EP1985924A1 - Drallvorrichtung - Google Patents

Drallvorrichtung Download PDF

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Publication number
EP1985924A1
EP1985924A1 EP07008236A EP07008236A EP1985924A1 EP 1985924 A1 EP1985924 A1 EP 1985924A1 EP 07008236 A EP07008236 A EP 07008236A EP 07008236 A EP07008236 A EP 07008236A EP 1985924 A1 EP1985924 A1 EP 1985924A1
Authority
EP
European Patent Office
Prior art keywords
swirler
twisted
central axis
vane
vanes
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.)
Withdrawn
Application number
EP07008236A
Other languages
English (en)
French (fr)
Inventor
Nigel Wilbraham
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 EP07008236A priority Critical patent/EP1985924A1/de
Priority to PCT/EP2008/054658 priority patent/WO2008128955A1/en
Priority to US12/597,261 priority patent/US20100175381A1/en
Priority to EP08736322A priority patent/EP2137460A1/de
Priority to CN2008800133415A priority patent/CN101668989B/zh
Priority to RU2009143010/06A priority patent/RU2467253C2/ru
Publication of EP1985924A1 publication Critical patent/EP1985924A1/de
Withdrawn legal-status Critical Current

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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
    • F23R3/02—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
    • 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
    • F23C7/004—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion using vanes
    • 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
    • F23D2900/14—Special features of gas burners
    • F23D2900/14021—Premixing burners with swirling or vortices creating means for fuel or air
    • 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
    • F23D2900/14—Special features of gas burners
    • F23D2900/14701—Swirling means inside the mixing tube or chamber to improve premixing

Definitions

  • the invention relates to a fuel injection system and improvements for the further diminishment of air pollutants such as nitrogen oxides (NO x ).
  • air pollutants such as nitrogen oxides (NO x ).
  • the first is to use a fine distribution of fuel in the air, generating a fuel/air mixture with a low fuel fraction.
  • the thermal mass of the excess air present in the reaction zone of a lean premixed combustor absorbs heat and limits the temperature rise of the products of combustion to a level where thermal NO x is not excessively formed.
  • the second measure is to provide a thorough mixing of fuel and air prior to combustion. The better the mixing, the fewer regions exist where the fuel concentration is significantly higher than average, the fewer the regions reaching higher temperatures than average, the lower the fraction of thermal NO x will be.
  • premixing of fuel and air in a gas turbine engine takes place by injecting fuel into an air stream in a swirling zone of a combustor which is located upstream from the combustion zone.
  • the swirling produces a mixing of fuel and air before the mixture enters the combustion zone.
  • An object of the invention is to provide a swirler, allowing for a better pre-mixing of gaseous fuel and compressor air to provide a homogeneous fuel/air mixture and thereby reduce formation of NO x .
  • Another objective is to provide a burner with an improved swirler.
  • Still another objective is to provide a gas turbine with an improved swirler.
  • An inventive swirler incorporates a modified radial swirler assembly.
  • the modification is best described by a partly twisted radial swirler.
  • None of the prior art is targeting the generation of turbulent secondary flows along the swirl vanes with the specific aim of assisting fuel air mixing.
  • the twisted vanes comprise straight parts at the base portions of the twisted vanes.
  • This feature provides a well defined shear layer region for any reverse flow into the swirler assembly. This is advantageous because it increases the stability of any flame in that region.
  • the height of the straight parts should not exceed 50% of the twisted vanes' height in order to benefit from the turbulent secondary flows generated in the twisted parts. Therefore it is also advantageous to twist the vanes by an angle of up to 120°. However, twisted vanes with angles differing considerably from 120° will also provide desirable turbulent secondary flows.
  • FIG. 1 a typical prior art radial swirler 1 is shown.
  • the turning vanes 9 of a radial swirler 1 are arranged on a first plate 2 that is normal to the central axis 3 of the swirler 1 body.
  • the vanes 9 are of pie slice type with substantially triangular footprints 4 (see Figure 3 ) and rectangular side faces 13 and a slightly curved outer surface 10.
  • the turning vanes 9 are fixed to a second plate 8 with their sides showing away from the first plate 2.
  • Swirler passages 14 are formed by opposing side faces 13 of swirler vanes 9, by the surface of the first plate 2 and by a surface of the second plate 8.
  • the second plate 8 is connected to a combustion pre-chamber 11.
  • This configuration of the swirler 1 forces the airflow (as shown by the arrows) to move within the passages 14 radially inwardly towards the central axis 3 of the swirler 1 body.
  • a radial swirler 1 is capable of creating strong swirl and thorough mixing with little concern of the problem of aerodynamic wake flows.
  • FIG 2 shows the view of an embodiment of the inventive swirler 1.
  • Respective base portions 6 of the turning vanes 9 are arranged on a first plate 2 that is normal to the central axis 3 of the swirler 1 body and the footprints 4 (see Figure 3 ) of the vanes 9 are of substantially triangular shape.
  • the vanes 9 are twisted and will be referred to as twisted vanes 5.
  • the embodiment of Figure 2 comprises twisted vanes 5 with straight base portions 6 and twisted parts 7.
  • the straight base portions 6 have a shape described by a translation of the vane footprints 4 (see Figure 3 ) parallel to the central axis 3 of the swirler 1, whereas the twisted parts 7 have a shape described by a further translation of the vane footprints 4 along the central axis 3 superimposed by a rotation of the vane footprints 4 about the central axis 3.
  • an inventive swirler 1 is shown without second plate 8 and combustor pre-chamber 11 (see Figures 1 and 2 ) where the twisted vanes 5 are arranged on a first plate 2.
  • the substantially triangular vane footprints 4 can be seen very clearly in this view.
  • Figure 3 shows the turbulent secondary flows 12 generated along the twisted vanes 5, improving fuel/air mixing.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP07008236A 2007-04-23 2007-04-23 Drallvorrichtung Withdrawn EP1985924A1 (de)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP07008236A EP1985924A1 (de) 2007-04-23 2007-04-23 Drallvorrichtung
PCT/EP2008/054658 WO2008128955A1 (en) 2007-04-23 2008-04-17 Swirler
US12/597,261 US20100175381A1 (en) 2007-04-23 2008-04-17 Swirler
EP08736322A EP2137460A1 (de) 2007-04-23 2008-04-17 Verwirbler
CN2008800133415A CN101668989B (zh) 2007-04-23 2008-04-17 旋流器
RU2009143010/06A RU2467253C2 (ru) 2007-04-23 2008-04-17 Завихритель

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP07008236A EP1985924A1 (de) 2007-04-23 2007-04-23 Drallvorrichtung

Publications (1)

Publication Number Publication Date
EP1985924A1 true EP1985924A1 (de) 2008-10-29

Family

ID=38521629

Family Applications (2)

Application Number Title Priority Date Filing Date
EP07008236A Withdrawn EP1985924A1 (de) 2007-04-23 2007-04-23 Drallvorrichtung
EP08736322A Withdrawn EP2137460A1 (de) 2007-04-23 2008-04-17 Verwirbler

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP08736322A Withdrawn EP2137460A1 (de) 2007-04-23 2008-04-17 Verwirbler

Country Status (5)

Country Link
US (1) US20100175381A1 (de)
EP (2) EP1985924A1 (de)
CN (1) CN101668989B (de)
RU (1) RU2467253C2 (de)
WO (1) WO2008128955A1 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2010107401A3 (en) * 2009-03-19 2011-04-07 Brinox, D.O.O. Device for coating particles via an airflow vortex generation
WO2012156631A1 (fr) * 2011-05-17 2012-11-22 Snecma Chambre annulaire de combustion pour une turbomachine

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8517719B2 (en) * 2009-02-27 2013-08-27 Alstom Technology Ltd Swirl block register design for wall fired burners
US10928101B2 (en) * 2011-06-10 2021-02-23 Carrier Corporation Ejector with motive flow swirl
EP2685160B1 (de) * 2012-07-10 2018-02-21 Ansaldo Energia Switzerland AG Multikonus-Vormischungsbrenner für eine Gasturbine
CN103851623B (zh) * 2014-03-28 2017-03-15 李延新 一种强制回焰的燃烧室
EP3236157A1 (de) 2016-04-22 2017-10-25 Siemens Aktiengesellschaft Wirbler zum mischen von kraftstoff mit luft in einem verbrennungsmotor
JP7564779B2 (ja) * 2021-07-02 2024-10-09 本田技研工業株式会社 燃料ノズル装置の製造方法
US20230212984A1 (en) * 2021-12-30 2023-07-06 General Electric Company Engine fuel nozzle and swirler

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4203598C1 (en) * 1992-02-07 1993-06-24 Industrial Technology Research Institute, Chutung, Hsing-Chu, Tw Burner swirl-inducing component with axial vanes - has deflection points on curved vanes determined dependent on inner and outer radii edge curvature and passage diameter
US5394688A (en) * 1993-10-27 1995-03-07 Westinghouse Electric Corporation Gas turbine combustor swirl vane arrangement
EP0902237A2 (de) * 1997-09-10 1999-03-17 Mitsubishi Heavy Industries, Ltd. Verwundene Drallschaufeln für eine Brennkammer
US6141967A (en) * 1998-01-09 2000-11-07 General Electric Company Air fuel mixer for gas turbine combustor
US20030172655A1 (en) * 2002-03-12 2003-09-18 Verdouw Albert J. Dry low combustion system with means for eliminating combustion noise

Family Cites Families (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2657741A (en) * 1948-07-06 1953-11-03 Ralph C Brierly Air control ring
JPS6097351U (ja) * 1983-12-09 1985-07-03 アイシン精機株式会社 スタ−リング機関用スワラ−
US4681532A (en) * 1985-05-02 1987-07-21 Landy Chung Boiler furnace air register
US5144804A (en) * 1989-07-07 1992-09-08 Fuel Systems Textron Inc. Small airblast fuel nozzle with high efficiency inner air swirler
DE4110507C2 (de) * 1991-03-30 1994-04-07 Mtu Muenchen Gmbh Brenner für Gasturbinentriebwerke mit mindestens einer für die Zufuhr von Verbrennungsluft lastabhängig regulierbaren Dralleinrichtung
JPH06272862A (ja) * 1993-03-18 1994-09-27 Hitachi Ltd 燃料空気混合方法およびその混合装置
US5450724A (en) * 1993-08-27 1995-09-19 Northern Research & Engineering Corporation Gas turbine apparatus including fuel and air mixer
CN1162089A (zh) * 1995-12-21 1997-10-15 Abb研究有限公司 热发生器的燃烧器
FR2752917B1 (fr) * 1996-09-05 1998-10-02 Snecma Systeme d'injection a degre d'homogeneisation avancee
US5899075A (en) * 1997-03-17 1999-05-04 General Electric Company Turbine engine combustor with fuel-air mixer
DE59710380D1 (de) * 1997-11-21 2003-08-07 Alstom Brenner für den Betrieb eines Wärmeerzeugers
US6082113A (en) * 1998-05-22 2000-07-04 Pratt & Whitney Canada Corp. Gas turbine fuel injector
DE19859829A1 (de) * 1998-12-23 2000-06-29 Abb Alstom Power Ch Ag Brenner zum Betrieb eines Wärmeerzeugers
US7104066B2 (en) * 2003-08-19 2006-09-12 General Electric Company Combuster swirler assembly
US7131273B2 (en) * 2004-12-17 2006-11-07 General Electric Company Gas turbine engine carburetor with flat retainer connecting primary and secondary swirlers
CN101137869A (zh) * 2005-03-09 2008-03-05 阿尔斯托姆科技有限公司 用于使燃烧室运转的预混燃烧器
US7237730B2 (en) * 2005-03-17 2007-07-03 Pratt & Whitney Canada Corp. Modular fuel nozzle and method of making
EP1929208A1 (de) * 2005-09-30 2008-06-11 Ansaldo Energia S.P.A. Verfahren zum anfahren einer mit einem gasbrenner ausgestatteten gasturbine und axialer drallerzeuger für den brenner
FR2896031B1 (fr) * 2006-01-09 2008-04-18 Snecma Sa Dispositif d'injection multimode pour chambre de combustion, notamment d'un turboreacteur
JP4719059B2 (ja) * 2006-04-14 2011-07-06 三菱重工業株式会社 ガスタービンの予混合燃焼バーナー
US7762058B2 (en) * 2007-04-17 2010-07-27 Pratt & Whitney Rocketdyne, Inc. Ultra-compact, high performance aerovortical rocket thruster
US8037689B2 (en) * 2007-08-21 2011-10-18 General Electric Company Turbine fuel delivery apparatus and system
US8015821B2 (en) * 2008-01-11 2011-09-13 Spytek Aerospace Corporation Apparatus and method for a gas turbine entrainment system
US20090249789A1 (en) * 2008-04-08 2009-10-08 Baifang Zuo Burner tube premixer and method for mixing air and gas in a gas turbine engine

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4203598C1 (en) * 1992-02-07 1993-06-24 Industrial Technology Research Institute, Chutung, Hsing-Chu, Tw Burner swirl-inducing component with axial vanes - has deflection points on curved vanes determined dependent on inner and outer radii edge curvature and passage diameter
US5394688A (en) * 1993-10-27 1995-03-07 Westinghouse Electric Corporation Gas turbine combustor swirl vane arrangement
EP0902237A2 (de) * 1997-09-10 1999-03-17 Mitsubishi Heavy Industries, Ltd. Verwundene Drallschaufeln für eine Brennkammer
US6141967A (en) * 1998-01-09 2000-11-07 General Electric Company Air fuel mixer for gas turbine combustor
US20030172655A1 (en) * 2002-03-12 2003-09-18 Verdouw Albert J. Dry low combustion system with means for eliminating combustion noise

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2010107401A3 (en) * 2009-03-19 2011-04-07 Brinox, D.O.O. Device for coating particles via an airflow vortex generation
RU2542276C2 (ru) * 2009-03-19 2015-02-20 Бринокс, Д.О.О. Усовершенствованное устройство для нанесения покрытия на частицы новым способом с помощью вихревого генератора воздушного потока
WO2012156631A1 (fr) * 2011-05-17 2012-11-22 Snecma Chambre annulaire de combustion pour une turbomachine
US9951955B2 (en) 2011-05-17 2018-04-24 Snecma Annular combustion chamber for a turbine engine

Also Published As

Publication number Publication date
RU2467253C2 (ru) 2012-11-20
US20100175381A1 (en) 2010-07-15
RU2009143010A (ru) 2011-05-27
CN101668989A (zh) 2010-03-10
WO2008128955A1 (en) 2008-10-30
EP2137460A1 (de) 2009-12-30
CN101668989B (zh) 2012-01-04

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