EP0995066A1 - Agencement de bruleurs pour une installation de chauffe, notamment une chambre de combustion de turbine a gaz - Google Patents

Agencement de bruleurs pour une installation de chauffe, notamment une chambre de combustion de turbine a gaz

Info

Publication number
EP0995066A1
EP0995066A1 EP98943638A EP98943638A EP0995066A1 EP 0995066 A1 EP0995066 A1 EP 0995066A1 EP 98943638 A EP98943638 A EP 98943638A EP 98943638 A EP98943638 A EP 98943638A EP 0995066 A1 EP0995066 A1 EP 0995066A1
Authority
EP
European Patent Office
Prior art keywords
burner
air duct
fuel
air
inlets
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
EP98943638A
Other languages
German (de)
English (en)
Other versions
EP0995066B1 (fr
Inventor
Bernd Prade
Holger Streb
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.)
Siemens AG
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Publication of EP0995066A1 publication Critical patent/EP0995066A1/fr
Application granted granted Critical
Publication of EP0995066B1 publication Critical patent/EP0995066B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • 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
    • 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
    • F23D14/02—Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone
    • 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
    • F23D14/82—Preventing flashback or blowback
    • 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
    • F23D—BURNERS
    • F23D23/00—Assemblies of two or more burners
    • 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
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • 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
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03343—Pilot burners operating in premixed mode

Definitions

  • Burner arrangement for a furnace in particular a gas turbine combustion chamber
  • the present invention is in the field of burner assemblies for combustion plants, particularly for gas turbine combustors. Such burner assemblies are often designed for different fuels and different modes of operation, with great struggles to improve the assemblies and modes of operation so that pollutant emissions are reduced in view of increasingly stringent regulations for the emission of pollutants worldwide.
  • the present invention is particularly concerned with reducing nitrogen oxide emissions, hereinafter referred to as NOx.
  • Air and fuel are first mixed as evenly as possible and only then burned together in a flame area of a combustion chamber.
  • the combustion temperature can be kept lower overall than in the border area between fuel and air, and at the same time a desired ratio of fuel and air can be maintained evenly. This leads to a lower emission of pollutants, especially NOx.
  • premix burners The disadvantage of premix burners is that the combustion cannot be kept stable in all load conditions that the control range of premix burners is usually smaller than that of diffusion burners.
  • pilot burners which are usually arranged in the center of a main burner and stabilize the combustion of the main burner with their small but stable flame. Pilot burners are also needed to support the ignition of a main burner.
  • pilot burners can generate a considerable proportion of NOx in relation to the total pollutant emissions if they are operated as diffusion burners. For this reason, it is already suggested there that a pilot burner should also be designed as a premix burner, but which can be kept in a stable operating range, even if the main burner is operated in a different operating range. This measure can lead to a significant reduction in pollutant emissions.
  • a burner arrangement according to claim 1 is used to achieve the object. Advantageous and preferred refinements are described in the dependent claims.
  • the burner arrangement according to the invention for a combustion system, in particular a gas turbine combustion chamber, with a main burner and a pilot burner, which is used to ignite and / or stabilize the main burner, is in its
  • the pilot burner can always or temporarily be operated as a premix burner and the supply of fuel and combustion air to the pilot burner takes place through a lance-like supply system with concentrically arranged channels that are approximately circular in cross-section.
  • these channels is in particular the air channel for supplying combustion air for the pilot burner.
  • Inlets for fuel are arranged on this air duct, the fuel being supplied through ducts lying concentrically inside or outside of the air duct.
  • a swirl generator is arranged in the air duct in the air flow direction before the inlets. In this way, air already provided with a swirl reaches the inlets, so that there is a direct swirling of air and fuel at the inlets.
  • the fuel inlets can also be integrated into aerodynamically optimized swirl generation elements.
  • the pilot burner is typically designed for premixing operation with fuel gas, with several inlets approximately evenly distributed over the circumference being provided on the air duct.
  • the lance-like delivery system of the pilot burner consists of two or more concentrically arranged annular channels, one annular channel directly inside and / or outside the air channel for supplying fuel, in particular fuel gas.
  • Inlets in the partition between the air duct and the inner or outer ring duct bring the fuel, which is under higher pressure than the combustion air, into the air duct and is distributed there very evenly in the swirl flow generated by the swirl generator.
  • the inlets should be arranged at a certain distance from the swirl generator in order to reliably prevent flames from striking back to the swirl generator. The exact distance depends on the flow velocity of the air flowing in the air duct and the geometric conditions in the air duct.
  • the swirl generator can produce an axial and / or radial and / or tangential swirl, the swirl strength and the length of the pre-mixing section available for mixing with the fuel being selected so that the meridional flow rate is high in order to prevent the flames from striking back prevent, and that no so-called hub separation can occur, that is, the flow does not separate from the walls of the air duct.
  • the air duct has a diffuser at its end region opening into the furnace in a special embodiment of the invention, in particular formed by an increasing cross-section in the end region in the direction of flow.
  • a cooling system arranged concentrically to the air duct can be used, in which air, air-fuel mixture or steam cools the end region of the air duct.
  • the inlets for fuel are designed as mixing elements in the air duct of the pilot burner.
  • they can be designed in the form of small tubes, which distribute the fuel very finely in the air with a large number of inlet openings.
  • the arrangement of additional swirl generator blades with inlet openings for fuel is also possible.
  • the drawing shows a burner as known in principle from EP 093 838. The one from this
  • main burner 1 is supplied with main combustion air 2, into which fuel gas is injected finely distributed via a main fuel gas supply 3 and a main fuel gas injector 20 and / or via a main fuel oil supply 4 and a main fuel oil injector 21.
  • main combustion air 2 into which fuel gas is injected finely distributed via a main fuel gas supply 3 and a main fuel gas injector 20 and / or via a main fuel oil supply 4 and a main fuel oil injector 21.
  • main swirl generator 5 in particular in the form of a diagonal grid.
  • the main burner 1 In the center of the main burner 1 there is a pilot burner for igniting and stabilizing the main flame, the combustion air of which is supplied through an air duct 6, in a manner known per se.
  • a central fuel channel 7 for the operation of this pilot burner as a diffusion burner which, however, is possible according to the main idea of the present invention. is rarely used because the operation of the pilot burner as a diffusion burner generates too much NOx.
  • the air duct 6 has inlets 10, 11 through which fuel can be mixed into the combustion air of the pilot burner.
  • the concentric lance-like structure of the burner enables this fuel to be supplied through an outer fuel channel 8 and outer inlets 10 and / or through an inner fuel channel 9 and inner inlets 11.
  • mixing elements 15 can also be used, in the present exemplary embodiment in the form of small perforated tubes for more even distribution of fuel.
  • fuel oil or fuel gas can be considered as fuel, for which purpose the corresponding inlets or mixing elements must be suitably dimensioned.
  • the arrangement of the swirl generators in the flow direction upstream of the fuel inlets also has the advantage that, in the event of malfunctions, the flames of the pilot burner can in no case strike back further than the swirl generator 12.
  • the air duct 6 can be designed as a diffuser 13 in its end region.
  • a cooling system 14 in particular with a system which is concentrically arranged around the diffuser and which is cooled by means of air, air-fuel mixture or steam.
  • a burner according to the invention is connected in a manner known per se via corresponding control valves with its air inlet 16 an air supply connected and with its fuel inlets 17, 18, 19 for the central fuel channel 7, the outer fuel channel 8 or the inner fuel channel 9 to a fuel supply.
  • Burners according to the invention enable stable and low-pollutant operation in wide load ranges and are particularly suitable for combustion chambers of gas turbine systems.

Landscapes

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

Abstract

L'invention concerne un agencement de brûleurs destiné à une installation de chauffe, notamment une chambre de combustion de turbine à gaz, comportant un brûleur principal (1) et une veilleuse d'allumage servant à allumer et/ou à stabiliser le brûleur principal (1). Cette veilleuse s'utilise en permanence ou temporairement comme brûleur de prémélange, et un système d'amenée (6, 7, 8, 9) en forme de lance permet de lui amener du combustible et de l'air de combustion, ce système comportant au moins un canal d'air (6) de section approximativement circulaire, lequel est pourvu d'orifices d'admission (10; 11) pour le combustible. Dans le sens d'écoulement de l'air en amont de ces orifices d'admission (10; 11) qui sont disposés de préférence régulièrement sur le pourtour du canal d'air (6), un générateur de tourbillons (12) est disposé dans le canal d'air (6). Ce dernier fait office de diffuseur (13) au niveau de sa région terminale débouchant dans l'installation de chauffe et présente notamment une région terminale (13) s'évasant de plus en plus en section et pouvant également être refroidie. La disposition du générateur de tourbillons (12) en amont des orifices d'admission de combustible (10; 11) permet un fonctionnement stable et sûr de la veilleuse avec une faible production de NOx.
EP98943638A 1997-07-17 1998-07-07 Agencement de bruleurs pour une installation de chauffe, notamment une chambre de combustion de turbine a gaz Expired - Lifetime EP0995066B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19730734 1997-07-17
DE19730734 1997-07-17
PCT/DE1998/001871 WO1999004196A1 (fr) 1997-07-17 1998-07-07 Agencement de bruleurs pour une installation de chauffe, notamment une chambre de combustion de turbine a gaz

Publications (2)

Publication Number Publication Date
EP0995066A1 true EP0995066A1 (fr) 2000-04-26
EP0995066B1 EP0995066B1 (fr) 2001-09-26

Family

ID=7836051

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98943638A Expired - Lifetime EP0995066B1 (fr) 1997-07-17 1998-07-07 Agencement de bruleurs pour une installation de chauffe, notamment une chambre de combustion de turbine a gaz

Country Status (4)

Country Link
EP (1) EP0995066B1 (fr)
JP (1) JP2001510885A (fr)
DE (1) DE59801583D1 (fr)
WO (1) WO1999004196A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8893511B2 (en) 2009-07-24 2014-11-25 General Electric Company Systems and methods for a gas turbine combustor having a bleed duct

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WO2000049337A1 (fr) * 1999-02-16 2000-08-24 Siemens Aktiengesellschaft Systeme de bruleurs et procede permettant de le faire fonctionner
US6354072B1 (en) * 1999-12-10 2002-03-12 General Electric Company Methods and apparatus for decreasing combustor emissions
AU1736401A (en) 1999-12-15 2001-06-25 Osaka Gas Co., Ltd. Fluid distributor, burner device, gas turbine engine, and cogeneration system
US6327860B1 (en) * 2000-06-21 2001-12-11 Honeywell International, Inc. Fuel injector for low emissions premixing gas turbine combustor
US6367262B1 (en) * 2000-09-29 2002-04-09 General Electric Company Multiple annular swirler
US6363726B1 (en) * 2000-09-29 2002-04-02 General Electric Company Mixer having multiple swirlers
DE10104695B4 (de) * 2001-02-02 2014-11-20 Alstom Technology Ltd. Vormischbrenner für eine Gasturbine
US6484489B1 (en) * 2001-05-31 2002-11-26 General Electric Company Method and apparatus for mixing fuel to decrease combustor emissions
US6848260B2 (en) * 2002-09-23 2005-02-01 Siemens Westinghouse Power Corporation Premixed pilot burner for a combustion turbine engine
EP1460339A1 (fr) * 2003-03-21 2004-09-22 Siemens Aktiengesellschaft Turbine à gaz
US7303388B2 (en) * 2004-07-01 2007-12-04 Air Products And Chemicals, Inc. Staged combustion system with ignition-assisted fuel lances
EP1624252A1 (fr) * 2004-08-06 2006-02-08 Siemens Aktiengesellschaft Brûleur, turbine à gaz et procédé opératoire pour un brûleur
ITTO20050208A1 (it) * 2005-03-30 2006-09-30 Ansaldo Energia Spa Gruppo bruciatore a gas per una turbina a gas
EP1764553A1 (fr) * 2005-09-14 2007-03-21 Enel Produzione S.p.A. Brûleur à prémélange à stabilité élevée pour turbine a gaz
EP2023041A1 (fr) * 2007-07-27 2009-02-11 Siemens Aktiengesellschaft Brûleur à prémélange et procédé de mise en oeuvre du brûleur
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US20100307160A1 (en) * 2009-06-03 2010-12-09 Vinayak Barve Convex Pilot Cone
EP2397764A1 (fr) * 2010-06-18 2011-12-21 Siemens Aktiengesellschaft Brûleur de turbines
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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8893511B2 (en) 2009-07-24 2014-11-25 General Electric Company Systems and methods for a gas turbine combustor having a bleed duct

Also Published As

Publication number Publication date
DE59801583D1 (de) 2001-10-31
WO1999004196A1 (fr) 1999-01-28
JP2001510885A (ja) 2001-08-07
EP0995066B1 (fr) 2001-09-26

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