WO2019188588A1 - タービン動翼及びガスタービン - Google Patents

タービン動翼及びガスタービン Download PDF

Info

Publication number
WO2019188588A1
WO2019188588A1 PCT/JP2019/011455 JP2019011455W WO2019188588A1 WO 2019188588 A1 WO2019188588 A1 WO 2019188588A1 JP 2019011455 W JP2019011455 W JP 2019011455W WO 2019188588 A1 WO2019188588 A1 WO 2019188588A1
Authority
WO
WIPO (PCT)
Prior art keywords
cooling
side opening
wall
ventral
wing
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/JP2019/011455
Other languages
English (en)
French (fr)
Japanese (ja)
Inventor
靖夫 宮久
羽田　哲
進 若園
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Mitsubishi Power Ltd
Original Assignee
Mitsubishi Hitachi Power Systems Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Mitsubishi Hitachi Power Systems Ltd filed Critical Mitsubishi Hitachi Power Systems Ltd
Priority to DE112019000921.4T priority Critical patent/DE112019000921B4/de
Priority to CN201980019689.3A priority patent/CN111936724B/zh
Priority to US16/981,387 priority patent/US11346231B2/en
Priority to KR1020207026110A priority patent/KR102526809B1/ko
Publication of WO2019188588A1 publication Critical patent/WO2019188588A1/ja
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Images

Classifications

    • 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
    • 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
    • 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
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—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
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/185—Two-dimensional patterned serpentine-like
    • 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
    • F05D2250/29—Three-dimensional machined; miscellaneous
    • F05D2250/292—Three-dimensional machined; miscellaneous tapered
    • 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
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/314—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being inclined in relation to each other
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/232—Heat transfer, e.g. cooling characterized by the cooling medium

Definitions

  • the present disclosure relates to a turbine blade and a gas turbine.
  • a turbine rotor blade used in a gas turbine or the like since a turbine rotor blade used in a gas turbine or the like is used in high-temperature combustion gas, it has a cooling flow path for cooling inside, and the cooling air is circulated through the cooling flow path so that the blade The temperature rise of the metal is suppressed (see Patent Document 1).
  • At least one embodiment of the present invention aims to efficiently utilize the cooling capacity of a cooling fluid.
  • a turbine rotor blade includes: A turbine rotor blade including a wing body including a ventral wing wall and a back wing wall,
  • the wing body is A serpentine channel comprising a cooling channel partitioned by a partition wall connecting the ventral wing wall and the back wing wall and extending along the height direction of the wing body;
  • One end communicates with the cooling flow path through a first inlet side opening formed in the inner wall surface of the ventral wing wall or the inner wall surface of the back wing wall, and the other end is outside the ventral wing wall of the wing body.
  • a cooling hole communicating with a first outlet side opening formed on a wall surface or an outer wall surface of the back wing wall, and extending in a front edge direction from the first inlet side opening toward the first outlet side opening. 1 cooling hole.
  • the first cooling hole communicating with the cooling flow path through the first inlet opening is the flow path on the downstream side in the flow direction of the cooling fluid of the partition wall forming the cooling flow path. It is formed on the inner wall surface.
  • the cooling fluid supplied to the first cooling hole is a cooling fluid after cooling the upstream cooling channel disposed on the upstream side of the cooling channel via the partition wall.
  • the supplied cooling fluid cools the cooling channel on the downstream side of the partition wall, and then convectively cools the wing body in the vicinity of the partition wall in the process of flowing through the first cooling hole. Therefore, the cooling capacity of the cooling fluid can be efficiently used by reusing the cooling fluid.
  • the first cooling hole is One end communicates with the cooling flow path through a vent side first inlet side opening formed on the inner wall surface of the ventral wing wall, and the other end is formed on the outer wall surface of the ventral wing wall of the wing body.
  • the cooling hole communicated with the abdominal side first outlet side opening, which extends in the front edge direction from the abdominal side first inlet side opening toward the abdominal side first outlet side opening.
  • the cooling side hole communicating with the back side first outlet side opening, the back side first cooling extending in the front edge direction from the back side first inlet side opening toward the back side first outlet side opening. And at least one of the holes.
  • the blade body can be cooled at least one of the abdominal side and the back side.
  • the cooling flow path includes a rear edge side cooling flow path that communicates with the first cooling hole, and a front edge side cooling flow path that is disposed adjacent to the front edge side of the rear edge side cooling flow path,
  • the wing body is One end communicates with the leading edge side cooling channel via a second inlet side opening formed in the inner wall surface of the ventral blade wall or the inner wall surface of the back blade wall, and the other end of the outer wall of the blade body.
  • a cooling hole communicating with a second outlet side opening formed in the wall surface, the second cooling hole extending in a trailing edge direction from the second inlet side opening toward the second outlet side opening. It is out.
  • the cooling of the region in the partition wall forming the cooling flow path of the blade body that is difficult to cool is further strengthened.
  • the wing body can be cooled more effectively.
  • the second cooling hole is One end communicates with the leading edge side cooling channel via a vent side second inlet side opening formed in the inner wall surface of the ventral wing wall, and the other end communicates with the outer wall surface of the ventral wing wall of the wing body.
  • the cooling hole communicating with the formed ventral second outlet side opening, which extends in the rear edge direction from the ventral second inlet side opening toward the ventral second outlet side opening.
  • 2 cooling holes One end communicates with the front edge side cooling channel through a back second inlet side opening formed in the inner wall surface of the back wing wall, and the other end communicates with the outer wall surface of the back wing wall of the wing body.
  • the cooling hole communicating with the formed back side second outlet side opening, the back side second extending in the rear edge direction from the back side second inlet side opening toward the back side second outlet side opening And at least one of the two cooling holes.
  • the second cooling hole includes at least one of the abdominal side second cooling hole and the back side second cooling hole. Convection cooling is performed from at least one of the sides, and the blade body can be cooled more efficiently.
  • the length in the front edge-rear edge direction between the position of the first outlet side opening and the position of the second outlet side opening is the position of the first inlet side opening and the position of the second inlet side opening. Shorter than the length in the front edge-rear edge direction.
  • the length in the front edge-rear edge direction between the position of the first outlet side opening and the position of the second outlet side opening is equal to the position of the first inlet side opening and the second position. Since it is shorter than the length in the front edge-rear edge direction between the position of the opening on the inlet side, the first cooling hole and the second cooling hole arranged across the partition wall approach the outlet side opening and further approach the partition wall As a result, the cooling of the region where the partition wall is difficult to cool is further strengthened.
  • the front edge-rear edge direction between the position of the first outlet side opening and the position of the second outlet side opening The length is shorter than the thickness of the partition wall.
  • the length in the front edge-rear edge direction between the position of the first outlet side opening and the position of the second outlet side opening of the first cooling hole is shorter than the thickness of the partition wall.
  • the position of the first outlet side opening is closer to the position of the second outlet side opening. Accordingly, the first cooling hole and the second cooling hole are further brought closer to the front edge-rear edge direction, and the cooling of the region where the partition is difficult to cool is further strengthened.
  • ventral wing wall and the dorsal wing wall each include a partition joining region to which the partition is joined, At least one of the first cooling hole and the second cooling hole passes through a part of the partition wall bonding region.
  • the partition wall bonding region is a region that is not easily cooled because it is not in direct contact with the cooling channel, and it is difficult to obtain a cooling effect by the cooling fluid that flows through the cooling channel.
  • at least one of the first cooling hole and the second cooling hole passes through a part of the partition wall bonding region. It can cool with the cooling fluid which flows through at least one of the 2nd cooling hole.
  • At least one of the first outlet side opening and the second outlet side opening has the wing such that a center position exists in the partition wall junction region. It is formed on the outer wall surface of the body.
  • the wing body includes a top plate formed on the tip side, At least one of the first outlet side opening and the second outlet side opening is formed on the outer wall surface of the top plate.
  • the gap between the top plate and the casing is small, so the flow velocity of the combustion gas increases, and the blade Since the heat transfer rate to the body is improved, the heat load on the top plate is higher than that of other parts.
  • the configuration of (9) above since at least one of the first outlet side opening and the second outlet side opening is formed on the outer wall surface of the top plate, at least one of the first cooling hole and the second cooling hole is formed.
  • the top plate having a higher heat load than other parts can be effectively cooled by the passing cooling fluid.
  • the wing body includes a top plate formed on the tip side, In the connecting portion between the ventral wing wall and the top plate, an inclined surface inclined with respect to the ventral wing wall and the top plate is formed on the outer wall surface side of the wing body, At least one of the first outlet side opening and the second outlet side opening is formed on the inclined surface.
  • the cooling fluid that has passed through can cool the top plate, which has a higher thermal load than other parts, and can effectively cool the connection between the ventral wing wall and the top plate, which tend to be high in temperature.
  • the first inlet side opening and the second inlet side opening are formed at a position facing the serpentine flow path and away from the top plate on the base end side of the wing body.
  • first inlet side opening and the second inlet side opening face the serpentine flow path and are formed at positions separated from the top plate to the base end side of the wing body, the stress concentration It is possible to avoid the formation of the first inlet side opening and the second inlet side opening in a place where the occurrence of mist occurs easily.
  • the first inlet side opening has a height of the wing body at a rearmost edge side of the serpentine channel. It is formed facing the cooling channel extending along the direction.
  • the cooling channel on the upstream side of the cooling channel since the first inlet side opening is formed facing the cooling channel on the most trailing edge side in the serpentine channel, the cooling channel on the upstream side of the cooling channel. Compared with the case where the first inlet side opening is formed, the cooling fluid discharged from the first cooling hole to the outside of the blade body flows through a longer distance along the serpentine flow path, and more You can take away heat. Thus, according to the configuration of the above (12), more heat can be taken away by the cooling fluid discharged from the first cooling hole to the outside of the blade body, so that the flow rate of the cooling fluid can be suppressed, and the turbine Reduction in efficiency can be suppressed.
  • the abdominal side first inlet side opening is a base of the wing body rather than the back side first inlet side opening. It is formed on the end side.
  • the ventral first inlet side opening is formed closer to the base end side of the wing body than the back side first inlet side opening.
  • the ventral first inlet side opening can be formed at a position further away from the connection between the top plate and the ventral wing wall where stress concentration tends to occur.
  • the partition wall is a center of the partition wall that is directed from one of the ventral blade wall and the back blade wall to the other.
  • the line is inclined with respect to the camber line.
  • the combination of the first cooling hole and the second cooling hole can suppress an increase in temperature of at least one of the abdominal partition junction region and the back partition junction region.
  • the gas turbine according to at least one embodiment of the present invention includes the turbine rotor blade of any one of the above configurations (1) to (14), the blade can be efficiently utilized using the cooling capacity of the cooling fluid.
  • the body can be cooled effectively. Thereby, the flow volume of a cooling fluid can be suppressed and the fall of turbine efficiency can be suppressed.
  • the cooling capacity of the cooling fluid can be used efficiently.
  • FIG. 3 is a cross-sectional view of the turbine blade according to the embodiment, taken along the line AA in FIG. 2.
  • FIG. 2 is a view of the vicinity of a trailing edge of a turbine rotor blade according to an embodiment as viewed from the front end side of the turbine rotor blade 1 in the radial inner direction.
  • FIG. 4B is an enlarged sectional view around the partition wall in FIG. 4A. It is typical sectional drawing for demonstrating the extension state of each cooling hole in the blade body of the turbine rotor blade of one Embodiment shown to FIG.
  • FIG. 9 is a view (a cross-sectional view taken along the line BB in FIG. 8) of the vicinity of the trailing edge of a turbine blade according to another embodiment as viewed from the front end side of the turbine blade. It is typical sectional drawing for demonstrating the extension state of each cooling hole in the blade body of the turbine rotor blade of other embodiment shown in FIG.
  • an expression indicating that things such as “identical”, “equal”, and “homogeneous” are in an equal state not only represents an exactly equal state, but also has a tolerance or a difference that can provide the same function. It also represents the existing state.
  • expressions representing shapes such as quadrangular shapes and cylindrical shapes represent not only geometrically strict shapes such as quadrangular shapes and cylindrical shapes, but also irregularities and chamfers as long as the same effects can be obtained. A shape including a part or the like is also expressed.
  • the expressions “comprising”, “comprising”, “comprising”, “including”, or “having” one constituent element are not exclusive expressions for excluding the existence of the other constituent elements.
  • FIG. 1 is a schematic configuration diagram illustrating a gas turbine 100 according to an embodiment in which turbine blades according to some embodiments are used.
  • a gas turbine 100 includes a compressor 102 for generating compressed air, a combustor 104 for generating combustion gas using the compressed air and fuel, and a combustion gas. And a turbine 106 configured to be rotationally driven by the motor.
  • a power generator (not shown) is connected to the turbine 106 so that power is generated by the rotational energy of the turbine 106.
  • the compressor 102 is provided on the compressor casing 110, the inlet side of the compressor casing 110, and penetrates both the compressor casing 110 and a turbine casing 122 described later.
  • the rotor shaft 108 provided and various blades disposed in the compressor casing 110 are provided.
  • the various blades are alternately arranged in the axial direction with respect to the inlet guide vanes 114 provided on the air intake 112 side, a plurality of compressor vanes 116 fixed to the compressor casing 110 side, and the compressor vane 116.
  • the compressor 102 may include other components such as a bleed chamber (not shown).
  • the air taken in from the air intake 112 passes through the plurality of compressor stationary blades 116 and the plurality of compressor blades 118 to be compressed, thereby generating compressed air.
  • the compressed air is sent from the compressor 102 to the subsequent combustor 104.
  • the combustor 104 is disposed in a casing (combustor casing) 120. As shown in FIG. 1, a plurality of combustors 104 may be arranged in a ring shape around the rotor shaft 108 in the casing 120.
  • the combustor 104 is supplied with fuel and compressed air generated by the compressor 102, and burns the fuel to generate high-temperature and high-pressure combustion gas that is a working fluid of the turbine 106. Then, the combustion gas is sent from the combustor 104 to the subsequent turbine 106.
  • the turbine 106 includes a turbine casing (casing) 122 and various turbine blades disposed in the turbine casing 122.
  • the various turbine blades are a plurality of turbine stationary blades 124 fixed to the turbine casing 122 side, and a plurality of turbine blades implanted in the rotor shaft 108 so as to be alternately arranged in the axial direction with respect to the turbine stationary blades 124.
  • the rotor shaft 108 extends in the axial direction, and the combustion gas flows from the left side to the right side in FIG. In FIG. 1, the left side in the figure is the upstream side in the axial direction, and the right side in the figure is the downstream side in the axial direction.
  • the turbine rotor blade 1 is configured to generate a rotational driving force from high-temperature and high-pressure combustion gas flowing in the turbine casing 122 together with the turbine stationary blade 124. By transmitting this rotational driving force to the rotor shaft 108, the generator connected to the rotor shaft 108 is driven.
  • a specific configuration example of the turbine rotor blade 1 will be described later.
  • An exhaust chamber 129 is connected to the downstream side of the turbine casing 122 via an exhaust casing 128.
  • the combustion gas after driving the turbine 106 is discharged outside through the exhaust casing 128 and the exhaust chamber 129.
  • FIG. 2 is an internal cross-sectional view of the turbine rotor blade 1 according to an embodiment.
  • FIG. 3 is a cross-sectional view of the turbine blade 1 according to the embodiment taken along the line AA in FIG.
  • FIG. 4A is a view of the vicinity of the trailing edge of the turbine rotor blade 1 according to an embodiment as viewed from the tip 17a side of the turbine rotor blade 1 in the radially inward direction.
  • 4B is an enlarged cross-sectional view around the partition wall 10 in FIG. 4A.
  • the turbine rotor blade 1 is a turbine rotor blade used for the turbine 106, and includes a platform, a shank portion 2 and a wing portion (wing body) 3 on the base end 17 b side, and the wing body 3. Are exposed to high temperature and high pressure combustion gases.
  • the wing body 3 includes an abdominal wall portion (abdominal wing wall) 13 which is a pressure surface having a wing surface formed in a concave shape, and a back wall portion (back surface) which is a suction surface having a wing surface formed in a convex shape.
  • a leading edge side serpentine flow path 6 for flowing cooling air as a cooling fluid (cooling medium) between the inner wall surface 13 a of the opposed ventral wing wall 13 and the inner wall surface 14 a of the back wing wall 14 The trailing edge side serpentine flow path 7 is formed, and the serpentine flow path 5 is formed as a whole.
  • partition walls 10a, 10b, 10c, 10d, and 10e that connect the ventral blade wall 13 and the back blade wall 14 are provided inside the wing body 3, and the partition walls 10a, 10b, 10c, and 10d are provided.
  • 10e, and the cooling flow paths 4a, 4b, 4c, 4d, 4e, and 4f surrounded by the ventral blade wall 13 and the back blade wall 14 are formed.
  • Each cooling flow path 4a, 4b, 4c, 4d, 4e, 4f is a flow path extending in the radial direction of the turbine rotor blade 1, that is, orthogonal to the rotor shaft 108 and along the radial direction.
  • the wing body 3 is partition walls 10 a, 10 b, 10 c, 10 d, and 10 e that connect the ventral wing wall 13 and the back wing wall 14 and extend along the height direction of the wing body 3.
  • 10c, 10d, and 10e are divided into a plurality of cooling channels 4a, 4b, 4c, 4d, 4e, and 4f, and serpentine channel 5 (front edge side serpentine channel 6 and rear edge side serpentine channel 7) inside.
  • the front edge side serpentine flow path 6 is a cooling flow path provided on the front edge 18 side of the rear edge side serpentine flow path 7, and includes cooling flow paths 4a, 4b, and 4c.
  • the cooling channel 4a and the cooling channel 4b are connected by a turning part 4g, and the cooling channel 4b and the cooling channel 4c are connected by a turning part 4h.
  • the inlet 9c of the cooling air supply channel 9a of the leading edge side serpentine channel 6 is provided on the base end 17b side of the turbine rotor blade 1, and the cooling air outlet 6b is provided on the end of the blade body 3 on the tip 17a side. ing.
  • the rear edge side serpentine flow path 7 is a cooling flow path provided on the rear edge 19 side of the front edge side serpentine flow path 6, and includes cooling flow paths 4d, 4e, and 4f.
  • the cooling flow path 4d and the cooling flow path 4e are connected by the turning part 4i, and the cooling flow path 4e and the cooling flow path 4f are connected by the turning part 4j.
  • the inlet 9d of the cooling air supply passage 9b of the trailing edge side serpentine passage 7 is provided on the base end 17b side of the turbine rotor blade 1, and the cooling air outlet 7b is the flow of cooling air in the trailing edge side serpentine passage 7.
  • it communicates with the cooling channel 4f on the most downstream side and opens on the rear edge 19a of the rear edge 19 of the blade body 3.
  • a plurality of dam-like ribs 12 are provided to promote heat transfer to the cooling air.
  • a trailing edge cooling channel 8 that opens to the trailing edge end surface 19a of the trailing edge 19 is formed in the cooling channel 4f that is the most downstream side in the trailing edge side serpentine channel 7, and convectively cools the trailing edge region.
  • the trailing edge cooling flow path 8 is provided with a plurality of pin fins 20 for promoting heat transfer to the cooling air.
  • the trailing edge cooling channel 8 may be provided with a cooling structure in which a plurality of cooling holes are arranged instead of the pin fins 20.
  • compressed air extracted from the compressor 102 is used as the cooling air supplied to the turbine rotor blade 1.
  • the cooling air flowing in from the inlet 9c flows in order through the cooling flow paths 4a, 4b, and 4c via the supply flow path 9a, so that the tip 17a side and the base end 17b side of the wing body 3 And flows out of the turbine rotor blade 1 from the outlet 6b.
  • the cooling air flows in order in the cooling flow paths 4 a, 4 b, 4 c, so that the front edge 18 side toward the rear edge 19 side in the wing body 3, that is, It flows from the upstream side to the downstream side in the flow direction of the combustion gas.
  • the cooling air flowing in from the inlet 9d sequentially flows through the cooling flow paths 4d, 4e, and 4f through the supply flow path 9b, so that the tip 17a side and the base end 17b side of the wing body 3 A meandering flow path is formed between them and flows out of the turbine rotor blade 1 from the outlet 7b.
  • the cooling air flows in order in the cooling flow paths 4d, 4e, and 4f, so that in the wing body 3, from the leading edge 18 side toward the trailing edge 19 side, that is, It flows from the upstream side to the downstream side in the flow direction of the combustion gas.
  • the cooling channel 4f closest to the trailing edge 19 side forms the final channel of the trailing edge side serpentine channel 7, and a part of the cooling air flowing through the final channel is formed on the top plate 15 on the tip 17a side. It is discharged from the outlet 7a into the external combustion gas.
  • the other cooling air convectively cools the trailing edge region by the trailing edge cooling flow path 8 and is discharged into the combustion gas from the trailing edge end face 19a.
  • cooling flow path 4c and the cooling flow path 4d may be connected by the turning part, and the front edge side serpentine flow path 6 and the rear edge side serpentine flow path 7 may be integrated.
  • the cooling air that has flowed in from the cooling air supply passage 9a flows in order through the cooling passages 4a, 4b, 4c, 4d, 4e, and 4f, so that the blade body 3 has a distal end 17a side and a proximal end 17b side.
  • a meandering flow path is formed between them and flows out of the turbine rotor blade 1 from the outlet 7b.
  • the wing structure shown in FIG. 2 circulates cooling air through the serpentine flow path 5 to convectively cool the wing body, and film cooling holes (not shown) provided in the wing walls (ventral side wing wall 13 and back side wing wall 14). The film is cooled on the wing wall.
  • the wing body 3 has a ventral first inlet side opening 32 ⁇ / b> A (first inlet side opening) formed at one end on the inner wall surface 13 a of the ventral wing wall 13. 31A), the other end communicates with the cooling flow path 4, and the other end communicates with the ventral first outlet side opening 32B (first outlet side opening 31B) formed in the outer wall surface 13b of the ventral blade wall 13 of the blade body 3.
  • a ventral first cooling hole 32 is provided.
  • the ventral first cooling hole 32 extends from the first inlet side opening 31A (abdominal side first inlet side opening 32A) toward the first outlet side opening 31B (abdominal side first outlet side opening 32B) in the direction of the front edge 18. Stretch. In other words, along the camber line C of the wing body 3, the first outlet side opening 31B (abdominal side first outlet side opening 32B) is the leading edge than the first inlet side opening 31A (abdominal side first inlet side opening 32A).
  • a ventral side first cooling hole 32 is formed so as to be located on the 18th side. As shown in FIGS.
  • the wing body 3 has a cooling flow through a back side first inlet side opening 33 ⁇ / b> A formed at one end on the inner wall surface 14 a of the back side wing wall 14.
  • route 4 and the other end is connected to the back side 1st exit side opening 33B formed in the outer wall surface 14b of the wing
  • the back side first cooling hole 33 extends in the direction of the front edge 18 from the back side first inlet side opening 33A toward the back side first outlet side opening 33B. In other words, the back side first cooling hole 33 is formed along the camber line C of the wing body 3 such that the back side first outlet side opening 33B is positioned on the front edge 18 side of the back side first inlet side opening 33A. Has been.
  • the cooling fluid convectively cools the blade body 3, and the temperature of the cooling fluid rises.
  • the pressure of the cooling fluid decreases due to the pressure loss of the cooling fluid.
  • the cooling fluid that flows on the downstream side in the flow direction of the cooling fluid is used more efficiently by reusing the cooling fluid than the cooling fluid that flows on the upstream side.
  • the blade 3 flows through the upstream cooling flow path 4e (upstream cooling flow path 4U described later) with the partition wall 10e interposed therebetween.
  • the cooling fluid that has been convectively cooled flows into the cooling flow path 4f (the downstream cooling flow path 4D described later) adjacent to the downstream side in the flow direction of the cooling fluid in the partition wall 10e via the turning portion 4j.
  • the cooling fluid is supplied to the cooling flow path 4f with a pressure reduced due to pressure loss. Further, the cooling fluid further cools the blade wall and the like of the cooling flow path 4f in the process of flowing through the cooling flow path 4f.
  • the cooling fluid flowing through the cooling flow path 4e on the upstream side in the flow direction of the cooling fluid across the partition wall 10e is still low in temperature, high in pressure, and has sufficient cooling capacity.
  • the cooling fluid having the cooling capacity is wasted.
  • the cooling fluid supplied to the cooling channel 4f on the downstream side of the partition wall 10e further cools the cooling channel 4f.
  • the first cooling holes 31, 32, 33 are discharged into the combustion gas. Therefore, the cooling fluid flowing through the downstream cooling flow path 4f with the partition wall 10e interposed therebetween burns from the upstream cooling flow path 4e with the partition wall 10e interposed therebetween via the second cooling holes 41, 42, 43.
  • the cooling fluid Compared with the cooling fluid discharged into the gas, after cooling the downstream cooling flow path 4f, it further flows through the first cooling holes 31, 32, 33. Since the wing body 3 is convectively cooled in the process of flowing through the first cooling holes 31, 32, 33, the cooling fluid is reused and efficient cooling is performed. In particular, when the cooling flow path 4f is the final flow path closest to the trailing edge 19, the effect is greatest as compared with other upstream flow paths.
  • the cooling air flowing in from the ventral first inlet side opening 32A facing the cooling flow path 4 passes through the ventral first cooling hole 32 toward the ventral first outlet side opening 32B in the direction of the front edge 18.
  • the ventral wing body 3 in the vicinity of the partition wall 10 is convectively cooled.
  • the cooling air flowing in from the back side first inlet side opening 33A facing the cooling flow path 4 passes through the back side first cooling hole 33 toward the back side first outlet side opening 33B in the direction of the front edge 18.
  • the back side wing body 3 in the vicinity of the partition wall 10 is convectively cooled.
  • the wing body 3 can be effectively cooled by efficiently using the cooling capacity of the cooling air.
  • the gas turbine 100 since the gas turbine 100 according to some embodiments includes the turbine rotor blade 1 according to some embodiments, the blade body 3 is effectively cooled by efficiently using the cooling capacity of the cooling air. can do. Thereby, the flow volume of cooling air can be suppressed and the fall of turbine efficiency can be suppressed.
  • the wing body 3 only needs to be provided with at least one of the abdominal side first cooling hole 32 and the back side first cooling hole 33. If the wing body 3 is provided with both the ventral first cooling hole 32 and the dorsal first cooling hole 33, the wing body 3 can be efficiently cooled from both the ventral and dorsal sides.
  • the upstream cooling flow path 4U and the cooling flow path 4 located downstream of the partition wall 10 with respect to the flow of cooling air is referred to as a downstream cooling flow path 4D.
  • the cooling flow path 4e is the upstream cooling flow path 4U with respect to the partition wall 10e, but is the downstream cooling flow path 4D with respect to the partition wall 10d.
  • the upstream cooling channel 4U is disposed adjacent to the front edge 18 side with respect to the downstream cooling channel 4D.
  • the upstream side cooling channel 4U may be referred to as the leading edge side cooling channel 4U.
  • the downstream side cooling channel 4D is disposed adjacent to the rear edge 19 side with respect to the upstream side cooling channel 4U. Therefore, in the following description, the downstream side cooling channel 4D may be referred to as the trailing edge side cooling channel 4D.
  • the partition wall 10 serves as a partition wall that divides the cooling flow path 4 and forms a serpentine flow path 5 (front edge side serpentine flow path 6, rear edge side serpentine flow path 7), but is integrated with the blade walls 13 and 14 by casting. Formed with.
  • the partition wall 10 extends in the radial direction from the distal end 17a side to the proximal end 17b side except for the turning portions 4g, 4i on the distal end 17a side and the turning portions 4h, 4j on the proximal end 17b side, thereby forming each passage. .
  • FIG. 4B is used to explain the cross-sectional structure around the partition walls 10 and 10e when the wing body is viewed in the radial direction.
  • the partition wall 10 is formed so as to be smoothly inscribed in the abdominal side inner wall surface 13a and the back side inner wall surface 14a. That is, the joint portions 10A1, 10A2, 10B1, and 10B2 that form a part of the partition wall 10 and in contact with the inner wall surfaces 13a and 14a of the wing body 3 are formed with a curved shape for convenience of manufacturing. .
  • the joints 10A1, 10A2, 10B1, and 10B2 are the inner wall surfaces. Terminals in contact with 13a and 14a correspond to points P11, P12, P21 and P22.
  • the camber line C defining the central axis in the front edge-rear edge direction of the wing body 3 is a point P51 where the position on the front edge side where the camber line C intersects the partition wall is the point P52 and the position on the rear edge side is the point P52, the points P51 and P52 Is equivalent to the minimum thickness of the partition wall 10.
  • a line segment connecting two points may be expressed by combining the signs of both ends with a hyphen between them.
  • a line segment connecting the points P51 and P52 may be simply expressed as P51-P52.
  • the positions passing through the inner edges P11, P12, P21, P22 and parallel to the center line Wx of the partition wall 10 intersect the ventral wing wall 13 and the back wing wall 14 which are the outer surfaces of the wing body 3.
  • a point P13, P14, P23, P24, a region surrounded by points P11, P12, P13, P14 is called a ventral septum junction region 52, and a region surrounded by points P21, P22, P23, P24 This is referred to as a back partition wall junction region 53.
  • both the abdominal-side partition wall junction region 52 and the back-side partition wall junction region 53 are regions that are not directly in contact with the cooling flow path 4 and are therefore difficult to cool with the cooling fluid.
  • a region including the abdominal partition junction region 52 and the back partition junction region 53 is collectively referred to as a partition junction region 51.
  • the lengths of the inner edges P11 and P12 and the inner edges P21 and P22 forming the inner regions of the abdominal partition wall junction region 52 and the back side partition wall junction region 53 are the lengths in the front edge-rear edge direction of the partition wall 10, respectively. It becomes larger than the thickness (minimum thickness P51-P52).
  • the center line Wx of the partition wall 10 is formed on the midpoint of the line (boundary line P11-P12) connecting the inner edges P11 and P12 formed on the inner wall surface 13a of the ventral wing wall 13 and the inner wall surface 14a of the back wing wall 14. It is defined by a straight line connecting the midpoint of the line connecting the inner edges P21 and P22 (boundary lines P21-P22) and the midpoint of the minimum partition wall thickness P51-P52.
  • the ventral wing wall 13 and the dorsal wing wall 14 are structures connected by a partition wall 10. Accordingly, the blade walls 13 and 14 are thermally stretched by heat input from the combustion gas side.
  • the ventral partition wall junction region 52 and the back partition wall joint region which are joint portions between the blade walls 13 and 14 and the partition wall 10. No. 53 tends to generate a large thermal stress.
  • the abdominal-side partition wall bonding region 52 and the back-side partition wall bonding region 53 are not in direct contact with the cooling flow path 4, the metal temperature tends to increase due to heat input from the combustion gas side.
  • the partition wall 10 is in direct contact with the cooling flow path 4 (upstream cooling flow path 4U and downstream cooling flow path 4D) on both the upstream side and the downstream side in the cooling air flow direction. Lower. Due to the difference in temperature difference between them, the thermal stress tends to be further increased.
  • Boundary lines P11-P12, P21-P22 demarcating positions on the inner wall surfaces 13a, 14a side of the ventral partition wall junction region 52 and the back partition wall junction region 53 (lines connecting the inner edge P11 and the inner edge P12 and the inner edge P21 and the inner edge P22) ) Becomes longer, the abdominal partition junction region 52 and the back partition junction region 53 are more difficult to cool, and the thermal stress is further increased.
  • the first cooling holes 31, 32, 33 and the second cooling holes 41, 42, 43 are arranged to cool the abdominal-side partition junction region 52 and the back-side partition junction region 53. Yes. Details of the arrangement structure will be described later.
  • a structure in which the ventral partition wall junction region 52 and the back partition wall junction region 53 are cooled by only one of the first cooling holes 31, 32, 33 or the second cooling holes 41, 42, 43 is also assumed.
  • FIG. 4B An example will be described with reference to FIG. 4B.
  • a case is assumed in which only the ventral first cooling holes 32 are disposed to cool the ventral partition wall bonding region 52.
  • the position of the inner edge P11 does not interfere with at least the inner edge P11 of the joint portion 10A1 of the partition wall 10 so that the opening of the ventral first inlet side opening 32A formed on the inner wall surface 13a of the ventral first cooling hole 32 does not interfere. It is necessary to arrange at a position closer to the trailing edge side.
  • the other opening of the abdominal side first cooling hole 32, the abdominal side first outlet side opening 32B formed in the outer wall surface 13b defines a boundary line P12 ⁇ that defines the position of the front edge side of the abdominal side partition junction region 52.
  • ventral first inlet opening 32A is disposed further to the rear edge side than the inner edge P11, and the ventral first outlet side opening 32B is extended to the vicinity of the boundary line P12-P14 on the leading edge side, thereby forming the ventral first cooling hole 32.
  • the cooling hole is formed by electric discharge machining or machining, but there is a limit to the inclination angle of the machining nozzle with respect to the outer surface of the blade, and the center axis (camber line C) in the front edge-rear edge direction of the machining nozzle. If the inclination is small, drilling becomes difficult. This situation is the same for the back side first cooling holes 33 and the second cooling holes 41, 42, 43.
  • ventral-side partition wall junction region 52 and the back-side partition wall junction region 53 are cooled only by the first cooling holes 31, 32, 33, cooling may be insufficient. That is, the cooling air that flows through the cooling flow path 4f and is supplied to the first cooling holes 31, 32, and 33 is more than the cooling air that is supplied to the second cooling holes 41, 42, and 43 that open to the cooling flow path 4e. Pressure has dropped.
  • the ventral partition wall junction region 52 and the back partition wall junction region 53 are cooled only by the first cooling holes 31, 32, 33, the first cooling holes 31, 32, 33 are separated from the partition wall junction regions 51, 52, 53. It is extended to the vicinity of the boundary lines P12-P14 and P22-P24 on the front edge side.
  • the flow rate of the cooling air flowing through the first cooling holes 31, 32, 33 may not be sufficiently secured.
  • the cooling of the first cooling holes 31, 32, 33 alone is insufficient, and the combination of the first cooling holes 31, 32, 33 and the second cooling holes 41, 42, 43 is different. It may be desirable.
  • the shape of the cooling flow path 4 is such that the flow path width in the dorsoventral direction is small, the length of the flow path in the front edge-rear edge direction is long, and a deformed flow path such as a trapezoidal shape, a rhombus shape, or a triangular shape Become a shape. Therefore, the cross-sectional shape of the partition wall 10 connecting the inner wall surfaces 13a and 14a is also deformed into a rhombus shape, and the inclination of the center line Wx of the partition wall 10 with respect to the camber line C tends to be small.
  • the curvature of the joints 10A1, 10A2, 10B1, and 10B2 of the partition wall 10 is increased, and compared with the thickness of the partition wall 10 (P51-P52).
  • the lengths of the ventral bulkhead junction region 52 and the back bulkhead junction region 53 in the front edge-rear edge direction are relatively long, and the ventral bulkhead junction region 52 and the back bulkhead junction region 53 are more difficult to cool.
  • a combination of the first cooling holes 31, 32, 33 and the second cooling holes 41, 42, 43 that is, a combination of at least the ventral first cooling hole 32 and the ventral second cooling hole 42, or the back side first cooling. It is desirable to select one of the combinations of the hole 33 and the back side second cooling hole 43.
  • the ventral partition wall junction region 52 is defined by a boundary line La2 that defines a position on the front edge side in the front edge-rear edge direction, and a boundary line La1 that defines a position on the rear edge side in the front edge-rear edge direction.
  • the joint region 53 is defined by a boundary line Lb2 that defines a position on the front edge side in the front edge-rear edge direction and a boundary line Lb1 that defines a position on the rear edge side in the front edge-rear edge direction.
  • the cooling channel 4 is a trailing edge side cooling channel in which the ventral first cooling hole 32 and the back side first cooling hole 33 are communicated. (Downstream cooling flow path) 4D and a front edge side cooling flow path (upstream cooling flow path) 4U disposed adjacent to the front edge 18 side of the rear edge cooling flow path 4D.
  • One end of the wing body 3 communicates with the leading edge side cooling channel 4U through a ventral second inlet side opening 42A formed on the inner wall surface 13a of the ventral wing wall 13, and the other end of the wing body 3 is the outer wall surface 13b of the wing body 3.
  • the ventral side 2nd cooling hole 42 connected to the ventral side 2nd exit side opening 42B formed in this is included.
  • the ventral second cooling hole 42 extends in the direction of the trailing edge 19 from the ventral second inlet side opening 42A toward the ventral second outlet side opening 42B.
  • the wing body 3 has a back side second inlet side opening 43A formed at one end on the inner wall surface 14a of the back side wing wall 14.
  • a back side second cooling hole 43 that communicates with the leading edge side cooling flow path 4U and communicates with the back side second outlet side opening 43B formed at the outer wall surface 14b of the blade body 3 at the other end.
  • the back side second cooling hole 43 extends in the direction of the rear edge 19 from the back side second inlet side opening 43A toward the back side second outlet side opening 43B.
  • the wing body 3 includes at least one of the abdominal side first cooling hole 32 and the back side first cooling hole 33, the formation position of the first inlet side opening 31 ⁇ / b> A and the formation of the first outlet side opening 31 ⁇ / b> B in the wing body 3.
  • the region joined to the partition 10 between the positions can be convectively cooled. That is, the region joining the partition wall 10 between the position where the ventral first inlet side opening 32A is formed and the position where the ventral first outlet side opening 32B is formed, or the position where the back side first inlet side opening 33A is formed and the back side first.
  • the region joined to the partition wall 10 between the position where the one outlet side opening 33B is formed can be convectively cooled.
  • the wing body 3 includes at least one of the abdominal side second cooling hole 42 and the back side second cooling hole 43, the formation position of the abdominal side second inlet side opening 42 ⁇ / b> A and the abdominal side second outlet of the wing body 3.
  • the cooling air that flows out from at least one of the ventral second outlet side opening 42B and the back second outlet side opening 43B and flows to the trailing edge side along the surface of the wing is more than the ventral second outlet side opening 42B.
  • Film cooling can be performed on at least one of the outer surface of the wing body on the trailing edge side and the outer surface of the wing body on the rear edge side with respect to the back side second outlet side opening 43B.
  • blade body 3 for example can be cooled more effectively by the combination of two cooling holes.
  • the wing body 3 only needs to be provided with at least one of the abdominal side second cooling hole 42 and the back side second cooling hole 43. If both the abdominal side second cooling hole 42 and the back side second cooling hole 43 are provided in the wing body 3, the wing body 3 can be efficiently cooled from both the abdominal side and the back side.
  • the ventral first cooling hole 32 has at least a portion of the ventral first cooling hole 32 passing through the ventral septum junction region 52.
  • the ventral second cooling hole 42 has at least a portion of the ventral second cooling hole 42 passing through the ventral septum junction region 52. .
  • the back side first cooling hole 33 has at least a portion of the back side first cooling hole 33 passing through the back side partition wall junction region 53. . As shown in FIGS. 4A, 4B, and 7, at least part of the back side second cooling hole 43 passes through the back side partition junction region 53 in the back side second cooling hole 43.
  • FIG. 5 is a schematic cross-sectional view for explaining the extended state of the cooling holes 32, 33, 42, 43 in the blade body 3 of the turbine rotor blade 1 according to the embodiment shown in FIG. 4A.
  • FIG. 6 shows the extension of the cooling holes 32, 33, 42, 43 for other embodiments of the cooling holes 32, 33, 42, 43 in the blade body 3 of the turbine rotor blade 1 of the embodiment shown in FIG. 4A. It is typical sectional drawing for demonstrating a present state.
  • FIG. 7 is a view of the vicinity of the rear end of the turbine rotor blade 1 of another embodiment as viewed from the front end 17a side of the turbine rotor blade 1.
  • FIG. 6 shows the extension of the cooling holes 32, 33, 42, 43 for other embodiments of the cooling holes 32, 33, 42, 43 in the blade body 3 of the turbine rotor blade 1 of the embodiment shown in FIG. 4A. It is typical sectional drawing for demonstrating a present state.
  • FIG. 7 is a view of the vicinity of the rear
  • FIG. 8 is a schematic cross-sectional view for explaining the extended state of the cooling holes 32, 33, 42, 43 in the blade body 3 of the turbine rotor blade 1 of the other embodiment shown in FIG. 5, 6, and 8, the cross sections of the cooling holes 32, 33, 42, and 43 are cut along the extending directions of the cooling holes 32, 33, 42, and 43 for convenience of explanation. It is the typical thing which projected the cross section which appears at the time of the front edge 18 side.
  • the cooling holes 32, 33, 42, 43 are located upstream and downstream across the partition wall 10e located on the most downstream side along the flow of cooling air. Located on the side wing wall.
  • the cooling air from the upstream side cooling flow path 4U or the downstream side cooling flow path 4D located on the upstream side and the downstream side is configured to be supplied to the cooling holes 32, 33, 42, and 43.
  • the cooling holes 32, 33, 42, and 43 are cooled from the upstream side cooling flow path 4U or the downstream side cooling flow path 4D located on the upstream side and the downstream side across any one of the partition walls 10a to 10d other than the partition wall 10e. You may be comprised so that air may be supplied.
  • the cooling holes 32, 33, 42, and 43 are formed as any one of the partition walls 10a to 10e. It is assumed that the cooling air is supplied from the upstream side cooling flow path 4U or the downstream side cooling flow path 4D located on the upstream side and the downstream side with respect to each other.
  • the wing body 3 includes a ventral first cooling hole 32, a ventral second cooling hole 42, and a dorsal first cooling hole 33. And a back-side second cooling hole 43.
  • the partition wall bonding region 51 through which at least a part of at least one of the cooling holes passes can be cooled. .
  • the wing body 3 may have at least one of the ventral first cooling hole 32 and the dorsal first cooling hole 33.
  • the length in the front edge-rear edge direction between the position of the outlet side opening 42B, that is, the length in the chord direction connecting the front edge 18 and the rear edge 19, is the position of the ventral first inlet side opening 32A. And shorter than the length in the front edge-rear edge direction between the position of the ventral second inlet side opening 42A.
  • the abdominal side 1st cooling hole 32 and the abdominal side 2nd cooling hole 42 which are arrange
  • the cooling of the region that is difficult to cool the partition wall 10e is further strengthened.
  • the position of the back side first outlet side opening 33B in the back side first cooling hole 33 and the back side second cooling hole 43 in some embodiments.
  • the length in the front edge-rear edge direction between the position of the back side second outlet side opening 43B is between the position of the back side first inlet side opening 33A and the position of the back side second inlet side opening 43A. Leading edge-shorter than the length in the trailing edge direction. Accordingly, the back side first cooling hole 33 and the back side second cooling hole 43 arranged with the partition wall 10e interposed therebetween approach the back side first outlet side opening 33B and the back side second outlet side opening 43B, and the partition wall 10e. Thus, the cooling of the region of the partition wall 10e that is difficult to cool is further strengthened.
  • the position of the ventral first outlet side opening 32B of the ventral first cooling hole 32, and the position of the ventral second outlet side opening 42B of the ventral second cooling hole 42 The length between the leading edge and the trailing edge is shorter than the thickness of the partition wall 10e.
  • the position of the back side first outlet side opening 33 ⁇ / b> B of the back side first cooling hole 33 and the back side second outlet side opening 43 ⁇ / b> B of the back side second cooling hole 43 ⁇ / b> B of the back side second cooling hole 43.
  • the length in the front edge-rear edge direction between these positions is shorter than the thickness of the partition wall 10e.
  • the front edge side cooling flow path 4U has a ventral side second cooling hole 42 and The back side second cooling hole 43 communicates, and the abdominal side first cooling hole 32 and the back side first cooling hole 33 communicate with the trailing edge side cooling flow path 4D. Therefore, the front edge-rear edge direction between the position of the ventral first outlet side opening 32B of the ventral first cooling hole 32 and the position of the ventral second outlet side opening 42B of the ventral second cooling hole 42.
  • the abdominal side first cooling hole 32 and the abdominal side second cooling hole 42 come closer to the partition wall 10e, and the cooling of the abdominal partition wall junction region 52 is enhanced.
  • the front edge-the rear edge between the position of the back side first outlet side opening 33B of the back side first cooling hole 33 and the position of the back side second outlet side opening 43B of the back side second cooling hole 43 When the length in the direction is shorter than the thickness of the partition wall 10e, the back side first cooling hole 33 and the back side second cooling hole 43 come closer to the partition wall 10e, and the cooling of the back side partition wall junction region 53 is enhanced.
  • At least one of the abdominal side first cooling hole 32 and the abdominal side second cooling hole 42 is changed from the abdominal side partition wall joining region 52 which is difficult to cool compared to the region facing the cooling flow path 4 in the abdominal side wing wall 13. Can be cooled by flowing cooling air.
  • at least one of the back-side first cooling hole 33 and the back-side second cooling hole 43 is used as the back-side partition wall joining region 53 that is difficult to cool compared to the region facing the cooling flow path 4 in the back-side wing wall 14. Can be cooled by flowing cooling air.
  • the abdominal side first cooling hole 32 and the abdominal side second cooling hole 42 are the abdominal side first inlet side opening 32 ⁇ / b> A and the abdominal side second that are formed facing the serpentine channel 5. It has an inlet side opening 42A and a ventral first outlet side opening 32B and a ventral second outlet side opening 42B formed on the surface (outer wall surface) 15b of the top plate 15, respectively.
  • the ventral first outlet side opening 32 ⁇ / b> B of the ventral first cooling hole 32 is formed along the thickness direction of the ventral blade wall 13 from the ventral first inlet side opening 32 ⁇ / b> A of the ventral first cooling hole 32. It is formed on the outer wall surface 13b side.
  • ventral second outlet side opening 42B of the ventral second cooling hole 42 is formed along the thickness direction of the ventral blade wall 13 with respect to the ventral second inlet side opening 42A of the ventral second cooling hole 42 along the thickness direction of the ventral blade wall 13. It is formed on the outer wall surface 13b side.
  • the abdominal side first outlet side opening 32 ⁇ / b> B and the abdominal side second outlet side opening 42 ⁇ / b> B of the abdominal side first cooling hole 32 and the abdominal side second cooling hole 42 are the surface 15 b of the top plate 15.
  • ventral side first cooling hole 32 and the ventral side second cooling hole 42 are more in the thickness direction of the ventral wing wall 13 than the ventral side first inlet side opening 32A and the ventral side second inlet side opening 42A. If it is along the outer wall surface 13b side of the wing body 3, it flows into the abdominal side first cooling hole 32 and the abdominal side second cooling hole 42 from the abdominal side first inlet side opening 32A and the abdominal side second inlet side opening 42A.
  • the ventral partition junction region 52 can be cooled while cooling the top plate 15 having a higher heat load than the other portions effectively by the cooling air. Note that only one of the ventral first outlet side opening 32B and the ventral second outlet side opening 42B of the ventral first cooling hole 32 and ventral second cooling hole 42 may be configured as described above. Good.
  • the back side first cooling hole 33 and the back side second cooling hole 43 include the back side first inlet side opening 33 ⁇ / b> A and the back side formed to face the serpentine flow path 5.
  • Side second inlet side opening 43A, and back side first outlet side opening 33B and back side second outlet side opening 43B formed in the outer wall surface 15b of the top plate 15, respectively.
  • the back side first outlet side opening 33B of the back side first cooling hole 33 is an outer wall surface of the wing body 3 along the thickness direction of the back side blade wall 14 rather than the back side first cooling hole back side first inlet side opening 33A. It is formed on the 14b side.
  • the back side second outlet side opening 43 ⁇ / b> B of the back side second cooling hole 43 is formed along the thickness direction of the back side blade wall 14 with respect to the back side second inlet side opening 43 ⁇ / b> A of the back side second cooling hole 43. It is formed on the outer wall surface 14b side. Thereby, the cooling air flowing into the back side first cooling hole 33 and the back side second cooling hole 43 from the back side first inlet side opening 33A and the back side second inlet side opening 43A causes a heat load more than other parts.
  • the back partition wall junction region 53 can be cooled while the top plate 15 having a high height is effectively cooled. Even if only one of the back side first outlet side opening 33B and the back side second outlet side opening 43B of the back side first cooling hole 33 and the back side second cooling hole 43 is configured as described above. Good.
  • the abdominal side first cooling hole 32 and the abdominal side second cooling hole 42 are the abdominal side first inlet side opening 32 ⁇ / b> A and the abdominal side second that are formed facing the serpentine channel 5.
  • Each has an inlet side opening 42A, and a ventral first outlet side opening 32B and a ventral second outlet side opening 42B formed on the surface of the ventral wing wall 13.
  • the ventral first outlet side opening 32 ⁇ / b> B of the ventral first cooling hole 32 is formed closer to the distal end 17 a than the ventral first inlet side opening 32 ⁇ / b> A of the ventral first cooling hole 32.
  • the ventral second outlet side opening 42B of the ventral second cooling hole 42 is formed closer to the distal end 17a than the ventral second inlet side opening 42A of the ventral second cooling hole 42.
  • the thermal load on the top plate 15 is higher than that of other portions. Therefore, the temperature of the blade wall near the tip 17 a is increased by the heat transfer from the top plate 15. The side tends to be high.
  • the ventral first outlet side opening 32 ⁇ / b> B and the ventral second outlet side opening 42 ⁇ / b> B of the ventral first cooling hole 32 and the ventral second cooling hole 42 are the surfaces of the ventral wing wall 13.
  • the inlet The ventral partition wall joining region 52 can be cooled by the cooling air flowing into the ventral first cooling hole 32 and the ventral second cooling hole 42 from the side openings 32A, 42A, and the ventral blade wall 13 near the tip 17a side is effective. Can be cooled. Note that only one of the ventral first outlet side opening 32B and the ventral second outlet side opening 42B of the ventral first cooling hole 32 and ventral second cooling hole 42 may be configured as described above. Good.
  • the back side first cooling hole 33 and the back side second cooling hole 43 face the serpentine flow path 5 (the front edge side serpentine flow path 6, the rear edge side serpentine flow path 7).
  • the back side first outlet side opening 33 ⁇ / b> B of the back side first cooling hole 33 is formed closer to the tip end 17 a than the back side first inlet side opening 33 ⁇ / b> A of the back side first cooling hole 33.
  • the back side second outlet side opening 43 ⁇ / b> B of the back side second cooling hole 43 is formed closer to the tip end 17 a than the back side second inlet side opening 43 ⁇ / b> A of the back side second cooling hole 43. Accordingly, the back partition wall junction region 53 is formed by the cooling air flowing into the back side first cooling hole 33 and the back side second cooling hole 43 from the back side first inlet side opening 33A and the back side second inlet side opening 43A. While being able to cool, the back side wing wall 14 near the tip 17a side can be effectively cooled. Even if only one of the back side first outlet side opening 33B and the back side second outlet side opening 43B of the back side first cooling hole 33 and the back side second cooling hole 43 is configured as described above. Good.
  • FIG. 7 and FIG. 8 in order to suppress the turbulence of the flow of combustion gas in the vicinity of the connection portion between the ventral blade wall 13 and the top plate 15 in the wing body 3, for this purpose, a connecting portion 16 having an inclined surface 16 a that is inclined with respect to both the ventral wing wall 13 and the top plate 15 on the outer side of the wing body 3 is provided.
  • FIG. 7 and FIG. 8 are used for the purpose of reducing the loss due to the leakage flow of the clearance between the top plate 15 and the casing 122 facing the top plate 15.
  • the top plate 15 may be provided with squealer ribs 27.
  • the wing body 3 is a connection portion between the ventral wing wall 13 and the top plate 15, and both the ventral wing wall 13 and the top plate 15 are outside the wing body 3.
  • a connecting portion 16 having an inclined surface 16a inclined with respect to the surface.
  • the ventral side first cooling hole 32 and the ventral side second cooling hole 42 are inlet side openings 32A and 42A formed facing the serpentine flow path 5 and an outlet side opening formed on the inclined surface 16a of the connecting portion 16. 32B and 42B, respectively.
  • the connection part 16 which has the inclined surface 16a is provided. If the outlet side openings 32B and 42B of the abdominal side first cooling hole 32 and the abdominal side second cooling hole 42 are formed in the inclined surface 16a as in the embodiment shown in FIGS. While cooling the top plate 15 having a higher heat load than other portions by the cooling air flowing into the cooling holes 32 and the ventral second cooling holes 42, the ventral blade wall 13 and the top plate 15, which are regions on the tip 17 a side, are cooled. The connection part 16 can be effectively cooled. Only one of the outlet side openings 32B and 42B of the ventral first cooling hole 32 and the ventral second cooling hole 42 may be configured as described above.
  • the back blade wall 14 and the top plate are connected to the connecting portion between the back blade wall 14 and the top plate 15 outside the wing body 3.
  • 15 are formed on the inclined surfaces
  • the outlet side openings 33B and 43B of the back side first cooling hole 33 and the back side second cooling hole 43 are formed on the inclined surface, similarly to the above-described configuration. May be formed.
  • the cooling air flowing into the back side first cooling hole 33 and the back side second cooling hole 43 cools the top plate 15 having a higher thermal load than the other parts, while The region on the tip 17a side where the temperature tends to be higher can be effectively cooled.
  • only one of the outlet side openings 33B and 43B of the back side first cooling hole 33 and the back side second cooling hole 43 may be configured as described above.
  • the back side first cooling hole 33 and the back side second cooling hole 43 are formed in the squealer rib 27 in the same manner as described above.
  • the outlet side openings 33B and 43B may be formed. 7 and 8, when the squealer rib 27 has an inclined surface 27a inclined with respect to both the back wing wall 14 and the top plate 15, the scalloped rib 27 has an inclined surface 27a on the back side.
  • the outlet side openings 33B and 43B of the first cooling hole 33 and the back side second cooling hole 43 may be formed. Even with such a configuration, it is possible to effectively cool the back wing wall 14 and the squealer rib 27 on the tip 17a side while cooling the top plate 15 having a higher heat load than other portions.
  • the ventral first cooling hole 32 and the ventral second cooling hole 42 are provided with inlet-side openings 32 ⁇ / b> A and 42 ⁇ / b> A formed facing the serpentine channel 5, and It has outlet side openings 32B and 42B formed on the surface of the wing body 3 so that the center position exists in the ventral-side partition joint region 52.
  • the surface of the wing body 3 includes not only the surfaces of the wing walls 13 and 14 but also the surfaces of the top plate 15, the connection portion 16, and the squealer rib 27.
  • the outlet side openings 32B and 42B of the abdominal side first cooling hole 32 and the abdominal side second cooling hole 42 are located at the center position of the abdominal side partition junction region.
  • the vent-side first cooling hole 32 is formed on the surface of the blade body 3 so as to be present at 52, as compared with the case where the center position of the openings of the outlet-side openings 32B, 42B does not exist in the ventral-partition junction region 52.
  • the distance which ventral side 2nd cooling hole 42 passes ventral side partition junction area 52 can be enlarged. Thereby, the ventral-side partition junction area
  • region 52 can be cooled effectively.
  • outlet side openings 32B and 42B of the ventral first cooling hole 32 and the ventral second cooling hole 42 are formed on the surface of the blade body 3 so that the center position thereof exists in the ventral partition wall joining region 52.
  • effective cooling can be performed on the blade surface in the ventral-side partition joint region 52 by the cooling air that has flowed out of the outlet-side openings 32B and 42B.
  • Only one of the outlet side openings 32B and 42B of the ventral first cooling hole 32 and the ventral second cooling hole 42 may be configured as described above.
  • the back side first cooling hole 33 and the back side second cooling hole 43 include the inlet side openings 33 ⁇ / b> A and 43 ⁇ / b> A formed facing the serpentine channel 5, and Each has outlet side openings 33B and 43B formed on the surface of the wing body 3 so that the center position exists in the back partition wall joining region 53.
  • the center positions of the openings of the outlet side openings 33B and 43B are set.
  • the distance that the backside first cooling hole 33 and the backside second cooling hole 43 pass through the backside partition wall junction region 53 can be increased.
  • region 53 can be cooled effectively.
  • the outlet side openings 33B and 43B of the back side first cooling hole 33 and the back side second cooling hole 43 are formed on the surface of the blade body 3 so that the center position of the opening exists in the back side partition wall junction region 53.
  • effective cooling can be performed on the blade surface in the back-side partition wall junction region 53 by the cooling air flowing out from the outlet-side openings 33B and 43B.
  • only one of the outlet side openings 33B and 43B of the back side first cooling hole 33 and the back side second cooling hole 43 may be configured as described above.
  • the ventral first cooling hole 32 is located on the most downstream side of the serpentine flow path 5, that is, at the position closest to the trailing edge 19 side. It has an inlet-side opening 32A formed facing the cooling flow paths 4c and 4f extending along the radial direction. Thereby, on the upstream side of the cooling flow paths 4c, 4f, the ventral first inlet side opening of the ventral first cooling hole 32 is provided in one of the cooling flow paths extending along the radial direction of the turbine rotor blade 1.
  • the cooling air discharged from the abdominal side first cooling hole 32 to the outside of the blade body 3 flows along a longer distance along the serpentine channel 5, and the cooling channel More heat can be taken from the wings that form. Therefore, since the wing body 3 is further cooled by the cooling air discharged from the abdominal side first cooling hole 32 to the outside of the wing body 3, the flow rate of the cooling air can be suppressed, and a decrease in turbine efficiency can be suppressed.
  • the ventral first cooling hole 32 having the inlet side opening 32A formed facing the cooling flow path 4c of the front edge side serpentine flow path 6 and the cooling flow path 4f of the rear edge side serpentine flow path 7 are faced. Both the ventral first cooling hole 32 having the inlet side opening 32A to be formed may be provided, or only one of them may be provided. The same applies to the back side described below.
  • the back-side first cooling hole 33 extends along the radial direction of the turbine rotor blade 1 on the most downstream side of the serpentine flow path 5. It has an inlet-side opening 33A formed facing the cooling flow paths 4c and 4f. Thereby, the inlet side opening 33A of the back side first cooling hole 33 is formed in any one of the cooling flow paths extending along the radial direction of the turbine rotor blade 1 on the upstream side of the cooling flow paths 4c and 4f. Compared to the case, the cooling air discharged from the back side first cooling hole 33 to the outside of the blade body 3 flows along a longer distance along the serpentine flow path 5, and more heat is transferred to the blade body 3.
  • the wing body 3 is further cooled by the cooling air discharged from the back side first cooling hole 33 to the outside of the wing body 3, the flow rate of the cooling air can be suppressed, and a decrease in turbine efficiency can be suppressed.
  • the ventral first cooling hole 32 is formed at a position facing the serpentine channel 5 and away from the top plate 15 on the base end 17 b side of the wing body 3.
  • Each has an inlet side opening 32A.
  • the top plate 15 and the ventral wing wall 13 having different extending directions are connected, so that thermal stress is likely to occur.
  • the inlet side opening 32 ⁇ / b> A of the abdominal side first cooling hole 32 faces the serpentine flow path 5 from the top plate 15 to the base end 17 b of the wing body 3.
  • the entrance side opening 32A can be prevented from being formed at a place where thermal stress is likely to occur.
  • the back side first cooling hole 33 faces the serpentine flow path 5 and is located away from the top plate 15 toward the base end 17 b side of the wing body 3.
  • Each has an inlet side opening 33A.
  • the inlet-side opening 33 ⁇ / b> A of the back-side first cooling hole 33 faces the serpentine flow path 5 from the top plate 15 to the base end 17 b of the wing body 3. Since it is formed at a position distant to the side, it is possible to avoid the formation of the entrance-side opening 33A in a place where thermal stress is likely to occur.
  • the wing body 3 includes the abdominal side first cooling hole 32 and the back side first cooling hole 33.
  • the abdominal side first cooling hole 32 and the back side first cooling hole 33 face the serpentine flow path 5 and are formed on the inlet side opening 32A formed at a position away from the top plate 15 toward the base end 17b side of the wing body 3. 33A respectively.
  • the inlet side opening 32 ⁇ / b> A of the ventral first cooling hole 32 is formed closer to the base end 17 b of the blade body 3 than the inlet side opening 33 ⁇ / b> A of the back side first cooling hole 33.
  • the top plate 15 and the ventral wing wall 13 having different extending directions are connected, so that thermal stress is likely to occur.
  • a thermal stress tends to generate
  • the inlet side openings 32 ⁇ / b> A and 33 ⁇ / b> A of the abdominal side first cooling hole 32 and the back side first cooling hole 33 face the serpentine channel 5.
  • the entrance-side openings 32A and 33A can be prevented from being formed in a place where thermal stress is likely to occur because the top plate 15 is formed at a position away from the base end 17b of the wing body 3.
  • the temperature of the blade body 3 tends to be higher on the ventral side than on the back side.
  • the inlet side opening 32 ⁇ / b> A of the abdominal side first cooling hole 32 is closer to the base end 17 b side of the blade body 3 than the inlet side opening 33 ⁇ / b> A of the back side first cooling hole 33.
  • the ventral side first cooling is further away from the connection between the top plate 15 and the ventral wing wall 13 where thermal stress is likely to occur.
  • An entrance side opening 32A of the hole 32 can be formed.
  • the wing body 3 includes the abdominal side second cooling hole 42 and the back side second cooling hole 43.
  • the ventral side second cooling hole 42 and the back side second cooling hole 43 face the serpentine flow path 5 and are formed on the inlet side opening 42A formed at a position away from the top plate 15 toward the base end 17b side of the wing body 3. 43A respectively.
  • the inlet side opening 42 ⁇ / b> A of the ventral second cooling hole 42 is formed closer to the base end 17 b side of the blade body than the inlet side opening 43 ⁇ / b> A of the back side second cooling hole 43.
  • thermal stress is likely to occur at the connection portion between the top plate 15 and the ventral wing wall 13 and the connection portion between the top plate 15 and the back wing wall 14.
  • the inlet side openings 42 ⁇ / b> A and 43 ⁇ / b> A of the ventral second cooling hole 42 and the back second cooling hole 43 face the serpentine channel 5 and the top plate 15 is formed at a position distant from the base end 17b side of the wing body 3, it is possible to avoid the formation of the inlet side openings 42A and 43A in a place where thermal stress is likely to occur.
  • the temperature of the blade body 3 tends to be higher on the ventral side than on the back side.
  • the inlet side opening 42 ⁇ / b> A of the ventral second cooling hole 42 is closer to the base end 17 b side of the blade body 3 than the inlet side opening 43 ⁇ / b> A of the back second cooling hole 43.
  • the second side cooling on the ventral side is further away from the connection between the top plate 15 and the ventral wing wall 13 where thermal stress is likely to occur.
  • An inlet side opening 42A of the hole 42 can be formed.
  • the partition wall 10 is inclined with respect to the camber line C by the center line Wx of the partition wall 10 from one of the ventral wing wall 13 and the back wing wall 14 to the other.
  • the partition wall 10 includes a line segment in which the center line Wx of the partition wall 10 extending from one of the ventral wing wall 13 and the back wing wall 14 to the other is perpendicular to the camber line C. Intersect.
  • the center line Wx of the partition wall is inclined with respect to the camber line C that is the center line of the airfoil, and therefore, the ventral blade wall 13 and the dorsal blade wall 14. It is connected in a tilted state. Therefore, the abdominal-side partition junction region 52 and the back-side partition junction region 53 are enlarged.
  • the ventral partition wall bonding region 52 and the back partition wall bonding region 53 become large, it becomes difficult to cool the ventral partition wall bonding region 52 and the back partition wall bonding region 53 by the cooling air flowing through the serpentine channel 5.
  • the present invention is not limited to the above-described embodiments, and includes forms obtained by modifying the above-described embodiments and forms obtained by appropriately combining these forms.
  • the wing body 3 has at least one of the cooling holes 32, 33, 42, and 43, at least a part of at least one of the cooling holes passes therethrough.
  • the partition junction region 51 can be cooled.
  • the blade body 3 is configured to have at least one of the cooling holes 32, 33, 42, 43, the cooling holes 32, 33, 42, 43 according to some of the embodiments described above.
  • the cooling holes of any of the embodiments can be employed.
  • the cooling holes 32, 33, 42, and 43 when the blade body 3 is configured to have at least two of the cooling holes 32, 33, 42, and 43, the cooling holes 32, 33, 42, and 43 according to some embodiments described above are provided.
  • the cooling holes of different embodiments from the inside can be used in appropriate combination.
  • the first cooling hole 31 includes a ventral first cooling hole 32 and a dorsal first cooling hole 33
  • the second cooling hole 41 includes a ventral second cooling hole 42 and a dorsal side.
  • a second cooling hole 43 is included.
  • the ventral side first inlet side opening 32A, the ventral side second inlet side opening 42A, the back side first inlet side opening 33A, and the back side second inlet are provided. It includes a side opening 43A.
  • abdominal side first outlet side opening 32B, abdominal side second outlet side opening 42B, back side first outlet side opening 33B, back side second outlet The side opening 43B is included.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
PCT/JP2019/011455 2018-03-27 2019-03-19 タービン動翼及びガスタービン Ceased WO2019188588A1 (ja)

Priority Applications (4)

Application Number Priority Date Filing Date Title
DE112019000921.4T DE112019000921B4 (de) 2018-03-27 2019-03-19 Turbinenrotorschaufel und gasturbine
CN201980019689.3A CN111936724B (zh) 2018-03-27 2019-03-19 涡轮动叶以及燃气轮机
US16/981,387 US11346231B2 (en) 2018-03-27 2019-03-19 Turbine rotor blade and gas turbine
KR1020207026110A KR102526809B1 (ko) 2018-03-27 2019-03-19 터빈 동익 및 가스 터빈

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2018060015A JP7093658B2 (ja) 2018-03-27 2018-03-27 タービン動翼及びガスタービン
JP2018-060015 2018-03-27

Publications (1)

Publication Number Publication Date
WO2019188588A1 true WO2019188588A1 (ja) 2019-10-03

Family

ID=68061619

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/JP2019/011455 Ceased WO2019188588A1 (ja) 2018-03-27 2019-03-19 タービン動翼及びガスタービン

Country Status (6)

Country Link
US (1) US11346231B2 (https=)
JP (1) JP7093658B2 (https=)
KR (1) KR102526809B1 (https=)
CN (1) CN111936724B (https=)
DE (1) DE112019000921B4 (https=)
WO (1) WO2019188588A1 (https=)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3974618A1 (en) * 2020-09-24 2022-03-30 Doosan Heavy Industries & Construction Co., Ltd. A technique for cooling squealer tip of a gas turbine blade

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SG11201607376VA (en) 2014-05-05 2016-12-29 Sulzer Management Ag Seal arrangement for a high-pressure pump and high-pressure pump having such a one
KR102466386B1 (ko) * 2020-09-25 2022-11-10 두산에너빌리티 주식회사 터빈 블레이드 및 이를 포함하는 터빈
US20250188843A1 (en) * 2022-08-24 2025-06-12 General Electric Company Turbine engine airfoil

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH1054203A (ja) * 1996-05-28 1998-02-24 Toshiba Corp 構造要素
US7645122B1 (en) * 2006-12-01 2010-01-12 Florida Turbine Technologies, Inc. Turbine rotor blade with a nested parallel serpentine flow cooling circuit
JP2010216472A (ja) * 2009-03-18 2010-09-30 General Electric Co <Ge> タービン翼形部用のフィルム冷却増強装置の使用及び再構成方法
US20120282108A1 (en) * 2011-05-03 2012-11-08 Ching-Pang Lee Turbine blade with chamfered squealer tip and convective cooling holes

Family Cites Families (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS62228603A (ja) * 1986-03-31 1987-10-07 Toshiba Corp ガスタ−ビンの翼
JPS6466401A (en) * 1987-09-07 1989-03-13 Toshiba Corp Turbine cooling blade
US5326224A (en) * 1991-03-01 1994-07-05 General Electric Company Cooling hole arrangements in jet engine components exposed to hot gas flow
JP3137527B2 (ja) * 1994-04-21 2001-02-26 三菱重工業株式会社 ガスタービン動翼チップ冷却装置
US6092982A (en) * 1996-05-28 2000-07-25 Kabushiki Kaisha Toshiba Cooling system for a main body used in a gas stream
JPH10231703A (ja) 1997-02-17 1998-09-02 Toshiba Corp ガスタービンの翼
JPH11200805A (ja) * 1998-01-14 1999-07-27 Toshiba Corp 構造要素の冷却方法、冷却用流路付構造要素および冷却用流路付ガスタービン翼
US6491496B2 (en) * 2001-02-23 2002-12-10 General Electric Company Turbine airfoil with metering plates for refresher holes
US6494678B1 (en) * 2001-05-31 2002-12-17 General Electric Company Film cooled blade tip
JP4137508B2 (ja) 2002-05-02 2008-08-20 ゼネラル・エレクトリック・カンパニイ リフレッシュ用孔のメータリング板を備えるタービン翼形部
FR2885645A1 (fr) * 2005-05-13 2006-11-17 Snecma Moteurs Sa Aube creuse de rotor pour la turbine d'un moteur a turbine a gaz, equipee d'une baignoire
US7249934B2 (en) 2005-08-31 2007-07-31 General Electric Company Pattern cooled turbine airfoil
US8920124B2 (en) * 2013-02-14 2014-12-30 Siemens Energy, Inc. Turbine blade with contoured chamfered squealer tip
WO2014137686A1 (en) * 2013-03-04 2014-09-12 United Technologies Corporation Gas turbine engine high lift airfoil cooling in stagnation zone
JP6565105B2 (ja) 2015-09-29 2019-08-28 三菱日立パワーシステムズ株式会社 動翼及びこれを備えるガスタービン
US10605170B2 (en) * 2015-11-24 2020-03-31 General Electric Company Engine component with film cooling
US10227876B2 (en) 2015-12-07 2019-03-12 General Electric Company Fillet optimization for turbine airfoil
KR20190096569A (ko) * 2018-02-09 2019-08-20 두산중공업 주식회사 가스 터빈

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH1054203A (ja) * 1996-05-28 1998-02-24 Toshiba Corp 構造要素
US7645122B1 (en) * 2006-12-01 2010-01-12 Florida Turbine Technologies, Inc. Turbine rotor blade with a nested parallel serpentine flow cooling circuit
JP2010216472A (ja) * 2009-03-18 2010-09-30 General Electric Co <Ge> タービン翼形部用のフィルム冷却増強装置の使用及び再構成方法
US20120282108A1 (en) * 2011-05-03 2012-11-08 Ching-Pang Lee Turbine blade with chamfered squealer tip and convective cooling holes

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3974618A1 (en) * 2020-09-24 2022-03-30 Doosan Heavy Industries & Construction Co., Ltd. A technique for cooling squealer tip of a gas turbine blade
US11555411B2 (en) 2020-09-24 2023-01-17 Doosan Enerbility Co., Ltd. Technique for cooling squealer tip of a gas turbine blade

Also Published As

Publication number Publication date
US11346231B2 (en) 2022-05-31
CN111936724B (zh) 2022-12-27
DE112019000921B4 (de) 2024-12-24
US20210071535A1 (en) 2021-03-11
KR20200116517A (ko) 2020-10-12
DE112019000921T5 (de) 2020-11-05
JP7093658B2 (ja) 2022-06-30
CN111936724A (zh) 2020-11-13
KR102526809B1 (ko) 2023-04-27
JP2019173595A (ja) 2019-10-10

Similar Documents

Publication Publication Date Title
EP2825748B1 (en) Cooling channel for a gas turbine engine and gas turbine engine
US10830051B2 (en) Engine component with film cooling
BR102016023911A2 (pt) aerofólio e pá para um motor de turbina a gás
WO2019188588A1 (ja) タービン動翼及びガスタービン
CN107366555A (zh) 叶片以及涡轮转子叶片
BR102016022589A2 (pt) aerofólio e pá para um motor de turbina à gás
JP2019173595A5 (https=)
KR20220040981A (ko) 가스 터빈 블레이드의 스퀄러 팁의 냉각 기술
US10655478B2 (en) Turbine blade and gas turbine
JP2019031973A (ja) 不均一なシェブロンピンを備えたエンジン構成要素
WO2024252886A1 (ja) タービン動翼及びガスタービン
US11629601B2 (en) Turbomachine rotor blade with a cooling circuit having an offset rib
US11187085B2 (en) Turbine bucket with a cooling circuit having an asymmetric root turn
JP6996947B2 (ja) タービン翼及びガスタービン
US12385403B2 (en) Turbine stator vane
JP7646030B2 (ja) タービン翼及びガスタービン
JP2021071085A (ja) タービン翼及びこれを備えたガスタービン
JP7847031B2 (ja) タービン翼及びガスタービン
JP7746562B2 (ja) タービン翼及びガスタービン
EP4520921A1 (en) Turbine component for gas turbine engine
JP2019085973A5 (https=)
JP2024174303A (ja) タービン動翼及びガスタービン
JP2026023829A (ja) タービン動翼、及びガスタービン
JP2025026364A (ja) ターボマシンエアフォイルの後縁冷却回路
JP6806599B2 (ja) タービン翼、タービン及びタービン翼の冷却方法

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 19775297

Country of ref document: EP

Kind code of ref document: A1

ENP Entry into the national phase

Ref document number: 20207026110

Country of ref document: KR

Kind code of ref document: A

122 Ep: pct application non-entry in european phase

Ref document number: 19775297

Country of ref document: EP

Kind code of ref document: A1