EP0778445A2 - Brûleur à prémélange - Google Patents

Brûleur à prémélange Download PDF

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Publication number
EP0778445A2
EP0778445A2 EP96810791A EP96810791A EP0778445A2 EP 0778445 A2 EP0778445 A2 EP 0778445A2 EP 96810791 A EP96810791 A EP 96810791A EP 96810791 A EP96810791 A EP 96810791A EP 0778445 A2 EP0778445 A2 EP 0778445A2
Authority
EP
European Patent Office
Prior art keywords
premix burner
fuel
lance
burner according
downstream end
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
EP96810791A
Other languages
German (de)
English (en)
Other versions
EP0778445A3 (fr
EP0778445B1 (fr
Inventor
Robin Mcmillan
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.)
General Electric Switzerland GmbH
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 EP0778445A2 publication Critical patent/EP0778445A2/fr
Publication of EP0778445A3 publication Critical patent/EP0778445A3/fr
Application granted granted Critical
Publication of EP0778445B1 publication Critical patent/EP0778445B1/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
    • F23D—BURNERS
    • F23D17/00—Burners for combustion simultaneously or alternately of gaseous or liquid or pulverulent fuel
    • F23D17/002—Burners for combustion simultaneously or alternately of gaseous or liquid or pulverulent fuel gaseous or liquid fuel
    • 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
    • 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 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07002—Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners

Definitions

  • the invention relates to a premix burner, consisting essentially of at least two partial cone bodies nested one inside the other in the flow direction, the respective cone axes of which are offset from a central axis, as a result of which tangential slots are formed for the combustion air.
  • Such premix burners are known, for example, from EP-B1-0 321 809.
  • the flame itself is stabilized by the recirculation zone in front of the burner without the need for a mechanical flame holder.
  • the thermoacoustic behavior of such burners is normally stable and they are characterized by a simple and inexpensive construction.
  • gas inflow openings distributed in the longitudinal direction are provided in the region of the tangential slots formed by the two conical half-shells in the walls of the two partial bodies.
  • the mixture formation with the combustion air therefore begins in the zone of the inlet slots.
  • a fuel nozzle for liquid fuel is arranged at the tip of the conical half-shells.
  • the fuel is injected into the hollow cone at an acute angle.
  • the resulting conical fuel profile is enclosed by the tangentially flowing air.
  • concentration of the fuel is continuously reduced due to the mixing with the compressed air.
  • the injection angle of the fuel is determined by the opening angle of the premix burner.
  • the small opening angle makes it difficult to mix liquid and gaseous fuel well, which can lead to increased pollutant emissions.
  • the invention has for its object to reduce the pollutant emission in a premix burner of the type mentioned and to stabilize the backflow zone.
  • a feed lance is arranged which extends downstream into the interior of the premix burner and runs essentially symmetrically to the central axis and that at least one fuel nozzle is arranged at the downstream end of the feed lance.
  • the advantages of the invention can be seen, inter alia, in that the axial distance between the backflow zone and the fuel nozzle is shortened by the feed lance projecting into the interior of the burner. As a result, the backflow zone is stabilized in the axial direction in each load area and pulsations are avoided.
  • By injecting the fuel through the fuel nozzle in the vicinity of the backflow zone less fuel is also required to stabilize the flame. It is therefore possible to operate the premix burner with low nitrogen oxide emissions even at partial load.
  • the outer surface of the feed lance also serves as a shear surface, which supports the mixing of gaseous fuel and combustion air and thus reduces pollutant emissions.
  • the injection angle of the fuel nozzle for liquid fuel can be increased. This improves premixing when using liquid fuels and reduces nitrogen oxide emissions.
  • the feed lance is located downstream at least into the lower third of the premix burner extends. This prevents the flame front from kicking back into the interior of the burner.
  • the feed lance from a lance tube and a fuel line arranged therein.
  • part of the combustion air can be blown through the lance tube, which supports the mixing of fuel and air. It also prevents the flame from attaching to the end of the feed lance.
  • the premix burner has a circular cross section at least in the area of the burner outlet.
  • the circular burner outlet creates an axially symmetrical flow with respect to the central axis. This prevents pulsations caused by the partial cone axes and further stabilizes the backflow zone.
  • a premix burner 11 is shown schematically in FIGS. 1 and 2. It is essentially a so-called double-cone burner, as is known from EP-B1-0 321 809 mentioned at the beginning.
  • the premix burner is used to mix combustion air and fuel prior to combustion, for example in a gas turbine group.
  • Such a premix burner 11 consists of two hollow, semi-conical partial bodies 12 and 13 which are nested one inside the other in the direction of flow.
  • the respective cone axes 14 and 15 of the two partial bodies are offset with respect to the central axis 10 of the premix burner 11.
  • the adjacent walls of the two partial bodies form tangential slots 16 for the compressed in their longitudinal extension Combustion air 9, which gets into the interior of the burner in this way.
  • gas supply lines 18 running in the longitudinal direction are provided on the walls of the two partial bodies.
  • the gaseous fuel is injected via gas inflow openings, not shown, branching off from the gas supply line 18.
  • a feed lance 1 extending downstream is arranged symmetrically to the central axis 10 of the premix burner 11, starting from the tip formed by the partial cone bodies 12, 13. It consists of a lance tube 2 and a fuel line 3 arranged therein.
  • the axial position of the downstream end of the feed lance 1 is preferably at least in the lower third of the premix burner 11, i.e. the feed lance can also protrude from the premix burner 11.
  • the feed lance 1 can protrude up to twenty percent of the axial height of the premix burner from the premix burner 11.
  • a swirl body 6 is arranged in the interior of the lance tube 2, preferably in the vicinity of the downstream end.
  • the swirl body 6 consists of a plurality of deflection bodies 7 which are arranged between the inner wall of the lance tube and the fuel line 3.
  • An annular outer fuel feed channel 5 and an inner fuel feed channel 4 are arranged inside the fuel line 3.
  • a fuel nozzle 8 located at the downstream end of the fuel line 3 is supplied with fuel.
  • This nozzle 8 is designed as a dual nozzle for the injection of liquid and gaseous fuels.
  • the outer channel 5 branches off via the deflection bodies 7 into an outer fuel supply channel 5a in the interior of the downstream end of the lance tube 2.
  • the liquid fuel 30 conveyed through the outer channel 5 is thereby turned on the downstream end of the lance tube 2 out.
  • the outer edge of the lance tube located at the downstream end of the lance tube 2 serves as the atomizing edge 17.
  • the compressed combustion air 9 generated in a compressor enters the interior of the premix burner 11 via the tangential slots 16.
  • the design of the premix burner 11 causes the air 9 to rotate, the swirl number increasing in the direction of flow.
  • the mixture formation with the combustion air 9 begins in the zone of the inlet slots 16.
  • the outer wall of the lance tube 2 serves as an additional shear surface, which further supports the mixing of combustion air 9 and gaseous fuel.
  • a fuel concentration that is as homogeneous as possible is established over the cross section acted upon.
  • a defined dome-shaped backflow zone 21 is formed, at the tip of which the ignition takes place.
  • the axial position of the backflow zone 21 is fixed by the axial position of the downstream end of the feed lance 1. This prevents the backflow zone from axially shifting and thus pulsating.
  • gaseous fuel is injected via the nozzle 8.
  • the gaseous fuel is thereby injected in the vicinity of the backflow zone 21, thereby avoiding pulsations between full-load and part-load operation.
  • the required amount of fuel that has to be injected through the nozzle 8 is reduced, since the fuel is injected directly into the backflow zone 21.
  • Combustion air 9a is also conveyed through the cavity between lance tube 2 and fuel line 3.
  • the combustion air portion 9a conveyed through the lance tube can amount to up to 25% of the total air flow.
  • the combustion air 9a is set in rotation by the swirl body 6.
  • the type and strength of the swirl must be adapted to the respective conditions of the premix burner.
  • the swirl body 6 can be designed such that the swirl generated by it runs opposite to the swirl of the premix burner 11. This increases the mixing of combustion air 9, 9a and fuel and additionally prevents the smoke flow zone 21 and thus the flame from striking back to the downstream end of the feed lance 1.
  • the premix burner 11 is operated with liquid fuel
  • the fuel is injected by means of the feed lance 1. This takes place by means of the outer channel 5, via which liquid fuel 30 is conveyed to the atomizing edge 17 '.
  • the air 9a conveyed through the lance tube 2
  • an air-assisted atomizing nozzle 22 is thereby formed.
  • the air 9a may have to be compressed further with respect to the air 9.
  • liquid fuel can be injected via the fuel nozzle 8. Because of the axial position of the nozzle 8 inside the premix burner 11, the spray angle of the nozzle 8 can be chosen to be very large. This improves the mixing of air 9, 9a and fuel.
  • the premix burner can be equipped with a circular outlet at least at the burner outlet 20.
  • the two axes 14, 15 of the partial cone bodies 12, 13 must be brought together, for example on the central axis 10.
  • the return flow zone 21 is further stabilized by the circular outlet and pulsations are avoided.
  • an adapter 39 can be attached to convert the cross section of the premix burner 11 into a circular cross section at the downstream end of the premix burner 11.
  • the inner radius R i of the two partial cone bodies 12, 13 at the transition to the adapter 39 is larger than the exit radius R a of the adapter 39.
  • the height h and the size of the angle ⁇ of the adapter 39 depend on the shape of the entry into the adapter 39.
  • the angle ⁇ corresponds to the average flow angle, so that no separation can occur.
  • the flowable free area of the adapter 39 decreases in the direction from the inlet to the outlet of the adapter 39, therefore the flow through the adapter is additionally accelerated here.
  • the premix burner can of course be provided with several tangential inlet slots.
  • the feed lance can also be installed in premix burners other than the double cone burner.
  • the dual nozzle can also be constructed from two nozzles, in which case the inner feed channel must be adapted accordingly.
  • the outer fuel supply channel can also be laid from the fuel line into the lance tube.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
EP96810791A 1995-12-05 1996-11-14 Brûleur à prémélange Expired - Lifetime EP0778445B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19545309 1995-12-05
DE19545309A DE19545309A1 (de) 1995-12-05 1995-12-05 Vormischbrenner

Publications (3)

Publication Number Publication Date
EP0778445A2 true EP0778445A2 (fr) 1997-06-11
EP0778445A3 EP0778445A3 (fr) 1999-04-28
EP0778445B1 EP0778445B1 (fr) 2003-05-14

Family

ID=7779213

Family Applications (1)

Application Number Title Priority Date Filing Date
EP96810791A Expired - Lifetime EP0778445B1 (fr) 1995-12-05 1996-11-14 Brûleur à prémélange

Country Status (5)

Country Link
US (1) US5833451A (fr)
EP (1) EP0778445B1 (fr)
JP (1) JP3863608B2 (fr)
CN (1) CN1109847C (fr)
DE (2) DE19545309A1 (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0903540A1 (fr) * 1997-09-19 1999-03-24 Abb Research Ltd. Brûleur pour la mise en oeuvre d'un générateur de chaleur
EP0849527A3 (fr) * 1996-12-20 1999-06-09 United Technologies Corporation Procédé de combustion avec un ajutage d'entrée tangentiel à deux courants
EP0849529A3 (fr) * 1996-12-20 1999-06-09 United Technologies Corporation Ajutage d'entrée tangentiel
EP1340942A3 (fr) * 1997-12-15 2003-09-10 United Technologies Corporation Injecteur de carburant équipé d'un corps perturbateur et procédé de prémélange de carburant et d'air
US7241138B2 (en) 2001-12-24 2007-07-10 Alstom Technology Ltd. Burner with stepped fuel injection
US8033821B2 (en) 2007-11-27 2011-10-11 Alstom Technology Ltd. Premix burner for a gas turbine
EP2179222B2 (fr) † 2007-08-07 2021-12-01 Ansaldo Energia IP UK Limited Brûleur pour une chambre de combustion d'un turbogroupe

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1262714A1 (fr) * 2001-06-01 2002-12-04 ALSTOM (Switzerland) Ltd Brûleur avec recirculation des gaz de combustion
DE10205839B4 (de) * 2002-02-13 2011-08-11 Alstom Technology Ltd. Vormischbrenner zur Verminderung verbrennungsgetriebener Schwingungen in Verbrennungssystemen
EP1510755B1 (fr) * 2003-09-01 2016-09-28 General Electric Technology GmbH Brûleur avec lance et alimentation étagée en carburant
DE102004027702A1 (de) * 2004-06-07 2006-01-05 Alstom Technology Ltd Injektor für Flüssigbrennstoff sowie gestufter Vormischbrenner mit diesem Injektor
EP1828684A1 (fr) * 2004-12-23 2007-09-05 Alstom Technology Ltd Bruleur de premelange dote d'un parcours de melange
EP2058590B1 (fr) * 2007-11-09 2016-03-23 Alstom Technology Ltd Procédé de fonctionnement d'un brûleur
WO2009068424A1 (fr) * 2007-11-27 2009-06-04 Alstom Technology Ltd Procédé et dispositif pour la combustion d'hydrogène dans un brûleur à prémélange
EP2685163B1 (fr) 2012-07-10 2020-03-25 Ansaldo Energia Switzerland AG Brûleur de prémélange du type multi-cônes destiné à une turbine à gaz
KR102129052B1 (ko) * 2013-11-12 2020-07-02 한화에어로스페이스 주식회사 스월러 어셈블리
DE102014205198A1 (de) 2014-03-20 2015-09-24 Kba-Metalprint Gmbh Brenner und Vorrichtung zur thermischen Nachverbrennung von Abluft
DE102014205201A1 (de) 2014-03-20 2015-09-24 Kba-Metalprint Gmbh Vorrichtung zur thermischen Nachverbrennung von Abluft
DE102014205200B3 (de) * 2014-03-20 2015-06-11 Kba-Metalprint Gmbh Vorrichtung zur thermischen Nachverbrennung von Abluft
DE102014205203B3 (de) * 2014-03-20 2015-05-21 Kba-Metalprint Gmbh Vorrichtung zur thermischen Nachverbrennung von Abluft
CN120083998B (zh) * 2025-03-18 2025-12-16 成都中科翼能科技有限公司 一种燃气轮机及其燃烧室的双燃料喷嘴

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0321809B1 (fr) 1987-12-21 1991-05-15 BBC Brown Boveri AG Procédé pour la combustion de combustible liquide dans un brûleur

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2806517A (en) * 1950-11-16 1957-09-17 Shell Dev Oil atomizing double vortex burner
DE1451393A1 (de) * 1964-09-19 1969-03-27 Koppers Gmbh Heinrich Brenner fuer fluessige oder gasfoermige Brennstoffe
DE3424031A1 (de) * 1984-06-29 1986-01-09 Linde Ag, 6200 Wiesbaden Verfahren zum verbrennen eines fluessigen oder festen, pulverfoermigen brennstoffes
EP0210462B1 (fr) * 1985-07-30 1989-03-15 BBC Brown Boveri AG Chambre de combustion double
CH680816A5 (fr) * 1989-04-27 1992-11-13 Asea Brown Boveri
US4988287A (en) * 1989-06-20 1991-01-29 Phillips Petroleum Company Combustion apparatus and method
US5307634A (en) * 1992-02-26 1994-05-03 United Technologies Corporation Premix gas nozzle
US5240409A (en) * 1992-04-10 1993-08-31 Institute Of Gas Technology Premixed fuel/air burners
DE4237187A1 (de) * 1992-11-04 1994-05-05 Raimund Prof Dr Ruderich Wirbelerzeuger für einen Brenner
DE4316474A1 (de) * 1993-05-17 1994-11-24 Abb Management Ag Vormischbrenner zum Betrieb einer Brennkraftmaschine, einer Brennkammer einer Gasturbogruppe oder Feuerungsanlage
DE4326802A1 (de) * 1993-08-10 1995-02-16 Abb Management Ag Brennstofflanze für flüssige und/oder gasförmige Brennstoffe sowie Verfahren zu deren Betrieb
GB9326367D0 (en) * 1993-12-23 1994-02-23 Rolls Royce Plc Fuel injection apparatus
DE4435266A1 (de) * 1994-10-01 1996-04-04 Abb Management Ag Brenner

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0321809B1 (fr) 1987-12-21 1991-05-15 BBC Brown Boveri AG Procédé pour la combustion de combustible liquide dans un brûleur

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0849527A3 (fr) * 1996-12-20 1999-06-09 United Technologies Corporation Procédé de combustion avec un ajutage d'entrée tangentiel à deux courants
EP0849529A3 (fr) * 1996-12-20 1999-06-09 United Technologies Corporation Ajutage d'entrée tangentiel
EP0903540A1 (fr) * 1997-09-19 1999-03-24 Abb Research Ltd. Brûleur pour la mise en oeuvre d'un générateur de chaleur
US5944511A (en) * 1997-09-19 1999-08-31 Abb Research Ltd. Burner for operating a heat generator
EP1340942A3 (fr) * 1997-12-15 2003-09-10 United Technologies Corporation Injecteur de carburant équipé d'un corps perturbateur et procédé de prémélange de carburant et d'air
US7241138B2 (en) 2001-12-24 2007-07-10 Alstom Technology Ltd. Burner with stepped fuel injection
EP2179222B2 (fr) † 2007-08-07 2021-12-01 Ansaldo Energia IP UK Limited Brûleur pour une chambre de combustion d'un turbogroupe
US8033821B2 (en) 2007-11-27 2011-10-11 Alstom Technology Ltd. Premix burner for a gas turbine

Also Published As

Publication number Publication date
US5833451A (en) 1998-11-10
DE59610441D1 (de) 2003-06-18
CN1109847C (zh) 2003-05-28
EP0778445A3 (fr) 1999-04-28
CN1163372A (zh) 1997-10-29
EP0778445B1 (fr) 2003-05-14
DE19545309A1 (de) 1997-06-12
JP3863608B2 (ja) 2006-12-27
JPH09178120A (ja) 1997-07-11

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