EP1508670A3 - Cooled vane of a gas turbine - Google Patents

Cooled vane of a gas turbine Download PDF

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Publication number
EP1508670A3
EP1508670A3 EP04300530A EP04300530A EP1508670A3 EP 1508670 A3 EP1508670 A3 EP 1508670A3 EP 04300530 A EP04300530 A EP 04300530A EP 04300530 A EP04300530 A EP 04300530A EP 1508670 A3 EP1508670 A3 EP 1508670A3
Authority
EP
European Patent Office
Prior art keywords
opening
gas turbine
longitudinal
casting
slide
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
EP04300530A
Other languages
German (de)
French (fr)
Other versions
EP1508670A2 (en
EP1508670B1 (en
Inventor
Christophe Texier
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
SNECMA Moteurs SA
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 SNECMA Moteurs SA filed Critical SNECMA Moteurs SA
Publication of EP1508670A2 publication Critical patent/EP1508670A2/en
Publication of EP1508670A3 publication Critical patent/EP1508670A3/en
Application granted granted Critical
Publication of EP1508670B1 publication Critical patent/EP1508670B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • 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
    • F05D2250/14—Two-dimensional elliptical
    • F05D2250/141—Two-dimensional elliptical circular
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/232—Three-dimensional prismatic conical
    • 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
    • F05D2250/32—Arrangement of components according to their shape
    • F05D2250/323—Arrangement of components according to their shape convergent
    • 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
    • F05D2250/70—Shape
    • 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
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • 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
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'aube de moteur à turbine à gaz refroidie comprend une pièce de fonderie (11) et une chemise longitudinale (14) obtenue par formage de tôle; la pièce de fonderie (11) comporte un corps longitudinal pourvu d'une cavité longitudinale (16) avec une première ouverture (19) et une seconde ouverture (20) aux extrémités, la chemise (14) étant montée dans la cavité (16) en étant fixée de façon solidaire à la paroi de la première ouverture (19), et dont une portion d'extrémité (21) est libre de coulisser dans la seconde ouverture formant glissière (20). Ladite portion d'extrémité (21) comprend une portion (22) aux dimensions transversales rétrécies par rapport aux dimensions transversales de la glissière (20).

Figure 00000001
The cooled gas turbine engine blade comprises a casting (11) and a longitudinal liner (14) obtained by forming sheet metal; the casting (11) comprises a longitudinal body provided with a longitudinal cavity (16) with a first opening (19) and a second opening (20) at the ends, the sleeve (14) being mounted in the cavity (16) being secured to the wall of the first opening (19), and having an end portion (21) free to slide in the second slider opening (20). Said end portion (21) comprises a portion (22) with transverse dimensions narrowed relative to the transverse dimensions of the slide (20).
Figure 00000001
EP04300530.5A 2003-08-12 2004-08-11 Cooled vane of a gas turbine Active EP1508670B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0309869A FR2858829B1 (en) 2003-08-12 2003-08-12 AUBE COOLING OF GAS TURBINE ENGINE
FR0309869 2003-08-12

Publications (3)

Publication Number Publication Date
EP1508670A2 EP1508670A2 (en) 2005-02-23
EP1508670A3 true EP1508670A3 (en) 2005-03-09
EP1508670B1 EP1508670B1 (en) 2017-12-13

Family

ID=34043774

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04300530.5A Active EP1508670B1 (en) 2003-08-12 2004-08-11 Cooled vane of a gas turbine

Country Status (7)

Country Link
US (1) US7204675B2 (en)
EP (1) EP1508670B1 (en)
JP (1) JP4234650B2 (en)
CA (1) CA2478954C (en)
FR (1) FR2858829B1 (en)
RU (1) RU2351768C2 (en)
UA (1) UA84395C2 (en)

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7921654B1 (en) 2007-09-07 2011-04-12 Florida Turbine Technologies, Inc. Cooled turbine stator vane
FR2921937B1 (en) * 2007-10-03 2009-12-04 Snecma METHOD FOR STEAM PHASE ALUMINIZATION OF A TURBOMACHINE METAL PIECE
FR2922597B1 (en) 2007-10-19 2012-11-16 Snecma AUBE COOLING TURBOMACHINE
US8353668B2 (en) * 2009-02-18 2013-01-15 United Technologies Corporation Airfoil insert having a tab extending away from the body defining a portion of outlet periphery
FR2943380B1 (en) * 2009-03-20 2011-04-15 Turbomeca DISTRIBUTOR VANE COMPRISING AT LEAST ONE SLOT
IT1394713B1 (en) * 2009-06-04 2012-07-13 Ansaldo Energia Spa TURBINE SHOVEL
US8944751B2 (en) * 2012-01-09 2015-02-03 General Electric Company Turbine nozzle cooling assembly
US9771816B2 (en) 2014-05-07 2017-09-26 General Electric Company Blade cooling circuit feed duct, exhaust duct, and related cooling structure
US9638045B2 (en) * 2014-05-28 2017-05-02 General Electric Company Cooling structure for stationary blade
US9745920B2 (en) * 2014-09-11 2017-08-29 General Electric Company Gas turbine nozzles with embossments in airfoil cavities
US9909436B2 (en) 2015-07-16 2018-03-06 General Electric Company Cooling structure for stationary blade
FR3094034B1 (en) 2019-03-20 2021-03-19 Safran Aircraft Engines VENTILATION TUBULAR SHIRT FOR A TURBOMACHINE DISTRIBUTOR

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3767322A (en) * 1971-07-30 1973-10-23 Westinghouse Electric Corp Internal cooling for turbine vanes
EP0381955A1 (en) * 1989-02-06 1990-08-16 Westinghouse Electric Corporation Gas turbine with air-cooled vanes
US5511937A (en) * 1994-09-30 1996-04-30 Westinghouse Electric Corporation Gas turbine airfoil with a cooling air regulating seal
EP0974733A2 (en) * 1998-07-22 2000-01-26 General Electric Company Turbine nozzle having purge air circuit
US6109867A (en) * 1997-11-27 2000-08-29 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Cooled turbine-nozzle vane
EP1149982A2 (en) * 2000-04-11 2001-10-31 General Electric Company A method of joining a vane cavity insert to a nozzle segment of a gas turbine
EP1154124A1 (en) * 2000-05-10 2001-11-14 General Electric Company Impingement cooled airfoil
EP1160418A2 (en) * 2000-06-01 2001-12-05 General Electric Company Steam exit flow design for aft cavities of an airfoil
EP1191189A1 (en) * 2000-09-26 2002-03-27 Siemens Aktiengesellschaft Gas turbine blades
EP1251243A1 (en) * 2001-04-19 2002-10-23 Snecma Moteurs Turbine blade with cooling air baffle
US20030026689A1 (en) * 2001-08-03 2003-02-06 Burdgick Steven Sebastian Turbine vane segment and impingement insert configuration for fail-safe impingement insert retention

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4288201A (en) * 1979-09-14 1981-09-08 United Technologies Corporation Vane cooling structure
JP3480069B2 (en) * 1994-10-11 2003-12-15 石川島播磨重工業株式会社 Fixed cooling wing of jet engine
US5749701A (en) * 1996-10-28 1998-05-12 General Electric Company Interstage seal assembly for a turbine
US7008185B2 (en) * 2003-02-27 2006-03-07 General Electric Company Gas turbine engine turbine nozzle bifurcated impingement baffle

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3767322A (en) * 1971-07-30 1973-10-23 Westinghouse Electric Corp Internal cooling for turbine vanes
EP0381955A1 (en) * 1989-02-06 1990-08-16 Westinghouse Electric Corporation Gas turbine with air-cooled vanes
US5511937A (en) * 1994-09-30 1996-04-30 Westinghouse Electric Corporation Gas turbine airfoil with a cooling air regulating seal
US6109867A (en) * 1997-11-27 2000-08-29 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Cooled turbine-nozzle vane
EP0974733A2 (en) * 1998-07-22 2000-01-26 General Electric Company Turbine nozzle having purge air circuit
EP1149982A2 (en) * 2000-04-11 2001-10-31 General Electric Company A method of joining a vane cavity insert to a nozzle segment of a gas turbine
EP1154124A1 (en) * 2000-05-10 2001-11-14 General Electric Company Impingement cooled airfoil
EP1160418A2 (en) * 2000-06-01 2001-12-05 General Electric Company Steam exit flow design for aft cavities of an airfoil
EP1191189A1 (en) * 2000-09-26 2002-03-27 Siemens Aktiengesellschaft Gas turbine blades
EP1251243A1 (en) * 2001-04-19 2002-10-23 Snecma Moteurs Turbine blade with cooling air baffle
US20030026689A1 (en) * 2001-08-03 2003-02-06 Burdgick Steven Sebastian Turbine vane segment and impingement insert configuration for fail-safe impingement insert retention

Also Published As

Publication number Publication date
UA84395C2 (en) 2008-10-27
FR2858829B1 (en) 2008-03-14
JP2005061412A (en) 2005-03-10
US7204675B2 (en) 2007-04-17
JP4234650B2 (en) 2009-03-04
US20050089395A1 (en) 2005-04-28
CA2478954C (en) 2012-05-01
FR2858829A1 (en) 2005-02-18
EP1508670A2 (en) 2005-02-23
RU2351768C2 (en) 2009-04-10
RU2004124543A (en) 2006-01-27
CA2478954A1 (en) 2005-02-12
EP1508670B1 (en) 2017-12-13

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