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WO2013028164A3 - Tangential annular combustor with premixed fuel and air for use on gas turbine engines - Google Patents

Tangential annular combustor with premixed fuel and air for use on gas turbine engines Download PDF

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Publication number
WO2013028164A3
WO2013028164A3 PCT/US2011/048595 US2011048595W WO2013028164A3 WO 2013028164 A3 WO2013028164 A3 WO 2013028164A3 US 2011048595 W US2011048595 W US 2011048595W WO 2013028164 A3 WO2013028164 A3 WO 2013028164A3
Authority
WO
WIPO (PCT)
Prior art keywords
air
fuel
combustion
gas turbine
turbine engines
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.)
Ceased
Application number
PCT/US2011/048595
Other languages
French (fr)
Other versions
WO2013028164A8 (en
WO2013028164A2 (en
Inventor
Majed Toqan
Brent Allan Gregory
Jonathan David Regele
Ryan Sadao YAMANIE
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
Application filed by Individual filed Critical Individual
Priority to KR1020147007517A priority Critical patent/KR101774630B1/en
Priority to PCT/US2011/048595 priority patent/WO2013028164A2/en
Priority to CN201180073012.1A priority patent/CN103930723A/en
Priority to EP11871342.9A priority patent/EP2748533A4/en
Priority to RU2014110629A priority patent/RU2626887C2/en
Priority to JP2014527125A priority patent/JP6110854B2/en
Publication of WO2013028164A2 publication Critical patent/WO2013028164A2/en
Anticipated expiration legal-status Critical
Publication of WO2013028164A3 publication Critical patent/WO2013028164A3/en
Publication of WO2013028164A8 publication Critical patent/WO2013028164A8/en
Ceased legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
    • 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
    • F23R3/06—Arrangement of apertures along the flame tube
    • 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
    • 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
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • 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
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • 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
    • 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
    • F23R3/58—Cyclone or vortex type combustion chambers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/128—Nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/314—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being inclined in relation to each other
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00002—Gas turbine combustors adapted for fuels having low heating value [LHV]
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03045—Convection cooled combustion chamber walls provided with turbolators or means for creating turbulences to increase cooling
    • 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
    • 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
    • F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
    • 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
    • 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
    • Y02T50/678—Aviation using fuels of non-fossil origin

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

A combustion device used in gas turbine engines to produce propulsion or rotate a shaft for power generation includes an annular combustor with a system of fuel and air inlet passages and nozzles that results in a staged combustion of premixed fuel and air. The fuel and air inlets are placed at various longitudinal locations circumferentially, and can take on different configurations where all nozzles inject a fuel-air mixture or some may inject only air. The combustion device provides an optimal mixing of fuel and air, creates an environment for combustion that reduces pollutant emissions reducing the need for costly pollution control devices, enhances ignition and flame stability, reduces piloting issues, allows increased fuel flexibility, decreases the required size of the first stage nozzle guide vane (NGV), and improves vibration reduction.
PCT/US2011/048595 2011-08-22 2011-08-22 Tangential annular combustor with premixed fuel and air for use on gas turbine engines Ceased WO2013028164A2 (en)

Priority Applications (6)

Application Number Priority Date Filing Date Title
KR1020147007517A KR101774630B1 (en) 2011-08-22 2011-08-22 Tangential annular combustor with premixed fuel and air for use on gas turbine engines
PCT/US2011/048595 WO2013028164A2 (en) 2011-08-22 2011-08-22 Tangential annular combustor with premixed fuel and air for use on gas turbine engines
CN201180073012.1A CN103930723A (en) 2011-08-22 2011-08-22 Tangential annular combustor with premixed fuel and air for use on a gas turbine
EP11871342.9A EP2748533A4 (en) 2011-08-22 2011-08-22 Tangential annular combustor with premixed fuel and air for use on gas turbine engines
RU2014110629A RU2626887C2 (en) 2011-08-22 2011-08-22 Tangential annular combustor with premixed fuel and air for use on gas turbine engines
JP2014527125A JP6110854B2 (en) 2011-08-22 2011-08-22 Tangential annular combustor with premixed fuel air for use in gas turbine engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/US2011/048595 WO2013028164A2 (en) 2011-08-22 2011-08-22 Tangential annular combustor with premixed fuel and air for use on gas turbine engines

Publications (3)

Publication Number Publication Date
WO2013028164A2 WO2013028164A2 (en) 2013-02-28
WO2013028164A3 true WO2013028164A3 (en) 2014-03-20
WO2013028164A8 WO2013028164A8 (en) 2014-04-10

Family

ID=47747017

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2011/048595 Ceased WO2013028164A2 (en) 2011-08-22 2011-08-22 Tangential annular combustor with premixed fuel and air for use on gas turbine engines

Country Status (6)

Country Link
EP (1) EP2748533A4 (en)
JP (1) JP6110854B2 (en)
KR (1) KR101774630B1 (en)
CN (1) CN103930723A (en)
RU (1) RU2626887C2 (en)
WO (1) WO2013028164A2 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104949154B (en) * 2015-03-11 2017-10-31 龚雨晋 Realize the device of constant volume burning and the dynamical system including the device

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013028163A1 (en) * 2011-08-22 2013-02-28 Majed Toqan Tangential and flameless annular combustor for use on gas turbine engines
CN104180398A (en) * 2014-08-24 2014-12-03 武汉英康汇通电气有限公司 Annular combustor
US11378277B2 (en) 2018-04-06 2022-07-05 General Electric Company Gas turbine engine and combustor having air inlets and pilot burner
CN108826357A (en) * 2018-07-27 2018-11-16 清华大学 The toroidal combustion chamber of engine
CN110081429B (en) * 2019-05-31 2024-04-12 南方电网电力科技股份有限公司 Sludge and garbage mixing incineration method and device
US11035298B1 (en) * 2020-03-16 2021-06-15 Heleng Inc. Turbine engine system
US11692709B2 (en) * 2021-03-11 2023-07-04 General Electric Company Gas turbine fuel mixer comprising a plurality of mini tubes for generating a fuel-air mixture
US11448175B1 (en) * 2021-06-03 2022-09-20 General Electric Company Fuel nozzle
KR102583222B1 (en) * 2022-01-06 2023-09-25 두산에너빌리티 주식회사 Nozzle for combustor, combustor, and gas turbine including the same
CN115823618A (en) * 2022-10-31 2023-03-21 西安交通大学 A vortex nozzle and a rapid mixing device for two-phase medium with large temperature difference

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US3433015A (en) * 1965-06-23 1969-03-18 Nasa Gas turbine combustion apparatus
US4216652A (en) * 1978-06-08 1980-08-12 General Motors Corporation Integrated, replaceable combustor swirler and fuel injector
US4891936A (en) * 1987-12-28 1990-01-09 Sundstrand Corporation Turbine combustor with tangential fuel injection and bender jets
US20040144098A1 (en) * 2000-02-24 2004-07-29 Willis Jeffrey W. Multi-stage multi-plane combustion method for a gas turbine engine
US20110020118A1 (en) * 2009-07-21 2011-01-27 Honeywell International Inc. Turbine nozzle assembly including radially-compliant spring member for gas turbine engine

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US3433015A (en) * 1965-06-23 1969-03-18 Nasa Gas turbine combustion apparatus
US4216652A (en) * 1978-06-08 1980-08-12 General Motors Corporation Integrated, replaceable combustor swirler and fuel injector
US4891936A (en) * 1987-12-28 1990-01-09 Sundstrand Corporation Turbine combustor with tangential fuel injection and bender jets
US20040144098A1 (en) * 2000-02-24 2004-07-29 Willis Jeffrey W. Multi-stage multi-plane combustion method for a gas turbine engine
US20110020118A1 (en) * 2009-07-21 2011-01-27 Honeywell International Inc. Turbine nozzle assembly including radially-compliant spring member for gas turbine engine

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104949154B (en) * 2015-03-11 2017-10-31 龚雨晋 Realize the device of constant volume burning and the dynamical system including the device

Also Published As

Publication number Publication date
JP6110854B2 (en) 2017-04-05
RU2626887C2 (en) 2017-08-02
CN103930723A (en) 2014-07-16
KR20140090141A (en) 2014-07-16
WO2013028164A8 (en) 2014-04-10
EP2748533A2 (en) 2014-07-02
RU2014110629A (en) 2015-09-27
WO2013028164A2 (en) 2013-02-28
KR101774630B1 (en) 2017-09-19
JP2014524562A (en) 2014-09-22
EP2748533A4 (en) 2015-03-04

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