EP0034961A1 - Gekühlte Gasturbinenschaufeln - Google Patents

Gekühlte Gasturbinenschaufeln Download PDF

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Publication number
EP0034961A1
EP0034961A1 EP19810400179 EP81400179A EP0034961A1 EP 0034961 A1 EP0034961 A1 EP 0034961A1 EP 19810400179 EP19810400179 EP 19810400179 EP 81400179 A EP81400179 A EP 81400179A EP 0034961 A1 EP0034961 A1 EP 0034961A1
Authority
EP
European Patent Office
Prior art keywords
blade
trailing edge
improvement
turbine blades
cavity
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.)
Granted
Application number
EP19810400179
Other languages
English (en)
French (fr)
Other versions
EP0034961B1 (de
Inventor
Michel Léonard Cuvillier
Thierry Marie Charles Schindler
Jacques Philippe Henri Tirole
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.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0034961A1 publication Critical patent/EP0034961A1/de
Application granted granted Critical
Publication of EP0034961B1 publication Critical patent/EP0034961B1/de
Expired 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
    • 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
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • 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
    • F05D2240/126—Baffles or ribs
    • 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 present invention relates to an improvement to the blades of cooled turbines.
  • the improved blade according to the invention which makes it possible to meet these criteria, comprises two cavities supplied by a flow of cooling fluid including an upstream cavity and a downstream cavity divided into two zones of radial and "tangential" flow towards the trailing edge (that is to say, substantially parallel to the trailing edge of the profile).
  • the upstream cavity has flow deflecting members and the downstream cavity comprises, in the central zone for the radial flow of the fluid, bridges of large section, while in the zone of flow trailing edge "tangential", said downstream cavity comprises bridges of smaller cross section supplemented by deflector members guiding the radial flow, tangentially towards the orifices of the trailing edge.
  • This turbine blade according to the invention has a simple and efficient cooling circuit and is remarkable for its ease of manufacture and the distribution of the heat exchanger members.
  • This blade is very easy to make, because it allows the use of a core with two cavities.
  • this blade has a high permeability, as well as the absence of. baffles. Furthermore, by modifying the entry conditions (section of the diaphragms in particular), the exit conditions (apertures at the top, section and location of the emission zones) and by varying the size and spacing of the bridges, it is possible to control the local cooling of each portion of the blade, therefore avoid temperature heterogeneities in the metal of the blade.
  • the good general cooling conditions and this absence of hot spots mean that this blade can be adapted to the temperature conditions of the hot gases which can be much more severe than those of the blades of the prior art.
  • FIGs 1 and 2 there is shown an embodiment of a turbine blade according to the invention which is cast in refractory metal and which comprises an upstream cavity 1 with radial flow and a downstream cavity 2 separated into two zones, one at radial flow and a tangential flow towards the trailing edge 3.
  • the upstream cavity 1 is delimited by a leading edge 4 and by a partition 5 and it is crossed by an air flow which moves according to the arrows F, by entering through an opening 6 formed in the foot 7 of the blade which has a platform 23, said flow being evacuated in part by holes 8 drilled in the leading edge and in part by an orifice 9 formed in hat 10 of dawn.
  • the hat 10 of the dawn is brought back or came from foundry with the dawn.
  • the holes 8 of the leading edge are drilled either on the upper surface at 8a, or on the lower surface at 8b, and either at the end of the leading edge at 8c if the available cooling air pressure is sufficient .
  • the internal face of the leading edge 4 over the upper 2/3 of its height is provided with fins 11 promoting heat exchanges made up of small parallel ribs, extending in an axial plane. These ribs 11 may have the same height or different heights. It may also be advantageous to vary their spacing along the cavity.
  • the downstream cavity 2, delimited by the internal partition 5 and by the trailing edge 3, is divided into two zones including a central zone comprising bridges 12 of large section and a trailing edge zone comprising bridges 13 of small section arranged in staggered rows and deflector elements 14, these divert part of the radial flow from the cavity 2 towards the orifices 15 of the trailing edge 3. This part of the flow is thus deflected to pass from the substantially radial direction to the direction according to the arrows F2.
  • the air flow which enters the cavity 2 through the orifice 16 located at the foot of the blade, along the arrow F1 is divided into a radial flow moving in 1a central area comprising the bridges 12 and / a tangential flow moving in the area of the trailing edge comprising the bridges 13 of smaller section.
  • the radial air flow is evacuated through the orifice 17 provided in the cap 10 of the blade, while the tangential air flow is evacuated through the orifices 15 of the trailing edge which open either on the lower surface of the edge of leakage, either on the edge of the latter as shown in Figure 2.
  • the size and spacing of the bridges 12 of the first zone limit the pressure drops and prevent the entry of hot gases through the opening 17 of the cap 10.
  • FIGS 3, 4 and 5 there is shown the cap 1 0 of the blade which has flanges 18 defining with the upper face of the blade a groove 19 in which is engaged by sliding a plate 20 provided with calibrated orifices 21, 22.
  • the plate 20, after positioning in the groove 19, can be fixed for example by soldering (shown in bold lines in Figure 4).
  • the diameter of the orifices 21, 22 can be optimized at will. Optimization of the diameter of the orifices 21 and 22, which are dusting holes, will be carried out by successive approaches during the tests, by changing the insert 20.
  • A As an example, in a cooled blade where the cooling holes drilled in the leading edge and the trailing edge would have a diameter of 0.5 mm, it was found that a diameter of 1 mm was suitable for the orifices 21 and 22. It is even possible to completely seal the orifices 21 and 22 of the upstream 1 or downstream 2 cavities, or both, which makes it possible to increase the pressures in the cavities and to increase the flow rate near the leading edge or towards the trailing edge.
EP19810400179 1980-02-19 1981-02-05 Gekühlte Gasturbinenschaufeln Expired EP0034961B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8003552 1980-02-19
FR8003552A FR2476207A1 (fr) 1980-02-19 1980-02-19 Perfectionnement aux aubes de turbines refroidies

Publications (2)

Publication Number Publication Date
EP0034961A1 true EP0034961A1 (de) 1981-09-02
EP0034961B1 EP0034961B1 (de) 1984-10-03

Family

ID=9238706

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19810400179 Expired EP0034961B1 (de) 1980-02-19 1981-02-05 Gekühlte Gasturbinenschaufeln

Country Status (4)

Country Link
EP (1) EP0034961B1 (de)
JP (1) JPS56159507A (de)
DE (1) DE3166389D1 (de)
FR (1) FR2476207A1 (de)

Cited By (41)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3248163A1 (de) * 1981-12-28 1983-07-07 United Technologies Corp., 06101 Hartford, Conn. Kuehlbare schaufel
EP0140257A1 (de) * 1983-10-28 1985-05-08 Westinghouse Electric Corporation Anordnung für die Kühlung der Hinterkante einer Leitschaufel
GB2152150A (en) * 1983-12-27 1985-07-31 Gen Electric Anti-icing inlet guide vane
FR2573130A1 (fr) * 1984-11-13 1986-05-16 United Technologies Corp Joint d'etancheite refroidissable pour un moteur a turbine a gaz.
US4786233A (en) * 1986-01-20 1988-11-22 Hitachi, Ltd. Gas turbine cooled blade
US4820123A (en) * 1988-04-25 1989-04-11 United Technologies Corporation Dirt removal means for air cooled blades
US4820122A (en) * 1988-04-25 1989-04-11 United Technologies Corporation Dirt removal means for air cooled blades
EP0381955A1 (de) * 1989-02-06 1990-08-16 Westinghouse Electric Corporation Gasturbine mit luftgekühlten Schaufeln
WO1996013652A1 (en) * 1994-10-31 1996-05-09 Westinghouse Electric Corporation Gas turbine vane with enhanced cooling
US5601399A (en) * 1996-05-08 1997-02-11 Alliedsignal Inc. Internally cooled gas turbine vane
EP0768448A1 (de) * 1995-10-10 1997-04-16 United Technologies Electro Systems, Inc. Gekühlte Schaufeln für ein Turbinenleitgitter
EP0785339A1 (de) 1996-01-04 1997-07-23 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Gekühlte Turbinenleitschaufel
US5772397A (en) * 1996-05-08 1998-06-30 Alliedsignal Inc. Gas turbine airfoil with aft internal cooling
EP0835985A3 (de) * 1996-09-26 1999-11-03 General Electric Company Konfiguration von Kühlkanälen zur Kühlung der Hinterkanten von Strömungsmaschinenschaufeln
GB2345942A (en) * 1998-12-24 2000-07-26 Rolls Royce Plc Gas turbine engine blade cooling air system
FR2798421A1 (fr) * 1990-01-24 2001-03-16 United Technologies Corp Pales refroidies pour moteurs a turbine a gaz
FR2798423A1 (fr) * 1990-01-24 2001-03-16 United Technologies Corp Commande de jeu pour turbine de moteur a turbine a gaz
WO2001031171A1 (en) * 1999-10-22 2001-05-03 Pratt & Whitney Canada Corp. Cast airfoil structure with openings which do not require plugging
WO2001098634A1 (de) * 2000-06-21 2001-12-27 Siemens Aktiengesellschaft Konfiguration einer kühlbaren turbinenschaufel
US6406260B1 (en) 1999-10-22 2002-06-18 Pratt & Whitney Canada Corp. Heat transfer promotion structure for internally convectively cooled airfoils
EP1340884A2 (de) * 2002-02-28 2003-09-03 General Electric Company Verfahren und Vorrichtung für die Kühlung von Gasturbinenleitschaufeln
EP1288436A3 (de) * 2001-08-30 2004-04-21 General Electric Company Turbinenschaufelblatt
EP1437483A1 (de) * 2003-01-13 2004-07-14 United Technologies Corporation Kühlung der Abströmkante einer Turbinenschaufel
GB2405451A (en) * 2003-08-23 2005-03-02 Rolls Royce Plc A vane assembly for a gas turbine engine
WO2006025847A2 (en) * 2004-01-09 2006-03-09 United Technologies Corporation Fanned trailing edge teardrop array
GB2441148A (en) * 2006-08-23 2008-02-27 Rolls Royce Plc Gas turbine engine component with coolant passages
US7520723B2 (en) 2006-07-07 2009-04-21 Siemens Energy, Inc. Turbine airfoil cooling system with near wall vortex cooling chambers
EP2063071A1 (de) * 2007-11-26 2009-05-27 Snecma Laufradschaufel eines Turbotriebwerks
FR2924156A1 (fr) * 2007-11-26 2009-05-29 Snecma Sa Aube de turbomachine
US7934906B2 (en) 2007-11-14 2011-05-03 Siemens Energy, Inc. Turbine blade tip cooling system
FR2954798A1 (fr) * 2009-12-31 2011-07-01 Snecma Aube a ventilation interieure
US20140064983A1 (en) * 2012-08-31 2014-03-06 General Electric Company Airfoil and method for manufacturing an airfoil
EP2832956A1 (de) * 2013-07-29 2015-02-04 Siemens Aktiengesellschaft Turbinenschaufel mit tragflächenprofilförmigen Kühlkörpern
EP2565382A3 (de) * 2011-08-30 2015-04-22 General Electric Company Schaufelprofil mit Anordnung von Kühlstiften
WO2015147672A1 (en) * 2014-03-27 2015-10-01 Siemens Aktiengesellschaft Blade for a gas turbine and method of cooling the blade
CN107304683A (zh) * 2016-04-25 2017-10-31 通用电气公司 具有可变槽分离的翼型件
US20170362942A1 (en) * 2016-06-21 2017-12-21 Rolls-Royce Plc Trailing edge ejection cooling
FR3062675A1 (fr) * 2017-02-07 2018-08-10 Safran Helicopter Engines Aube haute pression ventilee de turbine d'helicoptere comprenant un conduit amont et une cavite centrale de refroidissement
CN110234840A (zh) * 2017-01-31 2019-09-13 西门子股份公司 用于燃气涡轮的涡轮动叶或涡轮静叶
CN112177685A (zh) * 2020-10-21 2021-01-05 中国航发沈阳发动机研究所 一种高压涡轮转子叶片尾缝冷却结构
CN112392550A (zh) * 2020-11-17 2021-02-23 上海交通大学 涡轮叶片尾缘针肋冷却结构及冷却方法、涡轮叶片

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4474532A (en) * 1981-12-28 1984-10-02 United Technologies Corporation Coolable airfoil for a rotary machine
JPS5997205U (ja) * 1982-12-21 1984-07-02 株式会社東芝 ガスタ−ビンの翼
US7001151B2 (en) * 2004-03-02 2006-02-21 General Electric Company Gas turbine bucket tip cap
US7165940B2 (en) * 2004-06-10 2007-01-23 General Electric Company Method and apparatus for cooling gas turbine rotor blades
US7607891B2 (en) * 2006-10-23 2009-10-27 United Technologies Corporation Turbine component with tip flagged pedestal cooling
FR2928405B1 (fr) * 2008-03-05 2011-01-21 Snecma Refroidissement de l'extremite d'une aube.
US8790084B2 (en) * 2011-10-31 2014-07-29 General Electric Company Airfoil and method of fabricating the same
JP6345319B1 (ja) 2017-07-07 2018-06-20 三菱日立パワーシステムズ株式会社 タービン翼及びガスタービン

Citations (8)

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Publication number Priority date Publication date Assignee Title
US3017159A (en) * 1956-11-23 1962-01-16 Curtiss Wright Corp Hollow blade construction
FR1503348A (fr) * 1965-12-11 1967-11-24 Daimler Benz Ag Aube pour turbines à gaz, en particulier pour réacteurs d'avions
FR2147971A1 (de) * 1971-07-02 1973-03-11 Rolls Royce
FR2168801A5 (de) * 1972-01-18 1973-08-31 Bbc Sulzer Turbomaschinen
FR2223550A1 (de) * 1973-03-30 1974-10-25 Gen Electric
FR2323012A1 (fr) * 1975-09-02 1977-04-01 Gen Electric Aube de turbine perfectionnee
US4073599A (en) * 1976-08-26 1978-02-14 Westinghouse Electric Corporation Hollow turbine blade tip closure
US4180373A (en) * 1977-12-28 1979-12-25 United Technologies Corporation Turbine blade

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3017159A (en) * 1956-11-23 1962-01-16 Curtiss Wright Corp Hollow blade construction
FR1503348A (fr) * 1965-12-11 1967-11-24 Daimler Benz Ag Aube pour turbines à gaz, en particulier pour réacteurs d'avions
FR2147971A1 (de) * 1971-07-02 1973-03-11 Rolls Royce
FR2168801A5 (de) * 1972-01-18 1973-08-31 Bbc Sulzer Turbomaschinen
FR2223550A1 (de) * 1973-03-30 1974-10-25 Gen Electric
FR2323012A1 (fr) * 1975-09-02 1977-04-01 Gen Electric Aube de turbine perfectionnee
US4073599A (en) * 1976-08-26 1978-02-14 Westinghouse Electric Corporation Hollow turbine blade tip closure
US4180373A (en) * 1977-12-28 1979-12-25 United Technologies Corporation Turbine blade

Cited By (73)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3248163A1 (de) * 1981-12-28 1983-07-07 United Technologies Corp., 06101 Hartford, Conn. Kuehlbare schaufel
US4515526A (en) * 1981-12-28 1985-05-07 United Technologies Corporation Coolable airfoil for a rotary machine
EP0140257A1 (de) * 1983-10-28 1985-05-08 Westinghouse Electric Corporation Anordnung für die Kühlung der Hinterkante einer Leitschaufel
GB2152150A (en) * 1983-12-27 1985-07-31 Gen Electric Anti-icing inlet guide vane
FR2573130A1 (fr) * 1984-11-13 1986-05-16 United Technologies Corp Joint d'etancheite refroidissable pour un moteur a turbine a gaz.
US4650394A (en) * 1984-11-13 1987-03-17 United Technologies Corporation Coolable seal assembly for a gas turbine engine
US4786233A (en) * 1986-01-20 1988-11-22 Hitachi, Ltd. Gas turbine cooled blade
US4820122A (en) * 1988-04-25 1989-04-11 United Technologies Corporation Dirt removal means for air cooled blades
US4820123A (en) * 1988-04-25 1989-04-11 United Technologies Corporation Dirt removal means for air cooled blades
EP0381955A1 (de) * 1989-02-06 1990-08-16 Westinghouse Electric Corporation Gasturbine mit luftgekühlten Schaufeln
FR2798421A1 (fr) * 1990-01-24 2001-03-16 United Technologies Corp Pales refroidies pour moteurs a turbine a gaz
FR2798423A1 (fr) * 1990-01-24 2001-03-16 United Technologies Corp Commande de jeu pour turbine de moteur a turbine a gaz
WO1996013652A1 (en) * 1994-10-31 1996-05-09 Westinghouse Electric Corporation Gas turbine vane with enhanced cooling
EP0768448A1 (de) * 1995-10-10 1997-04-16 United Technologies Electro Systems, Inc. Gekühlte Schaufeln für ein Turbinenleitgitter
EP0785339A1 (de) 1996-01-04 1997-07-23 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Gekühlte Turbinenleitschaufel
US5772398A (en) * 1996-01-04 1998-06-30 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Cooled turbine guide vane
US5601399A (en) * 1996-05-08 1997-02-11 Alliedsignal Inc. Internally cooled gas turbine vane
US5772397A (en) * 1996-05-08 1998-06-30 Alliedsignal Inc. Gas turbine airfoil with aft internal cooling
EP0835985A3 (de) * 1996-09-26 1999-11-03 General Electric Company Konfiguration von Kühlkanälen zur Kühlung der Hinterkanten von Strömungsmaschinenschaufeln
GB2345942B (en) * 1998-12-24 2002-08-07 Rolls Royce Plc Gas turbine engine internal air system
GB2345942A (en) * 1998-12-24 2000-07-26 Rolls Royce Plc Gas turbine engine blade cooling air system
US6357999B1 (en) 1998-12-24 2002-03-19 Rolls-Royce Plc Gas turbine engine internal air system
WO2001031171A1 (en) * 1999-10-22 2001-05-03 Pratt & Whitney Canada Corp. Cast airfoil structure with openings which do not require plugging
US6257831B1 (en) 1999-10-22 2001-07-10 Pratt & Whitney Canada Corp. Cast airfoil structure with openings which do not require plugging
CZ298005B6 (cs) * 1999-10-22 2007-05-23 Pratt & Whitney Canada Corp. Konstrukce odlévaného reakcního profilu s otvory nevyžadujícími zátkování
US6406260B1 (en) 1999-10-22 2002-06-18 Pratt & Whitney Canada Corp. Heat transfer promotion structure for internally convectively cooled airfoils
WO2001098634A1 (de) * 2000-06-21 2001-12-27 Siemens Aktiengesellschaft Konfiguration einer kühlbaren turbinenschaufel
US6835046B2 (en) 2000-06-21 2004-12-28 Siemens Aktiengesellschaft Configuration of a coolable turbine blade
EP1167689A1 (de) * 2000-06-21 2002-01-02 Siemens Aktiengesellschaft Konfiguration einer kühlbaren Turbinenschaufel
EP1288436A3 (de) * 2001-08-30 2004-04-21 General Electric Company Turbinenschaufelblatt
EP1340884A2 (de) * 2002-02-28 2003-09-03 General Electric Company Verfahren und Vorrichtung für die Kühlung von Gasturbinenleitschaufeln
EP1340884A3 (de) * 2002-02-28 2004-06-09 General Electric Company Verfahren und Vorrichtung für die Kühlung von Gasturbinenleitschaufeln
EP1437483A1 (de) * 2003-01-13 2004-07-14 United Technologies Corporation Kühlung der Abströmkante einer Turbinenschaufel
US6942449B2 (en) 2003-01-13 2005-09-13 United Technologies Corporation Trailing edge cooling
US7179047B2 (en) 2003-08-23 2007-02-20 Rolls-Royce Plc Vane apparatus for a gas turbine engine
GB2405451A (en) * 2003-08-23 2005-03-02 Rolls Royce Plc A vane assembly for a gas turbine engine
GB2405451B (en) * 2003-08-23 2008-03-19 Rolls Royce Plc Vane apparatus for a gas turbine engine
WO2006025847A2 (en) * 2004-01-09 2006-03-09 United Technologies Corporation Fanned trailing edge teardrop array
WO2006025847A3 (en) * 2004-01-09 2006-05-26 United Technologies Corp Fanned trailing edge teardrop array
US7520723B2 (en) 2006-07-07 2009-04-21 Siemens Energy, Inc. Turbine airfoil cooling system with near wall vortex cooling chambers
GB2441148A (en) * 2006-08-23 2008-02-27 Rolls Royce Plc Gas turbine engine component with coolant passages
US7934906B2 (en) 2007-11-14 2011-05-03 Siemens Energy, Inc. Turbine blade tip cooling system
US8147205B2 (en) 2007-11-26 2012-04-03 Snecma Turbomachine blade
EP2063071A1 (de) * 2007-11-26 2009-05-27 Snecma Laufradschaufel eines Turbotriebwerks
FR2924156A1 (fr) * 2007-11-26 2009-05-29 Snecma Sa Aube de turbomachine
FR2924155A1 (fr) * 2007-11-26 2009-05-29 Snecma Sa Aube de turbomachine
RU2554397C2 (ru) * 2009-12-31 2015-06-27 Снекма Лопатка с внутренним вентилированием
CN102713160A (zh) * 2009-12-31 2012-10-03 斯奈克玛 内部通风叶片
WO2011080319A1 (fr) * 2009-12-31 2011-07-07 Snecma Aube a ventilation interieure
FR2954798A1 (fr) * 2009-12-31 2011-07-01 Snecma Aube a ventilation interieure
EP2565382A3 (de) * 2011-08-30 2015-04-22 General Electric Company Schaufelprofil mit Anordnung von Kühlstiften
US20140064983A1 (en) * 2012-08-31 2014-03-06 General Electric Company Airfoil and method for manufacturing an airfoil
EP2832956A1 (de) * 2013-07-29 2015-02-04 Siemens Aktiengesellschaft Turbinenschaufel mit tragflächenprofilförmigen Kühlkörpern
WO2015014566A1 (de) 2013-07-29 2015-02-05 Siemens Aktiengesellschaft Turbinenschaufel mit tragflächenprofilförmigen kühlkörpern
CN105408586A (zh) * 2013-07-29 2016-03-16 西门子股份公司 具有翼型轮廓形状散热器的涡轮叶片
CN105408586B (zh) * 2013-07-29 2017-06-16 西门子股份公司 具有翼型轮廓形状散热器的涡轮叶片
WO2015147672A1 (en) * 2014-03-27 2015-10-01 Siemens Aktiengesellschaft Blade for a gas turbine and method of cooling the blade
US10598027B2 (en) 2014-03-27 2020-03-24 Siemens Aktiengesellschaft Blade for a gas turbine and method of cooling the blade
CN107304683A (zh) * 2016-04-25 2017-10-31 通用电气公司 具有可变槽分离的翼型件
CN107304683B (zh) * 2016-04-25 2022-02-11 通用电气公司 具有可变槽分离的翼型件
US10156146B2 (en) 2016-04-25 2018-12-18 General Electric Company Airfoil with variable slot decoupling
EP3260661A1 (de) * 2016-04-25 2017-12-27 General Electric Company Schaufel mit variablen schaufelhinterkantenschlitzen
EP3260658A1 (de) * 2016-06-21 2017-12-27 Rolls-Royce plc Austrittskantenausstosskühlung
US10641104B2 (en) 2016-06-21 2020-05-05 Rolls-Royce Plc Trailing edge ejection cooling
US20170362942A1 (en) * 2016-06-21 2017-12-21 Rolls-Royce Plc Trailing edge ejection cooling
CN110234840A (zh) * 2017-01-31 2019-09-13 西门子股份公司 用于燃气涡轮的涡轮动叶或涡轮静叶
US11053802B2 (en) 2017-01-31 2021-07-06 Siemens Energy Global GmbH & Co. KG Turbine blade or a turbine vane for a gas turbine
WO2018146403A1 (fr) * 2017-02-07 2018-08-16 Safran Helicopter Engines Aube ventilee de turbine haute pression
CN110268137A (zh) * 2017-02-07 2019-09-20 赛峰直升机发动机公司 高压涡轮的通风叶片
FR3062675A1 (fr) * 2017-02-07 2018-08-10 Safran Helicopter Engines Aube haute pression ventilee de turbine d'helicoptere comprenant un conduit amont et une cavite centrale de refroidissement
CN112177685A (zh) * 2020-10-21 2021-01-05 中国航发沈阳发动机研究所 一种高压涡轮转子叶片尾缝冷却结构
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CN112392550B (zh) * 2020-11-17 2021-09-28 上海交通大学 涡轮叶片尾缘针肋冷却结构及冷却方法、涡轮叶片

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FR2476207A1 (fr) 1981-08-21
EP0034961B1 (de) 1984-10-03
JPS6326242B2 (de) 1988-05-28
JPS56159507A (en) 1981-12-08
DE3166389D1 (en) 1984-11-08
FR2476207B1 (de) 1983-05-13

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