WO2013028169A8 - Can-annular combustor with premixed tangential fuel-air nozzles for use on gas turbine engines - Google Patents

Can-annular combustor with premixed tangential fuel-air nozzles for use on gas turbine engines Download PDF

Info

Publication number
WO2013028169A8
WO2013028169A8 PCT/US2011/048622 US2011048622W WO2013028169A8 WO 2013028169 A8 WO2013028169 A8 WO 2013028169A8 US 2011048622 W US2011048622 W US 2011048622W WO 2013028169 A8 WO2013028169 A8 WO 2013028169A8
Authority
WO
WIPO (PCT)
Prior art keywords
fuel
air
gas turbine
reduces
premixed
Prior art date
Application number
PCT/US2011/048622
Other languages
French (fr)
Other versions
WO2013028169A1 (en
Inventor
Majed Toqan
Brent Allan Gregory
Jonathan David Regele
Ryan Sadao Yamane
Original Assignee
Majed Toqan
Brent Allan Gregory
Jonathan David Regele
Ryan Sadao Yamane
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 Majed Toqan, Brent Allan Gregory, Jonathan David Regele, Ryan Sadao Yamane filed Critical Majed Toqan
Priority to KR1020147007519A priority Critical patent/KR101774094B1/en
Priority to CN201180073014.0A priority patent/CN104053883B/en
Priority to EP11871108.4A priority patent/EP2748443B1/en
Priority to PCT/US2011/048622 priority patent/WO2013028169A1/en
Priority to JP2014527127A priority patent/JP6086371B2/en
Priority to RU2014110631A priority patent/RU2619673C2/en
Priority to PL11871108T priority patent/PL2748443T3/en
Publication of WO2013028169A1 publication Critical patent/WO2013028169A1/en
Publication of WO2013028169A8 publication Critical patent/WO2013028169A8/en

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
    • F23R3/346—Feeding into different combustion zones for staged 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
    • F23R3/425—Combustion chambers comprising a tangential or helicoidal arrangement of the flame tubes
    • 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
    • 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
    • F23R3/28—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
    • F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Electrical Discharge Machining, Electrochemical Machining, And Combined Machining (AREA)

Abstract

A combustion device used in gas turbine engines to produce propulsion or rotate a shaft for power generation includes a can-annular combustor with a system of fuel and air inlet passages and nozzles that results in an optimal combustion environment of premixed fuel and air. The fuel-air inlets are placed at various longitudinal locations and circumferentially distributed, and direct the flow tangentially or nearly tangent to the can liner. The combustion device provides effective mixing of fuel and air, creates an environment for combustion that reduces pollutant emissions, reduces the need for costly pollution control devices, enhances ignition and flame stability, reduces piloting issues, and improves vibration reduction.
PCT/US2011/048622 2011-08-22 2011-08-22 Can-annular combustor with premixed tangential fuel-air nozzles for use on gas turbine engines WO2013028169A1 (en)

Priority Applications (7)

Application Number Priority Date Filing Date Title
KR1020147007519A KR101774094B1 (en) 2011-08-22 2011-08-22 Can-annular combustor with premixed tangential fuel-air nozzles for use on gas turbine engines
CN201180073014.0A CN104053883B (en) 2011-08-22 2011-08-22 Method for mixing combustion reactants combusting in gas turbine engine
EP11871108.4A EP2748443B1 (en) 2011-08-22 2011-08-22 Method of mixing combustion reactants for combustion in a gas turbine engine
PCT/US2011/048622 WO2013028169A1 (en) 2011-08-22 2011-08-22 Can-annular combustor with premixed tangential fuel-air nozzles for use on gas turbine engines
JP2014527127A JP6086371B2 (en) 2011-08-22 2011-08-22 Combustion reactant mixing method in annular cylindrical combustor for gas turbine engine
RU2014110631A RU2619673C2 (en) 2011-08-22 2011-08-22 Mixing of combustible substances procedure for gas turbine engine combustion chamber
PL11871108T PL2748443T3 (en) 2011-08-22 2011-08-22 Method of mixing combustion reactants for combustion in a gas turbine engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/US2011/048622 WO2013028169A1 (en) 2011-08-22 2011-08-22 Can-annular combustor with premixed tangential fuel-air nozzles for use on gas turbine engines

Publications (2)

Publication Number Publication Date
WO2013028169A1 WO2013028169A1 (en) 2013-02-28
WO2013028169A8 true WO2013028169A8 (en) 2014-04-17

Family

ID=47746712

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2011/048622 WO2013028169A1 (en) 2011-08-22 2011-08-22 Can-annular combustor with premixed tangential fuel-air nozzles for use on gas turbine engines

Country Status (7)

Country Link
EP (1) EP2748443B1 (en)
JP (1) JP6086371B2 (en)
KR (1) KR101774094B1 (en)
CN (1) CN104053883B (en)
PL (1) PL2748443T3 (en)
RU (1) RU2619673C2 (en)
WO (1) WO2013028169A1 (en)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR102010646B1 (en) 2017-07-04 2019-08-13 두산중공업 주식회사 Turning guide, fuel nozzle, fuel nozzle assembly and gas turbine having the same
CN107631323B (en) * 2017-09-05 2019-12-06 中国联合重型燃气轮机技术有限公司 Nozzle for gas turbine
CN108487988A (en) * 2018-03-14 2018-09-04 罗显平 A kind of combustion gas screwed pipe rotary engine loopful shape combustion chamber
CN109404965A (en) * 2018-12-04 2019-03-01 新奥能源动力科技（上海）有限公司 A kind of combustion chamber of gas turbine and gas turbine
US11156164B2 (en) 2019-05-21 2021-10-26 General Electric Company System and method for high frequency accoustic dampers with caps
US11174792B2 (en) 2019-05-21 2021-11-16 General Electric Company System and method for high frequency acoustic dampers with baffles
CN112923398B (en) * 2021-03-04 2022-07-22 西北工业大学 Afterburning chamber antivibration heat screen
CN114646077B (en) * 2022-03-23 2023-08-11 西北工业大学 Air atomizing nozzle with holes in annular cavity

Family Cites Families (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4098075A (en) * 1976-06-01 1978-07-04 United Technologies Corporation Radial inflow combustor
SU1176678A1 (en) * 1984-03-01 1995-08-27 О.Г. Жирицкий Fire tube of internal combustion gas-turbine engine
SU1471748A1 (en) * 1986-10-27 1995-08-09 О.Г. Жирицкий Flame tube of gas-turbine engine combustion chamber
US4938020A (en) * 1987-06-22 1990-07-03 Sundstrand Corporation Low cost annular combustor
US4891936A (en) * 1987-12-28 1990-01-09 Sundstrand Corporation Turbine combustor with tangential fuel injection and bender jets
JPH0375414A (en) * 1989-08-15 1991-03-29 Nissan Motor Co Ltd Gas turbine combustor
US5113647A (en) * 1989-12-22 1992-05-19 Sundstrand Corporation Gas turbine annular combustor
GB2295887A (en) * 1994-12-08 1996-06-12 Rolls Royce Plc Combustor assembly
US6453658B1 (en) * 2000-02-24 2002-09-24 Capstone Turbine Corporation Multi-stage multi-plane combustion system for a gas turbine engine
US6427446B1 (en) * 2000-09-19 2002-08-06 Power Systems Mfg., Llc Low NOx emission combustion liner with circumferentially angled film cooling holes
JP4608154B2 (en) * 2001-09-27 2011-01-05 大阪瓦斯株式会社 Gas turbine combustion apparatus and gas turbine provided with the same
US6751961B2 (en) * 2002-05-14 2004-06-22 United Technologies Corporation Bulkhead panel for use in a combustion chamber of a gas turbine engine
JP3959632B2 (en) * 2002-09-04 2007-08-15 石川島播磨重工業株式会社 Diffusion combustion type low NOx combustor
JP3901629B2 (en) * 2002-11-11 2007-04-04 石川島播磨重工業株式会社 Annular swirl diffusion flame combustor
US7052231B2 (en) * 2003-04-28 2006-05-30 General Electric Company Methods and apparatus for injecting fluids in gas turbine engines
US6923001B2 (en) * 2003-07-14 2005-08-02 Siemens Westinghouse Power Corporation Pilotless catalytic combustor
US20070107437A1 (en) * 2005-11-15 2007-05-17 Evulet Andrei T Low emission combustion and method of operation
US20070119183A1 (en) * 2005-11-28 2007-05-31 General Electric Company Gas turbine engine combustor
GB0610578D0 (en) * 2006-05-27 2006-07-05 Rolls Royce Plc Method of removing deposits
US8863528B2 (en) * 2006-07-27 2014-10-21 United Technologies Corporation Ceramic combustor can for a gas turbine engine
JP4931024B2 (en) * 2006-10-20 2012-05-16 株式会社Ｉｈｉ Gas turbine combustor
US8015814B2 (en) * 2006-10-24 2011-09-13 Caterpillar Inc. Turbine engine having folded annular jet combustor
US20080163627A1 (en) * 2007-01-10 2008-07-10 Ahmed Mostafa Elkady Fuel-flexible triple-counter-rotating swirler and method of use
US8176739B2 (en) * 2008-07-17 2012-05-15 General Electric Company Coanda injection system for axially staged low emission combustors
US8079804B2 (en) * 2008-09-18 2011-12-20 Siemens Energy, Inc. Cooling structure for outer surface of a gas turbine case
US8661779B2 (en) * 2008-09-26 2014-03-04 Siemens Energy, Inc. Flex-fuel injector for gas turbines
JP2010243009A (en) * 2009-04-02 2010-10-28 Ihi Corp Burner for gas turbine
US8904799B2 (en) * 2009-05-25 2014-12-09 Majed Toqan Tangential combustor with vaneless turbine for use on gas turbine engines

Also Published As

Publication number Publication date
WO2013028169A1 (en) 2013-02-28
EP2748443A1 (en) 2014-07-02
CN104053883B (en) 2017-02-15
JP2014526030A (en) 2014-10-02
RU2619673C2 (en) 2017-05-17
PL2748443T3 (en) 2019-09-30
EP2748443A4 (en) 2015-05-27
RU2014110631A (en) 2015-09-27
KR20140082659A (en) 2014-07-02
EP2748443B1 (en) 2019-04-24
KR101774094B1 (en) 2017-09-04
JP6086371B2 (en) 2017-03-01
CN104053883A (en) 2014-09-17

Similar Documents

Publication Publication Date Title
WO2013028167A3 (en) Can-annular combustor with staged and tangential fuel-air nozzles for use on gas turbine engines
WO2013028169A8 (en) Can-annular combustor with premixed tangential fuel-air nozzles for use on gas turbine engines
WO2013028164A8 (en) Tangential annular combustor with premixed fuel and air for use on gas turbine engines
EP2481982B1 (en) Mixer assembly for a gas turbine engine
US10330319B2 (en) Sequential combustion with dilution gas mixer
JP6203530B2 (en) Fuel / air premixing system for turbine engines
JP5964045B2 (en) Combustor with staggered fuel supply for flame holding mitigation
UA108082C2 (en) INVENTORY FOR PREVIOUS MIXING OF FUEL AND AIR AND UNIT (OPTIONS) CONTAINING
US9447971B2 (en) Acoustic resonator located at flow sleeve of gas turbine combustor
US10718524B2 (en) Mixer assembly for a gas turbine engine
JP2014132214A (en) Fuel injector for supplying fuel to combustor
US8850822B2 (en) System for pre-mixing in a fuel nozzle
JP6196868B2 (en) Fuel nozzle and its assembly method
WO2011149973A8 (en) Tangential combustor with vaneless turbine for use on gas turbine engines
WO2010014125A3 (en) Combustor apparatus in a gas turbine engine
WO2009056425A3 (en) A combustor for a gas-turbine engine
US20150241065A1 (en) Combustor cap having non-round outlets for mixing tubes
WO2015108583A3 (en) Circumferentially and axially staged annular combustor for gas turbine engine combustor
WO2015126489A3 (en) Exhaust section for an aircraft gas turbine engine
US20190011132A1 (en) Pilot nozzle with inline premixing
KR20170107391A (en) Axially staged fuel injector assembly mounting
WO2013126125A3 (en) Radial inflow gas turbine engine with advanced transition duct
EP2554909A2 (en) Fuel injector
US8322141B2 (en) Power generation system including afirst turbine stage structurally incorporating a combustor
US20140123653A1 (en) Enhancement for fuel injector

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 11871108

Country of ref document: EP

Kind code of ref document: A1

ENP Entry into the national phase in:

Ref document number: 2014527127

Country of ref document: JP

Kind code of ref document: A

NENP Non-entry into the national phase in:

Ref country code: DE

ENP Entry into the national phase in:

Ref document number: 20147007519

Country of ref document: KR

Kind code of ref document: A

ENP Entry into the national phase in:

Ref document number: 2014110631

Country of ref document: RU

Kind code of ref document: A