EP0393484A1 - Agencement pour chambre de combustion - Google Patents

Agencement pour chambre de combustion Download PDF

Info

Publication number
EP0393484A1
EP0393484A1 EP90106905A EP90106905A EP0393484A1 EP 0393484 A1 EP0393484 A1 EP 0393484A1 EP 90106905 A EP90106905 A EP 90106905A EP 90106905 A EP90106905 A EP 90106905A EP 0393484 A1 EP0393484 A1 EP 0393484A1
Authority
EP
European Patent Office
Prior art keywords
burner
combustion chamber
fuel
nozzles
swirl
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.)
Granted
Application number
EP90106905A
Other languages
German (de)
English (en)
Other versions
EP0393484B1 (fr
Inventor
Jakob Dr. Keller
Dr. Sattelmayer
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.)
ABB Asea Brown Boveri Ltd
ABB AB
Original Assignee
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
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 ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
Publication of EP0393484A1 publication Critical patent/EP0393484A1/fr
Application granted granted Critical
Publication of EP0393484B1 publication Critical patent/EP0393484B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C5/00—Disposition of burners with respect to the combustion chamber or to one another; Mounting of burners in combustion apparatus
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F23C7/002—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
    • F23C7/004—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion using vanes
    • 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
    • F23D14/20—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone
    • F23D14/22—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone with separate air and gas feed ducts, e.g. with ducts running parallel or crossing each other
    • F23D14/24—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone with separate air and gas feed ducts, e.g. with ducts running parallel or crossing each other at least one of the fluids being submitted to a swirling motion
    • 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
    • F23D14/26—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid with provision for a retention flame

Definitions

  • the invention is based on a burner arrangement with a main feed channel for a fuel-air mixture opening into a combustion chamber.
  • a swirl body equipped with swirl blades is provided, which is penetrated by a burner lance.
  • Outlet openings for the fuel supply open into the main supply duct.
  • a generic burner arrangement is known from a US patent (Appl. No. 07/129 172).
  • fuel and air are mixed in a prechamber and passed through a swirl body equipped with swirl vanes into a combustion chamber.
  • the swirl body ensures a more intensive mixing of fuel and air, so that a perfect, low-pollution combustion process can take place.
  • ignitions of the fuel-air mixture occur as soon as they enter the swirl body, which can have a negative effect on the stability of the burner arrangement.
  • the invention seeks to remedy this.
  • the invention as characterized in the claims, solves the problem of creating a burner arrangement in which no undesired ignitions can occur outside the combustion chamber.
  • the single figure shows a greatly simplified section through a burner arrangement according to the invention.
  • a main feed channel 2 opens into a combustion chamber 1 and leads a fuel / air mixture into the combustion chamber 1. Furthermore, the main feed channel 2 concentrically surrounds a burner lance 3, the head 4 of which projects somewhat into the combustion chamber 1.
  • the burner lance 3 passes through a swirl body rigidly arranged in the main feed channel 2 with swirl vanes 5 which are curved in a known manner.
  • the combustion chamber 1, the burner lance 3 and the main feed channel 2 are only partially shown and greatly simplified.
  • Arrows 7 indicate the inflow direction of the air required for the combustion into the main supply duct 2 and further into the combustion chamber 1.
  • Fuel is fed into the burner lance 3 through a feed channel 8 and injected into the main feed channel 2 through nozzles 9, as indicated by an arrow 10.
  • the nozzles 9 are arranged in such a way that the fuel is mixed with the air to form a combustible fuel-air mixture between the swirl blades 5.
  • the swirl blades 5 have lugs 5a which are drawn in in the opposite direction to the air flow and which channel the air flow.
  • the nozzles 9 are distributed over the circumference of the burner lance 3 in such a way that at least one nozzle 9 is provided between two swirl blades 5 in each space.
  • the injection of the fuel leads to intensive mixing with the air flowing in the main feed channel 2. Edges protruding into the flow of the fuel-air mixture can lead to local overheating and to undesired ignitions of the mixture outside the combustion chamber 1. Becomes If the fuel is now injected in such a way that no combustible mixture can occur in front of the front edges of the swirl blades 5, as seen in the direction of flow, a cause of undesired ignitions is thus eliminated.
  • the lugs 5a which are drawn against the direction of flow of the air and which channel the air flow. No mixture formation and therefore no ignition is possible at the front edge of the lugs 5a. In the area between the swirl blades 5, the flow is additionally accelerated as a result of the reduction in cross-section caused by this, so that no combustion that might occur could stabilize there.
  • the mixing of fuel and air in the area of the swirl blades 5 is sufficient to ensure good combustion in the combustion chamber 1, so that only comparatively small amounts of harmful substances leave the combustion chamber 1.
  • the length of the burner arrangement is advantageously short due to the omission of the premixing chamber, so that a comparatively compact arrangement is created.
  • Such a burner arrangement can be provided for operation with gaseous, liquid or fluidized dusty fuel. It is comparatively robust and less susceptible to wear and ensures high operational availability.
  • the fuel is supplied through the burner lance 3.
  • the burner lance 3 can be designed with a smaller outside diameter.
  • the nozzle 9 advantageously has a longitudinal axis which is at right angles to the longitudinal axis of the burner lance 3. It is ever but it is also possible to incline the longitudinal axis of the nozzle 9 towards the combustion chamber 1. Angles in the range from 90 ° to approximately 45 ° to the longitudinal axis of the burner lance 3 must be provided in this case. In this way it is ensured that the fuel-air mixture can only arise between the swirl blades 5.
  • the burner lance 3 has both a support burner and a holding burner.
  • the support burner is preferably designed as a diffusion burner and the holding burner as a premix burner. A combination of both concepts is preferably used.
  • a fuel channel 16 is provided in the burner lance 3, which has outlet openings 17 leading radially outwards in the vicinity of the head 4 of the burner lance 3.
  • a premixing chamber 18 is provided in the head 4 of the burner lance 3, into which a channel for combustion air 19 and the already mentioned fuel channel 16 open and which has outlet openings 20 which are axially aligned with the combustion chamber 1.
  • the premixing chamber 18 is designed as an annular chamber.
  • the outlet openings 20 can be distributed uniformly over their circumference or can be designed as an annular gap.
  • the proportion of fuel in the fuel-air mixture emerging from the outlet openings 20 of the premixing chamber 18 is adjusted such that the mixture is not combustible directly in front of the head 4 of the burner lance 3. It can ignite only when it strikes a vortex backflow zone 21 present in the combustion chamber 1, through which it is braked. There The flame supported by the holding burner only forms at a safe distance from the head 4 of the burner lance 3, which also reliably prevents the flame from striking back, in particular into the premixing chamber 18.
  • the supply for the fuel and the combustion air for the support burner and the holding burner is preferably designed to be controllable. This makes it possible to throttle these burners during normal operation of the burner arrangement (partial load) or to switch them off (full load) and to start them up only when required, depending on the operating state of the burner arrangement.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
EP90106905A 1989-04-20 1990-04-10 Agencement pour chambre de combustion Expired - Lifetime EP0393484B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH1507/89 1989-04-20
CH150789 1989-04-20

Publications (2)

Publication Number Publication Date
EP0393484A1 true EP0393484A1 (fr) 1990-10-24
EP0393484B1 EP0393484B1 (fr) 1992-11-04

Family

ID=4212057

Family Applications (1)

Application Number Title Priority Date Filing Date
EP90106905A Expired - Lifetime EP0393484B1 (fr) 1989-04-20 1990-04-10 Agencement pour chambre de combustion

Country Status (6)

Country Link
US (1) US5101633A (fr)
EP (1) EP0393484B1 (fr)
JP (1) JP2834531B2 (fr)
KR (1) KR900016676A (fr)
CA (1) CA2014828C (fr)
DE (1) DE59000422D1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1995002789A1 (fr) * 1993-07-16 1995-01-26 Radian Corporation APPAREIL ET PROCEDE DESTINES A REDUIRE LES REJETS DE NOx, DE CO ET D'HYDROCARBURES LORS DE LA COMBUSTION DE COMBUSTIBLES GAZEUX
US5470224A (en) * 1993-07-16 1995-11-28 Radian Corporation Apparatus and method for reducing NOx , CO and hydrocarbon emissions when burning gaseous fuels
WO1997012178A1 (fr) * 1995-09-25 1997-04-03 European Gas Turbines Ltd. Dispositif d'injection de carburant pour appareil a combustion tel qu'une turbine a gaz
DE19618058B4 (de) * 1996-05-06 2008-12-04 Alstom Brenner

Families Citing this family (52)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5218824A (en) * 1992-06-25 1993-06-15 Solar Turbines Incorporated Low emission combustion nozzle for use with a gas turbine engine
US5407347A (en) * 1993-07-16 1995-04-18 Radian Corporation Apparatus and method for reducing NOx, CO and hydrocarbon emissions when burning gaseous fuels
DE4326802A1 (de) * 1993-08-10 1995-02-16 Abb Management Ag Brennstofflanze für flüssige und/oder gasförmige Brennstoffe sowie Verfahren zu deren Betrieb
US5461865A (en) * 1994-02-24 1995-10-31 United Technologies Corporation Tangential entry fuel nozzle
GB9410233D0 (en) * 1994-05-21 1994-07-06 Rolls Royce Plc A gas turbine engine combustion chamber
US5943866A (en) * 1994-10-03 1999-08-31 General Electric Company Dynamically uncoupled low NOx combustor having multiple premixers with axial staging
US5664944A (en) * 1994-12-05 1997-09-09 The Babcock & Wilcox Company Low pressure drop vanes for burners and NOX ports
US5813232A (en) * 1995-06-05 1998-09-29 Allison Engine Company, Inc. Dry low emission combustor for gas turbine engines
US5678499A (en) * 1995-07-03 1997-10-21 Foster Wheeler Energy Corporation System for preheating fuel
WO1997011311A2 (fr) * 1995-09-22 1997-03-27 Siemens Aktiengesellschaft Bruleur, en particlier pour turbine a gaz
US5749229A (en) * 1995-10-13 1998-05-12 General Electric Company Thermal spreading combustor liner
US5647215A (en) * 1995-11-07 1997-07-15 Westinghouse Electric Corporation Gas turbine combustor with turbulence enhanced mixing fuel injectors
JP2858104B2 (ja) * 1996-02-05 1999-02-17 三菱重工業株式会社 ガスタービン燃焼器
US5755567A (en) * 1996-02-21 1998-05-26 The Babcock & Wilcox Company Low vortex spin vanes for burners and overfire air ports
US5983642A (en) * 1997-10-13 1999-11-16 Siemens Westinghouse Power Corporation Combustor with two stage primary fuel tube with concentric members and flow regulating
US6176087B1 (en) * 1997-12-15 2001-01-23 United Technologies Corporation Bluff body premixing fuel injector and method for premixing fuel and air
US6109038A (en) * 1998-01-21 2000-08-29 Siemens Westinghouse Power Corporation Combustor with two stage primary fuel assembly
DE19905996A1 (de) * 1999-02-15 2000-08-17 Abb Alstom Power Ch Ag Brennstofflanze zum Eindüsen von flüssigen und/oder gasförmigen Brennstoffen in eine Brennkammer
US6820411B2 (en) * 2002-09-13 2004-11-23 The Boeing Company Compact, lightweight high-performance lift thruster incorporating swirl-augmented oxidizer/fuel injection, mixing and combustion
US7007477B2 (en) * 2004-06-03 2006-03-07 General Electric Company Premixing burner with impingement cooled centerbody and method of cooling centerbody
US20060191268A1 (en) * 2005-02-25 2006-08-31 General Electric Company Method and apparatus for cooling gas turbine fuel nozzles
US8062027B2 (en) * 2005-08-11 2011-11-22 Elster Gmbh Industrial burner and method for operating an industrial burner
US7536862B2 (en) * 2005-09-01 2009-05-26 General Electric Company Fuel nozzle for gas turbine engines
AU2007233890B2 (en) * 2006-03-30 2010-07-01 Ansaldo Energia Ip Uk Limited Burner arrangement
US7762077B2 (en) * 2006-12-05 2010-07-27 Pratt & Whitney Rocketdyne, Inc. Single-stage hypersonic vehicle featuring advanced swirl combustion
US20080128547A1 (en) * 2006-12-05 2008-06-05 Pratt & Whitney Rocketdyne, Inc. Two-stage hypersonic vehicle featuring advanced swirl combustion
US7690192B2 (en) * 2007-04-17 2010-04-06 Pratt & Whitney Rocketdyne, Inc. Compact, high performance swirl combustion rocket engine
US7762058B2 (en) * 2007-04-17 2010-07-27 Pratt & Whitney Rocketdyne, Inc. Ultra-compact, high performance aerovortical rocket thruster
CN100526720C (zh) * 2007-08-20 2009-08-12 上海诺特飞博燃烧设备有限公司 一种确保工业燃烧器稳定燃烧的方法及其装置
US8485813B2 (en) * 2008-01-11 2013-07-16 Hauck Manufacturing Company Three stage low NOx burner system with controlled stage air separation
US8312722B2 (en) * 2008-10-23 2012-11-20 General Electric Company Flame holding tolerant fuel and air premixer for a gas turbine combustor
US8333075B2 (en) * 2009-04-16 2012-12-18 General Electric Company Gas turbine premixer with internal cooling
US8677760B2 (en) * 2010-01-06 2014-03-25 General Electric Company Fuel nozzle with integrated passages and method of operation
US8919673B2 (en) 2010-04-14 2014-12-30 General Electric Company Apparatus and method for a fuel nozzle
US8661825B2 (en) * 2010-12-17 2014-03-04 General Electric Company Pegless secondary fuel nozzle including a unitary fuel injection manifold
EP2685160B1 (fr) * 2012-07-10 2018-02-21 Ansaldo Energia Switzerland AG Brûleur de prémélange du type multi-cônes destiné à une turbine à gaz
US9347378B2 (en) 2013-05-13 2016-05-24 Solar Turbines Incorporated Outer premix barrel vent air sweep
CN103267307B (zh) * 2013-05-16 2015-09-09 上海诺特飞博燃烧设备有限公司 一种工业燃气燃烧器点火稳燃装置
CN105465786A (zh) * 2015-12-08 2016-04-06 上海华之邦科技股份有限公司 一种适用各种低热值/低压力燃气的低NOx燃烧器
US10663171B2 (en) * 2017-06-19 2020-05-26 General Electric Company Dual-fuel fuel nozzle with gas and liquid fuel capability
US11149948B2 (en) * 2017-08-21 2021-10-19 General Electric Company Fuel nozzle with angled main injection ports and radial main injection ports
US11480338B2 (en) * 2017-08-23 2022-10-25 General Electric Company Combustor system for high fuel/air ratio and reduced combustion dynamics
US11561008B2 (en) * 2017-08-23 2023-01-24 General Electric Company Fuel nozzle assembly for high fuel/air ratio and reduced combustion dynamics
WO2020066999A1 (fr) * 2018-09-25 2020-04-02 泰工技研工業株式会社 Buse de mélange de gaz-liquide multi-fluides, brûleur, équipement de combustion, chaudière, moteur à combustion interne, machines à moteur, et maison agricole de désinfection de purification environnementale
CN116133980A (zh) 2020-06-03 2023-05-16 现代电子公司 本地产生和/或消耗氢气的系统和方法
WO2022212776A1 (fr) 2021-04-01 2022-10-06 Modern Electron Systèmes et procédés de génération et/ou de consommation locale d'hydrogène gazeux
EP4347481A1 (fr) 2021-06-04 2024-04-10 Modern Electron, Inc. Réacteurs combinés de combustion et de pyrolyse pour la production d'hydrogène et systèmes et méthodes associés
KR102583223B1 (ko) * 2022-01-28 2023-09-25 두산에너빌리티 주식회사 연소기용 노즐, 연소기 및 이를 포함하는 가스터빈
CA3250252A1 (fr) * 2022-02-03 2023-08-10 Nuovo Pignone Tecnologie - S.R.L. Buse de carburant pour turbine à gaz, chambre de combustion comprenant la buse de carburant, et turbine à gaz
CN114992640B (zh) * 2022-05-23 2023-05-12 江西协成锂业有限公司 一种回转窑用多通道混合燃料燃烧器
US20250128942A1 (en) * 2023-10-24 2025-04-24 Modern Hydrogen, Inc. Pyrolysis and combustion control in pyrolysis reactors, and associated systems and methods
CN119755674B (zh) * 2024-12-17 2025-12-26 北京航空航天大学 旋流燃烧器

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US3713588A (en) * 1970-11-27 1973-01-30 Gen Motors Corp Liquid fuel spray nozzles with air atomization
EP0169431A1 (fr) * 1984-07-10 1986-01-29 Hitachi, Ltd. Chambre de combustion pour turbine à gaz
EP0274630A1 (fr) * 1986-12-11 1988-07-20 BBC Brown Boveri AG Agencement pour un brûleur
EP0276696A2 (fr) * 1987-01-26 1988-08-03 Siemens Aktiengesellschaft Brûleur hybride pour fonctionnement en prémélange au gaz et/ou au mazout, notamment pour turbines à gaz

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US4426841A (en) * 1981-07-02 1984-01-24 General Motors Corporation Gas turbine combustor assembly
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US3713588A (en) * 1970-11-27 1973-01-30 Gen Motors Corp Liquid fuel spray nozzles with air atomization
EP0169431A1 (fr) * 1984-07-10 1986-01-29 Hitachi, Ltd. Chambre de combustion pour turbine à gaz
EP0274630A1 (fr) * 1986-12-11 1988-07-20 BBC Brown Boveri AG Agencement pour un brûleur
EP0276696A2 (fr) * 1987-01-26 1988-08-03 Siemens Aktiengesellschaft Brûleur hybride pour fonctionnement en prémélange au gaz et/ou au mazout, notamment pour turbines à gaz

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1995002789A1 (fr) * 1993-07-16 1995-01-26 Radian Corporation APPAREIL ET PROCEDE DESTINES A REDUIRE LES REJETS DE NOx, DE CO ET D'HYDROCARBURES LORS DE LA COMBUSTION DE COMBUSTIBLES GAZEUX
US5470224A (en) * 1993-07-16 1995-11-28 Radian Corporation Apparatus and method for reducing NOx , CO and hydrocarbon emissions when burning gaseous fuels
WO1997012178A1 (fr) * 1995-09-25 1997-04-03 European Gas Turbines Ltd. Dispositif d'injection de carburant pour appareil a combustion tel qu'une turbine a gaz
US6050096A (en) * 1995-09-25 2000-04-18 European Gas Turbines Ltd. Fuel injector arrangement for a combustion apparatus
DE19618058B4 (de) * 1996-05-06 2008-12-04 Alstom Brenner

Also Published As

Publication number Publication date
JPH02293510A (ja) 1990-12-04
US5101633A (en) 1992-04-07
CA2014828C (fr) 2000-08-01
EP0393484B1 (fr) 1992-11-04
JP2834531B2 (ja) 1998-12-09
KR900016676A (ko) 1990-11-14
DE59000422D1 (de) 1992-12-10
CA2014828A1 (fr) 1990-10-20

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