに前記仕切部材(51)に他端が接続される複数の負圧面側ピンフィン(62)と
が設けられている。
前記複数の圧力面側ピンフィン(61)のそれぞれと、前記複数の負圧面側ピンフィン(62)のいずれかとは、互いの中心線(L1,L2)が一致する。
前記後縁(44)側から前記前縁(42)側に向かって、隣り合う圧力面側ピンフィン(61,61)間のピッチ(P2)が一定であるとともに隣り合う負圧面側ピンフィン(62,62)間のピッチ(P2’)が一定である。
前記仕切部材(51)の前記後縁(44)側の前記端部(51a)は、前記複数の圧力面側ピンフィン(61)のうち最も前記後縁(44)側に位置する最下流圧力面側ピンフィン(61a)及び前記複数の負圧面側ピンフィン(62)のうち最も前記後縁(44)側に位置する最下流負圧面側ピンフィン(62a)のいずれよりも前記後縁(44)側に位置する。
前記複数の圧力面側ピンフィン(61)のそれぞれと、前記複数の負圧面側ピンフィン(62)のいずれかとは、互いの中心線(L1,L2)が一致し、
前記後縁(44)側から前記前縁(42)側に向かって、隣り合う圧力面側ピンフィン(61,61)間のピッチ(P2)が一定であるとともに隣り合う負圧面側ピンフィン(62,62)間のピッチ(P2’)が一定であり、かつ、両ピッチは同じであり、
前記仕切部材(51)の前記後縁(44)側の前記端部(51a)と前記最下流圧力面側ピンフィン(61a)及び前記最下流負圧面側ピンフィン(62a)の中心線(L1,L2)とのピッチをP1とし、前記隣り合う圧力面側ピンフィン(61,61)間のピッチ及び前記隣り合う負圧面側ピンフィン(62,62)のピッチをP2とすると、0.5P2<P1<2P2である。
前記圧力面側ピンフィン(61)の外径と、前記負圧面側ピンフィン(62)の外径とが互いに異なるか、又は、
前記後縁(44)側から前記前縁(42)側に向かって、隣り合う圧力面側ピンフィン(61,61)間のピッチ(P2)と、隣り合う負圧面側ピンフィン(62,62)間のピッチ(P2’)とが異なる。
前記合流部(54)は、前記仕切部材(51)の前記後縁(44)側の前記端部(51a)と、該端部(51a)に対向する通路内面(54a)とによって画定され、
前記仕切部材(51)の前記後縁(44)側の前記端部(51a)と前記通路内面(54a)とはそれぞれ、丸みを帯びた形状を有する。
前記負圧面側壁(49)の厚さは、前記仕切部材(51)の前記前縁(42)側の端部(51b)よりも前記後縁(44)側に比べて、前記仕切部材(51)の前記前縁(42)側の端部(51b)よりも前記前縁(42)側の方が大きい。
前縁(42)と後縁(44)とこれらの間を延びる圧力面(46)及び負圧面(48)とを含む翼形部(34)を備え、該翼形部(34)の内部に冷却通路(50)が形成されたタービン翼(静翼24,動翼26)であって、
前記冷却通路(50)は、
前記負圧面(48)よりも前記圧力面(46)に近い位置にある第1冷却通路(52)と、
前記圧力面(46)よりも前記負圧面(48)に近い位置にある第2冷却通路(53)と、
前記第1冷却通路(52)の前記後縁(44)側の端部と前記第2冷却通路(53)の前記後縁(44)側の端部とが接続されて構成された合流部(54)に一端が開口するとともに前記後縁(44)に他端が開口する複数の流出通路(55)と
を含み、
前記第1冷却通路(52)と前記第2冷却通路(53)とは、前記翼形部(34)の内部に設けられた仕切部材(51)によって分離され、
前記負圧面(48)を含む負圧面側壁(49)の厚さは、前記仕切部材(51)の前記前縁(42)側の端部(51b)よりも前記後縁(44)側に比べて、前記仕切部材(51)の前記前縁(42)側の端部(51b)よりも前記前縁(42)側の方が大きい。
一端が前記冷却通路(50)に開口するとともに他端が前記圧力面(46)に開口するフィルム孔(30)が前記翼形部に設けられ、
前記フィルム孔(30)の前記冷却通路(50)に開口する開口部(30b)は、前記仕切部材(51)の前記前縁(42)側の端部(51b)よりも前記前縁(42)側に位置する。
前縁(42)と後縁(44)とこれらの間を延びる圧力面(46)及び負圧面(48)とを含む翼形部(34)を備え、該翼形部(34)の内部に冷却通路(50)が形成されたタービン翼(静翼24,動翼26)を製造する方法であって、
前記冷却通路(50)は、
前記負圧面(48)よりも前記圧力面(46)に近い位置にある第1冷却通路(52)と、
前記圧力面(46)よりも前記負圧面(48)に近い位置にある第2冷却通路(53)と、
前記第1冷却通路(52)の前記後縁(44)側の端部と前記第2冷却通路(53)の前記後縁(44)側の端部とが接続されて構成された合流部(54)に一端が開口するとともに前記後縁(44)に他端が開口する複数の流出通路(55)と
を含み、
前記第1冷却通路(52)と前記第2冷却通路(53)とは、前記翼形部(34)の内部に設けられた仕切部材(51)によって分離され、
前記冷却通路(50)には、前記仕切部材(51)の前記後縁(44)側の端部(51a)よりも前記前縁(42)側にのみ、
前記第1冷却通路(52)において、前記圧力面(46)を含む圧力面側壁(47)に一端が接続されるとともに前記仕切部材(51)に他端が接続される複数の圧力面側ピンフィン(61)と、
前記第2冷却通路(53)において、前記負圧面(48)を含む負圧面側壁(49)に一端が接続されるとともに前記仕切部材(51)に他端が接続される複数の負圧面側ピンフィン(62)と
が設けられ、
前記方法は、
前記タービン翼(24,26)を作製する作製ステップと、
前記作製ステップの後に、前記翼形部(34)に対して前記複数の流出通路(55)を加工する加工ステップと
を含む。
26 動翼(タービン翼)
30 フィルム孔
30b (フィルム孔の)開口部
34 翼形部
42 前縁
44 後縁
46 圧力面
47 圧力面側壁
48 負圧面
49 負圧面側壁
50 冷却通路
51 仕切部材
51a (仕切部材の後縁側の)端部
51b (仕切部材の前縁側の)端部
52 第1冷却通路
53 第2冷却通路
54 合流部
54a (合流部の)通路内面
55 流出通路
61 圧力面側ピンフィン
61a 最下流圧力面側ピンフィン
62 負圧面側ピンフィン
62a 最下流負圧面側ピンフィン
L1 (圧力面側ピンフィンの)中心線
L2 (負圧面側ピンフィンの)中心線
Claims (11)
- 前縁と後縁とこれらの間を延びる圧力面及び負圧面とを含む翼形部を備え、該翼形部の内部に冷却通路が形成されたタービン翼であって、
前記冷却通路は、
前記負圧面よりも前記圧力面に近い位置にある第1冷却通路と、
前記圧力面よりも前記負圧面に近い位置にある第2冷却通路と、
前記第1冷却通路の前記後縁側の端部と前記第2冷却通路の前記後縁側の端部とが接続されて構成された合流部に一端が開口するとともに前記後縁に他端が開口する複数の流出通路と
を含み、
前記第1冷却通路と前記第2冷却通路とは、前記翼形部の内部に設けられた仕切部材によって分離され、
前記冷却通路には、前記仕切部材の前記後縁側の端部から前記前縁側にのみ、
前記第1冷却通路において、前記圧力面を含む圧力面側壁に一端が接続されるとともに前記仕切部材に他端が接続される複数の圧力面側ピンフィンと、
前記第2冷却通路において、前記負圧面を含む負圧面側壁に一端が接続されるとともに前記仕切部材に他端が接続される複数の負圧面側ピンフィンと
が設けられているタービン翼。 - 前記複数の圧力面側ピンフィンのそれぞれと、前記複数の負圧面側ピンフィンのいずれかとは、互いの中心線が一致する、請求項1に記載のタービン翼。
- 前記後縁側から前記前縁側に向かって、隣り合う圧力面側ピンフィン間のピッチが一定であるとともに隣り合う負圧面側ピンフィン間のピッチが一定である、請求項1または2に記載のタービン翼。
- 前記仕切部材の前記後縁側の前記端部は、前記複数の圧力面側ピンフィンのうち最も前記後縁側に位置する最下流圧力面側ピンフィン及び前記複数の負圧面側ピンフィンのうち最も前記後縁側に位置する最下流負圧面側ピンフィンのいずれよりも前記後縁側に位置する、請求項1~3のいずれか一項に記載のタービン翼。
- 前記複数の圧力面側ピンフィンのそれぞれと、前記複数の負圧面側ピンフィンのいずれかとは、互いの中心線が一致し、
前記後縁側から前記前縁側に向かって、隣り合う圧力面側ピンフィン間のピッチが一定であるとともに隣り合う負圧面側ピンフィン間のピッチが一定であり、かつ、両ピッチは同じであり、
前記仕切部材の前記後縁側の前記端部と前記最下流圧力面側ピンフィン及び前記最下流負圧面側ピンフィンの中心線とのピッチをP1とし、前記隣り合う圧力面側ピンフィン間のピッチ及び前記隣り合う負圧面側ピンフィンのピッチをP2とすると、0.5P2<P1<2P2である、請求項4に記載のタービン翼。 - 前記圧力面側ピンフィンの外径と、前記負圧面側ピンフィンの外径とが互いに異なるか、又は、
前記後縁側から前記前縁側に向かって、隣り合う圧力面側ピンフィン間のピッチと、隣り合う負圧面側ピンフィン間のピッチとが異なる、請求項1に記載のタービン翼。 - 前記合流部は、前記仕切部材の前記後縁側の前記端部と、該端部に対向する通路内面とによって画定され、
前記仕切部材の前記後縁側の前記端部と前記通路内面とはそれぞれ、丸みを帯びた形状を有する、請求項1~6のいずれか一項に記載のタービン翼。 - 前記負圧面側壁の厚さは、前記仕切部材の前記前縁側の端部よりも前記後縁側に比べて、前記仕切部材の前記前縁側の端部よりも前記前縁側の方が大きい、請求項1~7のいずれか一項に記載のタービン翼。
- 前縁と後縁とこれらの間を延びる圧力面及び負圧面とを含む翼形部を備え、該翼形部の内部に冷却通路が形成されたタービン翼であって、
前記冷却通路は、
前記負圧面よりも前記圧力面に近い位置にある第1冷却通路と、
前記圧力面よりも前記負圧面に近い位置にある第2冷却通路と、
前記第1冷却通路の前記後縁側の端部と前記第2冷却通路の前記後縁側の端部とが接続されて構成された合流部に一端が開口するとともに前記後縁に他端が開口する複数の流出通路と
を含み、
前記第1冷却通路と前記第2冷却通路とは、前記翼形部の内部に設けられた仕切部材によって分離され、
前記負圧面を含む負圧面側壁の厚さは、前記仕切部材の前記前縁側の端部よりも前記後縁側に比べて、前記仕切部材の前記前縁側の端部よりも前記前縁側の方が大きい、タービン翼。 - 一端が前記冷却通路に開口するとともに他端が前記圧力面に開口するフィルム孔が前記翼形部に設けられ、
前記フィルム孔の前記冷却通路に開口する開口部は、前記仕切部材の前記前縁側の端部よりも前記前縁側に位置する、請求項1~9のいずれか一項に記載のタービン翼。 - 前縁と後縁とこれらの間を延びる圧力面及び負圧面とを含む翼形部を備え、該翼形部の内部に冷却通路が形成されたタービン翼を製造する方法であって、
前記冷却通路は、
前記負圧面よりも前記圧力面に近い位置にある第1冷却通路と、
前記圧力面よりも前記負圧面に近い位置にある第2冷却通路と、
前記第1冷却通路の前記後縁側の端部と前記第2冷却通路の前記後縁側の端部とが接続されて構成された合流部に一端が開口するとともに前記後縁に他端が開口する複数の流出通路と
を含み、
前記第1冷却通路と前記第2冷却通路とは、前記翼形部の内部に設けられた仕切部材によって分離され、
前記冷却通路には、前記仕切部材の前記後縁側の端部よりも前記前縁側にのみ、
前記第1冷却通路において、前記圧力面を含む圧力面側壁に一端が接続されるとともに前記仕切部材に他端が接続される複数の圧力面側ピンフィンと、
前記第2冷却通路において、前記負圧面を含む負圧面側壁に一端が接続されるとともに前記仕切部材に他端が接続される複数の負圧面側ピンフィンと
が設けられ、
前記方法は、
前記タービン翼を作製する作製ステップと、
前記作製ステップの後に、前記翼形部に対して前記複数の流出通路を加工する加工ステップと
を含む、タービン翼を製造する方法。
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