BE810491A - Moteur a turbine a gaz a dispositif de post-combustion - Google Patents

Moteur a turbine a gaz a dispositif de post-combustion

Info

Publication number
BE810491A
BE810491A BE140448A BE140448A BE810491A BE 810491 A BE810491 A BE 810491A BE 140448 A BE140448 A BE 140448A BE 140448 A BE140448 A BE 140448A BE 810491 A BE810491 A BE 810491A
Authority
BE
Belgium
Prior art keywords
post
gas turbine
turbine engine
combustion device
combustion
Prior art date
Application number
BE140448A
Other languages
English (en)
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 filed Critical
Publication of BE810491A publication Critical patent/BE810491A/fr

Links

Classifications

    • C—CHEMISTRY; METALLURGY
    • C07—ORGANIC CHEMISTRY
    • C07D—HETEROCYCLIC COMPOUNDS
    • C07D277/00—Heterocyclic compounds containing 1,3-thiazole or hydrogenated 1,3-thiazole rings
    • C07D277/02—Heterocyclic compounds containing 1,3-thiazole or hydrogenated 1,3-thiazole rings not condensed with other rings
    • C07D277/20—Heterocyclic compounds containing 1,3-thiazole or hydrogenated 1,3-thiazole rings not condensed with other rings having two or three double bonds between ring members or between ring members and non-ring members
    • C07D277/587—Heterocyclic compounds containing 1,3-thiazole or hydrogenated 1,3-thiazole rings not condensed with other rings having two or three double bonds between ring members or between ring members and non-ring members with aliphatic hydrocarbon radicals substituted by carbon atoms having three bonds to hetero atoms with at the most one bond to halogen, e.g. ester or nitrile radicals, directly attached to ring carbon atoms, said aliphatic radicals being substituted in the alpha-position to the ring by a hetero atom, e.g. with m >= 0, Z being a singly or a doubly bound hetero atom
    • 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
    • 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; Infra-red radiation suppressors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • 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
BE140448A 1973-02-01 1974-02-01 Moteur a turbine a gaz a dispositif de post-combustion BE810491A (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US00328769A US3826088A (en) 1973-02-01 1973-02-01 Gas turbine engine augmenter cooling liner stabilizers and supports

Publications (1)

Publication Number Publication Date
BE810491A true BE810491A (fr) 1974-05-29

Family

ID=23282361

Family Applications (1)

Application Number Title Priority Date Filing Date
BE140448A BE810491A (fr) 1973-02-01 1974-02-01 Moteur a turbine a gaz a dispositif de post-combustion

Country Status (8)

Country Link
US (1) US3826088A (fr)
JP (1) JPS5920861B2 (fr)
BE (1) BE810491A (fr)
CA (1) CA995015A (fr)
DE (1) DE2404040C2 (fr)
FR (1) FR2216450B1 (fr)
GB (1) GB1454614A (fr)
IT (1) IT1007066B (fr)

Families Citing this family (62)

* Cited by examiner, † Cited by third party
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FR2288868A1 (fr) * 1973-12-03 1976-05-21 Snecma Canal d'ejection de turboreacteur et reacteur pourvu d'un tel canal
US4833881A (en) * 1984-12-17 1989-05-30 General Electric Company Gas turbine engine augmentor
US4718230A (en) * 1986-11-10 1988-01-12 United Technologies Corporation Augmentor liner construction
US4706453A (en) * 1986-11-12 1987-11-17 General Motors Corporation Support and seal assembly
US4866942A (en) * 1987-10-13 1989-09-19 The United States Of America As Represented By The Secretary Of The Air Force Augmentor curtain liner for equalizing pressure therein
US4854122A (en) * 1988-01-28 1989-08-08 The United States Of America As Represented By The Secretary Of The Air Force Augmentor curtain liner assembly for sharing tensile loading
US4864818A (en) * 1988-04-07 1989-09-12 United Technologies Corporation Augmentor liner construction
US4920742A (en) * 1988-05-31 1990-05-01 General Electric Company Heat shield for gas turbine engine frame
US4848081A (en) * 1988-05-31 1989-07-18 United Technologies Corporation Cooling means for augmentor liner
DE58908665D1 (de) * 1988-06-13 1995-01-05 Siemens Ag Hitzeschildanordnung mit geringem kühlfluidbedarf.
US4907946A (en) * 1988-08-10 1990-03-13 General Electric Company Resiliently mounted outlet guide vane
US4987736A (en) * 1988-12-14 1991-01-29 General Electric Company Lightweight gas turbine engine frame with free-floating heat shield
US4989406A (en) * 1988-12-29 1991-02-05 General Electric Company Turbine engine assembly with aft mounted outlet guide vanes
GB9127505D0 (en) * 1991-03-11 2013-12-25 Gen Electric Multi-hole film cooled afterburner combustor liner
US5201887A (en) * 1991-11-26 1993-04-13 United Technologies Corporation Damper for augmentor liners
FR2708086B1 (fr) * 1993-06-30 1995-09-01 Snecma Structure tubulaire sectorisée travaillant à l'implosion.
US5369952A (en) * 1993-07-20 1994-12-06 General Electric Company Variable friction force damper
US6199371B1 (en) 1998-10-15 2001-03-13 United Technologies Corporation Thermally compliant liner
US6171009B1 (en) * 1998-10-20 2001-01-09 Lockheed Martin Corporation Method and apparatus for temperature-stabilizing a joint
US6347508B1 (en) * 2000-03-22 2002-02-19 Allison Advanced Development Company Combustor liner support and seal assembly
US6668441B1 (en) * 2000-06-07 2003-12-30 Lockheed Martin Corporation Screw mounting installation method
FR2834533B1 (fr) * 2002-01-10 2004-10-29 Hurel Hispano Le Havre Dispositif de refroidissement de la tuyere commune sur une nacelle
US6866479B2 (en) * 2003-05-16 2005-03-15 Mitsubishi Heavy Industries, Ltd. Exhaust diffuser for axial-flow turbine
FR2856744B1 (fr) * 2003-06-25 2007-05-25 Snecma Moteurs Canaux de ventilation sur tole de confluence d'une chambre de post-combustion
FR2865002B1 (fr) * 2004-01-12 2006-05-05 Snecma Moteurs Turboreacteur a double flux comprenant un support de distribution de servitudes et le support de distribution de servitudes.
GB2432902B (en) * 2005-12-03 2011-01-12 Alstom Technology Ltd Gas turbine sub-assemblies
US7721522B2 (en) * 2006-01-05 2010-05-25 United Technologies Corporation Torque load transfer attachment hardware
US7581399B2 (en) * 2006-01-05 2009-09-01 United Technologies Corporation Damped coil pin for attachment hanger hinge
US7966823B2 (en) * 2006-01-06 2011-06-28 General Electric Company Exhaust dust flow splitter system
FR2899280B1 (fr) * 2006-03-30 2012-08-31 Snecma Dispositif de montage d'une paroi de separation de flux dans une chambre de post-combustion d'un turboreacteur
FR2900444B1 (fr) * 2006-04-28 2008-06-13 Snecma Sa Turboreacteur comprenant un canal de post combustion refroidi par un flux de ventilation a debit variable
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
GB2449477B (en) * 2007-05-24 2009-05-13 Rolls Royce Plc A duct installation
US8312726B2 (en) * 2007-12-21 2012-11-20 United Technologies Corp. Gas turbine engine systems involving I-beam struts
US10132196B2 (en) 2007-12-21 2018-11-20 United Technologies Corporation Gas turbine engine systems involving I-beam struts
FR2964415B1 (fr) * 2010-09-08 2015-11-13 Snecma Treillis hyperstatique de suspension de moteur
FR2976974B1 (fr) * 2011-06-24 2016-09-30 Safran Dispositif d'assemblage de panneaux acoustiques d'une nacelle de turbomachine
WO2013157976A1 (fr) * 2012-04-19 2013-10-24 General Electric Company Butée de chemise de chambre de combustion
US9309834B2 (en) 2012-05-31 2016-04-12 United Technologies Corporation Liner hanger cable
US9316174B2 (en) 2012-06-04 2016-04-19 United Technologies Corporation Liner hanger with spherical washers
US10253651B2 (en) 2012-06-14 2019-04-09 United Technologies Corporation Turbomachine flow control device
EP2679780B8 (fr) * 2012-06-28 2016-09-14 General Electric Technology GmbH Diffuseur pour section d'échappement d'une turbine à gaz et turbine à gaz dotée d'un tel diffuseur
US20140026590A1 (en) * 2012-07-25 2014-01-30 Hannes A. Alholm Flexible combustor bracket
US9133768B2 (en) 2012-08-21 2015-09-15 United Technologies Corporation Liner bracket for gas turbine engine
FR2994712B1 (fr) * 2012-08-27 2018-04-13 Safran Aircraft Engines Procede d'assemblage d'une tuyere et d'un carter d'echappement d'une turbomachine
US9366185B2 (en) * 2012-09-28 2016-06-14 United Technologies Corporation Flexible connection between a wall and a case of a turbine engine
US9309833B2 (en) 2012-10-22 2016-04-12 United Technologies Corporation Leaf spring hanger for exhaust duct liner
US10054080B2 (en) 2012-10-22 2018-08-21 United Technologies Corporation Coil spring hanger for exhaust duct liner
GB201302125D0 (en) * 2013-02-07 2013-03-20 Rolls Royce Plc A panel mounting arrangement
WO2014126641A1 (fr) 2013-02-14 2014-08-21 United Technologies Corporation Ensemble support de chemise de protection thermique adaptatif destiné à des moteurs de turbine à gaz
US9188024B2 (en) 2013-02-22 2015-11-17 Pratt & Whitney Canada Corp. Exhaust section for bypass gas turbine engines
FR3004494B1 (fr) * 2013-04-15 2018-01-19 Safran Nacelles Tuyere pour turbopropulseur d’aeronef a soufflante non carenee
WO2015001927A1 (fr) * 2013-07-04 2015-01-08 株式会社Ihi Mécanisme de transmission de puissance d'actionneur et turbocompresseur
GB2517203B (en) * 2013-08-16 2016-07-20 Rolls Royce Plc A panel attachment system
WO2015119754A1 (fr) * 2014-02-04 2015-08-13 United Technologies Corporation Supports pour composants de moteur à turbine à gaz
GB2525197A (en) * 2014-04-15 2015-10-21 Rolls Royce Plc A panel attachment system and a method of using the same
US10385868B2 (en) * 2016-07-05 2019-08-20 General Electric Company Strut assembly for an aircraft engine
US10533457B2 (en) 2017-05-11 2020-01-14 United Technologies Corporation Exhaust liner cable fastener
GB201717768D0 (en) * 2017-10-30 2017-12-13 Rolls Royce Plc Gas turbine exhaust cooling system
US11293637B2 (en) * 2018-10-15 2022-04-05 Raytheon Technologies Corporation Combustor liner attachment assembly for gas turbine engine
US11255547B2 (en) * 2018-10-15 2022-02-22 Raytheon Technologies Corporation Combustor liner attachment assembly for gas turbine engine
US11105222B1 (en) 2020-02-28 2021-08-31 Pratt & Whitney Canada Corp. Integrated thermal protection for an exhaust case assembly

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2581999A (en) * 1946-02-01 1952-01-08 Gen Electric Hemispherical combustion chamber end dome having cooling air deflecting means
US2544538A (en) * 1948-12-01 1951-03-06 Wright Aeronautical Corp Liner for hot gas chambers
GB675300A (en) * 1949-05-24 1952-07-09 Rolls Royce Improvements in or relating to exhaust ducting of gas-turbine engines
US2846842A (en) * 1952-10-25 1958-08-12 United Aircraft Corp Afterburner shroud construction
US2801520A (en) * 1954-08-05 1957-08-06 Axel L Highberg Removable burner cans
US2851854A (en) * 1955-01-21 1958-09-16 United Aircraft Corp Afterburner liner
US3138930A (en) * 1961-09-26 1964-06-30 Gen Electric Combustion chamber liner construction
GB1183143A (en) * 1968-01-17 1970-03-04 Rolls Royce Improvements in or relating to the Mounting of a Liner in a Duct

Also Published As

Publication number Publication date
JPS49105018A (fr) 1974-10-04
FR2216450B1 (fr) 1980-06-27
GB1454614A (en) 1976-11-03
JPS5920861B2 (ja) 1984-05-16
US3826088A (en) 1974-07-30
IT1007066B (it) 1976-10-30
CA995015A (en) 1976-08-17
DE2404040C2 (de) 1983-09-01
FR2216450A1 (fr) 1974-08-30
DE2404040A1 (de) 1974-08-08

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