EP0828115A1 - Brennstoffeinspritzsystem für eine Brennkammer - Google Patents

Brennstoffeinspritzsystem für eine Brennkammer Download PDF

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Publication number
EP0828115A1
EP0828115A1 EP97402058A EP97402058A EP0828115A1 EP 0828115 A1 EP0828115 A1 EP 0828115A1 EP 97402058 A EP97402058 A EP 97402058A EP 97402058 A EP97402058 A EP 97402058A EP 0828115 A1 EP0828115 A1 EP 0828115A1
Authority
EP
European Patent Office
Prior art keywords
spin
sleeve
fuel
air
radial
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
EP97402058A
Other languages
English (en)
French (fr)
Other versions
EP0828115B1 (de
Inventor
Denis Roger Henri Ansart
Gilles Gérard Claude Lepretre
Denis Jean Maurice Sandelis
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.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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.)
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Publication date
Application filed by Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0828115A1 publication Critical patent/EP0828115A1/de
Application granted granted Critical
Publication of EP0828115B1 publication Critical patent/EP0828115B1/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
    • 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

Definitions

  • the invention relates to fuel and air supply primary of a combustion chamber, especially for turbomachinery.
  • a typical example of antagonistic performances is that of flame stability at idle and the need to avoid fumes and the emission of nitrogen oxides at full gas. So the injection system of fuel and air must ensure proper combustion at rpm and under very diverse conditions.
  • FR-A-2 596 102 shows in FIG. 18 a mechanical injector which has a spin having an even number of fins defining an equal number of air intake passages, one passage in two being at radial inlet in order to deliver an air flow around the injection channel of fuel to constitute a first mixture in a chamber delimited by a socket with a converging / diverging internal contour, the other passages being at axial entry and delivering an air flow to the downstream periphery of the sleeve.
  • the present invention proposes to produce a device mechanical injection combined with strong premix tendrils permeability which makes it possible to meet the criteria of pollution and performance, at different speeds, imposed on engine manufacturers.
  • the invention therefore relates to an air injection device and fuel in a combustion chamber, in particular of turbomachine, said device comprising from upstream to downstream, an injector of axis A fuel, a venturi sleeve arranged coaxially to axis A and having a converging / diverging internal contour delimiting a premix chamber in which the fuel is injected, a bowl flared downstream and having a sleeve upstream for fixing it around the socket, and means for injecting air from spraying fuel.
  • this device is characterized in that the means for injecting the fuel spray air have a first high-permeability radial spin arranged upstream of the socket and allowing a first air-fuel mixture to be produced in the premix chamber, a second radial spin having a plurality of channels provided in the upstream part of the socket and opening into the converging internal contour, said second spin being intended to ensure homogeneous carburetion in the venturi, and a third axial spin arranged at the periphery of the downstream part of the bush, and by the fact that the axial outlets of the third spin circumferentially alternate with the radial outlets of the second spin.
  • the inputs of the third spin are supplied in air through radial passages in the upstream part of the socket and alternating with the channels of the second spin.
  • the third spin is formed by grooves in the peripheral wall of the sleeve, said grooves being covered by the bowl fixing sleeve.
  • the drawing shows an air and fuel injection device 1, of this mechanical type, in a combustion chamber, not shown, of a turbomachine.
  • This device 1 comprises a fuel injector 2 of axis A which injects fuel downstream into a premix chamber 3 located at the bottom of the combustion chamber upstream of the zone primary 4 combustion.
  • the premix chamber 3 is delimited by the internal contour 5 of a socket 6 coaxial with the axis A.
  • This internal contour 5 is extended downstream by a flared wall 7 of a traditional bowl 8.
  • Bowl 8 comprises upstream of the flared wall 7 a sleeve 9 allowing its attachment to the socket 6.
  • the bowl 8 is mounted in a known manner in a orifice provided in the bottom of the combustion chamber.
  • a first radial spin 10 carried by a ring of centering 11 of the fuel injector 2.
  • the internal contour 5 of the socket 6 is convergent / divergent from upstream downstream and constitutes a venturi.
  • the passages 14a, 14b of the first series of passages are radial, pass right through the upstream part 12 of the socket 6 and open upstream of the neck 15 of the venturi.
  • Passages 16a, 16b of the second series of passages extend from the periphery of the part upstream 12 of the socket 6, to a zone located radially at the inside of the sleeve 9 of the bowl 8, where they axially tilt towards downstream.
  • axial grooves 18a, 18b, of rectangular section which extend the passages 16a, 16b of the second series of passages and which lead to the downstream periphery of the socket 6.
  • the passages 14a, 14b constitute a second radial spin intended to inject air into the premix chamber 3, and the grooves 18a, 18b, covered by the sleeve 9 of the bowl 8 constitute a third axial spin.
  • the outputs of the third axial spin are alternated circumferentially with the outputs of the second radial spin.
  • the number of passages 14a, 14b is equal to the number of passages 16a, 16b.
  • the number of the first spin 10 is equal to the total number of passage 14a, 14b; 16a, 16b formed in the upstream part 12 of the sleeve 6.
  • the first spin 10 therefore has a high permeability.
  • the fins 13 are wedged tangentially by an angle ⁇ between 30 and 40 • relative to the axis A of the fuel injector 2.
  • the axes of the outlet orifices of the passages 14a, 14b of the second spin are also inclined at an angle ⁇ relative to the radial at these points. The second spin therefore creates a swirling movement in the venturi.
  • the fins 20 of the first radial spin 10 are also radially wedged, and preferably the first spin 10 and the second spin are contra-rotating.
  • the first radial spin 10 makes it possible to produce a first premix in the bottom of the premix chamber 3. It makes plus purge office.
  • the second radial spin, wedged tangentially and also radially, ensures a uniform carburetion in the venturi.
  • the tangential incidence of the second radial spin must make an angle of 60 • to 90 • with respect to the tangential component of the first mixture.
  • the timing of the third axial spin is determined by the blading axial located at its outlet, that is to say by the angle of the side walls of the grooves 18a, 18b relative to the axis A.
  • the exit from the third axial spin can be corotative or counter-rotating with respect to the tangential component of the vortex in the venturi depending on the desired fuel table.
  • the tangential tilt of the third spin is depending on the bowl technology used, depending on whether it is a bowl with conventional ports, a bowl with swirling ports corotatives or contrarotatives or a bowl without orifices.
  • the ratio of the speeds of the air injected by the third spin and the mixture at the outlet of the venturi must be between 0.8 and 1.6, this report being dependent on the bowl technology used.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Nozzles (AREA)
EP97402058A 1996-09-05 1997-09-04 Brennstoffeinspritzsystem für eine Brennkammer Expired - Lifetime EP0828115B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9610823 1996-09-05
FR9610823A FR2752917B1 (fr) 1996-09-05 1996-09-05 Systeme d'injection a degre d'homogeneisation avancee

Publications (2)

Publication Number Publication Date
EP0828115A1 true EP0828115A1 (de) 1998-03-11
EP0828115B1 EP0828115B1 (de) 2003-08-13

Family

ID=9495455

Family Applications (1)

Application Number Title Priority Date Filing Date
EP97402058A Expired - Lifetime EP0828115B1 (de) 1996-09-05 1997-09-04 Brennstoffeinspritzsystem für eine Brennkammer

Country Status (6)

Country Link
US (1) US5941075A (de)
EP (1) EP0828115B1 (de)
JP (1) JP3954165B2 (de)
CA (1) CA2207831C (de)
DE (1) DE69724054T2 (de)
FR (1) FR2752917B1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1995521A1 (de) * 2007-05-24 2008-11-26 Siemens Aktiengesellschaft Wirbelblech
CN101373075B (zh) * 2007-08-21 2013-03-06 通用电气公司 涡轮机燃料输送设备和系统
CN111578313A (zh) * 2020-05-25 2020-08-25 中国航发湖南动力机械研究所 气动辅助雾化的燃油预分配装置

Families Citing this family (45)

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US6550251B1 (en) * 1997-12-18 2003-04-22 General Electric Company Venturiless swirl cup
FR2836986B1 (fr) * 2002-03-07 2004-11-19 Snecma Moteurs Systeme d'injection multi-modes d'un melange air/carburant dans une chambre de combustion
US6986255B2 (en) * 2002-10-24 2006-01-17 Rolls-Royce Plc Piloted airblast lean direct fuel injector with modified air splitter
GB2398375A (en) * 2003-02-14 2004-08-18 Alstom A mixer for two fluids having a venturi shape
US7104066B2 (en) * 2003-08-19 2006-09-12 General Electric Company Combuster swirler assembly
US7065972B2 (en) * 2004-05-21 2006-06-27 Honeywell International, Inc. Fuel-air mixing apparatus for reducing gas turbine combustor exhaust emissions
US7013649B2 (en) * 2004-05-25 2006-03-21 General Electric Company Gas turbine engine combustor mixer
JP4653985B2 (ja) * 2004-09-02 2011-03-16 株式会社日立製作所 燃焼器とガスタービン燃焼器、及び空気を燃焼器に供給する方法
WO2006048405A1 (de) * 2004-11-03 2006-05-11 Alstom Technology Ltd Vormischbrenner
US7340900B2 (en) * 2004-12-15 2008-03-11 General Electric Company Method and apparatus for decreasing combustor acoustics
US7810336B2 (en) * 2005-06-03 2010-10-12 Siemens Energy, Inc. System for introducing fuel to a fluid flow upstream of a combustion area
GB2432655A (en) * 2005-11-26 2007-05-30 Siemens Ag Combustion apparatus
JP5023526B2 (ja) * 2006-03-23 2012-09-12 株式会社Ｉｈｉ 燃焼器用バーナ及び燃焼方法
EP1843098A1 (de) * 2006-04-07 2007-10-10 Siemens Aktiengesellschaft Gasturbinenverbrennungskammer
NO325990B1 (no) * 2006-06-23 2008-09-01 Rolf B Rummelhoff Etterbrenner for gass fra gassifiseringsanlegg for trebrensel
FR2903169B1 (fr) * 2006-06-29 2011-11-11 Snecma Dispositif d'injection d'un melange d'air et de carburant, chambre de combustion et turbomachine munies d'un tel dispositif
FR2908867B1 (fr) * 2006-11-16 2012-06-15 Snecma Dispositif d'injection d'un melange d'air et de carburant, chambre de combustion et turbomachine munies d'un tel dispositif
EP1985924A1 (de) * 2007-04-23 2008-10-29 Siemens Aktiengesellschaft Drallvorrichtung
GB2455310B (en) * 2007-12-04 2009-11-18 Siemens Ag A combustion apparatus for a gas turbine engine
FR2925146B1 (fr) * 2007-12-14 2009-12-25 Snecma Systeme d'injection d'un melange d'air et de carburant dans une chambre de combustion de turbomachine
GB0815761D0 (en) * 2008-09-01 2008-10-08 Rolls Royce Plc Swirler for a fuel injector
EP2169312A1 (de) * 2008-09-25 2010-03-31 Siemens Aktiengesellschaft Abgestufter Wirbler zur dynamischen Steuerung
US8215116B2 (en) * 2008-10-02 2012-07-10 General Electric Company System and method for air-fuel mixing in gas turbines
ATE540265T1 (de) * 2009-04-06 2012-01-15 Siemens Ag Drallvorrichtung, brennkammer und gasturbine mit verbessertem drall
FR2945854B1 (fr) * 2009-05-19 2015-08-07 Snecma Vrille melangeuse pour un injecteur de carburant dans une chambre de combustion d'une turbine a gaz et dispositif de combustion correspondant
FR2952166B1 (fr) * 2009-11-05 2012-01-06 Snecma Dispositif melangeur de carburant pour chambre de combustion de turbomachine comprenant des moyens ameliores d'alimentation en air
US20110107767A1 (en) * 2009-11-06 2011-05-12 General Electric Company Secondary fuel nozzle venturi
JP5083302B2 (ja) * 2009-12-14 2012-11-28 株式会社日立製作所 燃焼器とガスタービン燃焼器、及び空気を燃焼器に供給する方法
US8453454B2 (en) * 2010-04-14 2013-06-04 General Electric Company Coannular oil injection nozzle
US8640463B2 (en) 2011-06-28 2014-02-04 United Technologies Corporation Swirler for gas turbine engine fuel injector
CN103836647B (zh) * 2014-02-27 2015-07-29 中国科学院工程热物理研究所 一种文丘里管流道壁面结构
US20160265779A1 (en) * 2015-03-11 2016-09-15 General Electric Company Twin radial splitter-chevron mixer with converging throat
ITUA20163988A1 (it) * 2016-05-31 2017-12-01 Nuovo Pignone Tecnologie Srl Ugello carburante per una turbina a gas con swirler radiale e swirler assiale e turbina a gas / fuel nozzle for a gas turbine with radial swirler and axial swirler and gas turbine
US10012196B1 (en) * 2017-08-30 2018-07-03 Caterpillar Inc. Duct structure for fuel injector assembly
US10801726B2 (en) 2017-09-21 2020-10-13 General Electric Company Combustor mixer purge cooling structure
US11346557B2 (en) * 2019-08-12 2022-05-31 Raytheon Technologies Corporation Aerodynamic guide plate collar for swirler assembly
US11378275B2 (en) * 2019-12-06 2022-07-05 Raytheon Technologies Corporation High shear swirler with recessed fuel filmer for a gas turbine engine
US11280495B2 (en) * 2020-03-04 2022-03-22 General Electric Company Gas turbine combustor fuel injector flow device including vanes
US11802693B2 (en) 2021-04-16 2023-10-31 General Electric Company Combustor swirl vane apparatus
US11598526B2 (en) 2021-04-16 2023-03-07 General Electric Company Combustor swirl vane apparatus
US11846423B2 (en) 2021-04-16 2023-12-19 General Electric Company Mixer assembly for gas turbine engine combustor
CN115523068A (zh) * 2021-06-24 2022-12-27 通用电气公司 旋流器套圈组件
CN116136308A (zh) * 2021-11-16 2023-05-19 通用电气公司 具有压降吹扫通道的旋流器套圈板
CN116147016A (zh) * 2021-11-22 2023-05-23 通用电气公司 用于燃料-空气混合器组件的套圈
US12072099B2 (en) * 2021-12-21 2024-08-27 General Electric Company Gas turbine fuel nozzle having a lip extending from the vanes of a swirler

Citations (8)

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Publication number Priority date Publication date Assignee Title
FR1014072A (fr) * 1950-03-08 1952-08-08 Chantier Et Ateliers De Saint Distributeur d'air à grande turbulence
US2958195A (en) * 1959-02-25 1960-11-01 Philip G Dooley Air inlet construction
FR1331085A (fr) * 1962-07-31 1963-06-28 Prvni Brnenska Strojirna Zd Y Brûleur pour combustible liquide ou gazeux notamment pour turbines à gaz
US3570242A (en) * 1970-04-20 1971-03-16 United Aircraft Corp Fuel premixing for smokeless jet engine main burner
FR2243333A1 (de) * 1973-09-10 1975-04-04 Gen Electric
FR2596102A1 (fr) * 1986-03-20 1987-09-25 Snecma Dispositif d'injection a vrille axialo-centripete
GB2272756A (en) * 1992-11-24 1994-05-25 Rolls Royce Plc Fuel injection apparatus
EP0636835A2 (de) * 1993-07-30 1995-02-01 United Technologies Corporation Wirbelmischvorrichtung für eine Brennkammer

Family Cites Families (2)

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Publication number Priority date Publication date Assignee Title
US4263780A (en) * 1979-09-28 1981-04-28 General Motors Corporation Lean prechamber outflow combustor with sets of primary air entrances
DE4228816C2 (de) * 1992-08-29 1998-08-06 Mtu Muenchen Gmbh Brenner für Gasturbinentriebwerke

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1014072A (fr) * 1950-03-08 1952-08-08 Chantier Et Ateliers De Saint Distributeur d'air à grande turbulence
US2958195A (en) * 1959-02-25 1960-11-01 Philip G Dooley Air inlet construction
FR1331085A (fr) * 1962-07-31 1963-06-28 Prvni Brnenska Strojirna Zd Y Brûleur pour combustible liquide ou gazeux notamment pour turbines à gaz
US3570242A (en) * 1970-04-20 1971-03-16 United Aircraft Corp Fuel premixing for smokeless jet engine main burner
FR2243333A1 (de) * 1973-09-10 1975-04-04 Gen Electric
FR2596102A1 (fr) * 1986-03-20 1987-09-25 Snecma Dispositif d'injection a vrille axialo-centripete
GB2272756A (en) * 1992-11-24 1994-05-25 Rolls Royce Plc Fuel injection apparatus
EP0636835A2 (de) * 1993-07-30 1995-02-01 United Technologies Corporation Wirbelmischvorrichtung für eine Brennkammer

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1995521A1 (de) * 2007-05-24 2008-11-26 Siemens Aktiengesellschaft Wirbelblech
WO2008141959A1 (en) * 2007-05-24 2008-11-27 Siemens Aktiengesellschaft Swirler vane
CN101373075B (zh) * 2007-08-21 2013-03-06 通用电气公司 涡轮机燃料输送设备和系统
CN111578313A (zh) * 2020-05-25 2020-08-25 中国航发湖南动力机械研究所 气动辅助雾化的燃油预分配装置

Also Published As

Publication number Publication date
JPH1089688A (ja) 1998-04-10
FR2752917B1 (fr) 1998-10-02
JP3954165B2 (ja) 2007-08-08
CA2207831C (fr) 2006-05-30
CA2207831A1 (fr) 1998-03-05
EP0828115B1 (de) 2003-08-13
DE69724054D1 (de) 2003-09-18
US5941075A (en) 1999-08-24
FR2752917A1 (fr) 1998-03-06
DE69724054T2 (de) 2004-04-15

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