EP2092245A1 - Brûleur pour turbine à gaz - Google Patents

Brûleur pour turbine à gaz

Info

Publication number
EP2092245A1
EP2092245A1 EP07857958A EP07857958A EP2092245A1 EP 2092245 A1 EP2092245 A1 EP 2092245A1 EP 07857958 A EP07857958 A EP 07857958A EP 07857958 A EP07857958 A EP 07857958A EP 2092245 A1 EP2092245 A1 EP 2092245A1
Authority
EP
European Patent Office
Prior art keywords
receptacle
heat shield
burner
kenn
ichnet
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
EP07857958A
Other languages
German (de)
English (en)
Other versions
EP2092245B1 (fr
Inventor
Andreas Böttcher
Jens Kleinfeld
Tobias Krieger
Sabine Tüschen
Ulrich Wörz
Thomas Grieb
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
Priority to EP07857958.8A priority Critical patent/EP2092245B1/fr
Publication of EP2092245A1 publication Critical patent/EP2092245A1/fr
Application granted granted Critical
Publication of EP2092245B1 publication Critical patent/EP2092245B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • 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
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • 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
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means

Definitions

  • the invention relates to a burner for a gas turbine with a main burner and a pilot burner.
  • Gas turbines include, as known, for example, from US 6,038,861, a compressor for compressing air, a combustion chamber for generating hot gas by burning fuel in communication with the compressed air, and a turbine for expanding the hot gas. It is known that gas turbines eject undesirable nitrogen oxides (NO x ) and carbon monoxide (CO).
  • NO x nitrogen oxides
  • CO carbon monoxide
  • Two-stage combustion systems have been developed that simultaneously produce efficient combustion and reduced NO x emissions. In such a two-stage combustion system, diffusion combustion is performed in the first stage to ignite and stabilize the flame. Premix combustion is performed in the second stage to reduce NO x emissions.
  • the first stage is the so-called pilot stage, which is usually carried out by a diffusion burner and causes significant increases in NO x emissions.
  • the main burner includes several main fuel mixers, each with a swirler that creates turbulence in the airflow.
  • the fuel supply line In the center of the Swirlers is the fuel supply line, which introduces the gas into the airflow.
  • Fig. 1 shows a fuel supply line with a heat shield in a main burner according to the prior art.
  • the fuel supply line 16 is located inside a support structure 6, which is arranged in the center of the Swirlers 4.
  • lines 16 which introduce the fuel from the interior of the support structure 6 in the Swirler- blades 4.
  • the gas mixes with the compressed air.
  • a receptacle 8 which forwards the fuel to the tip 10 of the arrangement.
  • a heat shield 18 which isolates the fuel from the environment.
  • oil injection holes 19 At the end of the heat shield 18 there are oil injection holes 19.
  • the heat shield 18 serves to thermally decouple the support structure 6 of the swivel 4 from the oil passages 16 in the interior of the arrangement. It consists of a tube, which was previously soldered or welded into the support structure 6. 12. The cohesive connection points 12 obstruct the deformation of the support structure 6 due to the colder heat shield 18, so that thermal stresses can occur. Due to these possible voltages, the maximum possible starting numbers - and thus also the maximum possible service life - can not be realized.
  • the invention has for its object to provide a burner for a gas turbine available, in which the occurrence of thermal stresses between the support structure and the heat shield can be reduced.
  • the object is achieved in a burner for a gas turbine with a main burner and a lotbrenner.
  • the main burner comprises a support structure, a heat shield and a receptacle for the heat shield.
  • the receptacle is located at least partially within the support structure, in particular concentrically, within the support structure, and the heat shield is located at least partially within the receptacle, in particular concentrically, within the receptacle.
  • the heat shield is attached to the receptacle by frictional engagement and / or frictional engagement.
  • the non-positive and / or frictional connection is a clamping connection.
  • the heat shield is fixed by a press fit between the tip and the receptacle.
  • the clamped seat allows free thermal stretching, so that the stresses in the component can be significantly reduced.
  • the required start numbers can be achieved in this way.
  • the solution is less expensive compared to the soldered connection (prior art), which has a high accuracy required.
  • the heat shield can also be screwed to the receptacle.
  • the heat shield may further comprise a collar, which serves for better clamping of the heat shield.
  • the collar may have an external thread and the receptacle a corresponding internal thread, which cooperate when screwing the heat shield with the recording.
  • the tip is screwed to the receptacle.
  • the screw connection is a simple construction that allows the tip to be connected to the receptacle.
  • the tip may be crimped with the receptacle. Crimping provides protection against uncontrolled release during operation of the gas turbine.
  • the heat shield is tubular.
  • the oil channel is thermally insulated inside the heat shield over its entire length.
  • the burner may comprise a Swirler, in the center of which the support structure may be arranged.
  • Fig. 1 shows a main burner with a Swirler according to the prior art.
  • Fig. 2 shows a main burner with a Swirler and a heat shield according to the invention.
  • Fig. 3 is an enlarged detail view of the attachment of the heat shield.
  • FIG. 2 shows a main burner 2 with a swirler 4, a support structure 6, a receptacle 8, a tip 10, an oil channel 16, swirler channels 17 and a heat shield 18.
  • the support structure 6 is located in the center of the Swirlers 4. It is tubular and protrudes with its two ends in each case beyond the Swirler.
  • the receptacle 8 is also substantially tubular and is located inside the support structure 6, concentric to the swirler 4. The interior of the receptacle 8 is formed by an oil passage 16 which extends along the longitudinal axis of the receptacle 8.
  • the heat shield 18 is arranged in the downstream part of the receptacle 8.
  • the heat shield 18 connects to the oil passage 16 and protrudes beyond the receptacle 8.
  • the heat shield is also tubular and has at its downstream end bores 19, through which the oil, which is introduced through the oil passage 16 and is passed through the interior of the heat shield 18 and through the tip 10, exits into the combustion chamber 3 ,
  • the tip 10 has a conical and a cylindrical part.
  • the cylindrical part is screwed to the receptacle 8.
  • this part of the tip is crimped.
  • the tip 10 may also be secured by crimping alone on the receptacle 8.
  • At the transition between the cylindrical part and the conical part of the tip are ⁇ laustrittsboh- ments, through which the guided in the heat shield oil can escape into the combustion chamber 3.
  • air from the compressor (not shown) is introduced into the swirler of the main burner 2.
  • the Swirler swirls the air and the oil exiting through the oil channels 17 from the Swirlerschaufein is mixed with the supplied air.
  • oil is passed through the oil passage 16, passed through the interior of the heat shield and fed through the holes 19 in the heat shield and the passages in the top of the combustion chamber 3 of the main burner 2.
  • FIG. 3 shows a detailed view X of the heat shield arrangement in FIG. 2.
  • the heat shield 18 has a collar 22 with two clamping points 20 and an external thread 28.
  • Clamping points 20 are clamped between a shoulder 24 of the receptacle and a shoulder 26 of the tip.
  • the heat shield 18 is screwed with its external thread 28 in an internal thread of the receptacle 8.
  • the heat shield 18 is clamped in the present embodiment both between receptacle 8 and tip 10 and bolted to the receptacle, it is also possible in principle to fix it alone by clamping or alone by screwing.
  • the nipples 20 between heat shield, receptacle and tip allow during operation a free thermal stretching of the receptacle 8 and the tip 10 around the heat shield 18 around, which hardly expands due to its material (ceramic).
  • the metallic components 8 and 10 have a relatively high thermal expansion during operation.

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)

Abstract

L'invention concerne un brûleur pour turbine à gaz, qui présente un brûleur principal (2) et un brûleur pilote. Le brûleur principal (2) présente une structure porteuse (6), un pare-chaleur (18) et un logement (8) pour le pare-chaleur (18). Le logement (8) est situé au moins en partie à l'intérieur de la structure porteuse (6) et le pare-chaleur (18) est situé au moins en partie à l'intérieur du logement (8). Le brûleur est caractérisé en ce que le pare-chaleur (18) est fixé sur le logement (8) par une liaison à frottement.
EP07857958.8A 2006-12-22 2007-12-20 Brûleur pour turbine à gaz avec un écran thermique pour l'alimentation de combustible Active EP2092245B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP07857958.8A EP2092245B1 (fr) 2006-12-22 2007-12-20 Brûleur pour turbine à gaz avec un écran thermique pour l'alimentation de combustible

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP06026685A EP1936276A1 (fr) 2006-12-22 2006-12-22 Brûleur pour une turbine à gaz
EP07857958.8A EP2092245B1 (fr) 2006-12-22 2007-12-20 Brûleur pour turbine à gaz avec un écran thermique pour l'alimentation de combustible
PCT/EP2007/064338 WO2008077882A1 (fr) 2006-12-22 2007-12-20 Brûleur pour turbine à gaz

Publications (2)

Publication Number Publication Date
EP2092245A1 true EP2092245A1 (fr) 2009-08-26
EP2092245B1 EP2092245B1 (fr) 2016-11-16

Family

ID=38038921

Family Applications (2)

Application Number Title Priority Date Filing Date
EP06026685A Withdrawn EP1936276A1 (fr) 2006-12-22 2006-12-22 Brûleur pour une turbine à gaz
EP07857958.8A Active EP2092245B1 (fr) 2006-12-22 2007-12-20 Brûleur pour turbine à gaz avec un écran thermique pour l'alimentation de combustible

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP06026685A Withdrawn EP1936276A1 (fr) 2006-12-22 2006-12-22 Brûleur pour une turbine à gaz

Country Status (4)

Country Link
US (1) US8869534B2 (fr)
EP (2) EP1936276A1 (fr)
JP (1) JP5047309B2 (fr)
WO (1) WO2008077882A1 (fr)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2085695A1 (fr) * 2008-01-29 2009-08-05 Siemens Aktiengesellschaft Buse à combustible dotée d'un canal à tourbillon et procédé de fabrication d'une buse à combustible
US9341374B2 (en) * 2014-06-03 2016-05-17 Siemens Energy, Inc. Fuel nozzle assembly with removable components
DE102014220689A1 (de) 2014-10-13 2016-04-14 Siemens Aktiengesellschaft Brennstoffdüsenkörper
EP3247944B1 (fr) * 2015-01-22 2020-04-01 Siemens Aktiengesellschaft Système de mélange d'admission de chambre de combustion avec aubes de coupelle rotative comportant des fentes
KR101657535B1 (ko) 2015-05-21 2016-09-19 두산중공업 주식회사 버닝 저감 연료공급노즐.
US11486581B2 (en) * 2020-09-29 2022-11-01 Pratt & Whitney Canada Corp. Fuel nozzle and associated method of assembly

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GB854135A (en) * 1958-03-05 1960-11-16 Rolls Royce Improvements in or relating to combustion equipment
US3685741A (en) * 1970-07-16 1972-08-22 Parker Hannifin Corp Fuel injection nozzle
US4708293A (en) * 1983-02-24 1987-11-24 Enel-Ente Nazionale Per L'energia Elettrica Atomizer for viscous liquid fuels
US4898329A (en) * 1987-11-04 1990-02-06 United Technologies Corporation Apparatus for a fuel system
US4930703A (en) * 1988-12-22 1990-06-05 General Electric Company Integral fuel nozzle cover for gas turbine combustor
US5101634A (en) * 1989-12-20 1992-04-07 Sundstrand Corporation Fuel injector for a turbine engine
SE469145B (sv) * 1991-09-27 1993-05-17 Abb Carbon Ab Saett och munstycke foer tillfoersel av pastabraensle till en fluidiserad baedd
US5247790A (en) * 1992-09-18 1993-09-28 Westinghouse Electric Corp. Gas turbine fuel nozzle with replaceable cap
US5598696A (en) * 1994-09-20 1997-02-04 Parker-Hannifin Corporation Clip attached heat shield
US5697553A (en) * 1995-03-03 1997-12-16 Parker-Hannifin Corporation Streaked spray nozzle for enhanced air/fuel mixing
JPH09145058A (ja) * 1995-11-17 1997-06-06 Toshiba Corp ガスタービン燃焼器
WO1999019670A2 (fr) 1997-10-10 1999-04-22 Siemens Westinghouse Power Corporation DISTRIBUTEUR DE COMBUSTIBLE POUR DISPOSITIF COMBUSTOR A FAIBLE TENEUR EN NOx
US6038861A (en) * 1998-06-10 2000-03-21 Siemens Westinghouse Power Corporation Main stage fuel mixer with premixing transition for dry low Nox (DLN) combustors
JP4323723B2 (ja) * 1998-10-09 2009-09-02 ゼネラル・エレクトリック・カンパニイ ガスタービンエンジン燃焼器の燃料噴射組立体
US6298667B1 (en) * 2000-06-22 2001-10-09 General Electric Company Modular combustor dome
US6540162B1 (en) * 2000-06-28 2003-04-01 General Electric Company Methods and apparatus for decreasing combustor emissions with spray bar assembly
US6688534B2 (en) * 2001-03-07 2004-02-10 Delavan Inc Air assist fuel nozzle
JP2003028425A (ja) * 2001-07-17 2003-01-29 Mitsubishi Heavy Ind Ltd 予混合燃焼器のパイロットバーナー、予混合燃焼器、およびガスタービン
US6755024B1 (en) * 2001-08-23 2004-06-29 Delavan Inc. Multiplex injector
JP4134311B2 (ja) * 2002-03-08 2008-08-20 独立行政法人 宇宙航空研究開発機構 ガスタービン燃焼器
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Title
See references of WO2008077882A1 *

Also Published As

Publication number Publication date
JP2010513838A (ja) 2010-04-30
EP2092245B1 (fr) 2016-11-16
US20100170267A1 (en) 2010-07-08
US8869534B2 (en) 2014-10-28
EP1936276A1 (fr) 2008-06-25
JP5047309B2 (ja) 2012-10-10
WO2008077882A1 (fr) 2008-07-03

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