ES2126708T3 - Ensamblaje de junta hermetica para tobera de escape de motor de turbina de gas. - Google Patents

Ensamblaje de junta hermetica para tobera de escape de motor de turbina de gas.

Info

Publication number
ES2126708T3
ES2126708T3 ES94302346T ES94302346T ES2126708T3 ES 2126708 T3 ES2126708 T3 ES 2126708T3 ES 94302346 T ES94302346 T ES 94302346T ES 94302346 T ES94302346 T ES 94302346T ES 2126708 T3 ES2126708 T3 ES 2126708T3
Authority
ES
Spain
Prior art keywords
support structure
base plate
hooks
openings
gas turbine
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.)
Expired - Lifetime
Application number
ES94302346T
Other languages
English (en)
Inventor
Michael Alvin Lybarger
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Application granted granted Critical
Publication of ES2126708T3 publication Critical patent/ES2126708T3/es
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78—Other construction of jet pipes
    • F02K1/82—Jet pipe walls, e.g. liners
    • F02K1/822—Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78—Other construction of jet pipes
    • F02K1/80—Couplings or connections
    • F02K1/805—Sealing devices therefor, e.g. for movable parts of jet pipes or nozzle flaps
    • 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
    • F05D2250/324—Arrangement of components according to their shape divergent
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S239/00—Fluid sprinkling, spraying, and diffusing
    • Y10S239/19—Nozzle materials

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Gasket Seals (AREA)

Abstract

SE DESCUBRE UN MONTAJE DE ESCUDO TERMICO Y ESTRUCTURA DE SOPORTE PARA UN MOTOR DE TURBINA DE GAS EN EL QUE EL ESCUDO TERMICO PUEDE RETIRARSE MIENTRAS LA ESTRUCTURA DE SOPORTE (24) QUEDA MONTADA EN EL MOTOR. EL ESCUDO TERMICO, CON LA FORMA DE UNA PLACA BASE DIVERGENTE HERMETICA, Y LA ESTRUCTURA DE SOPORTE ES PARTICULARMENTE UTIL PARA SELLADOS DIVERGENTES Y PROPORCIONA UNA PLACA BASE REMOVIBLE QUE TIENE AL MENOS DOS GANCHOS (40) DISPUESTOS EN LA PARTE TRASERA DE LA PLACA BASE. LOS GANCHOS TIENEN APERTURAS QUE ENCARAN AXIALMENTE, PREFERIBLEMENTE ABIERTAS EN DIRECCION HACIA DELANTE Y OPERABLES PARA ENGANCHAR CLAVIJAS (52) QUE SE EXTIENDEN TRANSVERSALMENTE SOBRE LE MARCO DE LA ESTRUCTURA DE SOPORTE. TAMBIEN PUEDE USARSE UN MEDIO DE RETENCION AXIAL PARA EVITAR QUE LOS GANCHOS SE SUELTEN DE LAS CLAVIJAS QUE, EN UNA CONSTRUCCION CONCRETA, PROPORCIONA UN TIRADOR (60) QUE TIENE UNA PRIMERA APERTURA (62) Y QUE SE EXTIENDE LEJOS DE LA CARA POSTERIOR DE LA PLACA BASE PARA ENGANCHAR UNA HORQUILLA (64) QUE TIENE DOS BRAZOS CON SEGUNDAS APERTURAS ALINEABLES CON LA APERTURA DEL TIRADOR Y UN PERNO (70) U OTRO MEDIO DE SUJECION DISPUESTO A TRAVES DE LAS APERTURAS.
ES94302346T 1993-04-05 1994-03-31 Ensamblaje de junta hermetica para tobera de escape de motor de turbina de gas. Expired - Lifetime ES2126708T3 (es)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US4309693A 1993-04-05 1993-04-05

Publications (1)

Publication Number Publication Date
ES2126708T3 true ES2126708T3 (es) 1999-04-01

Family

ID=21925480

Family Applications (1)

Application Number Title Priority Date Filing Date
ES94302346T Expired - Lifetime ES2126708T3 (es) 1993-04-05 1994-03-31 Ensamblaje de junta hermetica para tobera de escape de motor de turbina de gas.

Country Status (8)

Country Link
US (1) US5584173A (es)
EP (1) EP0623742B1 (es)
JP (1) JP2544087B2 (es)
KR (1) KR970005490B1 (es)
AU (1) AU668275B2 (es)
DE (1) DE69415854T2 (es)
ES (1) ES2126708T3 (es)
IL (1) IL109085A (es)

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0750107B1 (en) * 1995-06-21 1999-10-27 Volvo Aero Corporation Exhaust nozzle flap
US5839663A (en) * 1996-07-23 1998-11-24 United Technologies Corporation Gas turbine exhaust nozzle flap and flap seal apparatus
US6471469B2 (en) * 2000-11-30 2002-10-29 General Electric Company Methods and apparatus for sealing gas turbine engine variable nozzles
US7250192B2 (en) * 2002-04-23 2007-07-31 General Electric Company Sprayable noble metal coating for high temperature use directly on aircraft engine alloys
US6720034B2 (en) * 2002-04-23 2004-04-13 General Electric Company Method of applying a metallic heat rejection coating onto a gas turbine engine component
US7310949B2 (en) * 2003-11-07 2007-12-25 General Electric Company Method and apparatus for arresting a crack within a body
US7028462B2 (en) * 2003-11-07 2006-04-18 General Electric Company Method and apparatus for arresting a crack within a body
US20050097893A1 (en) * 2003-11-07 2005-05-12 General Electric Company Method and apparatus for increasing a durability of a body
US6935118B2 (en) * 2003-12-19 2005-08-30 General Electric Company Exhaust nozzle segmented basesheet and production method thereof
FR2873757B1 (fr) * 2004-07-28 2006-09-29 Snecma Moteurs Sa Tuyere convergente de turboreacteur
US20060088727A1 (en) * 2004-10-25 2006-04-27 General Electric Company High reflectivity infrared coating applications for use in HIRSS applications
US7231724B2 (en) * 2005-10-28 2007-06-19 General Electric Company Nozzle seal slot measuring tool and method
US7624579B2 (en) 2006-02-15 2009-12-01 United Technologies Corporation Convergent divergent nozzle with supported divergent seals
US7975488B2 (en) * 2006-07-28 2011-07-12 United Technologies Corporation Low profile attachment hanger system for a cooling liner within a gas turbine engine swivel exhaust duct
US8156745B2 (en) * 2008-02-29 2012-04-17 General Electric Company Exhaust nozzle seal with segmented basesheet
US8122722B2 (en) * 2008-02-29 2012-02-28 General Electric Company Exhaust nozzle seal with segmented basesheet disposed between side rails
US9316315B2 (en) * 2012-03-09 2016-04-19 United Technologies Corporation Seal assembly
JP2014070548A (ja) * 2012-09-28 2014-04-21 Ihi Corp 再熱装置
RU2535798C1 (ru) * 2013-11-14 2014-12-20 Открытое акционерное общество "Уфимское моторостроительное производственное объединение" ОАО УМПО Регулируемое сопло турбореактивного двигателя
US9890953B2 (en) * 2014-01-10 2018-02-13 United Technologies Corporation Attachment of ceramic matrix composite panel to liner

Family Cites Families (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2794317A (en) * 1951-11-08 1957-06-04 Westinghouse Electric Corp Jet propulsion nozzle apparatus
US2910828A (en) * 1956-08-24 1959-11-03 United Aircraft Company Convergent-divergent variable area propulsion nozzle
US4555901A (en) * 1972-12-19 1985-12-03 General Electric Company Combustion chamber construction
US4614082A (en) * 1972-12-19 1986-09-30 General Electric Company Combustion chamber construction
US4022948A (en) * 1974-12-23 1977-05-10 United Technologies Corporation Resiliently coated metallic finger seals
US4081137A (en) * 1977-01-05 1978-03-28 The United States Of America As Represented By The Secretary Of The Air Force Finned surface cooled nozzle
US4128208A (en) * 1977-07-11 1978-12-05 General Electric Company Exhaust nozzle flap seal arrangement
US4171093A (en) * 1977-08-19 1979-10-16 The United States Of America As Represented By The Secretary Of The Air Force Durability flap and seal liner assembly for exhaust nozzles
US4544098A (en) * 1982-12-27 1985-10-01 United Technologies Corporation Cooled exhaust nozzle flaps
GB2151544B (en) * 1983-12-21 1987-04-15 Rolls Royce Method of manufacture of a non-metallic laminate
US4944151A (en) * 1988-09-26 1990-07-31 Avco Corporation Segmented combustor panel
US5039014A (en) * 1989-04-11 1991-08-13 General Electric Company Axisymmetric vectoring exhaust nozzle seal
US4994660A (en) * 1989-04-11 1991-02-19 Hitachi, Ltd. Axisymmetric vectoring exhaust nozzle
FR2646880A1 (fr) * 1989-05-11 1990-11-16 Snecma Chemise de protection thermique pour canal de post-combustion ou de transition d'un turboreacteur
US5000386A (en) * 1989-07-03 1991-03-19 General Electric Company Exhaust flaps
US5076496A (en) * 1990-02-05 1991-12-31 General Electric Company Exhaust nozzle flap seal
US5067324A (en) * 1990-04-04 1991-11-26 United Technologies Corporation Engine nozzle liner retainer
WO1992003649A1 (en) * 1990-08-23 1992-03-05 United Technologies Corporation Axisymmetric nozzle with gimbled unison ring
US5111992A (en) * 1991-04-19 1992-05-12 United Technologies Corporation Variable throat convergent/divergent nozzle
US5232158A (en) * 1992-08-11 1993-08-03 United Technologies Corporation Convergent/divergent nozzle with seal centering

Also Published As

Publication number Publication date
JP2544087B2 (ja) 1996-10-16
DE69415854D1 (de) 1999-02-25
AU5798594A (en) 1994-10-06
KR970005490B1 (ko) 1997-04-16
EP0623742A1 (en) 1994-11-09
IL109085A (en) 1997-08-14
DE69415854T2 (de) 1999-08-05
EP0623742B1 (en) 1999-01-13
US5584173A (en) 1996-12-17
JPH06346758A (ja) 1994-12-20
AU668275B2 (en) 1996-04-26

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