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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

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

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* 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
US11174792B2 (en) 2019-05-21 2021-11-16 General Electric Company System and method for high frequency acoustic dampers with baffles
US11156164B2 (en) 2019-05-21 2021-10-26 General Electric Company System and method for high frequency accoustic dampers with caps
CN112923398B (en) * 2021-03-04 2022-07-22 西北工业大学 A kind of afterburner anti-vibration heat shield
CN114646077B (en) * 2022-03-23 2023-08-11 西北工业大学 Air atomizing nozzle with holes in annular cavity

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SU1471748A1 (en) * 1986-10-27 1995-08-09 О.Г. Жирицкий Flame tube of gas-turbine engine combustion chamber
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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
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Also Published As

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

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