GB1414412A - Chamber assembly for use in a continuous combustion process - Google Patents

Chamber assembly for use in a continuous combustion process

Info

Publication number
GB1414412A
GB1414412A GB2155673A GB2155673A GB1414412A GB 1414412 A GB1414412 A GB 1414412A GB 2155673 A GB2155673 A GB 2155673A GB 2155673 A GB2155673 A GB 2155673A GB 1414412 A GB1414412 A GB 1414412A
Authority
GB
United Kingdom
Prior art keywords
chamber
mixing chamber
inlet
combustion chamber
air
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
GB2155673A
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.)
Ford Motor Co Ltd
Ford Motor Co
Original Assignee
Ford Motor Co Ltd
Ford Motor 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
Priority to US25688372 priority Critical patent/US3859786A/en
Application filed by Ford Motor Co Ltd, Ford Motor Co filed Critical Ford Motor Co Ltd
Publication of GB1414412A publication Critical patent/GB1414412A/en
Expired legal-status Critical Current

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/26Controlling the air flow
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/007Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04Air inlet arrangements
    • F23R3/10Air inlet arrangements for primary air
    • F23R3/12Air inlet arrangements for primary air inducing a vortex

Abstract

1414412 Gas turbine combustion chambers FORD MOTOR CO Ltd 7 May 1973 [25 May 1972] 21556/73 Heading F1L Cumbustion equipment comprises a mixing chamber having an inlet and an outlet there being means adjacent the inlet for producing a toroidal swirl in air under pressure flowing through the mixing chamber also means for supplying fuel adjacent the inlet, the mixing chamber opening into a combustion chamber, there being ignition means to cause ignition of the fuel/air mixture. A further chamber is provided in which the gases from the combustion chamber are cooled. In Fig. 1 the combustion equipment comprises a mixing chamber A, a combustion chamber B, and a dilution chamber C, the mixing chamber extending around the combustion chamber. The mixing chamber A has an air inlet 16 comprising swirl vanes 16a and a fuel injector 15 disposed at the axis 14. Air under pressure is supplied from a comcompressor to the space between the outer casing 28 and the mixing chamber and passes to the inlet 16. The combustion chamber comprises a shell 5 formed with a series of tangentially-directed inlets 8 also a ceramic member 18 formed with inlets 20a which are aligned with the tangential inlets 8. The plurality of inlets 8 constitute air inlet D from the air/fuel mixing chamber A into the combustion chamber B. An ignition device F projects into the combustion chamber. The combustion chamber terminates in a restricted outlet 24 formed by an inwardly projected flange 23a of the ceramic member. The outlet opens to a dilution chamber C to which cooling or dilution air is supplied through the annular passage between the wall I of the mixing chamber and the outer wall 28, the air passing into the dilution chamber through inlet openings 31a the flow area of which may be controlled by an axially movable ring valve 34.
GB2155673A 1972-05-25 1973-05-07 Chamber assembly for use in a continuous combustion process Expired GB1414412A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US25688372 US3859786A (en) 1972-05-25 1972-05-25 Combustor

Publications (1)

Publication Number Publication Date
GB1414412A true GB1414412A (en) 1975-11-19

Family

ID=22973991

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2155673A Expired GB1414412A (en) 1972-05-25 1973-05-07 Chamber assembly for use in a continuous combustion process

Country Status (5)

Country Link
US (1) US3859786A (en)
JP (1) JPS5319722B2 (en)
CA (1) CA982829A (en)
DE (1) DE2326302C2 (en)
GB (1) GB1414412A (en)

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US4084371A (en) * 1974-07-24 1978-04-18 Howald Werner E Combustion apparatus including an air-fuel premixing chamber
GB1520402A (en) * 1974-07-30 1978-08-09 Mitsubishi Electric Corp Combustion apparatus
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JPS5129726A (en) * 1974-09-06 1976-03-13 Mitsubishi Heavy Ind Ltd Nenryononenshosochi
FR2289738A2 (en) * 1974-10-30 1976-05-28 Engelhard Min & Chem Method and apparatus for obtaining a sustained combustion in a gas turbine
US3938324A (en) * 1974-12-12 1976-02-17 General Motors Corporation Premix combustor with flow constricting baffle between combustion and dilution zones
JPS5181035A (en) * 1975-01-11 1976-07-15 Kubota Ltd Kyoshonenshoshitsuniokerukaenondonokojohohonarabisochi
US4049021A (en) * 1975-04-14 1977-09-20 Phillips Petroleum Company Variable dome valves and combustors provided with said valves
IT1075001B (en) * 1975-04-14 1985-04-22 Phillips Petroleum Co Combustion chambers, particularly for gas turbine engines and method to make them work
US4012904A (en) * 1975-07-17 1977-03-22 Chrysler Corporation Gas turbine burner
AR207091A1 (en) * 1975-09-29 1976-09-09 Westinghouse Electric Corp Combustion chamber arrangement for gas turbine
JPS5260507U (en) * 1975-10-30 1977-05-02
DE2629761A1 (en) * 1976-07-02 1978-01-05 Volkswagenwerk Ag Combustion chamber for gas turbines
GB1592858A (en) * 1977-01-21 1981-07-08 Rolls Royce Combustion equipment for gas turbine engines
US4120640A (en) * 1977-02-18 1978-10-17 Infern-O-Therm Corporation Burner for liquid fuel
JPS5632877Y2 (en) * 1977-04-30 1981-08-04
JPS625521Y2 (en) * 1977-10-25 1987-02-07
DE2832970A1 (en) * 1978-07-27 1980-02-07 Schmidt Gmbh Karl Built liquid-cooled piston for internal combustion engines
US4385490A (en) * 1978-08-14 1983-05-31 Phillips Petroleum Company Combustors and methods of operating same
US4498287A (en) * 1980-12-23 1985-02-12 Phillips Petroleum Company Combustors and methods of operating same
US4246757A (en) * 1979-03-27 1981-01-27 General Electric Company Combustor including a cyclone prechamber and combustion process for gas turbines fired with liquid fuel
US4590769A (en) * 1981-01-12 1986-05-27 United Technologies Corporation High-performance burner construction
US4845940A (en) * 1981-02-27 1989-07-11 Westinghouse Electric Corp. Low NOx rich-lean combustor especially useful in gas turbines
DE3301355C2 (en) * 1983-01-18 1984-11-08 Deutsche Forschungs- Und Versuchsanstalt Fuer Luft- Und Raumfahrt E.V., 5000 Koeln, De
US4702073A (en) * 1986-03-10 1987-10-27 Melconian Jerry O Variable residence time vortex combustor
DE3742891A1 (en) * 1987-12-17 1989-06-29 Bayerische Motoren Werke Ag Gas turbine system
US5285628A (en) * 1990-01-18 1994-02-15 Donlee Technologies, Inc. Method of combustion and combustion apparatus to minimize Nox and CO emissions from a gas turbine
US5462430A (en) * 1991-05-23 1995-10-31 Institute Of Gas Technology Process and apparatus for cyclonic combustion
US5220888A (en) * 1991-08-01 1993-06-22 Institute Of Gas Technology Cyclonic combustion
US5209187A (en) * 1991-08-01 1993-05-11 Institute Of Gas Technology Low pollutant - emission, high efficiency cyclonic burner for firetube boilers and heaters
US5185541A (en) * 1991-12-02 1993-02-09 21St Century Power & Light Corporation Gas turbine for converting fuel to electrical and mechanical energy
DE4232383A1 (en) * 1992-09-26 1994-03-31 Asea Brown Boveri Gas turbine group
DE69431969T2 (en) * 1993-07-30 2003-10-30 United Technologies Corp Vortex mixing device for a combustion chamber
EP0660046B1 (en) * 1993-12-22 1999-12-01 Siemens Westinghouse Power Corporation Combustor bybass system for a gas turbine
DE4435266A1 (en) * 1994-10-01 1996-04-04 Abb Management Ag Burner
US5601789A (en) * 1994-12-15 1997-02-11 W. R. Grace & Co.-Conn. Raw gas burner and process for burning oxygenic constituents in process gas
DE19523094A1 (en) * 1995-06-26 1997-01-02 Abb Management Ag Combustion chamber
EP0918190A1 (en) * 1997-11-21 1999-05-26 Abb Research Ltd. Burner for the operation of a heat generator
US6240731B1 (en) * 1997-12-31 2001-06-05 United Technologies Corporation Low NOx combustor for gas turbine engine
US6983645B2 (en) * 2002-08-06 2006-01-10 Southwest Research Institute Method for accelerated aging of catalytic converters incorporating engine cold start simulation
US20040007056A1 (en) * 2001-08-06 2004-01-15 Webb Cynthia C. Method for testing catalytic converter durability
US7412335B2 (en) 2002-08-06 2008-08-12 Southwest Research Institute Component evaluations using non-engine based test system
US6729141B2 (en) * 2002-07-03 2004-05-04 Elliot Energy Systems, Inc. Microturbine with auxiliary air tubes for NOx emission reduction
US7617682B2 (en) * 2002-12-13 2009-11-17 Siemens Energy, Inc. Catalytic oxidation element for a gas turbine engine
WO2005017420A2 (en) * 2003-08-12 2005-02-24 L.B. White Co., Inc. Direct-fired, gas-fueled heater
US8425224B2 (en) 2005-03-17 2013-04-23 Southwest Research Institute Mass air flow compensation for burner-based exhaust gas generation system
WO2006101987A2 (en) * 2005-03-17 2006-09-28 Southwest Research Institute Use of recirculated exhaust gas in a burner-based exhaust generation system for reduced fuel consumption and for cooling
US20070039381A1 (en) * 2005-08-05 2007-02-22 Timmons Suzanne A Secondary Air Injector For Use With Exhaust Gas Simulation System
US8475124B2 (en) * 2007-11-13 2013-07-02 General Electric Company Exhaust hood for a turbine and methods of assembling the same
CA2710280A1 (en) * 2007-12-21 2009-07-09 Green Partners Technology Holdings Gmbh Gas turbine systems and methods employing a vaporizable liquid delivery device
EP2257736B1 (en) * 2008-03-07 2015-11-25 Alstom Technology Ltd Method for the production of hot gas
WO2009109452A1 (en) * 2008-03-07 2009-09-11 Alstom Technology Ltd Burner arrangement, and use of such a burner arrangement
US8622737B2 (en) 2008-07-16 2014-01-07 Robert S. Babington Perforated flame tube for a liquid fuel burner
US8745989B2 (en) * 2009-04-09 2014-06-10 Pratt & Whitney Canada Corp. Reverse flow ceramic matrix composite combustor
US9222674B2 (en) * 2011-07-21 2015-12-29 United Technologies Corporation Multi-stage amplification vortex mixture for gas turbine engine combustor
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US2621477A (en) * 1948-06-03 1952-12-16 Power Jets Res & Dev Ltd Combustion apparatus having valve controlled passages for preheating the fuel-air mixture
US2635564A (en) * 1948-09-15 1953-04-21 Power Jets Res & Dev Ltd Combustion system for pulverulent fuel
US2837893A (en) * 1952-12-12 1958-06-10 Phillips Petroleum Co Automatic primary and secondary air flow regulation for gas turbine combustion chamber
GB854135A (en) * 1958-03-05 1960-11-16 Rolls Royce Improvements in or relating to combustion equipment
FR1094871A (en) * 1959-01-22 1955-05-25 Thomson Houston Comp Francaise Improvements to injected fuel combustion apparatus
US3293852A (en) * 1963-03-19 1966-12-27 Boeing Co Plasma propulsion method and means
GB1039133A (en) * 1963-05-15 1966-08-17 Lucas Industries Ltd Liquid fuel combustion apparatus for gas turbine engines
US3360929A (en) * 1966-03-10 1968-01-02 Montrose K. Drewry Gas turbine combustors
US3368604A (en) * 1966-06-14 1968-02-13 American Air Filter Co Combustion apparatus
GB1256066A (en) * 1967-11-10 1971-12-08 Lucas Industries Ltd Flame tubes for gas turbine engines
GB1240009A (en) * 1968-07-27 1971-07-21 Leyland Gas Turbines Ltd Flame tube
GB1278590A (en) * 1968-09-20 1972-06-21 Lucas Industries Ltd Combustion chambers for gas turbine engines
US3570242A (en) * 1970-04-20 1971-03-16 United Aircraft Corp Fuel premixing for smokeless jet engine main burner
US3691762A (en) * 1970-12-04 1972-09-19 Caterpillar Tractor Co Carbureted reactor combustion system for gas turbine engine

Also Published As

Publication number Publication date
JPS4949011A (en) 1974-05-13
JPS5319722B2 (en) 1978-06-22
CA982829A (en) 1976-02-03
US3859786A (en) 1975-01-14
DE2326302A1 (en) 1974-01-17
DE2326302C2 (en) 1983-01-05
CA982829A1 (en)

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Legal Events

Date Code Title Description
PS Patent sealed
435 Patent endorsed 'licences of right' on the date specified (sect. 35/1949)
PCNP Patent ceased through non-payment of renewal fee