EP0598662A1 - Aerodynamisches Einspritzsystem für eine Brennkammer - Google Patents

Aerodynamisches Einspritzsystem für eine Brennkammer Download PDF

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Publication number
EP0598662A1
EP0598662A1 EP93402788A EP93402788A EP0598662A1 EP 0598662 A1 EP0598662 A1 EP 0598662A1 EP 93402788 A EP93402788 A EP 93402788A EP 93402788 A EP93402788 A EP 93402788A EP 0598662 A1 EP0598662 A1 EP 0598662A1
Authority
EP
European Patent Office
Prior art keywords
injection
fuel
combustion chamber
holes
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.)
Granted
Application number
EP93402788A
Other languages
English (en)
French (fr)
Other versions
EP0598662B1 (de
Inventor
Denis Roger Henri Ansart
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.)
Filing date
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 EP0598662A1 publication Critical patent/EP0598662A1/de
Application granted granted Critical
Publication of EP0598662B1 publication Critical patent/EP0598662B1/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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • 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

Definitions

  • the present invention relates to an aerodynamic injection system of an annular combustion chamber, comprising at least one injection head having a plurality of air and fuel injection devices regularly distributed circumferentially in the chamber bottom.
  • each of the fuel and air injection devices comprises a fuel injector, a spin external turbulence for the passage of the fuel atomizing air and a bowl-shaped body comprising a downstream web flared in the direction of flow and provided with a row of bowl holes for the injection of air in the sprayed fuel cone.
  • the object of the present invention is to make a modification to the bowls in order to reduce the number of injectors without impairing the proper functioning of the injection chamber.
  • the web has a cross section of substantially elliptical shape, the axis of smaller dimension being disposed in an axial plane of the combustion chamber, and in that the injector has a plurality of holes fuel injection of different diameters.
  • This arrangement makes it possible to obtain a more flat flame front, by playing on the different diameters of the fuel injection holes.
  • the chamber may have a single injection head or two injection heads spaced radially. Equipping a two-headed chamber with elliptical-shaped bowls according to the invention makes it possible to increase the permeability of the chamber bottom and therefore the average richness near the injectors.
  • FIGS 1 and 2 schematically show the arrangement of bowls 1 of the prior art in the chamber bottom 2 of an annular combustion chamber 3 of a turbomachine having a single injection head.
  • the combustion chamber 3 is delimited by an interior ferrule 4 and an exterior ferrule 5 connected by the chamber bottom 2.
  • the bowls 1 of frustoconical shape and of circular cross section are arranged upstream of the chamber bottom 2 and they each surround a fuel injector 6 with interposition of a turbulence spin 7.
  • the bowls 1 comprise a web 8 flared downstream in the direction of gas flow and having a row of bow holes 9 for the injection of air in the sprayed fuel cone.
  • the fuel is delivered through orifices 10 formed in the injector 6 and is sprayed by the swirling air penetrating through the swirling spin 7.
  • the consecutive bowls la and lb are located at a distance X from each other and the distance Y separating two neighboring injectors 6a and 6b is equal to the distance X increased by the diameter of a bowl 1.
  • the bowls 1 have a veil 8 which has a cross section of elliptical shape, the axis of smaller dimension 11 being disposed in an axial plane of the combustion chamber 3.
  • the orifice 12 allowing the fixing of the bowl 1 of the invention in the bottom of chamber 2 also has a elliptical section.
  • the bowl holes 9 are no longer equidistant from the injector 6. Thanks to this arrangement, the distance Y 'separating two consecutive injectors 6a and 6b from an injection head is increased relative to the distance Y of the art previous, if we keep the distance X separating two consecutive bowls la and lb and the radial dimensions of the combustion chamber. A smaller number of injectors is therefore required to equip the combustion chamber 3.
  • the bowl holes 9 can be equidistant from each other and have the same diameter. However, they can also be placed at variable intervals in order to distribute the air introduced as necessary. Likewise, they can be divided into sectors comprising bowl holes of different diameters as proposed in document FR-A-2 588 919.
  • the injector 6 has a plurality of fuel injection holes 10 distributed over its periphery in order to inject fuel into the swirling air delivered by the spin 7. These injection holes 10 do not all have the same diameter , in order to better homogenize the spray mixture delivered into the combustion chamber 3 downstream of the bowls 1.
  • the injection holes 10 are distributed in first sectors comprising injection holes 10 of small diameter and in second sectors with large diameter injection holes 10.
  • FIGS. 4 and 5 show a combustion chamber 3 which comprises a single injection head equipped with bowls 1 of elliptical shape regularly distributed circumferentially in the bottom of the chamber 2.
  • the bowls 1 described above can advantageously equip a combustion chamber with two heads which has a take-off head 13 and an idle head 14 radially spaced around the axis of the combustion chamber, as can be seen in the Figures 6 and 7.
  • the spacing of the bowls 1 of the idle head 14 is greater than the spacing of the bowls 1 of the take-off head and the total number of bowls 1 of elliptical shape fitted to the combustion chamber 3 is less than number of bowls of circular section necessary to equip a combustion chamber with two heads of the prior art.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)
EP93402788A 1992-11-18 1993-11-17 Aerodynamisches Einspritzsystem für eine Brennkammer Expired - Lifetime EP0598662B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9213832A FR2698157B1 (fr) 1992-11-18 1992-11-18 Système d'injection aérodynamique de chambre de combustion.
FR9213832 1992-11-18

Publications (2)

Publication Number Publication Date
EP0598662A1 true EP0598662A1 (de) 1994-05-25
EP0598662B1 EP0598662B1 (de) 1996-04-03

Family

ID=9435636

Family Applications (1)

Application Number Title Priority Date Filing Date
EP93402788A Expired - Lifetime EP0598662B1 (de) 1992-11-18 1993-11-17 Aerodynamisches Einspritzsystem für eine Brennkammer

Country Status (4)

Country Link
US (1) US5351475A (de)
EP (1) EP0598662B1 (de)
DE (1) DE69302078T2 (de)
FR (1) FR2698157B1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2743587A3 (de) * 2012-12-12 2014-09-03 Rolls-Royce plc Kraftstoffeinspritzdüse und Gasturbinenmotorbrennkammer

Families Citing this family (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2727193B1 (fr) * 1994-11-23 1996-12-20 Snecma Chambre de combustion a deux tetes fonctionnant du ralenti au plein gaz
US5619855A (en) * 1995-06-07 1997-04-15 General Electric Company High inlet mach combustor for gas turbine engine
FR2751054B1 (fr) * 1996-07-11 1998-09-18 Snecma Chambre de combustion anti-nox a injection de carburant de type annulaire
GB2319078B (en) * 1996-11-08 1999-11-03 Europ Gas Turbines Ltd Combustor arrangement
DE19720402A1 (de) * 1997-05-15 1998-11-19 Bmw Rolls Royce Gmbh Axial gestufte Ringbrennkammer einer Gasturbine
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
US6119459A (en) * 1998-08-18 2000-09-19 Alliedsignal Inc. Elliptical axial combustor swirler
DE19914666B4 (de) 1999-03-31 2009-08-20 Alstom Brenner für einen Wärmeerzeuger
DE10340826A1 (de) * 2003-09-04 2005-03-31 Rolls-Royce Deutschland Ltd & Co Kg Homogene Gemischbildung durch verdrallte Einspritzung des Kraftstoffs
DE10348604A1 (de) * 2003-10-20 2005-07-28 Rolls-Royce Deutschland Ltd & Co Kg Kraftstoffeinspritzdüse mit filmartiger Kraftstoffplatzierung
US7509809B2 (en) * 2005-06-10 2009-03-31 Pratt & Whitney Canada Corp. Gas turbine engine combustor with improved cooling
US7836699B2 (en) * 2005-12-20 2010-11-23 United Technologies Corporation Combustor nozzle
JP2008159524A (ja) * 2006-12-26 2008-07-10 Shinko Electric Ind Co Ltd 固体酸化物型燃料電池発電装置
US8146365B2 (en) * 2007-06-14 2012-04-03 Pratt & Whitney Canada Corp. Fuel nozzle providing shaped fuel spray
DE102007043626A1 (de) * 2007-09-13 2009-03-19 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenmagerbrenner mit Kraftstoffdüse mit kontrollierter Kraftstoffinhomogenität
US8402763B2 (en) * 2009-10-26 2013-03-26 General Electric Company Combustor headend guide vanes to reduce flow maldistribution into multi-nozzle arrangement
DE102012002465A1 (de) * 2012-02-08 2013-08-08 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammer mit unsymmetrischen Kraftstoffdüsen
US9145778B2 (en) 2012-04-03 2015-09-29 General Electric Company Combustor with non-circular head end
US9404656B2 (en) * 2012-12-17 2016-08-02 United Technologies Corporation Oblong swirler assembly for combustors
US9376985B2 (en) * 2012-12-17 2016-06-28 United Technologies Corporation Ovate swirler assembly for combustors
GB2548585B (en) * 2016-03-22 2020-05-27 Rolls Royce Plc A combustion chamber assembly
US20180058696A1 (en) * 2016-08-23 2018-03-01 General Electric Company Fuel-air mixer assembly for use in a combustor of a turbine engine
US11149952B2 (en) * 2016-12-07 2021-10-19 Raytheon Technologies Corporation Main mixer in an axial staged combustor for a gas turbine engine
JP7446077B2 (ja) * 2019-10-04 2024-03-08 三菱重工業株式会社 ガスタービン用燃焼器、ガスタービン及び油燃料の燃焼方法
FR3142533A1 (fr) * 2022-11-28 2024-05-31 Safran Aircraft Engines Chambre de combustion pour turbomachine

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4045956A (en) * 1974-12-18 1977-09-06 United Technologies Corporation Low emission combustion chamber
FR2357738A1 (fr) * 1976-07-07 1978-02-03 Snecma Chambre de combustion pour turbomachines
FR2588919A1 (fr) * 1985-10-18 1987-04-24 Snecma Dispositif d'injection a bol sectorise

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US3521824A (en) * 1968-10-11 1970-07-28 Delavan Manufacturing Co Air-liquid flat spray nozzle
US3834159A (en) * 1973-08-03 1974-09-10 Gen Electric Combustion apparatus
GB1539136A (en) * 1976-07-07 1979-01-24 Snecma Gas turbine combustion chambers
GB2028488B (en) * 1978-08-19 1983-02-02 Rolls Royce Gas turbine
US4218020A (en) * 1979-02-23 1980-08-19 General Motors Corporation Elliptical airblast nozzle
CH672541A5 (de) * 1986-12-11 1989-11-30 Bbc Brown Boveri & Cie
DE3837635A1 (de) * 1988-11-05 1990-05-10 Proizv Ob Nevskij Z Im V I Verfahren zum verbrennen von brennstoff in einer brennkammer

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4045956A (en) * 1974-12-18 1977-09-06 United Technologies Corporation Low emission combustion chamber
FR2357738A1 (fr) * 1976-07-07 1978-02-03 Snecma Chambre de combustion pour turbomachines
FR2588919A1 (fr) * 1985-10-18 1987-04-24 Snecma Dispositif d'injection a bol sectorise

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2743587A3 (de) * 2012-12-12 2014-09-03 Rolls-Royce plc Kraftstoffeinspritzdüse und Gasturbinenmotorbrennkammer
US9371990B2 (en) 2012-12-12 2016-06-21 Rolls-Royce Plc Elliptical air opening at an upstream end of a fuel injector shroud and a gas turbine engine combustion chamber

Also Published As

Publication number Publication date
US5351475A (en) 1994-10-04
EP0598662B1 (de) 1996-04-03
DE69302078D1 (de) 1996-05-09
DE69302078T2 (de) 1996-09-12
FR2698157A1 (fr) 1994-05-20
FR2698157B1 (fr) 1994-12-16

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