EP0689007A1 - Kühlung der Abflugdüse in einer Brennkammer mit zwei Brennerköpfen - Google Patents

Kühlung der Abflugdüse in einer Brennkammer mit zwei Brennerköpfen Download PDF

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Publication number
EP0689007A1
EP0689007A1 EP95401466A EP95401466A EP0689007A1 EP 0689007 A1 EP0689007 A1 EP 0689007A1 EP 95401466 A EP95401466 A EP 95401466A EP 95401466 A EP95401466 A EP 95401466A EP 0689007 A1 EP0689007 A1 EP 0689007A1
Authority
EP
European Patent Office
Prior art keywords
injector
fuel
take
circuit
idle
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
EP95401466A
Other languages
English (en)
French (fr)
Other versions
EP0689007B1 (de
Inventor
Jean-Paul Daniel Allary
Denis Jean Maurice Sandelis
Guy D'agostino
Pierre Schroer
Henry Roger Leclerc
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 EP0689007A1 publication Critical patent/EP0689007A1/de
Application granted granted Critical
Publication of EP0689007B1 publication Critical patent/EP0689007B1/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
    • 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 present invention relates to the cooling of the take-off injector of a combustion chamber with two heads.
  • the idle head In two-head combustion chambers, the idle head is continuously supplied with fuel, whatever the speed of the turbomachine. On the other hand, the take-off head is supplied with fuel only beyond a determined minimum speed which corresponds to approximately 20% of the nominal speed. In idle phase it is therefore necessary to cool the take-off injector properly and in particular the nozzle of the injector which includes the fuel injection orifices, in order to avoid any problem of coking of the fuel circuits and any problem fuel vapor cap formation.
  • a cooling solution has already been adopted on the CFM56-5B turbojet which consists in circulating the flow of fuel which feeds the idle injector into the take-off injector. This circulation of fuel cools this takeoff injector in passing, thus avoiding coking.
  • the CFM56-5B injectors are of the aeromechanical type with double flow per module.
  • the fuel supply circuit of the idle injector has two coaxial tubes, and the take-off injector is supplied by a third tube placed in the center of the first two and communicating with the interior of the combustion chamber. through the injection holes in the nozzle. These orifices are thus arranged at a relatively great distance from the passage between the ends of the first two tubes.
  • the object of the present invention is to improve the cooling of the take-off injector and in particular of its nozzle.
  • the present invention therefore relates to a device for cooling the take-off injector of a double injector fitted to a combustion chamber with two heads of a turbomachine, said double injector further comprising an idle injector which is supplied with fuel by a first circuit, said take-off injector having a nozzle provided with fuel injection orifices which are supplied with fuel by a second circuit separate from the first circuit.
  • this device is characterized in that the first fuel circuit comprises a first conduit which directs the entire flow of fuel supplying said idle injector to the end of the take-off injector and a second annular duct which is coaxial with the first duct and which returns said fuel flow to the idle injector, by the fact that the second fuel circuit comprises a third annular conduit interposed between the first conduit and the second conduit, and by the fact that in the nozzle are formed channels allowing the passage of fuel between the first conduit and the second conduit, said channels alternating with the injection orifices of said nozzle.
  • the reference 1 represents a double injector intended for the supply of an annular combustion chamber with double head of a turbomachine, which comprises a head 2 for its fixing on the external casing of the turbomachine, a take-off injector 3, distant of the head 2 and an idle injector 4 or pilot disposed midway between the head 2 and the take-off injector 3.
  • the take-off injector 3 comprises at its end a take-off nozzle 5 having orifices 6 for injecting , in the combustion chamber, a flow of fuel introduced into the head 2 through a feed orifice 7.
  • the idle injector 4 also includes an idle nozzle 8 fed by a flow of fuel introduced into the head 2 through a supply port 9.
  • the take-off nozzle 5 comprises a nozzle 10 mounted in the internal bore 11 of a socket 12, this socket 12 being itself mounted at the end of the hollow body 13 which forms the external wall of the double injector 1.
  • the end piece 10, of axis 14, has a blind axial bore 15 which communicates with the head orifice 9 by a first tube 16, and an annular cavity 17 which communicates with the injection orifices 6.
  • the annular cavity 17 surrounds the blind bore 15 and is separated from the latter by a cylindrical sleeve 18 at the upstream end of which is fixed the end of the first tube 16.
  • This second tube 19 surrounds the first tube 16.
  • An annular space 20 is delimited by the second tube 19, on the one hand , and the sleeve and the hollow body 13, on the other hand. Channels 21 are provided in the endpiece 10 in order to put the blind bore 15 into communication with the annular space 20.
  • the annular space 20 extends from the nozzle 3 to the head 2 of the double injector 1, where it is in permanent communication with the feed channel 22 of the idle head 4. It is delimited externally by a third tube 23, the downstream end 24 of which is tightly fixed to the sleeve 12.
  • the idle injector 4 feed circuit includes the inlet 9, the internal passage of the first tube 16, the blind bore 15, the channels 21, the annular space 20 and the feed channel 22. Thus, all the fuel flow Q1 which feeds by the idle injector 4 passes through the channels 21 located in the nozzle 10.
  • the feed circuit for the take-off injector 2 comprises the inlet orifice 7, the annular space 25 delimited by the first tube 16 and the second tube 19, the annular cavity 17 and the injection orifices 6.
  • the injection orifices 6 comprise, from the annular cavity 17, a first axial portion 6a and a second portion 6b inclined radially and tangentially which opens into the combustion chamber .
  • These injection orifices 6 are six in number in the example shown in the drawings, but this number could be different from six.
  • the nozzle 10 which constitutes the hottest part of the double injector 1 and therefore the part most sensitive to coking phenomena, has a large heat exchange surface with all of the fuel flow Q1 of the idle injector 4. This leads to a significant reduction in the risks of coking of the residual fuel in the take-off module circuit by decreasing the temperatures of the walls of the take-off circuit. Thermal calculations have shown a substantial gain of 68% on the surface of the walls at risk, in terms of coking, that is to say with a temperature above 200 ° C.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)
EP95401466A 1994-06-22 1995-06-21 Kühlung der Abflugdüse in einer Brennkammer mit zwei Brennerköpfen Expired - Lifetime EP0689007B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9407624 1994-06-20
FR9407624A FR2721694B1 (fr) 1994-06-22 1994-06-22 Refroidissement de l'injecteur de décollage d'une chambre de combustion à deux têtes.

Publications (2)

Publication Number Publication Date
EP0689007A1 true EP0689007A1 (de) 1995-12-27
EP0689007B1 EP0689007B1 (de) 1998-11-11

Family

ID=9464487

Family Applications (1)

Application Number Title Priority Date Filing Date
EP95401466A Expired - Lifetime EP0689007B1 (de) 1994-06-22 1995-06-21 Kühlung der Abflugdüse in einer Brennkammer mit zwei Brennerköpfen

Country Status (5)

Country Link
US (1) US5577386A (de)
EP (1) EP0689007B1 (de)
JP (1) JP2992456B2 (de)
DE (1) DE69505895T2 (de)
FR (1) FR2721694B1 (de)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0841517A3 (de) * 1996-11-07 1998-12-23 BMW Rolls-Royce GmbH Kraftstoffeinspritzvorrichtung für eine Gasturbinen-Brennkammer mit einer flüssigkeitsgekühlten Einspritzdüse
WO2000022347A1 (en) * 1998-10-09 2000-04-20 General Electric Company Fuel injection assembly for gas turbine engine combustor
US6357237B1 (en) 1998-10-09 2002-03-19 General Electric Company Fuel injection assembly for gas turbine engine combustor
EP2900974A4 (de) * 2012-09-28 2016-06-08 United Technologies Corp Durchflussmodifikator für eine brennstoffdüsenspitze einer brennkammer
EP3076083A1 (de) * 2015-03-31 2016-10-05 Delavan Inc Kraftstoffdüsen
US9897321B2 (en) 2015-03-31 2018-02-20 Delavan Inc. Fuel nozzles
US10309651B2 (en) 2011-11-03 2019-06-04 Delavan Inc Injectors for multipoint injection

Families Citing this family (39)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2770283B1 (fr) * 1997-10-29 1999-11-19 Snecma Chambre de combustion pour turbomachine
US6072172A (en) * 1997-12-22 2000-06-06 Bausch & Lomb Incorporated Method and apparatus for detecting packages in carton
US6082113A (en) * 1998-05-22 2000-07-04 Pratt & Whitney Canada Corp. Gas turbine fuel injector
US6289676B1 (en) 1998-06-26 2001-09-18 Pratt & Whitney Canada Corp. Simplex and duplex injector having primary and secondary annular lud channels and primary and secondary lud nozzles
US6711898B2 (en) 1999-04-01 2004-03-30 Parker-Hannifin Corporation Fuel manifold block and ring with macrolaminate layers
US6321541B1 (en) * 1999-04-01 2001-11-27 Parker-Hannifin Corporation Multi-circuit multi-injection point atomizer
US6256995B1 (en) 1999-11-29 2001-07-10 Pratt & Whitney Canada Corp. Simple low cost fuel nozzle support
US6351948B1 (en) * 1999-12-02 2002-03-05 Woodward Fst, Inc. Gas turbine engine fuel injector
FR2817017B1 (fr) 2000-11-21 2003-03-07 Snecma Moteurs Refroidissement integral des injecteurs de decollage d'une chambre de combustion a deux tetes
US6718770B2 (en) * 2002-06-04 2004-04-13 General Electric Company Fuel injector laminated fuel strip
US7061077B2 (en) * 2002-08-30 2006-06-13 Fairchild Semiconductor Corporation Substrate based unmolded package including lead frame structure and semiconductor die
US6898926B2 (en) * 2003-01-31 2005-05-31 General Electric Company Cooled purging fuel injectors
US6959535B2 (en) * 2003-01-31 2005-11-01 General Electric Company Differential pressure induced purging fuel injectors
US6898938B2 (en) 2003-04-24 2005-05-31 General Electric Company Differential pressure induced purging fuel injector with asymmetric cyclone
DE10324985B4 (de) * 2003-06-03 2005-06-16 Man B & W Diesel Ag Kraftstoffeinspritzdüse
US7104464B2 (en) 2003-12-25 2006-09-12 Kawasaki Jukogyo Kabushiki Kaisha Fuel supply method and fuel supply system
US7654088B2 (en) * 2004-02-27 2010-02-02 Pratt & Whitney Canada Corp. Dual conduit fuel manifold for gas turbine engine
ATE446588T1 (de) 2004-11-09 2009-11-15 Koninkl Philips Electronics Nv Fluoreszenzlampe mit der fähigkeit zur langsamen freigabe von organischen verdampfungsmaterialien bei niedriger temperatur
US20070033945A1 (en) * 2005-08-10 2007-02-15 Goldmeer Jeffrey S Gas turbine system and method of operation
US20070119179A1 (en) * 2005-11-30 2007-05-31 Haynes Joel M Opposed flow combustor
US20070151251A1 (en) * 2006-01-03 2007-07-05 Haynes Joel M Counterflow injection mechanism having coaxial fuel-air passages
US8387390B2 (en) * 2006-01-03 2013-03-05 General Electric Company Gas turbine combustor having counterflow injection mechanism
FR2896030B1 (fr) * 2006-01-09 2008-04-18 Snecma Sa Refroidissement d'un dispositif d'injection multimode pour chambre de combustion, notamment d'un turboreacteur
US8056326B2 (en) 2007-05-31 2011-11-15 Caterpillar Inc. Regeneration device having cooled injection housing
FR2920525B1 (fr) * 2007-08-31 2014-06-13 Snecma Separateur pour alimentation de l'air de refroidissement d'une turbine
US8151716B2 (en) * 2007-09-13 2012-04-10 General Electric Company Feed injector cooling apparatus and method of assembly
US7992390B2 (en) * 2008-09-23 2011-08-09 Pratt & Whitney Canada Corp. External rigid fuel manifold
US8393154B2 (en) * 2009-02-12 2013-03-12 Pratt & Whitney Canada Corp. Fuel delivery system with reduced heat transfer to fuel manifold seal
US9221704B2 (en) * 2009-06-08 2015-12-29 Air Products And Chemicals, Inc. Through-port oxy-fuel burner
CA2779199C (en) * 2009-11-16 2015-08-04 Bell Helicopter Textron Inc. Dual-path fluid injection jet
US8205598B2 (en) * 2010-02-08 2012-06-26 International Engine Intellectual Property Company, Llc Fuel injector nozzle
EP2362142A1 (de) * 2010-02-19 2011-08-31 Siemens Aktiengesellschaft Brenneranordnung
US8590311B2 (en) 2010-04-28 2013-11-26 General Electric Company Pocketed air and fuel mixing tube
US20110265485A1 (en) * 2010-04-30 2011-11-03 General Electric Company Fluid cooled injection nozzle assembly for a gas turbomachine
US9080540B2 (en) 2010-08-11 2015-07-14 Cummins Inc. Engine with injector mounting and cooling arrangement
EP2520858A1 (de) * 2011-05-03 2012-11-07 Siemens Aktiengesellschaft Brennstoffgekühlte Pilot-Brennstoff-Lanze für eine Gasturbine
WO2014058381A1 (en) * 2012-10-11 2014-04-17 Ecomb Ab (Publ) Supply device for a combustion chamber
US10400674B2 (en) * 2014-05-09 2019-09-03 United Technologies Corporation Cooled fuel injector system for a gas turbine engine and method for operating the same
US9989257B2 (en) 2015-06-24 2018-06-05 Delavan Inc Cooling in staged fuel systems

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2441725A1 (fr) * 1978-11-20 1980-06-13 Rolls Royce Turbine a gaz
WO1994008179A1 (en) * 1992-09-28 1994-04-14 Parker-Hannifin Corporation Multiple passage cooling circuit for gas turbine fuel injector nozzle

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB819042A (en) * 1956-09-27 1959-08-26 Dowty Fuel Syst Ltd Improvements relating to liquid fuel burners
US5269468A (en) * 1992-06-22 1993-12-14 General Electric Company Fuel nozzle
FR2712379B1 (fr) * 1993-11-10 1995-12-29 Snecma Chambre de combustion pour turbomachine munie d'un séparateur des gaz.

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2441725A1 (fr) * 1978-11-20 1980-06-13 Rolls Royce Turbine a gaz
WO1994008179A1 (en) * 1992-09-28 1994-04-14 Parker-Hannifin Corporation Multiple passage cooling circuit for gas turbine fuel injector nozzle

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0841517A3 (de) * 1996-11-07 1998-12-23 BMW Rolls-Royce GmbH Kraftstoffeinspritzvorrichtung für eine Gasturbinen-Brennkammer mit einer flüssigkeitsgekühlten Einspritzdüse
US6003781A (en) * 1996-11-07 1999-12-21 Bmw Rolls-Royce Gmbh Fuel injection device with a liquid-cooled injection nozzle for a combustion chamber of a gas turbine
WO2000022347A1 (en) * 1998-10-09 2000-04-20 General Electric Company Fuel injection assembly for gas turbine engine combustor
US6357237B1 (en) 1998-10-09 2002-03-19 General Electric Company Fuel injection assembly for gas turbine engine combustor
US10309651B2 (en) 2011-11-03 2019-06-04 Delavan Inc Injectors for multipoint injection
EP2900974A4 (de) * 2012-09-28 2016-06-08 United Technologies Corp Durchflussmodifikator für eine brennstoffdüsenspitze einer brennkammer
US9400104B2 (en) 2012-09-28 2016-07-26 United Technologies Corporation Flow modifier for combustor fuel nozzle tip
EP3076083A1 (de) * 2015-03-31 2016-10-05 Delavan Inc Kraftstoffdüsen
US9897321B2 (en) 2015-03-31 2018-02-20 Delavan Inc. Fuel nozzles
US10385809B2 (en) 2015-03-31 2019-08-20 Delavan Inc. Fuel nozzles
US11111888B2 (en) 2015-03-31 2021-09-07 Delavan Inc. Fuel nozzles

Also Published As

Publication number Publication date
JP2992456B2 (ja) 1999-12-20
JPH0814063A (ja) 1996-01-16
EP0689007B1 (de) 1998-11-11
DE69505895D1 (de) 1998-12-17
FR2721694B1 (fr) 1996-07-19
FR2721694A1 (fr) 1995-12-29
DE69505895T2 (de) 1999-06-02
US5577386A (en) 1996-11-26

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