WO1997040316A1 - Bruleur a melange prealable dote de dispositifs contre les retours de flamme - Google Patents

Bruleur a melange prealable dote de dispositifs contre les retours de flamme Download PDF

Info

Publication number
WO1997040316A1
WO1997040316A1 PCT/US1997/005543 US9705543W WO9740316A1 WO 1997040316 A1 WO1997040316 A1 WO 1997040316A1 US 9705543 W US9705543 W US 9705543W WO 9740316 A1 WO9740316 A1 WO 9740316A1
Authority
WO
WIPO (PCT)
Prior art keywords
fuel
turbine
combustion zone
air
air mixture
Prior art date
Application number
PCT/US1997/005543
Other languages
English (en)
Inventor
William Richard Ryan
Original Assignee
Westinghouse Electric Corporation
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 Westinghouse Electric Corporation filed Critical Westinghouse Electric Corporation
Publication of WO1997040316A1 publication Critical patent/WO1997040316A1/fr

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
    • F23R3/286—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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants

Definitions

  • the present invention relates to combustion turbines, and, more particularly, to combustors having fuel- air premixing passages.
  • a typical prior art premixed combustor 10 is illustrated in FIG. 1, and includes a fuel injector 20, a port for atmospheric air 30, fuel-air premixing passages 40, swirlers 50, and a combustion zone 60.
  • Premixed combustors 10 were developed, in part, to comply with the Clean Air Act ("CAA") of 1970, as amended in 1977 and 1990.
  • CAA Clean Air Act
  • the CAA environmental regulations place limits on the levels of NO x (nitrogen-oxide) emissions from stationary gas turbine systems.
  • the limits set by the CAA regulations are relatively low, for example, requiring less than 9 ppm (parts per million) NO x dry corrected to 15% 0 2 (dioxide) .
  • the combustor 10 shown in FIG. 1 achieves the required emission levels by employing premixing.
  • atmospheric air is received by an air port 30 and the lean fuel is received at the fuel injectors 20; fuel and air premixing passages 40 combine the atmospheric air and the fuel.
  • the resulting fuel-air mixture is passed through swirlers 50 and into a combustion zone 60, where the swirled
  • the present invention provides a premixed combustor that prevents flame flashback from a combustion zone into premixing passages.
  • a combustor made in accordance with the present invention includes a plurality of tubes located at the exit of the premixing passages. The plurality of tubes most preferably forms a honeycomb structure. The diameter of the individual tubes is selected to be less than a critical diameter of an opening that quenches flame produced by the lean fuel-air mixture of the turbine employing a combustor made in accordance with the present invention.
  • FIG. 1 is a partially cut away side elevation view of a prior art premixed combustor
  • FIG. 2 is an enlarged view of a section of combustor of the present invention, similar to a section taken from the dashed area of FIG. 1, illustrating a honeycomb structure located at an exit of fuel-air premixing passages of a combustor.
  • FIG. 2 a preferred embodiment of the present invention is illustrated. It will be understood that the combustor illustrated is substantially the same as that shown in FIG. 1.
  • the enlarged view of FIG. 2 is a modification of the portion of FIG. 1 set off by dashed lines and is enlarged to better illustrate the features of the present invention.
  • a segment of a premixed combustor 100 for use in a gas turbine system is shown.
  • the combustor ICQ premixes fuel and air, which flows into the fuel-air premixing passages 140.
  • the fuel-air mixture then passes through flashback arrestors 170, that are preferably located at the exit of the fuel-air premixing passages 140.
  • the fuel-air mixture then passes through swirlers 150 and into the combustion zone 160 where the fuel-air mixture is combusted.
  • the flashback arrestors 170 are comprised of a plurality of tubes 180 having a predetermined diameter and length. If, during combustion, the fuel-air mixture is halted, then flames in the combustion zone 160 will attempt to propagate or flash back from the combustion zone 160 into the fuel-air premixing passages 140. In order to propagate into the premixing passages 140, the flame must pass through the plurality of tubes 180 that create the honeycomb structure of the flashback arrestors 170. However, flashback will not occur if all openings between two chambers are less than a predetermined critical diameter.
  • the area where the flashback arrestors 170 are located is physically larger than the critical diameter, the area is filled by the above- described "honeycomb" structure, that is comprised of a number of smaller openings, each of which is less than the critical diameter.
  • the size of the openings of the flashback arrestors must be less than the critical diameter, it is not necessary for the cross-section of the elements of the arrestors to be circular.
  • the cross-section of the "honeycomb" tubes 180 may be circular, square, hexagonal, or any other shape.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)

Abstract

Cette invention concerne un dispositif contre les retours de flamme conçu pour une turbine à gaz. Conformément à la présente invention, une région, située entre la zone de combustion de la turbine et les passages de pré-mélange du carburant, est dotée d'une structure constituée d'une pluralité de tubes. Ledit dispositif contre les retours de flamme peut de ce fait être décrit comme ayant une structure à 'nid d'abeille' et chaque tube individuel ou élément de la structure en nid d'abeille a un diamètre qui est inférieur au diamètre critique au-dessous duquel les flammes ne se propagent pas pour un mélange air-carburant donné.
PCT/US1997/005543 1996-04-19 1997-04-03 Bruleur a melange prealable dote de dispositifs contre les retours de flamme WO1997040316A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US63512996A 1996-04-19 1996-04-19
US08/635,129 1996-04-19

Publications (1)

Publication Number Publication Date
WO1997040316A1 true WO1997040316A1 (fr) 1997-10-30

Family

ID=24546563

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US1997/005543 WO1997040316A1 (fr) 1996-04-19 1997-04-03 Bruleur a melange prealable dote de dispositifs contre les retours de flamme

Country Status (1)

Country Link
WO (1) WO1997040316A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20120279197A1 (en) * 2007-12-04 2012-11-08 Firestar Engineering, Llc Nitrous oxide flame barrier
EP1990581A3 (fr) * 2007-05-11 2017-04-26 General Electric Company Procédé et système pour stabilisateur poreux de flamme pour combustion d'hydrogène et de gaz de synthèse
US10634356B2 (en) 2014-09-29 2020-04-28 Kawasaki Jukogyo Kabushiki Kaisha Fuel injection nozzle, fuel injection module and gas turbine

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0029619A1 (fr) * 1979-11-23 1981-06-03 BBC Aktiengesellschaft Brown, Boveri & Cie. Chambre de combustion pour turbine à gaz avec éléments de prévaporisation/prémélange
GB2108651A (en) * 1981-11-02 1983-05-18 Westinghouse Electric Corp Combustion turbine combustor
EP0526152A1 (fr) * 1991-08-01 1993-02-03 General Electric Company Chambre de combustion étagée à prémélange résistant au retour de flammes
WO1994000197A1 (fr) * 1992-06-30 1994-01-06 Chem-Mech Engineering Laboratories Appareil pour arreter les flammes
EP0620402A1 (fr) * 1993-04-15 1994-10-19 Westinghouse Electric Corporation Chambre de combustion à prémélange avec des passages annulaires concentriques

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0029619A1 (fr) * 1979-11-23 1981-06-03 BBC Aktiengesellschaft Brown, Boveri & Cie. Chambre de combustion pour turbine à gaz avec éléments de prévaporisation/prémélange
GB2108651A (en) * 1981-11-02 1983-05-18 Westinghouse Electric Corp Combustion turbine combustor
EP0526152A1 (fr) * 1991-08-01 1993-02-03 General Electric Company Chambre de combustion étagée à prémélange résistant au retour de flammes
WO1994000197A1 (fr) * 1992-06-30 1994-01-06 Chem-Mech Engineering Laboratories Appareil pour arreter les flammes
EP0620402A1 (fr) * 1993-04-15 1994-10-19 Westinghouse Electric Corporation Chambre de combustion à prémélange avec des passages annulaires concentriques

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1990581A3 (fr) * 2007-05-11 2017-04-26 General Electric Company Procédé et système pour stabilisateur poreux de flamme pour combustion d'hydrogène et de gaz de synthèse
US20120279197A1 (en) * 2007-12-04 2012-11-08 Firestar Engineering, Llc Nitrous oxide flame barrier
US10634356B2 (en) 2014-09-29 2020-04-28 Kawasaki Jukogyo Kabushiki Kaisha Fuel injection nozzle, fuel injection module and gas turbine
DE112015004436B4 (de) 2014-09-29 2022-07-07 Kawasaki Jukogyo Kabushiki Kaisha Brennstoffeinspritzdüse, Brennstoffeinspritzmodul und Gasturbine

Similar Documents

Publication Publication Date Title
US5203796A (en) Two stage v-gutter fuel injection mixer
US6363726B1 (en) Mixer having multiple swirlers
EP1193448B1 (fr) Ensemble de vrilles d'une chambre de combustion annulaire comprenant un atomiseur pilote
US4292801A (en) Dual stage-dual mode low nox combustor
US6871501B2 (en) Method and apparatus to decrease gas turbine engine combustor emissions
US7797942B2 (en) Gas turbine combustor having multiple independently operable burners and staging method thereof
US5237812A (en) Auto-ignition system for premixed gas turbine combustors
US5611196A (en) Fuel/air mixing device for gas turbine combustor
EP1193447B1 (fr) Chambre de combustion comprenant plusieurs injecteurs
EP1985926A2 (fr) Équipement de combustion et procédé de combustion
JPH02208417A (ja) ガスタービン燃焼器及びその運転方法
US6502399B2 (en) Three-dimensional swirler in a gas turbine combustor
EP0952392B1 (fr) Chambre de combustion
EP1426690B1 (fr) Dispositif pour la réduction des émissions d'une chambre de combustion
EP0773410B1 (fr) Tube de mélange carburant/comburant
US4805411A (en) Combustion chamber for gas turbine
JPH10504891A (ja) 逆火システム
US6141954A (en) Premixing fuel injector with improved flame disgorgement capacity
WO1997040316A1 (fr) Bruleur a melange prealable dote de dispositifs contre les retours de flamme
JPH0828871A (ja) ガスタービン燃焼器
KR101468214B1 (ko) 연소기 내의 공기와 연료 혼합물의 균질성을 개선하기 위한혼합 구멍 장치 및 방법
US5797268A (en) Partially swirled multi-swirl combustor plate and chimneys
WO2007100710A2 (fr) Injecteur catalytique combustible-air avec stabilisation de flamme par un corps non profile
JP2001004138A (ja) ガスタービン用低ＮＯｘ燃焼器
KR960012389B1 (ko) 질소산화물 저발생 버너

Legal Events

Date Code Title Description
AK Designated states

Kind code of ref document: A1

Designated state(s): CA JP KR

AL Designated countries for regional patents

Kind code of ref document: A1

Designated state(s): AT BE CH DE DK ES FI FR GB GR IE IT LU MC NL PT SE

121 Ep: the epo has been informed by wipo that ep was designated in this application
NENP Non-entry into the national phase

Ref country code: JP

Ref document number: 97538088

Format of ref document f/p: F

NENP Non-entry into the national phase

Ref country code: CA

122 Ep: pct application non-entry in european phase