GB1454614A - Gas turbine engines including exhaust reheat combustion equipment - Google Patents

Gas turbine engines including exhaust reheat combustion equipment

Info

Publication number
GB1454614A
GB1454614A GB333274A GB333274A GB1454614A GB 1454614 A GB1454614 A GB 1454614A GB 333274 A GB333274 A GB 333274A GB 333274 A GB333274 A GB 333274A GB 1454614 A GB1454614 A GB 1454614A
Authority
GB
United Kingdom
Prior art keywords
liner
gas turbine
reheat combustion
reheat
combustion equipment
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
Application number
GB333274A
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
Publication of GB1454614A publication Critical patent/GB1454614A/en
Expired legal-status Critical Current

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; Infrared 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

Landscapes

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

Abstract

1454614 Gas turbine engine reheat combustion equipment GENERAL ELECTRIC CO 24 Jan 1974 [1 Feb 1973] 03332/74 Headings F1L and F1J The invention relates to a gas turbine engine of the kind having reheat combustion equipment located in the exhaust duct thereof and comprising a liner mounted within the exhaust duct. The engine shown is of the by-pass type and comprises a mixer (32) Fig. 1, (not shown) in which turbine exhaust gases and by-pass air are mixed. The reheat combustion section (40) is defined by a liner 46 mounted within the jet pipe 44 so as to define a cooling air-flow path 48 therebetween the liner being formed with openings 54 through which the cooling air flows into reheat combustion zone. Reheat fuel injectors are indicated at (36). The combustion liner 46 is supported by a number of mounting devices 64 each of which comprise a pad 66 secured to the liner, a strut 70 and an outer pad 68, the pad 68 being received within a C-shaped bracket 74 which is secured to the jet pipe 44, a circular band 80 being disposed therebetween. The band 80 is formed with a gap whereby the band may be contracted to permit assembly.
GB333274A 1973-02-01 1974-01-24 Gas turbine engines including exhaust reheat combustion equipment Expired GB1454614A (en)

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
GB1454614A true GB1454614A (en) 1976-11-03

Family

ID=23282361

Family Applications (1)

Application Number Title Priority Date Filing Date
GB333274A Expired GB1454614A (en) 1973-02-01 1974-01-24 Gas turbine engines including exhaust reheat combustion equipment

Country Status (8)

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

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2525197A (en) * 2014-04-15 2015-10-21 Rolls Royce Plc A panel attachment system and a method of using the same

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FR2288868A1 (en) * 1973-12-03 1976-05-21 Snecma TURBOREACTOR AND REACTOR EJECTION CHANNEL PROVIDED WITH SUCH A CHANNEL
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
US4848081A (en) * 1988-05-31 1989-07-18 United Technologies Corporation Cooling means for augmentor liner
US4920742A (en) * 1988-05-31 1990-05-01 General Electric Company Heat shield for gas turbine engine frame
JPH03504999A (en) * 1988-06-13 1991-10-31 シーメンス、アクチエンゲゼルシヤフト Thermal shielding devices for structures conducting high temperature fluids
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 (en) * 1993-06-30 1995-09-01 Snecma Sectorized tubular structure working on 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 (en) * 2002-01-10 2004-10-29 Hurel Hispano Le Havre DEVICE FOR COOLING THE COMMON NOZZLE ON A NACELLE
US6866479B2 (en) * 2003-05-16 2005-03-15 Mitsubishi Heavy Industries, Ltd. Exhaust diffuser for axial-flow turbine
FR2856744B1 (en) * 2003-06-25 2007-05-25 Snecma Moteurs VENTILATION CHANNELS ON POST-COMBUSTION CHAMBER CONFLUENCE ROOF
FR2865002B1 (en) * 2004-01-12 2006-05-05 Snecma Moteurs DOUBLE FLOW TURBOREACTOR COMPRISING A SERVITUDE DISTRIBUTION SUPPORT AND THE SERVITUDE DISTRIBUTION SUPPORT.
GB2432902B (en) * 2005-12-03 2011-01-12 Alstom Technology Ltd Gas turbine sub-assemblies
US7581399B2 (en) * 2006-01-05 2009-09-01 United Technologies Corporation Damped coil pin for attachment hanger hinge
US7721522B2 (en) * 2006-01-05 2010-05-25 United Technologies Corporation Torque load transfer attachment hardware
US7966823B2 (en) * 2006-01-06 2011-06-28 General Electric Company Exhaust dust flow splitter system
FR2899280B1 (en) * 2006-03-30 2012-08-31 Snecma DEVICE FOR MOUNTING A FLOW SEPARATION WALL IN A POST-COMBUSTION CHAMBER OF A TURBOREACTOR
FR2900444B1 (en) * 2006-04-28 2008-06-13 Snecma Sa TURBOREACTOR COMPRISING A POST COMBUSTION CHANNEL COOLED BY A VARIABLE FLOW VENTILATION FLOW
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 (en) * 2010-09-08 2015-11-13 Snecma HYPERSTATIC MOTOR SUSPENSION TRELLIS
FR2976974B1 (en) * 2011-06-24 2016-09-30 Safran DEVICE FOR ASSEMBLING ACOUSTIC PANELS OF A TURBOMACHINE NACELLE
US20150068212A1 (en) * 2012-04-19 2015-03-12 General Electric Company Combustor liner stop
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 (en) * 2012-06-28 2016-09-14 General Electric Technology GmbH Diffuser for the exhaust section of a gas turbine and gas turbine with such a diffuser
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 (en) * 2012-08-27 2018-04-13 Safran Aircraft Engines METHOD FOR ASSEMBLING A TUBE AND AN EXHAUST HOUSING OF A 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
US10077681B2 (en) 2013-02-14 2018-09-18 United Technologies Corporation Compliant heat shield liner hanger assembly for gas turbine engines
US9188024B2 (en) 2013-02-22 2015-11-17 Pratt & Whitney Canada Corp. Exhaust section for bypass gas turbine engines
FR3004494B1 (en) * 2013-04-15 2018-01-19 Safran Nacelles TUYERE FOR AIRCRAFT TURBOPROPULSER WITH NON-CARBONATED BLOWER
WO2015001927A1 (en) * 2013-07-04 2015-01-08 株式会社Ihi Actuator power transmission mechanism and supercharger
GB2517203B (en) * 2013-08-16 2016-07-20 Rolls Royce Plc A panel attachment system
WO2015119754A1 (en) * 2014-02-04 2015-08-13 United Technologies Corporation Brackets for gas turbine engine components
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

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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

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2525197A (en) * 2014-04-15 2015-10-21 Rolls Royce Plc A panel attachment system and a method of using the same

Also Published As

Publication number Publication date
BE810491A (en) 1974-05-29
DE2404040C2 (en) 1983-09-01
CA995015A (en) 1976-08-17
FR2216450B1 (en) 1980-06-27
DE2404040A1 (en) 1974-08-08
JPS5920861B2 (en) 1984-05-16
US3826088A (en) 1974-07-30
JPS49105018A (en) 1974-10-04
IT1007066B (en) 1976-10-30
FR2216450A1 (en) 1974-08-30

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PCNP Patent ceased through non-payment of renewal fee

Effective date: 19930124