EP0849533B1 - Brenneranordnung für eine Gasturbine - Google Patents

Brenneranordnung für eine Gasturbine Download PDF

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Publication number
EP0849533B1
EP0849533B1 EP97810834A EP97810834A EP0849533B1 EP 0849533 B1 EP0849533 B1 EP 0849533B1 EP 97810834 A EP97810834 A EP 97810834A EP 97810834 A EP97810834 A EP 97810834A EP 0849533 B1 EP0849533 B1 EP 0849533B1
Authority
EP
European Patent Office
Prior art keywords
burner
lance
axis
fuel
outlet openings
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.)
Expired - Lifetime
Application number
EP97810834A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0849533A3 (de
EP0849533A2 (de
Inventor
Jakob Prof. Dr. Keller
Paul Marlow
Robin Mc Millan
Martin Dr. Valk
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.)
Alstom SA
Original Assignee
Alstom Schweiz AG
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 Alstom Schweiz AG filed Critical Alstom Schweiz AG
Publication of EP0849533A2 publication Critical patent/EP0849533A2/de
Publication of EP0849533A3 publication Critical patent/EP0849533A3/de
Application granted granted Critical
Publication of EP0849533B1 publication Critical patent/EP0849533B1/de
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 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F23C7/02—Disposition of air supply not passing through burner
    • 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
    • F23D14/46—Details, e.g. noise reduction means
    • F23D14/72—Safety devices, e.g. operative in case of failure of gas supply
    • F23D14/76—Protecting flame and burner parts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D17/00—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel
    • F23D17/002—Burners for combustion conjointly or alternatively 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 
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2206/00—Burners for specific applications
    • F23D2206/10—Turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00015—Pilot burners specially adapted for low load or transient conditions, e.g. for increasing stability
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00016—Preventing or reducing deposit build-up on burner parts, e.g. from carbon

Definitions

  • the present invention relates to the field of Burner technology for gas turbines. It relates to a burner arrangement for a gas turbine, comprising at least one in Plenum of the gas turbine arranged burner, which with a internal injection chamber opens into a combustion chamber and outside with compressed air from a compressor stage of the gas turbine is applied, and a fuel lance assigned to the burner for the optional supply of liquid and / or gaseous fuels, which fuel lance is a central Liquid fuel pipe and a the liquid fuel pipe Has concentrically surrounding pilot gas pipe, the Tubes in a lance head at the top of the fuel lance end in associated outlet openings, and which fuel lance with the lance head in with the injection chamber in Connected inner tube of the burner is insertable.
  • Such a burner arrangement is e.g. from the German Publication DE-A1-43 06 956 known.
  • the burner lance is usually a two-fuel lance ("dual fuel lance"), i.e. in the fuel lance can optionally use gaseous fuel (pilot gas) and liquid fuel (usually an oil-water mixture) are fed. These are concentric in the lance appropriate pipes (liquid fuel pipe, pilot gas pipe) arranged, the channels for the gas and the liquid fuel form. The channels end at the lance tip (in the lance head) in associated outlet openings for the respective fuel. The lance is in a corresponding position with the lance head Inner tube of the burner, so that the exiting Fuel in the injection chamber connected to the inner tube arrives.
  • the inner liquid fuel pipe flows (Liquid fuel channel) of the fuel lance an oil-water mixture.
  • Flows in the start phase in contrast, in gas operation, pilot gas in the ring-shaped pilot gas channel between the liquid fuel pipe and the pilot gas pipe.
  • pilot gas in the ring-shaped pilot gas channel between the liquid fuel pipe and the pilot gas pipe A the two fuel channels are always out of operation. Sometimes both channels are not used at the same time.
  • the task is the one mentioned in your burner arrangement Kind of solved by protecting against intrusion of hot gases and / or hot liquid fuel into the outlet openings of the pipes when not in use Pipes in the lance head in the immediate vicinity of the outlet openings an additional opening is provided for the pipes is through which compressed air flows into the injection chamber, and that means are provided which compressed air the plenum surrounding the burner to the additional opening to lead. This will immediately on the lance head An air screen is located near the outlet openings of the fuel pipes generates a backflow into the outlet openings safely prevented. Because the compressed air required for this is direct is removed from the surrounding plenum on the burner, there are no additional lines in the lance and to the lance and associated connections, valves and the like.
  • a first preferred embodiment of the burner arrangement according to the invention is characterized in that the means to guide the compressed air include a space which in the flow direction in front of the lance head between the pilot gas pipe and the inner tube of the burner is arranged, that the space with the plenum surrounding the burner via at least one from outside through the burner the inner tube leading inlet bore is connected to that of the Gap with the additional opening over at least a compressed air duct led through the lance head stands, and that the space is annular and concentrically surrounds the pilot gas pipe.
  • the gap can be easily formed by that the (outer) pilot gas pipe of the lance in the direction of flow in front of the lance head in the outside diameter compared to the Inner tube of the burner is significantly reduced.
  • the inlet holes and compressed air ducts require very little change on the burner or lance head.
  • Burner arrangement is characterized in that several Inlet holes around the burner axis or lance axis are distributed that several compressed air channels around the Burner axis or lance axis are arranged distributed around and that the compressed air channels are inclined in the direction of flow Run the burner axis or lance axis.
  • the outlet opening for the liquid fuel in the lance head is preferably arranged centrally, and the additional The opening in the lance head is preferably designed as a ring opening, which is the central outlet for the liquid fuel concentrically surrounds. This creates an air jacket generates the central outlet for the liquid fuel encloses and shields in a ring.
  • the burner arrangement 1 is a first general embodiment in longitudinal section for a burner arrangement according to the present Invention reproduced.
  • the burner arrangement 1 comprises a burner 2, in the present case as a double-cone burner is trained.
  • the burner 2 encloses an injection chamber 8, in a combustion chamber, not shown opens (see DE-A1-43 06 956).
  • the burner is outside surrounded by the plenum 7 of the gas turbine, which with compressed air from the compressor stage of the gas turbine.
  • An inner tube 6 is arranged in the center of the burner 2, in which has a fuel lance 9 with an outer tube 10 and a lance tip is inserted, which is the end of a pilot gas pipe 11 and the adjoining lance head 12 includes.
  • the burner 2 further comprises two external ones Main gas channels 3 and 4 (see also Fig. 2) through which the Main gas introduced and through a variety of inflow openings 5 (of which in Fig. 1 for the sake of clarity only five are shown as examples) in the injection chamber 8 is injected.
  • the outside diameter of the pilot gas pipe 11 is opposite to that Inner diameter of the inner tube 6 (at least immediately behind the lance head 12) significantly reduced, so that between the pilot gas pipe 11 and the inner pipe 6 an annular space 13 results.
  • This space 13 can - as from the cross section in Fig. 2 is clear - by two opposite Inlet holes 14 and 15 compressed air from the inflow surrounding plenum 7 and is there to form a Air screen in the exit area of the lance head 12 for Available.
  • the formation of the air screen can be different Way and is to be based on two exemplary embodiments 3 and 4 are explained, the show the inner structure in the area of the lance head 12.
  • Fig. 3 shows a first embodiment in longitudinal section (Partial figure (b)) and in cross section (partial figure (a)) along level B-B from sub-figure (b).
  • the in the inner tube 6 of the burner 2 stuck fuel lance 9 includes next to that already mentioned pilot gas pipe 11 and the lance head 12 a concentric Liquid fuel tube arranged in the pilot gas tube 11 19.
  • the liquid fuel brought up and through an associated outlet opening 20 in Lance head 12 injected into the injection space 8.
  • With gas operation becomes pilot gas in the pilot gas channel 16 between the liquid fuel pipe 19 and the pilot gas pipe 11 and through several outlet openings 23 and 23a-c in the lance head injected into the injection chamber 8.
  • the outlet openings 23a-c are formed by the liquid fuel pipe 19 at the tip 21 a cross section in the form of a circular bore of the pilot gas pipe 11 inscribed Triangle (see Fig. 3 (a)).
  • annular opening 17 is provided, which is the central Outlet opening 22 of the liquid fuel channel 20 concentrically surrounds.
  • the ring opening 17 is by several (three) compressed air ducts distributed around the lance axis 18 or 18a-c with compressed air from the gap 13 supplied.
  • the compressed air channels 18 and 18a-c are located in the radial direction outside the outlet openings 23 or 23a-c, which open into the ring opening 17.
  • the compressed air channels 18 or 18a-c and the inner wall of the ring opening 17th are preferably oblique to the burner axis or lance axis trained to run. This forms the emerging Compressed air a conically tapered air screen that a backflow of hot gases and / or hot oil from the Injection chamber 8 in one of the (just not used) outlet openings 22 or 23, 23a-c effectively prevented.
  • FIG. 4 A second exemplary embodiment is shown in FIG. 4.
  • the one in the inner tube 6 of the burner 2 comprises Fuel lance 9 an outer pilot gas tube 24, which is concentric surrounds a central liquid fuel tube 31.
  • the liquid fuel formed by the two pipes 24 and 31 and pilot gas channels 32 and 25 correspond to the channels 20 and 16 from FIG. 3.
  • the tubes 24 and 31 also end in here the lance head 12, which also has an annular opening 27, which is the central outlet opening 33 for the liquid fuel channel 32 concentrically surrounds.
  • the compressed air for the ring opening 27 is made of the annular space 26, which in connection with the plenum via the inlet bores 14, 15 stands radially inward over a plurality of (six) directed compressed air channels 28 brought up.
  • the pilot gas is not in this embodiment in the Ring opening 27 injected, but by a plurality of (Six) separate outlet openings 29 that are connected to the pilot gas channel 25 via corresponding pilot gas bores 30 in connection stand.
  • the outlet openings 29 are outside the ring opening 27.
  • the air screen generated with the ring opening 27 not only shields the lance head 12 as a whole but also separates between the outlet openings 29 for the pilot gas and the outlet opening 33 for the Liquid fuel, which in particular causes a backflow effective between the different outlet openings of the lance is prevented.
  • the limited space in the lance head 12 is used particularly well when the outlet openings 29 for the pilot gas or pilot gas bores 30 and the compressed air channels 28 around the burner axis or lance axis are arranged alternately around.
  • the invention results in a burner arrangement, effective in a simple manner with little effort prevents hot gases and / or hot oil from escaping the burner into the unused channels of the burner lance can flow back.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Spray-Type Burners (AREA)
  • Gas Burners (AREA)
EP97810834A 1996-12-19 1997-11-06 Brenneranordnung für eine Gasturbine Expired - Lifetime EP0849533B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19652899 1996-12-19
DE19652899A DE19652899A1 (de) 1996-12-19 1996-12-19 Brenneranordnung für eine Gasturbine

Publications (3)

Publication Number Publication Date
EP0849533A2 EP0849533A2 (de) 1998-06-24
EP0849533A3 EP0849533A3 (de) 1999-08-11
EP0849533B1 true EP0849533B1 (de) 2003-06-04

Family

ID=7815276

Family Applications (1)

Application Number Title Priority Date Filing Date
EP97810834A Expired - Lifetime EP0849533B1 (de) 1996-12-19 1997-11-06 Brenneranordnung für eine Gasturbine

Country Status (5)

Country Link
US (1) US6038863A (zh)
EP (1) EP0849533B1 (zh)
JP (1) JP3995067B2 (zh)
CN (1) CN1103024C (zh)
DE (2) DE19652899A1 (zh)

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH1162622A (ja) 1997-08-22 1999-03-05 Toshiba Corp 石炭ガス化複合発電設備およびその運転方法
DE19905995A1 (de) * 1999-02-15 2000-08-17 Asea Brown Boveri Brennstofflanze zum Eindüsen von flüssigen und/oder gasförmigen Brennstoffen in eine Brennkammer sowie Verfahren zum Betrieb einer solchen Brennstofflanze
DE10049203A1 (de) * 2000-10-05 2002-05-23 Alstom Switzerland Ltd Verfahren zur Brennstoffeinleitung in einen Vormischbrenner
US6360776B1 (en) 2000-11-01 2002-03-26 Rolls-Royce Corporation Apparatus for premixing in a gas turbine engine
GB2373043B (en) * 2001-03-09 2004-09-22 Alstom Power Nv Fuel injector
DE50211068D1 (de) 2001-12-20 2007-11-22 Alstom Technology Ltd Verfahren zum Eindüsen eines Brennstoff-/Luftgemisches in eine Brennkammer
EP1730448B1 (de) 2004-03-31 2016-12-14 General Electric Technology GmbH Mehrfachbrenneranordnung zum betrieb einer brennkammer sowie verfahren zum betreiben der mehrfachbrenneranordnung
CN101365913A (zh) * 2005-11-04 2009-02-11 阿尔斯托姆科技有限公司 燃料喷管
JP4764391B2 (ja) * 2007-08-29 2011-08-31 三菱重工業株式会社 ガスタービン燃焼器
EP2693124A1 (en) * 2012-08-02 2014-02-05 Siemens Aktiengesellschaft Pilot burner, burner, combustor and gas turbine engine
JP5913503B2 (ja) * 2014-09-19 2016-04-27 三菱重工業株式会社 燃焼バーナ及び燃焼器、並びにガスタービン
US20180238548A1 (en) * 2017-02-22 2018-08-23 Delavan Inc Passive purge injectors

Family Cites Families (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL130010C (zh) * 1966-01-27
DE1992617U (de) * 1968-05-29 1968-08-29 Steinmueller Gmbh L & C Brenner zur wahlweisen verbrennung von fluessigen und/oder gasfoermigen brennstoffen.
GB1284439A (en) * 1969-12-09 1972-08-09 Rolls Royce Fuel injector for a gas turbine engine
US3763650A (en) * 1971-07-26 1973-10-09 Westinghouse Electric Corp Gas turbine temperature profiling structure
GB2122333B (en) * 1982-06-15 1985-08-14 Rolls Royce Improvements in or relating to dual fuel burners for gas turbine engines
FR2570473B1 (fr) * 1984-09-19 1989-07-13 Pillard Chauffage Perfectionnements aux bruleurs a gaz a ecoulement parallele comportant une rosace et un moyeu d'accrochage de flamme concernant les bruleurs a gaz et l'alimentation independante en air central
DE3860569D1 (de) * 1987-01-26 1990-10-18 Siemens Ag Hybridbrenner fuer vormischbetrieb mit gas und/oder oel, insbesondere fuer gasturbinenanlagen.
DE4109304A1 (de) * 1991-03-21 1992-09-24 Siemens Ag Verfahren zur verringerung der stickoxid-emission eines brenners bei heizoelbetrieb und gasbetrieb
US5337961A (en) * 1992-12-07 1994-08-16 General Electric Company Ceramic tip and compliant attachment interface for a gas turbine fuel nozzle
DE4306956A1 (de) 1993-03-05 1994-09-08 Abb Management Ag Brennstoffzuführung für eine Gasturbine
GB9321505D0 (en) * 1993-10-19 1993-12-08 Europ Gas Turbines Ltd Fuel injector
DE4424599A1 (de) * 1994-07-13 1996-01-18 Abb Research Ltd Verfahren und Vorrichtung zum Betreiben eines kombinierten Brenners für flüssige und gasförmige Brennstoffe
DE19524213A1 (de) * 1995-07-03 1997-01-09 Abb Management Ag Brennstoffzuführung für Gasturbinen mit Ringbrennkammer
DE19539246A1 (de) * 1995-10-21 1997-04-24 Asea Brown Boveri Airblast-Zerstäuberdüse
DE19547914A1 (de) * 1995-12-21 1997-06-26 Abb Research Ltd Vormischbrenner für einen Wärmeerzeuger
DE19618856B4 (de) * 1996-05-10 2006-04-13 Alstom Vorrichtung zum Betreiben einer mit kombinierten Brennern für flüssige und gasförmige Brennstoffe bestückten Ringbrennkammer

Also Published As

Publication number Publication date
JP3995067B2 (ja) 2007-10-24
EP0849533A3 (de) 1999-08-11
DE59710217D1 (de) 2003-07-10
CN1103024C (zh) 2003-03-12
US6038863A (en) 2000-03-21
EP0849533A2 (de) 1998-06-24
DE19652899A1 (de) 1998-06-25
CN1185565A (zh) 1998-06-24
JPH10185194A (ja) 1998-07-14

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