EP2426317A1 - Aube de turbine pour une turbine à gaz - Google Patents

Aube de turbine pour une turbine à gaz Download PDF

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Publication number
EP2426317A1
EP2426317A1 EP10175235A EP10175235A EP2426317A1 EP 2426317 A1 EP2426317 A1 EP 2426317A1 EP 10175235 A EP10175235 A EP 10175235A EP 10175235 A EP10175235 A EP 10175235A EP 2426317 A1 EP2426317 A1 EP 2426317A1
Authority
EP
European Patent Office
Prior art keywords
turbine blade
blade
side wall
turbine
channel
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.)
Withdrawn
Application number
EP10175235A
Other languages
German (de)
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
Original Assignee
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
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP10175235A priority Critical patent/EP2426317A1/fr
Priority to PCT/EP2011/064811 priority patent/WO2012028574A1/fr
Priority to US13/818,794 priority patent/US20130156599A1/en
Priority to EP11749827.9A priority patent/EP2611990B1/fr
Priority to CN201180042590.9A priority patent/CN103080478B/zh
Priority to JP2013526429A priority patent/JP5738996B2/ja
Publication of EP2426317A1 publication Critical patent/EP2426317A1/fr
Withdrawn legal-status Critical Current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 with an airfoil which can be flowed around by a hot gas and which comprises a suction sidewall and a pressure sidewall which extend in the direction of flow of the hot gas from a common leading edge to a trailing edge, wherein at the trailing edge at least one opening for blowing out a blade which previously cools the blade leaf Coolant is arranged, which is in flow communication with at least one opening with a arranged in the airfoil cavity by means of a channel, wherein the channel is also bounded by an inwardly facing surface of the suction side wall and an inwardly facing surface of the pressure side wall and for adjusting the from the Opening exiting coolant amount is provided a throttle element.
  • An aforementioned turbine blade and a casting core for producing such a turbine blade are, for example, from WO 2003/042503 A1 known.
  • the known turbine blade has a cooled trailing edge at which a plurality of openings for blowing out the cooling air by interposed webs - which are also known in English as "tear drops" - are separated from each other.
  • the arranged at the trailing edge of a common cavity is preceded by three rows of columnar sockets - in the English also known as "pin-fins" - are arranged, which increases the heat transfer of them passing cooling air and to increase the Pressure loss are provided there.
  • the casting core required for producing such a turbine blade is shown in FIG WO 2003/042503 A1 shown in perspective.
  • the space occupied by the casting core remains after production of the cast turbine blade as Cavity in the turbine blade, wherein arranged in the casting core openings are filled with casting material.
  • the casting core represents the negative image of the interior of the turbine blade.
  • the object of the invention is therefore to provide an initially mentioned turbine blade for a gas turbine, which is efficient and sufficiently coolable with the smallest possible amount of coolant.
  • the turbine blade for a gas turbine comprises an airfoil which can be flowed around by a hot gas and which comprises a suction sidewall and a pressure sidewall which extend from a common leading edge to a trailing edge in the direction of flow of the hot gas, at least one opening for blowing out the airfoil at or in the trailing edge previously cooling coolant is arranged, which is at least one opening in fluid communication with an arranged in the airfoil cavity by means of a channel, wherein the channel is also bounded by an inwardly facing surface of the suction side wall and an inwardly facing surface of the pressure side wall and adjusting the is provided from the opening exiting cooling air amount, a throttle element, according to the invention, the throttle element upstream - in relation to the flow direction of the channel - the respective opening is arranged and comprises two surveys, each a n one of the two inwardly facing surfaces are arranged.
  • the throttle element comprises on the inwardly facing surfaces arranged elevations which extend transversely to the flow direction of the channel and between which the minimum flow cross-section of the channel is arranged.
  • the minimum vertical distance between each to detect the neutral fiber of the coolant flow and one of the two side surfaces in the cooling channel is arranged.
  • the invention is based on the finding that the coolant consumption with the proposed construction is particularly simple and precisely adjustable, in which the throttle element is arranged in the blade interior upstream of the trailing edge opening.
  • the throttle element is to be formed by two mutually related elevations, each of which are arranged on the inwardly facing surface of the suction side wall and pressure side wall. None of the elevations connects the suction side wall with the pressure side wall.
  • This embodiment of the throttle element is particularly advantageous for turbine blades produced in the casting process.
  • turbine blades are usually produced in casting processes in which so-called lost casting cores are used to produce the internal cooling system. The production of these cores is usually done with the help of a core tool.
  • the core tool comprises two slider elements which can be moved towards and away from each other.
  • these slide elements When pushed together, these slide elements surround a cavity which has the same contour as the cavity of the turbine blade to be cast.
  • the casting core material is inserted 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 slide elements for producing a first prototype of the turbine blade series to be produced are designed such that in the turbine blade prototype to be produced the throttling, minimum distance between the elevations is in any case smaller than the theoretically required one.
  • the first turbine blade prototype produced therewith is then subjected to a coolant flow measurement. Desirably, due to the first time too small distance between the surveys, the throttle effect is too large, which initially too low flow leads.
  • the slide elements are changed. Their elevations are slightly changed, which increases in the collapsed state whose minimum distance. Subsequently, another casting core is produced with it. With this another turbine blade prototype is produced, the flow rate is then determined again and compared with the desired amount.
  • the manufacturing process of the slide elements is completed.
  • the slide elements are then designed so that casting cores are always produced with them, which can be used to manufacture serial turbine blades in series.
  • all steps for the production of a further turbine blade prototype are again carried out, the minimum distance of which is slightly larger than the previous prototype.
  • each of the two slides can be processed by itself - such as by grinding the survey arranged thereon - without fundamentally changing the construction of the turbine blade and its cooling system. It is possible that only one of the slide elements or both slide elements are processed during an iteration step.
  • This method is also particularly suitable for modifications of existing blades in the event that more cooling air is needed for sufficient cooling. In this case, only the smallest changes in the blade design are required. An additional qualification because of an otherwise required casting change is therefore not necessary.
  • the invention leads to the reduction of the scrap rate in the manufacture of turbine blades, which reduces the production costs and significantly improved the production time of turbine blades.
  • the two elevations - seen in the flow direction of the cooling channel - offset from one another.
  • the vertical distance between the inner surface of the pressure sidewall and the inner surface of the suction sidewall can be further reduced, resulting in particularly narrow trailing edge regions of airfoils. This reduces aerodynamic losses in hot gas flowing around the airfoil.
  • elevation which is arranged on the inwardly facing surface of the pressure side wall, arranged downstream of that elevation, which is arranged on the inwardly facing surface of the suction side wall.
  • This construction forces coolant flow in the channel, which flows more intensively past the inwardly facing surface of the suction sidewall.
  • cut-back trailing edges an extended film cooling effect of the unprotected end of the suction-side trailing edge can be achieved, which reduces wear phenomena there and extends the service life of the turbine blade.
  • a plurality of openings are arranged at the trailing edge, wherein the cooling channel jointly connects a plurality of openings with the cavity.
  • the elevations are formed as ribs, with the aid of this angular contour of the inwardly facing surfaces of the side walls of the airfoil turbulence in the coolant can be generated during operation.
  • these turbulences can contribute to the throttle effect and, on the other hand, to increase the heat transfer due to more turbulent coolant flow.
  • the interior of the turbine blade proposed by the invention can be used both for turbine blades with (for the side walls) common trailing edge and for turbine blades with a so-called cut-back trailing edge.
  • FIG. 1 A gas turbine blade 10 relating to the invention is shown in FIG FIG. 1 shown in perspective.
  • the gas turbine blade 10 is according to FIG. 1 designed as a blade.
  • the invention can also be used in a guide vane, not shown, of a gas turbine.
  • the turbine blade 10 comprises a cross-sectionally fir-shaped blade root 12 and a platform 14 arranged thereon.
  • the platform 14 is adjoined by an aerodynamically curved blade 16 on, which has a front edge 18 and a rear edge 20.
  • Provided at the front edge 18 are cooling holes arranged as so-called “shower heads", from which a coolant flowing inside, preferably cooling air, can emerge.
  • the airfoil 16 includes a - with respect FIG.
  • FIG. 2 shows the interior of a turbine blade known in the prior art in a longitudinal section along a plane, spanned by a center line extending from the leading edge 18 to the trailing edge 20 of the airfoil 16, and the blade longitudinal direction extending from the blade root 12 to the blade tip extends.
  • FIG. 2 are further to the right arranged the trailing edge openings 28 shown, between which the webs 30 are arranged.
  • the webs 30 extend substantially parallel to a hot gas flow which, during operation, flows around the airfoil 16 from the front edge 18 to the rear edge 20.
  • FIG. 2 shown on the left is a plurality of arranged in a grid column or sockets 32 are provided. Both the sockets 32 and the webs 30 extend from an inner surface 34 of the suction side wall 22 to an in FIG. 2 Consequently, the sockets 32 are arranged in a cavity 38 of the turbine blade 10, which is bounded laterally by the suction side wall 22 and the pressure side wall 24.
  • a coolant for example cooling air 40 or cooling steam
  • a coolant flows through the cavity 38 during operation.
  • the in FIG. 2 not shown part the turbine blade 10 formed in the interior so that the field of sockets 32 is substantially uniformly flowed through by cooling air 40.
  • the uniform flow of the arranged in grid base 32 is shown by the arrows marked 40.
  • the cooling air 40 impinges on individual pedestals 32 and is thereby deflected by them, the main flow direction of which remains essentially unchanged. This creates 40 turbulences in the cooling air.
  • the introduced from the hot gas in the blade walls 22, 24 heat is passed from these further into the base 32. There, the cooling air 40 impinging on the base 32 absorbs the heat and transports it.
  • cooling air 40 After the cooling air 40 has flowed through the base field, this enters into passages 41 which connect the cavity 38 with the openings 28. After flowing through the passages 41, the cooling air 40 passes out of the turbine blade 10 through the openings 28 and mixes with the hot gas flowing around the blade 16.
  • elevations 42, 44 are provided on the inner surfaces 34, 36 of the suction side wall 22 and the pressure side wall 24, respectively. 3, FIG. 4 ) intended.
  • One (42) of the two elevations 42, 44 is arranged on the inner surface 34 or part thereof, the other (44) of the two elevations 42, 44 is located on the inner surface 36 or part of this.
  • the inner surfaces 34, 36 define a cavity 38 and a cooling channel 46, which connects the cavity 38 with the openings 28. It is possible that cavity 38 and channel 46 merge into one another.
  • the minimum distance between the inner surface 34 and the inner surface 36 in the region of the two elevations 42, 44 is now provided. This is - in FIG.
  • the minimum distance A forming the throttle element is located between the two elevations 42, 44, whereby they are in relation to one another.
  • the elevations 42, 44 replace neither the base 32 nor the webs 30th
  • the elevations 42, 44 extend along the blade longitudinal direction (perpendicular to the sheet plane) over the entire height of the cooling channel 46.
  • the contour of the elevations 42, 44 are, as in the cross section shown in FIG. 3 , Such that they allow a stepless and edge-free course of the cooling channel in the flow direction of the coolant to the trailing edge opening 28 out.
  • the elevations are also designed in the form of ribs, as in FIG. 4 shown.
  • each iteration comprises producing a turbine blade with a defined rib height H 1 and H 2 and determining the coolant consumption of the corresponding turbine blade prototype.
  • a turbine blade 10 is specified, which during the phase of tool production allows a simple and inexpensive test phase to provide 10 accurately fabricated core tool after completion of the iterations for a series of turbine blades.
  • the throttle element instead of two surveys 42, 44 comprises only a single survey 44 (or 42), so that the flow rate determining minimum distance between a single survey 44 (or 42) and its opposite, then after inside facing surface 34 (or 36) of the suction side wall 22 (or the pressure side wall 36) is located.
  • the opposing surface 34 or 36 may then also be configured flat in the region of the minimum distance.
  • the invention specifies a turbine blade 10 whose amount of coolant 40 flowing out of the trailing edge 20 is set comparatively simply and exactly immediately upon casting of the turbine blade 10, without requiring reworking of the cast turbine blade 10 with regard to adjusting the coolant consumption.
  • elevations 42, 44 are located on the inner surfaces 34, 36 of the suction side wall 22 or pressure side wall 24, between which the throttle element is located, by means of which the quantity of outflowing coolant is set.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP10175235A 2010-09-03 2010-09-03 Aube de turbine pour une turbine à gaz Withdrawn EP2426317A1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP10175235A EP2426317A1 (fr) 2010-09-03 2010-09-03 Aube de turbine pour une turbine à gaz
PCT/EP2011/064811 WO2012028574A1 (fr) 2010-09-03 2011-08-29 Aube de turbine pour une turbine à gaz
US13/818,794 US20130156599A1 (en) 2010-09-03 2011-08-29 Turbine blade for a gas turbine
EP11749827.9A EP2611990B1 (fr) 2010-09-03 2011-08-29 Aube de turbine pour une turbine à gaz
CN201180042590.9A CN103080478B (zh) 2010-09-03 2011-08-29 用于燃气轮机的涡轮叶片
JP2013526429A JP5738996B2 (ja) 2010-09-03 2011-08-29 ガスタービンのためのタービンブレード

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP10175235A EP2426317A1 (fr) 2010-09-03 2010-09-03 Aube de turbine pour une turbine à gaz

Publications (1)

Publication Number Publication Date
EP2426317A1 true EP2426317A1 (fr) 2012-03-07

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ID=43545953

Family Applications (2)

Application Number Title Priority Date Filing Date
EP10175235A Withdrawn EP2426317A1 (fr) 2010-09-03 2010-09-03 Aube de turbine pour une turbine à gaz
EP11749827.9A Not-in-force EP2611990B1 (fr) 2010-09-03 2011-08-29 Aube de turbine pour une turbine à gaz

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP11749827.9A Not-in-force EP2611990B1 (fr) 2010-09-03 2011-08-29 Aube de turbine pour une turbine à gaz

Country Status (5)

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

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014031189A1 (fr) * 2012-05-09 2014-02-27 General Electric Company Trous de refroidissement de bord de fuite de forme asymétrique
WO2014179157A1 (fr) * 2013-04-29 2014-11-06 Siemens Aktiengesellschaft Système de refroidissement comprenant une chambre de refroidissement ondulée dans une partie de bord de fuite d'un ensemble de profil aérodynamique
JP2015512494A (ja) * 2012-04-03 2015-04-27 ゼネラル・エレクトリック・カンパニイ タービン翼の後縁冷却スロット
EP3147455A1 (fr) * 2015-09-23 2017-03-29 Siemens Aktiengesellschaft Aube directrice de turbine ayant un agencement d'étranglement
WO2017164935A1 (fr) * 2016-03-22 2017-09-28 Siemens Aktiengesellschaft Surface portante de turbine à éléments structuraux de bord de fuite
WO2019005425A1 (fr) * 2017-06-30 2019-01-03 Siemens Aktiengesellschaft Profil aérodynamique de turbine doté de caractéristiques de bord de fuite et noyau de coulée
EP3492700A1 (fr) * 2017-11-29 2019-06-05 Siemens Aktiengesellschaft Composant de turbomachine à refroidissement intérieur

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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
US10502066B2 (en) 2015-05-08 2019-12-10 United Technologies Corporation Turbine engine component including an axially aligned skin core passage interrupted by a pedestal
US10323524B2 (en) * 2015-05-08 2019-06-18 United Technologies Corporation Axial skin core cooling passage for a turbine engine component
US10260354B2 (en) * 2016-02-12 2019-04-16 General Electric Company Airfoil trailing edge cooling
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
US10753210B2 (en) * 2018-05-02 2020-08-25 Raytheon Technologies Corporation Airfoil having improved cooling scheme

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EP1091092A2 (fr) 1999-10-05 2001-04-11 United Technologies Corporation Méthode et dispositif de refroidissement d'une paroi dans une turbine à gaz
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EP1327747A2 (fr) * 2002-01-11 2003-07-16 General Electric Company Bord de fuite d'aube de turbine refroidi par impact
WO2008100305A1 (fr) * 2007-02-15 2008-08-21 Siemens Energy, Inc. Aube de turbine ayant un système de refroidissement de cavité convergent pour un bord de fuite

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EP1445423B1 (fr) * 1999-04-21 2006-08-02 Alstom Technology Ltd Aube de turbomachine refroidie
EP1245785B1 (fr) * 2001-03-26 2005-06-01 Siemens Aktiengesellschaft Méthode de fabrication d' une aube de turbine
EP1653046A1 (fr) * 2004-10-26 2006-05-03 Siemens Aktiengesellschaft Aube de turbine refroidie et procédé de réglage du débit de réfrigérant
US7575414B2 (en) * 2005-04-01 2009-08-18 General Electric Company Turbine nozzle with trailing edge convection and film cooling
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Publication number Priority date Publication date Assignee Title
US5356265A (en) * 1992-08-25 1994-10-18 General Electric Company Chordally bifurcated turbine blade
US5752801A (en) * 1997-02-20 1998-05-19 Westinghouse Electric Corporation Apparatus for cooling a gas turbine airfoil and method of making same
EP1091092A2 (fr) 1999-10-05 2001-04-11 United Technologies Corporation Méthode et dispositif de refroidissement d'une paroi dans une turbine à gaz
WO2003042503A1 (fr) 2001-11-14 2003-05-22 Honeywell International Inc. Aube ou pale de turbine a gaz refroidi interne
EP1327747A2 (fr) * 2002-01-11 2003-07-16 General Electric Company Bord de fuite d'aube de turbine refroidi par impact
WO2008100305A1 (fr) * 2007-02-15 2008-08-21 Siemens Energy, Inc. Aube de turbine ayant un système de refroidissement de cavité convergent pour un bord de fuite

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2015512494A (ja) * 2012-04-03 2015-04-27 ゼネラル・エレクトリック・カンパニイ タービン翼の後縁冷却スロット
WO2014031189A1 (fr) * 2012-05-09 2014-02-27 General Electric Company Trous de refroidissement de bord de fuite de forme asymétrique
CN104487658A (zh) * 2012-05-09 2015-04-01 通用电气公司 非对称成形的后缘冷却孔
JP2015516540A (ja) * 2012-05-09 2015-06-11 ゼネラル・エレクトリック・カンパニイ 非対称形状の後縁冷却孔
US9145773B2 (en) 2012-05-09 2015-09-29 General Electric Company Asymmetrically shaped trailing edge cooling holes
CN104487658B (zh) * 2012-05-09 2016-04-13 通用电气公司 非对称成形的后缘冷却孔
WO2014179157A1 (fr) * 2013-04-29 2014-11-06 Siemens Aktiengesellschaft Système de refroidissement comprenant une chambre de refroidissement ondulée dans une partie de bord de fuite d'un ensemble de profil aérodynamique
EP3147455A1 (fr) * 2015-09-23 2017-03-29 Siemens Aktiengesellschaft Aube directrice de turbine ayant un agencement d'étranglement
WO2017164935A1 (fr) * 2016-03-22 2017-09-28 Siemens Aktiengesellschaft Surface portante de turbine à éléments structuraux de bord de fuite
CN108779678A (zh) * 2016-03-22 2018-11-09 西门子股份公司 具有后缘框架特征的涡轮翼型件
CN108779678B (zh) * 2016-03-22 2021-05-28 西门子股份公司 具有后缘框架特征的涡轮翼型件
US11193378B2 (en) 2016-03-22 2021-12-07 Siemens Energy Global GmbH & Co. KG Turbine airfoil with trailing edge framing features
WO2019005425A1 (fr) * 2017-06-30 2019-01-03 Siemens Aktiengesellschaft Profil aérodynamique de turbine doté de caractéristiques de bord de fuite et noyau de coulée
US11415000B2 (en) 2017-06-30 2022-08-16 Siemens Energy Global GmbH & Co. KG Turbine airfoil with trailing edge features and casting core
EP3492700A1 (fr) * 2017-11-29 2019-06-05 Siemens Aktiengesellschaft Composant de turbomachine à refroidissement intérieur
WO2019105742A1 (fr) * 2017-11-29 2019-06-06 Siemens Aktiengesellschaft Composant de turbomachine à refroidissement interne

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JP2013536913A (ja) 2013-09-26
CN103080478B (zh) 2015-05-20
JP5738996B2 (ja) 2015-06-24
EP2611990B1 (fr) 2015-01-28
EP2611990A1 (fr) 2013-07-10
WO2012028574A1 (fr) 2012-03-08
US20130156599A1 (en) 2013-06-20
CN103080478A (zh) 2013-05-01

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