GB1314970A - Annular combustion chamber for dissimilar fluids in swirling flow relationship - Google Patents

Annular combustion chamber for dissimilar fluids in swirling flow relationship

Info

Publication number
GB1314970A
GB1314970A GB3455271A GB3455271A GB1314970A GB 1314970 A GB1314970 A GB 1314970A GB 3455271 A GB3455271 A GB 3455271A GB 3455271 A GB3455271 A GB 3455271A GB 1314970 A GB1314970 A GB 1314970A
Authority
GB
United Kingdom
Prior art keywords
annular
walls
passages
fluids
fuel
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
GB3455271A
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.)
Raytheon Technologies Corp
Original Assignee
United Aircraft Corp
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 United Aircraft Corp filed Critical United Aircraft Corp
Publication of GB1314970A publication Critical patent/GB1314970A/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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • 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
    • F02K1/38—Introducing air inside the jet
    • F02K1/386—Introducing air inside the jet mixing devices in the jet pipe, e.g. for mixing primary and secondary flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02G—HOT GAS OR COMBUSTION-PRODUCT POSITIVE-DISPLACEMENT ENGINE PLANTS; USE OF WASTE HEAT OF COMBUSTION ENGINES; NOT OTHERWISE PROVIDED FOR
    • F02G2243/00—Stirling type engines having closed regenerative thermodynamic cycles with flow controlled by volume changes
    • F02G2243/30—Stirling type engines having closed regenerative thermodynamic cycles with flow controlled by volume changes having their pistons and displacers each in separate cylinders
    • F02G2243/50—Stirling type engines having closed regenerative thermodynamic cycles with flow controlled by volume changes having their pistons and displacers each in separate cylinders having resonance tubes
    • F02G2243/52—Stirling type engines having closed regenerative thermodynamic cycles with flow controlled by volume changes having their pistons and displacers each in separate cylinders having resonance tubes acoustic
    • 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)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Spray-Type Burners (AREA)

Abstract

1314970 Combustion apparatus for gas turbine engines &c UNITED AIRCRAFT CORP 23 July 1971 [26 Oct 1970] 34552/71 Heading F1L An annular combustion chamber comprises an inner wall and an outer wall which define annular passages therebetween leading to a combustion zone, at least two dissimilar fluids being directed in swirling relation through the annular passages, the first of the fluids having a density #1 and a tangential velocity vtl and the second of the fluids having a density p2 and a tangential velocity vt2 means being provided to establish the product parameter #vt<2> of one of the fluids to be different from the corresponding product parameter of the other fluid so as to influence intermixing therebetween. Many embodiments of the invention are described. In Fig. 47 for example the annular combustion chamber is defined between inner and outer air casing walls 113, 54 and a series of annular walls 134, 138a, 140a, 138b and 140b is disposed at the inlet end'to define together with the casing walls 54, 113 dilution air passages 122, 130, 132, a pilot combustion passage 124a, a fuel and air mixing passage 126a a fuel and air mixing passage 124b and a fuel and air mixing passage 126b. Rings of swirl waves 116, 118a, 120a, 118b, 120b and 128 are disposed at the upstream ends of the passages. Flame holder devices in the form of perforated frusto-conical walls 161a, 161b are provided in the passages 124a, 124b. Fuel injection devices 422, 424, 426 are provided. Trigger devices 164, 166, 169 are provided at the downstream ends of the walls 138a, 138b, 140b to facilitate burning. The annular flame tube is defined by the walls 134, 140b together with downstream extensions which are radially spaced apart by swirl waves 172, 174, 176, 168, 170. The air inlet from the compressor is indicated at 114 and the outlet to the turbine at 46. The axis of the chamber is shown at 16, the pilot combustion zone at 160a, the main combustion zone at 60 and the dilution zone at 62.
GB3455271A 1970-10-26 1971-07-23 Annular combustion chamber for dissimilar fluids in swirling flow relationship Expired GB1314970A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US8408670A 1970-10-26 1970-10-26

Publications (1)

Publication Number Publication Date
GB1314970A true GB1314970A (en) 1973-04-26

Family

ID=22182799

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3455271A Expired GB1314970A (en) 1970-10-26 1971-07-23 Annular combustion chamber for dissimilar fluids in swirling flow relationship

Country Status (7)

Country Link
US (1) US3788065A (en)
AU (1) AU451788B2 (en)
CA (1) CA954313A (en)
DE (1) DE2153085A1 (en)
FR (1) FR2112339B1 (en)
GB (1) GB1314970A (en)
SE (1) SE389893B (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2269449A (en) * 1992-08-05 1994-02-09 Snecma Combustion chamber with fuel injectors of different types

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FR2221621B1 (en) * 1973-03-13 1976-09-10 Snecma
US3872664A (en) * 1973-10-15 1975-03-25 United Aircraft Corp Swirl combustor with vortex burning and mixing
US3999378A (en) * 1974-01-02 1976-12-28 General Electric Company Bypass augmentation burner arrangement for a gas turbine engine
US3974646A (en) * 1974-06-11 1976-08-17 United Technologies Corporation Turbofan engine with augmented combustion chamber using vorbix principle
US3937008A (en) * 1974-12-18 1976-02-10 United Technologies Corporation Low emission combustion chamber
US4058977A (en) * 1974-12-18 1977-11-22 United Technologies Corporation Low emission combustion chamber
US3973395A (en) * 1974-12-18 1976-08-10 United Technologies Corporation Low emission combustion chamber
US3973390A (en) * 1974-12-18 1976-08-10 United Technologies Corporation Combustor employing serially staged pilot combustion, fuel vaporization, and primary combustion zones
US4045956A (en) * 1974-12-18 1977-09-06 United Technologies Corporation Low emission combustion chamber
US3931707A (en) * 1975-01-08 1976-01-13 General Electric Company Augmentor flameholding apparatus
US3993449A (en) * 1975-04-07 1976-11-23 City Of North Olmsted Apparatus for pollution abatement
FR2312653A2 (en) * 1975-05-30 1976-12-24 Snecma Secondary combustion chamber for gas turbine - has additional fuel supplied through holes in radial vanes for improved combustion
US4012904A (en) * 1975-07-17 1977-03-22 Chrysler Corporation Gas turbine burner
US4204402A (en) * 1976-05-07 1980-05-27 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Reduction of nitric oxide emissions from a combustor
US4149373A (en) * 1977-08-29 1979-04-17 United Technologies Corporation Combustion chamber stress reducing means
US4194358A (en) * 1977-12-15 1980-03-25 General Electric Company Double annular combustor configuration
US4226083A (en) * 1978-01-19 1980-10-07 United Technologies Corporation Method and apparatus for reducing nitrous oxide emissions from combustors
US4389848A (en) * 1981-01-12 1983-06-28 United Technologies Corporation Burner construction for gas turbines
US4928479A (en) * 1987-12-28 1990-05-29 Sundstrand Corporation Annular combustor with tangential cooling air injection
US5076053A (en) * 1989-08-10 1991-12-31 United Technologies Corporation Mechanism for accelerating heat release of combusting flows
US5207064A (en) * 1990-11-21 1993-05-04 General Electric Company Staged, mixed combustor assembly having low emissions
US5197278A (en) * 1990-12-17 1993-03-30 General Electric Company Double dome combustor and method of operation
US5406799A (en) * 1992-06-12 1995-04-18 United Technologies Corporation Combustion chamber
US5335501A (en) * 1992-11-16 1994-08-09 General Electric Company Flow spreading diffuser
US5470224A (en) * 1993-07-16 1995-11-28 Radian Corporation Apparatus and method for reducing NOx , CO and hydrocarbon emissions when burning gaseous fuels
US5407347A (en) * 1993-07-16 1995-04-18 Radian Corporation Apparatus and method for reducing NOx, CO and hydrocarbon emissions when burning gaseous fuels
JPH08270950A (en) * 1995-02-01 1996-10-18 Mitsubishi Heavy Ind Ltd Gas turbine combustor
US6058710A (en) * 1995-03-08 2000-05-09 Bmw Rolls-Royce Gmbh Axially staged annular combustion chamber of a gas turbine
US6125627A (en) * 1998-08-11 2000-10-03 Allison Advanced Development Company Method and apparatus for spraying fuel within a gas turbine engine
DE59812944D1 (en) * 1998-09-16 2005-08-25 Alstom Technology Ltd Baden Method for preventing flow instabilities in a burner
CA2501862C (en) * 2002-10-10 2010-09-21 Combustion Science & Engineering, Inc. System for vaporization of liquid fuels for combustion and method of use
BRPI0518830B1 (en) * 2004-12-08 2019-06-04 Lpp Combustion,Llc METHOD AND APPARATUS FOR CONDITIONING FUELS OF LIQUID HYDROCARBON
US8529646B2 (en) * 2006-05-01 2013-09-10 Lpp Combustion Llc Integrated system and method for production and vaporization of liquid hydrocarbon fuels for combustion
US7827797B2 (en) * 2006-09-05 2010-11-09 General Electric Company Injection assembly for a combustor
EP2006606A1 (en) * 2007-06-21 2008-12-24 Siemens Aktiengesellschaft Swirling-free stabilising of the flame of a premix burner
US7775791B2 (en) * 2008-02-25 2010-08-17 General Electric Company Method and apparatus for staged combustion of air and fuel
FR2941742B1 (en) * 2009-02-05 2011-08-19 Snecma DIFFUSER-RECTIFIER ASSEMBLY FOR A TURBOMACHINE
RU2534189C2 (en) * 2010-02-16 2014-11-27 Дженерал Электрик Компани Gas turbine combustion chamber (versions) and method of its operation
ES2488404T3 (en) * 2011-03-07 2014-08-27 Eads Construcciones Aeronáuticas, S.A. Flow evacuation system for an aircraft engine
EP2500640A1 (en) * 2011-03-16 2012-09-19 L'AIR LIQUIDE, Société Anonyme pour l'Etude et l'Exploitation des Procédés Georges Claude Low NOx combustion process and burner therefor
US20140190178A1 (en) * 2011-08-11 2014-07-10 Beckett Gas, Inc. Combustor
US8943832B2 (en) * 2011-10-26 2015-02-03 General Electric Company Fuel nozzle assembly for use in turbine engines and methods of assembling same
EP2644997A1 (en) * 2012-03-26 2013-10-02 Alstom Technology Ltd Mixing arrangement for mixing fuel with a stream of oxygen containing gas
US9677766B2 (en) * 2012-11-28 2017-06-13 General Electric Company Fuel nozzle for use in a turbine engine and method of assembly
EP2837771A1 (en) * 2013-08-16 2015-02-18 Siemens Aktiengesellschaft Design of an axial diffuser taking built-in components into account
US10876407B2 (en) * 2017-02-16 2020-12-29 General Electric Company Thermal structure for outer diameter mounted turbine blades
US11428160B2 (en) 2020-12-31 2022-08-30 General Electric Company Gas turbine engine with interdigitated turbine and gear assembly

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US2477683A (en) * 1942-09-30 1949-08-02 Turbo Engineering Corp Compressed air and combustion gas flow in turbine power plant
DE847091C (en) * 1944-05-13 1952-08-21 Daimler Benz Ag Hot air jet engine
US2720750A (en) * 1947-11-04 1955-10-18 Helmut R Schelp Revolving fuel injection system for jet engines and gas turbines
US2627720A (en) * 1948-10-08 1953-02-10 Packard Motor Car Co Circumferentially arranged combustion chamber with arcuate walls defining an air flow path between chambers
US2773350A (en) * 1950-01-31 1956-12-11 Hillard E Barrett Combustion chamber assembly for ram jet fuel burner
BE502037A (en) * 1950-03-21
US3002351A (en) * 1951-01-26 1961-10-03 David H Sloan Ramjet device
US3088281A (en) * 1956-04-03 1963-05-07 Bristol Siddeley Engines Ltd Combustion chambers for use with swirling combustion supporting medium
US2945349A (en) * 1957-11-12 1960-07-19 Lear Inc Miniature gas turbine
US3034297A (en) * 1958-12-15 1962-05-15 Bristol Siddeley Engines Ltd Combustion chambers
FR1094871A (en) * 1959-01-22 1955-05-25 Thomson Houston Comp Francaise Improvements to injected fuel combustion devices
US3078672A (en) * 1959-03-28 1963-02-26 Maschf Augsburg Nuernberg Ag Process and apparatus for operating a continuous or intermittent combustion engine
US3373562A (en) * 1966-03-17 1968-03-19 Wingaersheek Turbine Co Inc Combustion chamber for gas turbines and the like having improved flame holder
GB1170255A (en) * 1966-07-01 1969-11-12 Rolls Royce Combustion Apparatus.
US3393516A (en) * 1966-12-05 1968-07-23 United Aircraft Corp Curved exhaust deflector

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2269449A (en) * 1992-08-05 1994-02-09 Snecma Combustion chamber with fuel injectors of different types
GB2269449B (en) * 1992-08-05 1995-06-28 Snecma Combustion chamber with fuel injectors of different types

Also Published As

Publication number Publication date
DE2153085A1 (en) 1972-04-27
AU451788B2 (en) 1974-08-15
SE7401957L (en) 1974-02-14
SE389893B (en) 1976-11-22
FR2112339B1 (en) 1976-03-26
US3788065A (en) 1974-01-29
FR2112339A1 (en) 1972-06-16
CA954313A (en) 1974-09-10
AU3177971A (en) 1973-02-01

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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