EP1319896A3 - Gas turbine engine fuel/air premixers with variable geometry exit and method for controlling exit velocities - Google Patents

Gas turbine engine fuel/air premixers with variable geometry exit and method for controlling exit velocities Download PDF

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Publication number
EP1319896A3
EP1319896A3 EP02027665A EP02027665A EP1319896A3 EP 1319896 A3 EP1319896 A3 EP 1319896A3 EP 02027665 A EP02027665 A EP 02027665A EP 02027665 A EP02027665 A EP 02027665A EP 1319896 A3 EP1319896 A3 EP 1319896A3
Authority
EP
European Patent Office
Prior art keywords
exit
air
fuel
mixing tube
mixture
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.)
Withdrawn
Application number
EP02027665A
Other languages
German (de)
French (fr)
Other versions
EP1319896A2 (en
Inventor
R. Jan Mowill
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.)
Individual
Original Assignee
Individual
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 claimed from US10/014,415 external-priority patent/US6925809B2/en
Application filed by Individual filed Critical Individual
Publication of EP1319896A2 publication Critical patent/EP1319896A2/en
Publication of EP1319896A3 publication Critical patent/EP1319896A3/en
Withdrawn legal-status Critical Current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
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
    • F23D11/101—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting before the burner outlet
    • F23D11/102—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting before the burner outlet in an internal mixing chamber
    • F23D11/103—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting before the burner outlet in an internal mixing chamber with means creating a swirl inside the mixing chamber
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details, e.g. noise reduction means
    • F23D14/62—Mixing devices; Mixing tubes
    • F23D14/64—Mixing devices; Mixing tubes with injectors
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Output Control And Ontrol Of Special Type Engine (AREA)

Abstract

Apparatus (1430) for premixing fuel and air to provide a fuel/air mixture includes a mixing tube (1434) configured for receiving fuel and air, a mixing tube axis (1442), and a mixing tube exit (1454) for discharging a fuel/air mixture. The apparatus further includes a mixture valve (1444) associated with the mixing tube exit (1454) and including inner and outer valve members that define an exit flow area (1402). The defined exit flow area includes at least two segmented, substantially opposed area portions with respect to angular position about the mixing tube axis provided by contours in the outer valve member for directing the mixture flow, and at least one of the inner and outer valve members is movable relative to the other of the valve members to selectively vary the defined exit flow area with respect to time. In a gas turbine gas generator or engine application, a separate controllable combustion air valve can be used with a fuel valve to provide controlled fuel/air ratios for the mixture.
EP02027665A 2001-12-14 2002-12-12 Gas turbine engine fuel/air premixers with variable geometry exit and method for controlling exit velocities Withdrawn EP1319896A3 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US14415 1993-02-05
US10/014,415 US6925809B2 (en) 1999-02-26 2001-12-14 Gas turbine engine fuel/air premixers with variable geometry exit and method for controlling exit velocities

Publications (2)

Publication Number Publication Date
EP1319896A2 EP1319896A2 (en) 2003-06-18
EP1319896A3 true EP1319896A3 (en) 2004-05-12

Family

ID=21765345

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02027665A Withdrawn EP1319896A3 (en) 2001-12-14 2002-12-12 Gas turbine engine fuel/air premixers with variable geometry exit and method for controlling exit velocities

Country Status (2)

Country Link
EP (1) EP1319896A3 (en)
JP (1) JP2003194338A (en)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7845157B2 (en) 2004-12-01 2010-12-07 United Technologies Corporation Axial compressor for tip turbine engine
US7854112B2 (en) 2004-12-01 2010-12-21 United Technologies Corporation Vectoring transition duct for turbine engine
US7882694B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Variable fan inlet guide vane assembly for gas turbine engine
US7921635B2 (en) 2004-12-01 2011-04-12 United Technologies Corporation Peripheral combustor for tip turbine engine
US7921636B2 (en) 2004-12-01 2011-04-12 United Technologies Corporation Tip turbine engine and corresponding operating method
US7934902B2 (en) 2004-12-01 2011-05-03 United Technologies Corporation Compressor variable stage remote actuation for turbine engine
US7937927B2 (en) 2004-12-01 2011-05-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
US7976272B2 (en) 2004-12-01 2011-07-12 United Technologies Corporation Inflatable bleed valve for a turbine engine
US7980054B2 (en) 2004-12-01 2011-07-19 United Technologies Corporation Ejector cooling of outer case for tip turbine engine
US8024931B2 (en) 2004-12-01 2011-09-27 United Technologies Corporation Combustor for turbine engine
US9541092B2 (en) 2004-12-01 2017-01-10 United Technologies Corporation Tip turbine engine with reverse core airflow

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10210034B4 (en) * 2002-03-07 2009-10-01 Webasto Ag Mobile heater with a fuel supply
GB2405197B (en) 2003-08-16 2005-09-28 Rolls Royce Plc Fuel injector
ATE374908T1 (en) * 2004-05-05 2007-10-15 Alstom Technology Ltd COMBUSTION CHAMBER FOR GAS TURBINE
FR2875585B1 (en) * 2004-09-23 2006-12-08 Snecma Moteurs Sa AERODYNAMIC SYSTEM WITH AIR / FUEL INJECTION EFFERVESCENCE IN A TURBOMACHINE COMBUSTION CHAMBER
WO2006059970A2 (en) 2004-12-01 2006-06-08 United Technologies Corporation Turbine engine with differential gear driven fan and compressor
US8171716B2 (en) * 2007-08-28 2012-05-08 General Electric Company System and method for fuel and air mixing in a gas turbine
US7891192B2 (en) * 2007-08-28 2011-02-22 General Electric Company Gas turbine engine combustor assembly having integrated control valves
US11015808B2 (en) 2011-12-13 2021-05-25 General Electric Company Aerodynamically enhanced premixer with purge slots for reduced emissions
CN105485722B (en) * 2015-12-30 2017-11-10 中国科学院工程热物理研究所 It is a kind of can driving fluid expansion segment burner
US10890329B2 (en) 2018-03-01 2021-01-12 General Electric Company Fuel injector assembly for gas turbine engine
GB2606206A (en) * 2021-04-29 2022-11-02 Bosch Thermotechnology Ltd Uk A two-stage air-gas mixing unit for an air-gas mixture burning appliance
US11821389B2 (en) 2021-08-20 2023-11-21 Caterpillar Inc. Method and system for supplying fuel gas
CN114321978B (en) * 2021-11-29 2022-10-21 南京航空航天大学 Diffuser outlet flow distribution intelligent adjusting system and adjusting method

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3306892A1 (en) * 1983-02-26 1984-08-30 Jörg 8775 Partenstein Köster Gas burner for the heating of industrial furnaces
EP0831275A2 (en) * 1996-09-24 1998-03-25 Mitsubishi Heavy Industries, Ltd. Annular type gas turbine combustor
EP1036988A2 (en) * 1999-02-26 2000-09-20 R. Jan Mowill Gas turbine engine fuel/air premixers with variable geometry exit and method for controlling exit velocities
WO2001040713A1 (en) * 1999-12-03 2001-06-07 Mowill Rolf Jan Cooled premixer exit nozzle for gas turbine combustor and method of operation therefor

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3894397A (en) 1974-08-05 1975-07-15 Samuel S Fair Beach erosion control structure
US4255927A (en) 1978-06-29 1981-03-17 General Electric Company Combustion control system
JPS5545739A (en) 1978-09-29 1980-03-31 Japan Crown Cork Co Ltd Bonding of polyolefin liner to metallic crown cap
US4297842A (en) 1980-01-21 1981-11-03 General Electric Company NOx suppressant stationary gas turbine combustor
JPS5741524A (en) 1980-08-25 1982-03-08 Hitachi Ltd Combustion method of gas turbine and combustor for gas turbine
EP0169431B1 (en) 1984-07-10 1990-04-11 Hitachi, Ltd. Gas turbine combustor
JPH0663646B2 (en) 1985-10-11 1994-08-22 株式会社日立製作所 Combustor for gas turbine
US4994149A (en) 1986-03-06 1991-02-19 Delta Projects Inc. Diluent substitution apparatus
JP2644745B2 (en) 1987-03-06 1997-08-25 株式会社日立製作所 Gas turbine combustor
EP0312620B1 (en) 1987-10-19 1991-06-12 Hitachi, Ltd. Combustion air flow rate adjusting device for gas turbine combustor
US5377483A (en) 1993-07-07 1995-01-03 Mowill; R. Jan Process for single stage premixed constant fuel/air ratio combustion
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
US5638674A (en) 1993-07-07 1997-06-17 Mowill; R. Jan Convectively cooled, single stage, fully premixed controllable fuel/air combustor with tangential admission

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3306892A1 (en) * 1983-02-26 1984-08-30 Jörg 8775 Partenstein Köster Gas burner for the heating of industrial furnaces
EP0831275A2 (en) * 1996-09-24 1998-03-25 Mitsubishi Heavy Industries, Ltd. Annular type gas turbine combustor
EP1036988A2 (en) * 1999-02-26 2000-09-20 R. Jan Mowill Gas turbine engine fuel/air premixers with variable geometry exit and method for controlling exit velocities
WO2001040713A1 (en) * 1999-12-03 2001-06-07 Mowill Rolf Jan Cooled premixer exit nozzle for gas turbine combustor and method of operation therefor

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7845157B2 (en) 2004-12-01 2010-12-07 United Technologies Corporation Axial compressor for tip turbine engine
US7854112B2 (en) 2004-12-01 2010-12-21 United Technologies Corporation Vectoring transition duct for turbine engine
US7882694B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Variable fan inlet guide vane assembly for gas turbine engine
US7921635B2 (en) 2004-12-01 2011-04-12 United Technologies Corporation Peripheral combustor for tip turbine engine
US7921636B2 (en) 2004-12-01 2011-04-12 United Technologies Corporation Tip turbine engine and corresponding operating method
US7934902B2 (en) 2004-12-01 2011-05-03 United Technologies Corporation Compressor variable stage remote actuation for turbine engine
US7937927B2 (en) 2004-12-01 2011-05-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
US7976272B2 (en) 2004-12-01 2011-07-12 United Technologies Corporation Inflatable bleed valve for a turbine engine
US7980054B2 (en) 2004-12-01 2011-07-19 United Technologies Corporation Ejector cooling of outer case for tip turbine engine
US8024931B2 (en) 2004-12-01 2011-09-27 United Technologies Corporation Combustor for turbine engine
US8950171B2 (en) 2004-12-01 2015-02-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
US9003768B2 (en) 2004-12-01 2015-04-14 United Technologies Corporation Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method
US9541092B2 (en) 2004-12-01 2017-01-10 United Technologies Corporation Tip turbine engine with reverse core airflow

Also Published As

Publication number Publication date
EP1319896A2 (en) 2003-06-18
JP2003194338A (en) 2003-07-09

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