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
air
combustion chamber
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
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

    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/26—Controlling the air flow
    • 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
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Air Supply (AREA)
  • Combustion Of Fluid Fuel (AREA)

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)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US256883A 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)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111927625A (en) * 2020-07-13 2020-11-13 西安航天动力研究所 Two-phase rotary detonation combustion cavity structure capable of stably and controllably unidirectionally spreading rotary detonation wave

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JPS5181035A (en) * 1975-01-11 1976-07-15 Kubota Ltd KYOSHONENSHOSHITSUNIOKERUKAENONDONOKOJOHOHONARABISOCHI
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US4049021A (en) * 1975-04-14 1977-09-20 Phillips Petroleum Company Variable dome valves and combustors provided with said valves
US4012904A (en) * 1975-07-17 1977-03-22 Chrysler Corporation Gas turbine burner
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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 für Luft- und Raumfahrt e.V., 5000 Köln Jump start device for a high pressure combustion chamber
US4702073A (en) * 1986-03-10 1987-10-27 Melconian Jerry O Variable residence time vortex combustor
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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
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US5209187A (en) * 1991-08-01 1993-05-11 Institute Of Gas Technology Low pollutant - emission, high efficiency cyclonic burner for firetube boilers and heaters
US5220888A (en) * 1991-08-01 1993-06-22 Institute Of Gas Technology Cyclonic combustion
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
DE69421766T2 (en) * 1993-07-30 2000-06-21 United Technologies Corp., Hartford Vortex mixing device for a combustion chamber
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DE4435266A1 (en) * 1994-10-01 1996-04-04 Abb Management Ag burner
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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
US20040007056A1 (en) * 2001-08-06 2004-01-15 Webb Cynthia C. Method for testing catalytic converter durability
US6983645B2 (en) * 2002-08-06 2006-01-10 Southwest Research Institute Method for accelerated aging of catalytic converters incorporating engine cold start simulation
US6729141B2 (en) * 2002-07-03 2004-05-04 Elliot Energy Systems, Inc. Microturbine with auxiliary air tubes for NOx emission reduction
US7412335B2 (en) 2002-08-06 2008-08-12 Southwest Research Institute Component evaluations using non-engine based test system
US7617682B2 (en) * 2002-12-13 2009-11-17 Siemens Energy, Inc. Catalytic oxidation element for a gas turbine engine
US20050051155A1 (en) * 2003-08-12 2005-03-10 Tomlinson John L. 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
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JP5453322B2 (en) * 2008-03-07 2014-03-26 アルストム テクノロジー リミテッド Burner device and use of burner device
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CN110107402B (en) * 2019-04-29 2021-06-08 中国航空工业集团公司金城南京机电液压工程研究中心 Ceramic turbine engine
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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

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111927625A (en) * 2020-07-13 2020-11-13 西安航天动力研究所 Two-phase rotary detonation combustion cavity structure capable of stably and controllably unidirectionally spreading rotary detonation wave
CN111927625B (en) * 2020-07-13 2022-08-19 西安航天动力研究所 Two-phase rotary detonation combustion cavity structure capable of stably and controllably unidirectionally spreading rotary detonation wave

Also Published As

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

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
435 Patent endorsed 'licences of right' on the date specified (sect. 35/1949)
PCNP Patent ceased through non-payment of renewal fee