GB1489496A - Gas turbine engines and premixing tubes therefor - Google Patents

Gas turbine engines and premixing tubes therefor

Info

Publication number
GB1489496A
GB1489496A GB35665/75A GB3566575A GB1489496A GB 1489496 A GB1489496 A GB 1489496A GB 35665/75 A GB35665/75 A GB 35665/75A GB 3566575 A GB3566575 A GB 3566575A GB 1489496 A GB1489496 A GB 1489496A
Authority
GB
United Kingdom
Prior art keywords
tube
gas turbine
air
fuel
passage
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
GB35665/75A
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 Technologies 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 Technologies Corp filed Critical United Technologies Corp
Publication of GB1489496A publication Critical patent/GB1489496A/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
    • F23R3/42—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
    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • 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
    • F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
    • 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
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Incineration Of Waste (AREA)
  • Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)

Abstract

1489496 Gas turbine engine combustion equipment UNITED TECHNOLOGIES CORP 29 Aug 1975 [29 Aug 1974] 35665/75 Heading F1L [Also in Division F4] Combustion equipment for a gas turbine engine comprises a staged premixing tube assembly 20, for directing a fuel/air mixture into a burner 12, the assembly having an outer tube 52 for receiving fuel/air, an inner tube 54, located adjacent the rear end of tube 52, forming a first passage 62, and a second outer annular passage 60, and a tube 56 located in tube 52 forwardly of tube 54 and being movable from the Fig. 3 position, where all of the flow passes through passage 62, to the Fig. 4 position, where the flow is directed through both passages 60, 62. The wall 25 of primary zone 22 is cooled by impinging air which passes through holes 44, and the dilution zone is supplied through air holes 46, 48. Swirl vanes 64, 68 are located in passages 60, 62, respectively and a purging opening 57 is provided in a centre body 55. Bell-mouth tube 56 is moved to the required position by a rack and pinion 86, 84 and fuel is delivered to an atomizing nozzle 72 by a conduit 13. A plurality of tube assemblies 20 is provided and each of the shafts 88 of the pinions 86 is connected to a control device (90) Fig. 1 (not shown), and the control devices can be actuated so that all of the bellmouth tube assemblies 20 are operated together or in the required sequence.
GB35665/75A 1974-08-29 1975-08-29 Gas turbine engines and premixing tubes therefor Expired GB1489496A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US501739A US3905192A (en) 1974-08-29 1974-08-29 Combustor having staged premixing tubes

Publications (1)

Publication Number Publication Date
GB1489496A true GB1489496A (en) 1977-10-19

Family

ID=23994832

Family Applications (1)

Application Number Title Priority Date Filing Date
GB35665/75A Expired GB1489496A (en) 1974-08-29 1975-08-29 Gas turbine engines and premixing tubes therefor

Country Status (9)

Country Link
US (1) US3905192A (en)
JP (1) JPS5185033A (en)
CA (1) CA1028511A (en)
DE (1) DE2538512A1 (en)
FR (1) FR2283321A1 (en)
GB (1) GB1489496A (en)
IN (1) IN142712B (en)
IT (1) IT1042151B (en)
SE (1) SE7509617L (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2307980A (en) * 1995-12-06 1997-06-11 Europ Gas Turbines Ltd Fuel injector arrangement
GB2332509A (en) * 1997-12-19 1999-06-23 Europ Gas Turbines Ltd Fuel/air mixing arrangement for combustion apparatus

Families Citing this family (51)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4012904A (en) * 1975-07-17 1977-03-22 Chrysler Corporation Gas turbine burner
GB1578474A (en) * 1976-06-21 1980-11-05 Gen Electric Combustor mounting arrangement
US4180974A (en) * 1977-10-31 1980-01-01 General Electric Company Combustor dome sleeve
IT1111808B (en) * 1978-03-28 1986-01-13 Rolls Royce REFINEMENTS MADE TO COMBUSTION DEVICES FOR GAS TURBINE ENGINES
GB2044431B (en) * 1979-03-20 1983-03-16 Rolls Royce Gas turbine
GB2055187B (en) * 1979-08-01 1983-12-14 Rolls Royce Gaseous fuel injector for a gas turbine engine
FR2465080A1 (en) * 1979-09-17 1981-03-20 Snecma Turbo-motor combustion chamber support - has radial pins with spherical end fitting in cup and cross pinned flanged cylindrical end
GB2109532B (en) * 1981-11-07 1985-01-03 Rolls Royce Gas fuel injector
US4606190A (en) * 1982-07-22 1986-08-19 United Technologies Corporation Variable area inlet guide vanes
US4532762A (en) * 1982-07-22 1985-08-06 The Garrett Corporation Gas turbine engine variable geometry combustor apparatus
US4497170A (en) * 1982-07-22 1985-02-05 The Garrett Corporation Actuation system for a variable geometry combustor
DE3241162A1 (en) * 1982-11-08 1984-05-10 Kraftwerk Union AG, 4330 Mülheim PRE-MIXING BURNER WITH INTEGRATED DIFFUSION BURNER
US4984429A (en) * 1986-11-25 1991-01-15 General Electric Company Impingement cooled liner for dry low NOx venturi combustor
US5117636A (en) * 1990-02-05 1992-06-02 General Electric Company Low nox emission in gas turbine system
US5207064A (en) * 1990-11-21 1993-05-04 General Electric Company Staged, mixed combustor assembly having low emissions
US5257499A (en) * 1991-09-23 1993-11-02 General Electric Company Air staged premixed dry low NOx combustor with venturi modulated flow split
US5638674A (en) * 1993-07-07 1997-06-17 Mowill; R. Jan Convectively cooled, single stage, fully premixed controllable fuel/air combustor with tangential admission
US6220034B1 (en) 1993-07-07 2001-04-24 R. Jan Mowill Convectively cooled, single stage, fully premixed controllable fuel/air combustor
US5572862A (en) * 1993-07-07 1996-11-12 Mowill Rolf Jan Convectively cooled, single stage, fully premixed fuel/air combustor for gas turbine engine modules
US5613357A (en) * 1993-07-07 1997-03-25 Mowill; R. Jan Star-shaped single stage low emission combustor system
US5377483A (en) * 1993-07-07 1995-01-03 Mowill; R. Jan Process for single stage premixed constant fuel/air ratio combustion
US5628182A (en) * 1993-07-07 1997-05-13 Mowill; R. Jan Star combustor with dilution ports in can portions
DE4408136A1 (en) * 1994-03-10 1995-09-14 Bmw Rolls Royce Gmbh Method for fuel preparation for gas turbine combustion chamber
DE69506308T2 (en) * 1994-04-20 1999-08-26 Rolls-Royce Plc Fuel injector for gas turbine engines
DE19507088B4 (en) * 1995-03-01 2005-01-27 Alstom premix
DE19512645A1 (en) * 1995-04-05 1996-10-10 Bmw Rolls Royce Gmbh Fuel preparation device for gas turbine combustion chamber
DE19516798A1 (en) * 1995-05-08 1996-11-14 Abb Management Ag Premix burner with axial or radial air flow
DE19527453B4 (en) * 1995-07-27 2009-05-07 Alstom premix
DE19547912A1 (en) * 1995-12-21 1997-06-26 Abb Research Ltd Burners for a heat generator
DE19547913A1 (en) * 1995-12-21 1997-06-26 Abb Research Ltd Burners for a heat generator
US5924276A (en) * 1996-07-17 1999-07-20 Mowill; R. Jan Premixer with dilution air bypass valve assembly
JP3706443B2 (en) * 1996-09-24 2005-10-12 三菱重工業株式会社 Annular gas turbine combustor
DE19649486A1 (en) * 1996-11-29 1998-06-04 Abb Research Ltd Combustion chamber
US6272842B1 (en) * 1999-02-16 2001-08-14 General Electric Company Combustor tuning
US6925809B2 (en) 1999-02-26 2005-08-09 R. Jan Mowill Gas turbine engine fuel/air premixers with variable geometry exit and method for controlling exit velocities
US6253538B1 (en) 1999-09-27 2001-07-03 Pratt & Whitney Canada Corp. Variable premix-lean burn combustor
US6286300B1 (en) 2000-01-27 2001-09-11 Honeywell International Inc. Combustor with fuel preparation chambers
US6508061B2 (en) * 2001-04-25 2003-01-21 Pratt & Whitney Canada Corp Diffuser combustor
US8590313B2 (en) * 2008-07-30 2013-11-26 Rolls-Royce Corporation Precision counter-swirl combustor
US8281597B2 (en) * 2008-12-31 2012-10-09 General Electric Company Cooled flameholder swirl cup
KR101614636B1 (en) * 2011-11-16 2016-04-21 미츠비시 히타치 파워 시스템즈 가부시키가이샤 Gas turbine combustor
WO2014130528A1 (en) * 2013-02-19 2014-08-28 United Technologies Corporation Aerating fuel injector system for a gas turbine engine
US9228747B2 (en) * 2013-03-12 2016-01-05 Pratt & Whitney Canada Corp. Combustor for gas turbine engine
EP2789915A1 (en) * 2013-04-10 2014-10-15 Alstom Technology Ltd Method for operating a combustion chamber and combustion chamber
WO2014204449A1 (en) * 2013-06-18 2014-12-24 Woodward, Inc. Gas turbine engine flow regulating
US9482433B2 (en) 2013-11-11 2016-11-01 Woodward, Inc. Multi-swirler fuel/air mixer with centralized fuel injection
US9587833B2 (en) 2014-01-29 2017-03-07 Woodward, Inc. Combustor with staged, axially offset combustion
US20150338101A1 (en) * 2014-05-21 2015-11-26 General Electric Company Turbomachine combustor including a combustor sleeve baffle
DE102017120370B4 (en) * 2017-09-05 2019-06-06 Deutsches Zentrum für Luft- und Raumfahrt e.V. Burner head, burner system and method of operating the burner system
GB202019219D0 (en) * 2020-12-07 2021-01-20 Rolls Royce Plc Lean burn combustor
GB202019222D0 (en) 2020-12-07 2021-01-20 Rolls Royce Plc Lean burn combustor

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1790927A (en) * 1931-02-03 kreager
US1136849A (en) * 1912-10-03 1915-04-20 Edwin W Tucker Fuel-oil-burning apparatus.
US2531538A (en) * 1948-05-06 1950-11-28 Cecil W Smith Air control unit for oil burners
US3007515A (en) * 1955-11-14 1961-11-07 John M Furdock Oil burners

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2307980A (en) * 1995-12-06 1997-06-11 Europ Gas Turbines Ltd Fuel injector arrangement
GB2307980B (en) * 1995-12-06 2000-07-05 Europ Gas Turbines Ltd A fuel injector arrangement; a method of operating a fuel injector arrangement
US6095791A (en) * 1995-12-06 2000-08-01 European Gas Turbines Limited Fuel injector arrangement; method of operating a fuel injector arrangement
GB2332509A (en) * 1997-12-19 1999-06-23 Europ Gas Turbines Ltd Fuel/air mixing arrangement for combustion apparatus
US6311496B1 (en) 1997-12-19 2001-11-06 Alstom Gas Turbines Limited Gas turbine fuel/air mixing arrangement with outer and inner radial inflow swirlers
GB2332509B (en) * 1997-12-19 2002-06-19 Europ Gas Turbines Ltd Fuel/air mixing arrangement for combustion apparatus

Also Published As

Publication number Publication date
IN142712B (en) 1977-08-20
JPS5185033A (en) 1976-07-26
DE2538512A1 (en) 1976-03-11
FR2283321A1 (en) 1976-03-26
CA1028511A (en) 1978-03-28
US3905192A (en) 1975-09-16
FR2283321B1 (en) 1980-01-04
IT1042151B (en) 1980-01-30
SE7509617L (en) 1976-03-01

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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