EP1334309B1 - Verfahren zur brennstoffversorgung eines vormischbrenners - Google Patents

Verfahren zur brennstoffversorgung eines vormischbrenners Download PDF

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Publication number
EP1334309B1
EP1334309B1 EP01970078A EP01970078A EP1334309B1 EP 1334309 B1 EP1334309 B1 EP 1334309B1 EP 01970078 A EP01970078 A EP 01970078A EP 01970078 A EP01970078 A EP 01970078A EP 1334309 B1 EP1334309 B1 EP 1334309B1
Authority
EP
European Patent Office
Prior art keywords
burner
premixing
gas
premix
region
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
EP01970078A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1334309A1 (de
Inventor
Adnan Eroglu
Peter Stuber
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 Technology GmbH
Original Assignee
Alstom Technology 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 Technology AG filed Critical Alstom Technology AG
Priority to EP07113855.6A priority Critical patent/EP1855054B1/de
Publication of EP1334309A1 publication Critical patent/EP1334309A1/de
Application granted granted Critical
Publication of EP1334309B1 publication Critical patent/EP1334309B1/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
    • 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 
    • 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
    • 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
    • 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 method for supplying fuel to a premix burner having at least one burner shell at least partially delimiting an axially extending premix burner space for operating a gas turbine having a premix gas supply directed into the premix burner space above the burner cup, the premix gas being mixed with combustion air and downstream, is ignited outside the premix burner.
  • Premix burners of the aforementioned type are well known for operating gas turbine plants and have different premix burner geometries. So is in the EP 0 321 809 B1 a cone-shaped premix burner consisting of several burner shells, a so-called double-cone burner, whose burner shells are composed in such a way that tangential air inlet slots for the combustion air are formed along the burner axis. At the inflow edges of the burner shells formed thereby are provided outlet openings for the premix gas, which are distributed in the direction of the burner axis. The injection of the Premixgases through the outlet openings along the inflow edges of the burner bowls leads due to the Brennerschalengeometrie in conjunction with the Brennungszu Kunststoff to a swirling mixing of the premixing gas and the combustion air supply.
  • premix burner geometry is in the WO 93/17279 shown, in which the premix burner is formed with an additional conical inner body. Also in this case, the premix gas is fed into the premix burner via respective exit openings arranged along the axially extending air inlet slots, where the premix gas is mixed with combustion air and ignited downstream within the combustion chamber.
  • the emission values, the extinguishing behavior of the flame forming in the combustion chamber, the flame backflow behavior and the flame stability can be decisively influenced by a suitable choice of the abovementioned parameters.
  • premix burners With the currently known premix burners, it is nearly impossible to use the premix burner with different types of fuel, such as liquid or gaseous fuel to operate, especially since the usually arranged centrally in the burner axis burner lance for supplying pilot gas, which is required as mentioned above for starting the gas turbine and for the lower load range, is located in close proximity to the central liquid fuel nozzle , Unintended ignition interactions between the two fuel outlets can not be excluded.
  • fuel such as liquid or gaseous fuel
  • the two writings DE-A1-44 46 945 and EP-A1-0 592 717 disclose gas-powered premix burners in which combustion air is introduced at least approximately tangentially into the pre-mixing chamber of the burner. Fuel is injected via a plurality of nozzles arranged in the longitudinal direction of the premixing chamber and mixed with the combustion air. The nozzles are divided into at least two groups with different fuel supply.
  • the object of the invention is to further develop a method and a device for supplying fuel to a premix burner according to the preamble of claim 1 in such a way that the above-mentioned disadvantages of the prior art are to be avoided.
  • it is necessary to take measures on the premix burner so that an optimized adaptation of the premix burner behavior in the entire load range of the gas turbine is possible. This should in particular be done without great technical and design effort and be feasible with only a small cost.
  • the idea underlying the invention is the axial stepped supply of premix gas along the flanks of the burner shells by the burner shells are divided into at least two axially successively arranged areas, which are each supplied via separated Premixgaszu effeten.
  • the separate areas along the burner shells are arranged axially one behind the other in the flow direction of the premix burner, wherein it has been recognized according to the invention that for starting the gas turbine more than 60% of the total premix gas supply over the upstream first area should be done and for the further start-up of the load Gas turbine to full load one step-wise or continuous redistribution of the Premixgaszu Adjust on the downstream of the first region adjacent areas.
  • FIG. 1 shows a schematic representation of a longitudinal section through a cone-shaped premix burner.
  • the premix burner has cone-shaped burner shells 1, 2, along which are provided in the axial direction to the burner longitudinal axis A outlet openings 3, can be fed by the premix gas into the interior of the premix burner.
  • the burner shells 1, 2 are subdivided into two differently separated regions S1, S2, which are supplied with premix gas by different premix gas supply lines 4, 5.
  • supply air is guided into the interior of the premix burner by air inlet slots, not shown in FIG. 1, which mixes with the premix gas 6 to form a fuel air mixture.
  • a liquid fuel atomization direction 7 can be provided in the center of the premix burner, which allows mixing operation or switching from gaseous fuel to liquid fuel.
  • the supply of liquid fuel takes place with the aid of a known atomizing nozzle, which is a conical spreading sputtering cloud generated within the premix burner.
  • the spreading liquid fuel cloud is surrounded by a protective air jacket.
  • a pedestal that is to ignite the premix burner is not made as usual in the prior art, a pedestal, but in the embodiment illustrated two-stage Vormischbrennerica each area of the burner shell is supplied with a Premixgaszussel which is arranged upstream within the premix burner. In the exemplary embodiment, this is the area stage 1, which is operated for starting and for operating the premix burner in the low load range with more than 60% of the total Premixgaszu exit.
  • FIG. 2 shows an overview diagram from which the percentage distribution of the premix gas distribution between area S1 and area S2 can be seen.
  • the fields entered in black correspond to the portion of the premix gas exiting via region 1, the brighter fields in each case to the premix gas fraction which reaches the interior of the burner via region S2 of the premix burner.
  • the lion's share ie, more than 90%
  • the proportion of premix gas exiting via region 2 increases slightly.
  • both areas S1 and S2 are supplied with premix gas in approximately equal parts.
  • a conical premix burner is provided, which has two regions S1 and S2, via which premix gas enters the interior of the premix burner separately.
  • a main control valve 9 is provided in a common supply line 8 is supplied via the premix to the premix burner.
  • the direct inflow of premix gas to the area S1 of the premix burner can be regulated.
  • a crossing point 10 is provided, at which a portion of the premix gas is discharged into a Zumonirast 11.
  • the area S1 of the premix burner is supplied with premix gas.
  • the pressure relief valve 12 has a conically shaped piston 15, the spring-loaded by a spring 16 gas-tight a counter-contour 17 rests. Now, if the piston 15 by means of gas pressure (see arrow on the left side of the throttle valve) pressurized, so the pressure acting on the piston 15 gas pressure, the spring 16 against a stop 18 can push together. This opens a gap between the piston 15 and the mating contour 17, whereby gas can pass through the pressure relief valve to the right.
  • the gas pressure-dependent flow rate of the premix gas by the pressure relief valve 12 is set individually.
  • a number of disadvantages are associated with the method according to the invention for supplying fuel to a premix burner:
  • the graduated premix gas feed into the premix burner allows it to be used in significantly larger range limits than just single-stage premix burners.
  • control unit designed as a pressure relief valve only a single control unit is required to operate the premix burner.
  • the entire device is structurally simple and inexpensive to produce.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Feeding And Controlling Fuel (AREA)
EP01970078A 2000-10-05 2001-10-03 Verfahren zur brennstoffversorgung eines vormischbrenners Expired - Lifetime EP1334309B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP07113855.6A EP1855054B1 (de) 2000-10-05 2001-10-03 Vorrichtung zur Brennstoffversorgung eines Vormischbrenners

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE10049205A DE10049205A1 (de) 2000-10-05 2000-10-05 Verfahren und Vorrichtung zur Brennstoffversorgung eines Vormischbrenners
DE10049205 2000-10-05
PCT/IB2001/001819 WO2002029318A1 (de) 2000-10-05 2001-10-03 Verfahren und vorrichtung zur brennstoffversorgung eines vormischbrenners

Related Child Applications (1)

Application Number Title Priority Date Filing Date
EP07113855.6A Division EP1855054B1 (de) 2000-10-05 2001-10-03 Vorrichtung zur Brennstoffversorgung eines Vormischbrenners

Publications (2)

Publication Number Publication Date
EP1334309A1 EP1334309A1 (de) 2003-08-13
EP1334309B1 true EP1334309B1 (de) 2007-09-26

Family

ID=7658698

Family Applications (2)

Application Number Title Priority Date Filing Date
EP07113855.6A Expired - Lifetime EP1855054B1 (de) 2000-10-05 2001-10-03 Vorrichtung zur Brennstoffversorgung eines Vormischbrenners
EP01970078A Expired - Lifetime EP1334309B1 (de) 2000-10-05 2001-10-03 Verfahren zur brennstoffversorgung eines vormischbrenners

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP07113855.6A Expired - Lifetime EP1855054B1 (de) 2000-10-05 2001-10-03 Vorrichtung zur Brennstoffversorgung eines Vormischbrenners

Country Status (7)

Country Link
US (1) US7003960B2 (ja)
EP (2) EP1855054B1 (ja)
JP (1) JP4143401B2 (ja)
CN (1) CN1236227C (ja)
AU (1) AU2001290191A1 (ja)
DE (2) DE10049205A1 (ja)
WO (1) WO2002029318A1 (ja)

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10049203A1 (de) * 2000-10-05 2002-05-23 Alstom Switzerland Ltd Verfahren zur Brennstoffeinleitung in einen Vormischbrenner
DE10051221A1 (de) * 2000-10-16 2002-07-11 Alstom Switzerland Ltd Brenner mit gestufter Brennstoff-Eindüsung
EP1510755B1 (de) 2003-09-01 2016-09-28 General Electric Technology GmbH Brenner mit Brennerlanze und gestufter Brennstoffeindüsung
DE102004002631A1 (de) * 2004-01-19 2005-08-11 Alstom Technology Ltd Verfahren zum Betreiben einer Gasturbinen-Brennkammer
EP1714081B1 (de) * 2004-02-12 2008-04-09 Alstom Technology Ltd Vormischbrenneranordnung zum betreiben einer brennkammer sowie verfahren zum betreiben einer brennkammer
DE502006007811D1 (de) 2005-06-17 2010-10-21 Alstom Technology Ltd Brenner zur vormischartigen Verbrennung
WO2007028711A1 (de) * 2005-09-05 2007-03-15 Siemens Aktiengesellschaft Brenneranordnung für eine brennkammer, zugehörige brennkammer sowie verfahren zum verbrennen eines brennstoffs
DE102006015529A1 (de) * 2006-03-31 2007-10-04 Alstom Technology Ltd. Brennersystem mit gestufter Brennstoff-Eindüsung
US8147121B2 (en) * 2008-07-09 2012-04-03 General Electric Company Pre-mixing apparatus for a turbine engine
EP2208927B1 (en) 2009-01-15 2016-03-23 Alstom Technology Ltd Burner of a gas turbine
EP2348256A1 (en) * 2010-01-26 2011-07-27 Alstom Technology Ltd Method for operating a gas turbine and gas turbine
CN101846319B (zh) * 2010-05-26 2012-02-08 清华大学 一种弱旋滞止气体燃烧器
CN109340752B (zh) * 2018-10-09 2019-09-03 新中天环保股份有限公司 一种窑头多功能燃烧器
DE112021002128T5 (de) * 2020-03-31 2023-03-09 Mitsubishi Heavy Industries, Ltd. Brennkammer für Gasturbine und Gasturbine
US11774093B2 (en) 2020-04-08 2023-10-03 General Electric Company Burner cooling structures

Family Cites Families (30)

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Publication number Priority date Publication date Assignee Title
US4112676A (en) * 1977-04-05 1978-09-12 Westinghouse Electric Corp. Hybrid combustor with staged injection of pre-mixed fuel
JPS57187531A (en) * 1981-05-12 1982-11-18 Hitachi Ltd Low nox gas turbine burner
JPS6057131A (ja) * 1983-09-08 1985-04-02 Hitachi Ltd ガスタ−ビン燃焼器の燃料供給方法
US4735052A (en) * 1985-09-30 1988-04-05 Kabushiki Kaisha Toshiba Gas turbine apparatus
US5193995A (en) * 1987-12-21 1993-03-16 Asea Brown Boveri Ltd. Apparatus for premixing-type combustion of liquid fuel
CH674561A5 (ja) * 1987-12-21 1990-06-15 Bbc Brown Boveri & Cie
US5013236A (en) * 1989-05-22 1991-05-07 Institute Of Gas Technology Ultra-low pollutant emission combustion process and apparatus
CH680946A5 (ja) * 1989-12-19 1992-12-15 Asea Brown Boveri
EP0554325B1 (en) 1990-10-23 1995-07-26 ROLLS-ROYCE plc Gasturbine combustion chamber and method of operation thereof
US5307634A (en) 1992-02-26 1994-05-03 United Technologies Corporation Premix gas nozzle
EP0592717B1 (de) * 1992-10-16 1998-02-25 Asea Brown Boveri Ag Gasbetriebener Vormischbrenner
JP2950720B2 (ja) * 1994-02-24 1999-09-20 株式会社東芝 ガスタービン燃焼装置およびその燃焼制御方法
DE4435266A1 (de) * 1994-10-01 1996-04-04 Abb Management Ag Brenner
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DE19523094A1 (de) * 1995-06-26 1997-01-02 Abb Management Ag Brennkammer
DE19605736A1 (de) * 1996-02-16 1997-08-21 Gutehoffnungshuette Man Verfahren zur Schnellumschaltung vom Vormischbetrieb in den Diffusionsbetrieb in einer Brennkammer einer mit Brenngas betriebenen Gasturbine
US5857320A (en) * 1996-11-12 1999-01-12 Westinghouse Electric Corporation Combustor with flashback arresting system
DE19654009B4 (de) * 1996-12-21 2006-05-18 Alstom Vormischbrenner zum Betrieb einer Brennkammer mit einem flüssigen und/oder gasförmigen Brennstoff
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JP4625609B2 (ja) * 2000-06-15 2011-02-02 アルストム テクノロジー リミテッド バーナーの運転方法と段階的予混合ガス噴射バーナー
DE10049203A1 (de) * 2000-10-05 2002-05-23 Alstom Switzerland Ltd Verfahren zur Brennstoffeinleitung in einen Vormischbrenner
DE10056124A1 (de) * 2000-11-13 2002-05-23 Alstom Switzerland Ltd Brennersystem mit gestufter Brennstoff-Eindüsung und Verfahren zum Betrieb
DE10061526A1 (de) * 2000-12-11 2002-06-20 Alstom Switzerland Ltd Vormischbrenneranordnung zum Betrieb einer Brennkammer
DE10064259B4 (de) * 2000-12-22 2012-02-02 Alstom Technology Ltd. Brenner mit hoher Flammenstabilität
EP1262714A1 (de) * 2001-06-01 2002-12-04 ALSTOM (Switzerland) Ltd Brenner mit Abgasrückführung

Also Published As

Publication number Publication date
US7003960B2 (en) 2006-02-28
EP1855054A2 (de) 2007-11-14
CN1468352A (zh) 2004-01-14
EP1334309A1 (de) 2003-08-13
DE50113065D1 (de) 2007-11-08
CN1236227C (zh) 2006-01-11
WO2002029318A1 (de) 2002-04-11
EP1855054B1 (de) 2016-08-17
US20040029058A1 (en) 2004-02-12
AU2001290191A1 (en) 2002-04-15
EP1855054A3 (de) 2008-04-09
JP4143401B2 (ja) 2008-09-03
DE10049205A1 (de) 2002-05-23
JP2004510918A (ja) 2004-04-08

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