EP1030109B1 - Injecteur de combustible pour l'injection de combustibles liquides et/ou gazeux dans une chambre de combustion - Google Patents

Injecteur de combustible pour l'injection de combustibles liquides et/ou gazeux dans une chambre de combustion Download PDF

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Publication number
EP1030109B1
EP1030109B1 EP00810118A EP00810118A EP1030109B1 EP 1030109 B1 EP1030109 B1 EP 1030109B1 EP 00810118 A EP00810118 A EP 00810118A EP 00810118 A EP00810118 A EP 00810118A EP 1030109 B1 EP1030109 B1 EP 1030109B1
Authority
EP
European Patent Office
Prior art keywords
fuel
passage
liquid
lance
air
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
EP00810118A
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German (de)
English (en)
Other versions
EP1030109A1 (fr
Inventor
Urs Benz
Adnan Dr. Eroglu
Franz Dr. Joos
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
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Filing date
Publication date
Application filed by Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP1030109A1 publication Critical patent/EP1030109A1/fr
Application granted granted Critical
Publication of EP1030109B1 publication Critical patent/EP1030109B1/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 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
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
    • F23D11/101—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting before the burner outlet
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2214/00—Cooling

Definitions

  • the present invention relates to the field of burner technology as it is is used in particular in gas turbines. It affects a fuel lance for injecting liquid and / or gaseous fuels into a combustion chamber, which fuel lance is part of a combustion air jet in a secondary or tertiary burner with a flow around it, and a liquid fuel channel within an outer lance jacket Supply of liquid fuel, a surrounding the liquid fuel channel Gas channel for the supply of gaseous fuel and one the gas channel surrounding air duct for supplying cooling or atomizing air, and first means for radially injecting the liquid fuel from the liquid fuel channel into the combustion chamber and second means for radial injection of the gaseous fuel from the gas channel into the combustion chamber.
  • Such a fuel lance is e.g. B. from a previous patent application DE-A1-43 26 802 known to the applicant.
  • a fuel lance is known from the document DE-A1-43 26 802 mentioned at the beginning known that the applicant is currently using their gas turbines (see also the publications US-A-5,341,018, US-A-5,626,017 and EP-A1-0 620 362) is used.
  • the nozzles for gaseous fuel and liquid fuel (Oil etc.) are combined.
  • the liquid fuel is injected according to the so-called air blast principle, i.e. that as a film on an atomizer lip Applied fuel is in the shear field of the surrounding air flow atomized and mixed with the combustion air as a fuel mist. Does that happen Injection transverse to the direction of flow of the combustion air, so is the depth of penetration determined exclusively by the air pulse.
  • the momentum of the liquid Fuel is only used for film production, but not to support the Fuel jet used.
  • the object is achieved by the entirety of the features of claim 1.
  • the essence of the invention is the liquid fuel by means of a suitable Guide tube arrangement as a plain jet radially to the main flow direction.
  • This type of injection means that the liquid fuel stays in the vehicle for a while is reduced in the premixing section and thus less water must be added to prevent a flashback.
  • Another advantage is the improved fuel-air mixture due to this arrangement.
  • the existing one that has already been optimized for gas injection can be used Air flow field of the main flow also for atomization and mixing of the liquid fuel.
  • the injection of the gaseous fuel and the surrounding air jacket turns out to be particularly favorable if according to a second preferred Embodiment, the second guide tube in the region of the air duct in the outer diameter tapered towards the mouth, and the first guide tube in the area of the gas channel tapers conically in the outside diameter towards the mouth.
  • a preferred embodiment is one in longitudinal section Fuel lance reproduced according to the invention.
  • the fuel lance 10 which extends along a lance axis 24, which in turn essentially parallel to the main flow direction 25 of a combustion air flow flowing around the lance is shown in the figure only with its head area.
  • a liquid fuel tube 16 In the fuel lance 10 are located one inside the other concentrically to the lance axis 24 a liquid fuel tube 16, a gas tube 14 and a lance jacket 12 are arranged.
  • the interior of the liquid fuel tube 16 forms a liquid fuel channel 17, through which liquid fuel, in particular oil or the like, for injection into Direction of the arrow shown is guided into the lance head 11.
  • a gas duct 15 formed by which gaseous fuel in the direction of the drawn Arrow is injected into the lance head 11.
  • an air duct 13 is formed through which Air is guided into the lance head 11 in the direction of the arrow shown becomes.
  • the liquid fuel from the liquid fuel channel 17 radially injected into the combustion chamber in the form of a plain jet into which the Fuel lance 10 protrudes.
  • a first guide tube 23 is provided for injection. which goes in the radial direction from the liquid fuel channel 17 and in Area of a (circular) jacket opening 22 in the lance jacket 12 ends.
  • the gaseous fuel is also radially from the gas channel 15 to the lance axis 24 and thus injected into the main flow direction 25 into the combustion chamber.
  • a second guide tube 21 is provided, which is in the radial direction starts from the gas channel 15 and also ends in the region of the jacket opening 22.
  • Both guide tubes 21, 23 are arranged concentrically one inside the other at a distance, so that the gaseous fuel in the annular gap thus formed between the two Guide tubes 21, 23 is guided.
  • the diameter of the jacket opening 22 is relative chosen for the outer diameter of the second guide tube 21 so that a annular gap for generating a protective surrounding the gas jet Air jacket remains free.
  • the flow conditions are particularly favorable for the Air jacket flow when the two guide tubes 21, 23 - as shown in the figure flush end with the inner contour of the lance jacket 12.
  • the deflection of the flows out of the gas duct 15 and the air duct 13 the axial direction in the radial direction and the formation of the desired Sheath flows can be further facilitated if the second guide tube 21 in the area of the air duct 14 in the outer diameter towards the mouth tapers, and the first guide tube 23 in the region of the gas duct 15 in the outer diameter tapered towards the mouth.
  • air from the air duct can be made in a manner known per se 13 for cooling the head part 18 and for generating an axial air curtain be guided into the lance head. Do this on a concentric ring arranged around the lance axis 24 around axial bores 20, through the air in can emerge in the axial direction. The air required for this comes from the air duct 13 led over a head channel 19 which in the edge area through the lance head 11 runs. This ensures that the lance head 11 through the air flowing through it is cooled.

Claims (6)

  1. Injecteur de combustible (10) pour l'injection de combustibles liquides et/ou gazeux dans une chambre de combustion, lequel injecteur de combustible (10) fait partie d'un brûleur secondaire ou tertiaire assurant l'écoulement d'un jet d'air de combustion dans un sens d'écoulement principal (25), et comprend à l'intérieur d'une enveloppe d'injecteur (12) extérieure un canal de combustible liquide (17) pour l'arrivée de combustible liquide, un canal de gaz 15 entourant le canal de combustible liquide (17) pour l'arrivée de combustible gazeux et un canal d'air (13) entourant le canal de gaz (15) pour l'arrivée d'air de refroidissement et/ou de pulvérisation, ainsi que des premiers moyens (23) pour l'injection radiale du combustible liquide sortant du canal de combustible liquide (17) dans la chambre de combustion et des seconds moyens (21) pour l'injection radiale du combustible gazeux. sortant du canal de gaz (15) dans la chambre de combustion, caractérisé en ce que les premiers moyens comprennent un premier tuyau conducteur (23), qui part dans le sens radial du canal de combustible liquide (17), traverse le canal de gaz (15) et le canal d'air (13) et va vers l'extérieur, en ce que les seconds moyens comprennent un second tuyau conducteur (21) qui part dans le sens radial du canal de gaz (15), traverse le canal d'air (13) et va vers l'extérieur et entoure le premier tuyau conducteur (23) à distance de façon concentrique, et en ce que les deux tuyaux conducteurs (21, 23) débouchent dans la zone d'une ouverture d'enveloppe (22) dans l'enveloppe d'injecteur (12) de telle sorte que le jet de combustible liquide sortant du premier tuyau conducteur (23) sort sous la forme d'un jet plein dans la chambre de combustion et les jets de combustible sortant des tuyaux conducteurs (21, 23) sont entourés à la façon d'une enveloppe par l'air sortant du canal d'air (13) et traversant l'ouverture d'enveloppe (22).
  2. Injecteur de combustible selon la revendication 1, caractérisé en ce que les deux tuyaux conducteurs (21, 23) se terminent au même niveau que le contour intérieur de l'enveloppe d'injecteur (12).
  3. Injecteur de combustible selon l'une quelconque des revendications 1 et 2, caractérisé en ce que le second tuyau conducteur (21) se rétrécit dans la zone du canal d'air (13) dans le diamètre extérieur à la façon d'un cône en direction de l'embouchure.
  4. Injecteur de combustible selon l'une quelconque des revendications 1 à 3, caractérisé en ce que le premier tuyau conducteur (23) se rétrécit dans la zone du canal du gaz (15) dans le diamètre extérieur à la façon d'un cône en direction de l'embouchure.
  5. Injecteur de combustible selon l'une quelconque des revendications 1 à 4, caractérisé en ce que le canal de combustible liquide (17) et le canal de gaz (15) sont disposés de façon concentrique l'un par rapport à l'autre.
  6. Injecteur de combustible selon l'une quelconque des revendications 1 à 4, caractérisé en ce que le canal de combustible liquide (17) et/ou le canal de -gaz (15) est/sont disposé(s) de façon excentrée.
EP00810118A 1999-02-15 2000-02-10 Injecteur de combustible pour l'injection de combustibles liquides et/ou gazeux dans une chambre de combustion Expired - Lifetime EP1030109B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19905996 1999-02-15
DE19905996A DE19905996A1 (de) 1999-02-15 1999-02-15 Brennstofflanze zum Eindüsen von flüssigen und/oder gasförmigen Brennstoffen in eine Brennkammer

Publications (2)

Publication Number Publication Date
EP1030109A1 EP1030109A1 (fr) 2000-08-23
EP1030109B1 true EP1030109B1 (fr) 2004-04-07

Family

ID=7897373

Family Applications (1)

Application Number Title Priority Date Filing Date
EP00810118A Expired - Lifetime EP1030109B1 (fr) 1999-02-15 2000-02-10 Injecteur de combustible pour l'injection de combustibles liquides et/ou gazeux dans une chambre de combustion

Country Status (5)

Country Link
US (1) US6325618B1 (fr)
EP (1) EP1030109B1 (fr)
JP (1) JP4465076B2 (fr)
CN (1) CN1175202C (fr)
DE (2) DE19905996A1 (fr)

Families Citing this family (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10050285C2 (de) * 2000-10-10 2003-03-06 Innovatherm Prof Dr Leisenberg Gmbh & Co Kg Gasbrenner für einen Tunnelofen
DE10056243A1 (de) 2000-11-14 2002-05-23 Alstom Switzerland Ltd Brennkammer und Verfahren zum Betrieb dieser Brennkammer
DE10330023A1 (de) * 2002-07-20 2004-02-05 Alstom (Switzerland) Ltd. Wirbelgenerator mit kontrollierter Nachlaufströmung
DE102004041272B4 (de) * 2004-08-23 2017-07-13 General Electric Technology Gmbh Hybridbrennerlanze
FR2875584B1 (fr) * 2004-09-23 2009-10-30 Snecma Moteurs Sa Injecteur a effervescence pour systeme aeromecanique d'injection air/carburant dans une chambre de combustion de turbomachine
US8387390B2 (en) 2006-01-03 2013-03-05 General Electric Company Gas turbine combustor having counterflow injection mechanism
GB0618196D0 (en) 2006-09-15 2006-10-25 Pursuit Dynamics Plc An improved mist generating apparatus and method
JP2008185254A (ja) * 2007-01-30 2008-08-14 General Electric Co <Ge> 同軸燃料−空気通路を有する逆流噴射機構
US7775791B2 (en) * 2008-02-25 2010-08-17 General Electric Company Method and apparatus for staged combustion of air and fuel
EP2116766B1 (fr) 2008-05-09 2016-01-27 Alstom Technology Ltd Brûleur avec lance à combustible
EP2199674B1 (fr) * 2008-12-19 2012-11-21 Alstom Technology Ltd Brûleur d'une turbine à gaz avec une configuration spéciale de lance
US8434291B2 (en) * 2009-01-08 2013-05-07 General Electric Company Systems and methods for detecting a flame in a fuel nozzle of a gas turbine
EP2211110B1 (fr) * 2009-01-23 2019-05-01 Ansaldo Energia Switzerland AG Brûleur pour turbine à gaz
EP2236934A1 (fr) 2009-03-18 2010-10-06 Siemens Aktiengesellschaft Agencement de brûleur
US9587823B2 (en) 2009-03-25 2017-03-07 Wallace Horn Laminar flow jets
US8087928B2 (en) * 2009-03-25 2012-01-03 Horn Wallace E Laminar flow jets
US20110072823A1 (en) * 2009-09-30 2011-03-31 Daih-Yeou Chen Gas turbine engine fuel injector
EP2388520B1 (fr) * 2010-05-20 2016-10-26 General Electric Technology GmbH Lance d'un brûleur d'une turbine à gaz
CN101936527B (zh) * 2010-09-07 2012-10-10 西安航天远征流体控制股份有限公司 油氧燃烧非预混式开工烧嘴
EP2789915A1 (fr) * 2013-04-10 2014-10-15 Alstom Technology Ltd Procédé de fonctionnement d'une chambre de combustion et chambre de combustion
DE102018204741A1 (de) * 2018-03-28 2019-10-02 Siemens Aktiengesellschaft Brennstoffzuführeinrichtung

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Also Published As

Publication number Publication date
CN1175202C (zh) 2004-11-10
DE19905996A1 (de) 2000-08-17
EP1030109A1 (fr) 2000-08-23
JP2000234735A (ja) 2000-08-29
JP4465076B2 (ja) 2010-05-19
CN1265455A (zh) 2000-09-06
DE50005950D1 (de) 2004-05-13
US6325618B1 (en) 2001-12-04

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