US20130156599A1 - Turbine blade for a gas turbine - Google Patents

Turbine blade for a gas turbine Download PDF

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Publication number
US20130156599A1
US20130156599A1 US13/818,794 US201113818794A US2013156599A1 US 20130156599 A1 US20130156599 A1 US 20130156599A1 US 201113818794 A US201113818794 A US 201113818794A US 2013156599 A1 US2013156599 A1 US 2013156599A1
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United States
Prior art keywords
turbine blade
side wall
turbine
inwardly facing
trailing edge
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.)
Abandoned
Application number
US13/818,794
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English (en)
Inventor
Fathi Ahmad
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.)
Siemens AG
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Siemens AG
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
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Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: AHMAD, FATHI
Publication of US20130156599A1 publication Critical patent/US20130156599A1/en
Abandoned legal-status Critical Current

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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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection 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
    • 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
    • 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
    • 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
    • F05D2250/184—Two-dimensional patterned sinusoidal
    • 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
    • F05D2250/60—Structure; Surface texture
    • 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
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2212—Improvement of heat transfer by creating turbulence
    • 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
    • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs

Definitions

  • the invention relates to a turbine blade comprising a main blade part, around which a hot gas can flow and which comprises a suction-side wall and a pressure-side wall which extend in the direction of flow of the hot gas from a common leading edge to a trailing edge, wherein at least one opening for blowing out a coolant which cools the main blade part beforehand is arranged on the trailing edge, which at least one opening is fluidically connected to a cavity arranged in the main blade part by means of a channel, wherein the channel is also delimited by an inwardly facing face of the suction-side wall and by an inwardly facing face of the pressure-side wall and a throttling element is provided for setting the quantity of coolant emerging from the opening.
  • a turbine blade of the type mentioned in the introduction and a casting core for producing such a turbine blade are known, for example, from WO 2003/042503 A1.
  • the known turbine blade has a cooled trailing edge, on which a plurality of openings for blowing out the cooling air are separated from one another by interposed webs (also known as “tear drops”).
  • a common cavity is arranged upstream of the openings arranged on the trailing edge, in which cavity there are three rows of pillar-like pedestals (also known as “pin fins”), which are provided for increasing the transfer of heat of the cooling air which brushes past them and for increasing the pressure loss there.
  • FIG. 7 of WO 2003/042503 A1 shows a perspective illustration of the casting core required for producing such a turbine blade.
  • the space occupied by the casting core remains, after the cast turbine blade has been produced, as a cavity in the turbine blade, with openings arranged in the casting core being filled with casting material.
  • the casting core represents the negative reflection of the interior of the turbine blade.
  • the pin fins known from WO 2003/042503 A1 have a cylindrical shape and connect the inner faces of the suction-side wall and pressure-side wall, which are located opposite one another, of the main blade part of the turbine blade.
  • WO 2003/042503 A1 discloses C-shaped guide elements for cooling air, which are arranged in turning regions of cooling channels and which are intended to bring about low-loss deflection and guidance of the cooling air in downstream zones.
  • EP 1 091 092 A2 discloses an air-cooled turbine blade.
  • pins are arranged in grid form in the cavity of the double wall.
  • the pins are diamond-shaped, with the corners thereof being rounded off and the edges thereof being curved concavely inward.
  • a network of passages therefore arises for cooling air, these passages each having a narrowed inlet opening and a narrowed outlet opening, between which there is a diffuser and nozzle portion.
  • the portions are intended to be used to decelerate and accelerate the cooling air in order to achieve the efficient cooling.
  • U.S. Pat. No. 5,752,801 discloses an internally cooled turbine blade, the cooling channels of which on the trailing edge side are configured with a zigzag shape by cast-in c-shaped fins. A better cooling action can thereby be achieved.
  • the casting cores required for the production can thereby be stiffened.
  • the turbine blade for a gas turbine comprises a main blade part, around which a hot gas can flow and which comprises a suction-side wall and a pressure-side wall which extend in the direction of flow of the hot gas from a common leading edge to a trailing edge, wherein at least one opening for blowing out a coolant which cools the main blade part beforehand is arranged on or in the trailing edge, which at least one opening is fluidically connected to a cavity arranged in the main blade part by means of a channel, wherein the channel is also delimited by an inwardly facing face of the suction-side wall and by an inwardly facing face of the pressure-side wall and a throttling element is provided for setting the quantity of cooling air emerging from the opening, wherein, according to the invention, the throttling element is arranged upstream—in relation to the throughflow direction of the channel—of the opening in question and comprises two elevations which are each arranged on one of the two inwardly facing faces.
  • the throttling element comprises elevations which are arranged on the inwardly facing faces and which extend transversely to the throughflow direction of the channel, and between which there is arranged the minimum throughflow cross section of the channel. To determine the minimum throughflow cross section, it is necessary to detect the minimum perpendicular distance between respective fibers of the neutral fibers of the coolant flow and one of the two side faces in the cooling channel.
  • the invention is based on the recognition that the coolant consumption can be set in a particularly simple and exact manner using the proposed design by arranging the throttling element upstream of the trailing edge opening in the interior of the blade.
  • the throttling element is to be formed by two elevations placed in relation to one another, of which one is arranged on the inwardly facing face of the suction-side wall and one on the inwardly facing face of the pressure-side wall. Neither of the elevations connects the suction-side wall to the pressure-side wall.
  • This embodiment of the throttling element is particularly advantageous for turbine blades produced by a casting process. It is known that turbine blades are mostly produced by casting processes, in which so-called lost casting cores are used to produce the inner cooling system.
  • the core die comprises two slider elements, which can be moved toward one another and away from one another. When pushed together, these slider elements surround a cavity, which has the same contour as the cavity of the turbine blade to be cast.
  • the casting core material is introduced into the cavity of the slider elements. After the casting core material has dried, the casting core is available for producing the turbine blade.
  • the slider elements are designed, for producing a first prototype of the turbine blade series to be produced, in such a way that, in the turbine blade prototype to be produced, the throttling, minimum distance between the elevations is in any case smaller than that required in theory.
  • the first turbine blade prototype thus produced is then subjected to a coolant flow rate measurement.
  • the slider elements are then modified.
  • the elevations thereof are modified slightly, as a result of which the minimum distance therebetween increases when pushed together. Then, a further casting core is produced therewith.
  • each of the two sliders can be machined on their own—for instance by grinding the elevation arranged thereon—without fundamentally changing the structure of the turbine blade and the cooling system thereof. It is possible in this respect for only one of the slider elements or else both slider elements to be machined during one iteration step.
  • This method is also suitable particularly in the case of modifications to already existing blades in the case where more cooling air is needed for sufficient cooling. In this case, only extremely small modifications are needed to the blade design. An additional qualification owing to an otherwise required change in casting is therefore not necessary.
  • the two elevations are arranged offset in relation to one another—as seen in the throughflow direction of the cooling channel.
  • the offset arrangement makes it possible for the perpendicular distance between the inner face of the pressure-side wall and the inner face of the suction-side wall to be reduced further, which leads to particularly narrow trailing edge regions of main blade parts. This reduces aerodynamic losses in the hot gas flowing around the main blade part.
  • the invention leads to a reduction in the reject rate during the production of turbine blades, which significantly improves the production costs and the production time for turbine blades.
  • elevation which is arranged on the inwardly facing face of the pressure-side wall is arranged downstream of that elevation which is arranged on the inwardly facing face of the suction-side wall.
  • This design enforces a flow of coolant in the channel which flows in an intensified manner past the inwardly facing face of the suction-side wall. This makes it possible, particularly in the case of the so-called cut-back trailing edges, to achieve a lengthened film cooling action of the unprotected end of the suction-side trailing edge, which reduces wear phenomena there and lengthens the service life of the turbine blade.
  • a plurality of openings are arranged on the trailing edge, the cooling channel collectively connecting a plurality of openings to the cavity.
  • the elevations are in the form of fins, it is also possible for turbulences to be generated in the coolant during operation with the aid of this angular contour of the inwardly facing faces of the side walls of the main blade part. These turbulences can contribute firstly to the throttling action and secondly to an increase in the transfer of heat on account of a more turbulent coolant flow.
  • the interior of the turbine blade as proposed by the invention can be employed both for turbine blades having a common (for the side walls) trailing edge and for turbine blades having a so-called cut-back trailing edge.
  • FIG. 1 shows a perspective illustration of a turbine rotor blade
  • FIG. 2 shows a longitudinal section through the region of the trailing edge of the turbine rotor blade known from the prior art
  • FIG. 3 shows a cross section through the trailing edge region of a turbine blade according to the invention according to a first configuration
  • FIG. 4 shows a cross section through the trailing edge region of a turbine blade according to the invention according to a second configuration.
  • FIG. 1 is a perspective illustration of a gas turbine blade 10 relating to the invention.
  • the gas turbine blade 10 is in the form of a rotor blade.
  • the invention can also be used in a guide vane (not shown) of a gas turbine.
  • the turbine blade 10 comprises a blade root 12 , with a fir tree-like cross section, and also a platform 14 arranged thereon.
  • An aerodynamically curved main blade part 16 adjoins the platform 14 and comprises a leading edge 18 and also a trailing edge 20 . Cooling openings arranged as a so-called “shower head” are provided on the leading edge 18 , from which cooling openings an internally flowing coolant, preferably cooling air, can emerge.
  • the main blade part 16 comprises a—with respect to FIG.
  • FIG. 1 rear-side suction-side wall 22 and also a front-side pressure-side wall 24 .
  • a multiplicity of openings 28 separated from one another by interposed webs 30 are provided along the trailing edge 20 .
  • the trailing edge 20 is in the form of a so-called cut-back trailing edge, and therefore the openings 28 lie more on the pressure side than in the center of the trailing edge 20 .
  • FIG. 2 shows the interior of a turbine blade known from the prior art in a longitudinal section along a plane, spanned by a center line, which extends from the leading edge 18 to the trailing edge 20 of the main blade part 16 , and by the longitudinal direction of the blade, which extends from the blade root 12 toward the blade tip.
  • the trailing edge openings 28 between which the webs 30 are arranged, are shown arranged further to the right.
  • the webs 30 extend substantially parallel to a flow of hot gas which, during operation, flows around the main blade part 16 from the leading edge 18 to the trailing edge 20 .
  • a multiplicity of pillars or pedestals 32 arranged in a grid are provided.
  • both the pedestals 32 and the webs 30 extend from an inner face 34 of the suction-side wall 22 to an inner face (not shown in FIG. 2 ) of the pressure-side wall 24 . Consequently, the pedestals 32 are arranged in a cavity 38 of the turbine blade 10 , which is laterally delimited by the suction-side wall 22 and the pressure-side wall 24 .
  • a coolant for example cooling air 40 or cooling steam
  • the part of the turbine blade 10 which is not shown in FIG. 2 is generally internally designed such that the field of pedestals 32 is subjected to a substantially uniform incident flow of cooling air 40 .
  • the uniform incident flow onto the pedestals 32 arranged in the grid is shown by the arrows marked with 40 .
  • the cooling air 40 impinges on individual pedestals 32 and, in the process, is deflected by these, with the main direction of flow of said cooling air remaining substantially unchanged. Turbulences are thereby produced in the cooling air 40 .
  • the heat introduced by the hot gas into the blade walls 22 , 24 is thereby conducted further into the pedestals 32 , where the cooling air 40 impinging on the pedestals 32 absorbs the heat and carries it away.
  • the cooling air 40 Once the cooling air 40 has flowed through the field of pedestals, it enters passages 41 which connect the cavity 38 to the openings 28 . Once it has flowed through the passages 41 , the cooling air 40 passes out of the turbine blade 10 through the openings 28 and blends with the hot gas flowing around the main blade part 16 .
  • elevations 42 , 44 are provided on the inner faces 34 , 36 of the suction-side wall 22 and pressure-side wall 24 .
  • One ( 42 ) of the two elevations 42 , 44 is arranged on the inner face 34 or part thereof, and the other ( 44 ) of the two elevations 42 , 44 is situated on the inner face 36 or part thereof.
  • the inner faces 34 , 36 delimit a cavity 38 and also a cooling channel 46 , which connects the cavity 38 to the openings 28 . In this respect, it is possible for the cavity 38 and channel 46 to merge into one another.
  • the minimum distance between the inner face 34 and the inner face 36 is then provided in the region of the two elevations 42 , 44 .
  • the neutral fiber 47 in FIG. 3 in relation to the cross section shown therein through the trailing edge 20 of the turbine blade 10 of the cooling channel 46 which is always at the same perpendicular distance from the inner face 34 and the inner face 36 .
  • the minimum distance A forming the throttling element is situated here between the two elevations 42 , 44 , as a result of which the latter are in relation to one another.
  • the elevations 42 , 44 replace neither the pedestals 32 nor the webs 30 .
  • the elevations 42 , 44 extend along the longitudinal direction of the blade (perpendicular to the plane of the sheet) over the entire height of the cooling channel 46 .
  • the contours of the elevations 42 , 44 are configured, as in the cross section shown in FIG. 3 , such that they make a continuous and edge-free profile of the cooling channel possible in the direction of flow of the coolant toward the trailing edge opening 28 .
  • the cooling channel 46 converges.
  • the elevations are also in the form of fins, as shown in FIG. 4 .
  • the elevations 42 , 44 have a fin-like contour with a height H 1 and H 2 , respectively.
  • the heights H 1 and H 2 are relatively large, and therefore it is possible to determine a coolant consumption which lies below the desired or predefined consumption.
  • the core die i.e. the corresponding slider elements
  • Each iteration in this case includes the production of a turbine blade having a defined fin height H 1 and H 2 and the determination of the coolant consumption of the corresponding turbine blade prototype.
  • the production of the slider elements is ended, and therefore the core die which is then available can be used to produce casting cores and therefore turbine blades with the desired coolant consumption to an increased extent, which significantly reduces the reject rate.
  • the proposed configuration provides a turbine blade 10 which, during the phase of die production, makes a simple and cost-effective test phase possible, in order to provide a core die produced exactly for a series of turbine blades 10 after the conclusion of the iterations.
  • the throttling element can comprise only a single elevation 44 (or 42 ) instead of two elevations 42 , 44 , such that the minimum distance which determines the flow rate is situated between a single elevation 44 (or 42 ) and the then inwardly directed face 34 (or 36 ) of the suction-side wall 22 (or of the pressure-side wall 36 ) which lies opposite it.
  • the opposing face 34 or 36 can then also have a planar configuration in the region of the minimum distance.
  • the invention specifies a turbine blade 10 , the quantity of coolant 40 of which flowing out from the trailing edge 20 is set relatively simply and exactly immediately upon casting of the turbine blade 10 , without it being necessary to rework the cast turbine blade 10 in terms of setting the coolant consumption.
  • elevations 42 , 44 are situated on the inner faces 34 , 36 of the suction-side wall 22 and pressure-side wall 24 , between which elevations the throttling element used to set the quantity of coolant flowing out is located. This arrangement makes it possible to simply produce a core die with which the casting cores required for casting the turbine blade 10 can always be produced in large quantities with the desired accuracy.
US13/818,794 2010-09-03 2011-08-29 Turbine blade for a gas turbine Abandoned US20130156599A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP10175235A EP2426317A1 (de) 2010-09-03 2010-09-03 Turbinenschaufel für eine Gasturbine
EP10175235.0 2010-09-03
PCT/EP2011/064811 WO2012028574A1 (de) 2010-09-03 2011-08-29 Turbinenschaufel für eine gasturbine

Publications (1)

Publication Number Publication Date
US20130156599A1 true US20130156599A1 (en) 2013-06-20

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ID=43545953

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Application Number Title Priority Date Filing Date
US13/818,794 Abandoned US20130156599A1 (en) 2010-09-03 2011-08-29 Turbine blade for a gas turbine

Country Status (5)

Country Link
US (1) US20130156599A1 (de)
EP (2) EP2426317A1 (de)
JP (1) JP5738996B2 (de)
CN (1) CN103080478B (de)
WO (1) WO2012028574A1 (de)

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US20160326884A1 (en) * 2015-05-08 2016-11-10 United Technologies Corporation Axial skin core cooling passage for a turbine engine component
US20190338652A1 (en) * 2018-05-02 2019-11-07 United Technologies Corporation Airfoil having improved cooling scheme
US11143039B2 (en) 2015-05-08 2021-10-12 Raytheon Technologies Corporation Turbine engine component including an axially aligned skin core passage interrupted by a pedestal
US11415000B2 (en) 2017-06-30 2022-08-16 Siemens Energy Global GmbH & Co. KG Turbine airfoil with trailing edge features and casting core

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US9017026B2 (en) * 2012-04-03 2015-04-28 General Electric Company Turbine airfoil trailing edge cooling slots
US9145773B2 (en) * 2012-05-09 2015-09-29 General Electric Company Asymmetrically shaped trailing edge cooling holes
US8985949B2 (en) * 2013-04-29 2015-03-24 Siemens Aktiengesellschaft Cooling system including wavy cooling chamber in a trailing edge portion of an airfoil assembly
US9132476B2 (en) * 2013-10-31 2015-09-15 Siemens Aktiengesellschaft Multi-wall gas turbine airfoil cast using a ceramic core formed with a fugitive insert and method of manufacturing same
EP3147455A1 (de) * 2015-09-23 2017-03-29 Siemens Aktiengesellschaft Turbinenleitschaufel mit einer drosseleinrichtung
US10260354B2 (en) * 2016-02-12 2019-04-16 General Electric Company Airfoil trailing edge cooling
JP6685425B2 (ja) * 2016-03-22 2020-04-22 シーメンス アクチエンゲゼルシヤフトＳｉｅｍｅｎｓ Ａｋｔｉｅｎｇｅｓｅｌｌｓｃｈａｆｔ 後縁骨組み特徴を備えるタービン翼
KR20180082118A (ko) * 2017-01-10 2018-07-18 두산중공업 주식회사 가스 터빈의 블레이드 또는 베인의 컷백
KR101875692B1 (ko) * 2017-04-10 2018-07-06 연세대학교 산학협력단 가스터빈 냉각을 위한 직물형태의 내부 유로 구조를 포함하는 가스터빈 블레이드
EP3492700A1 (de) * 2017-11-29 2019-06-05 Siemens Aktiengesellschaft Innengekühlte turbomaschinenkomponente

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US10323524B2 (en) * 2015-05-08 2019-06-18 United Technologies Corporation Axial skin core cooling passage for a turbine engine component
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JP5738996B2 (ja) 2015-06-24
CN103080478B (zh) 2015-05-20
EP2426317A1 (de) 2012-03-07
CN103080478A (zh) 2013-05-01
EP2611990B1 (de) 2015-01-28
WO2012028574A1 (de) 2012-03-08
JP2013536913A (ja) 2013-09-26
EP2611990A1 (de) 2013-07-10

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