EP0689006A1 - Verfahren und Vorrichtung zur Kraftstoffversorgung und zur Kühlung der Abflugdüse in einer Brennkammer mit zwei Brennerköpfen - Google Patents

Verfahren und Vorrichtung zur Kraftstoffversorgung und zur Kühlung der Abflugdüse in einer Brennkammer mit zwei Brennerköpfen Download PDF

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Publication number
EP0689006A1
EP0689006A1 EP95401465A EP95401465A EP0689006A1 EP 0689006 A1 EP0689006 A1 EP 0689006A1 EP 95401465 A EP95401465 A EP 95401465A EP 95401465 A EP95401465 A EP 95401465A EP 0689006 A1 EP0689006 A1 EP 0689006A1
Authority
EP
European Patent Office
Prior art keywords
injector
take
fuel
conduit
orifices
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
EP95401465A
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English (en)
French (fr)
Other versions
EP0689006B1 (de
Inventor
Jean-Paul Daniel Alary
Denis Jean Maurice Sandelis
Michel André Albert Desaulty
Pierre Schroer
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 EP0689006A1 publication Critical patent/EP0689006A1/de
Application granted granted Critical
Publication of EP0689006B1 publication Critical patent/EP0689006B1/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
    • F23D11/24—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space by pressurisation of the fuel before a nozzle through which it is sprayed by a substantial pressure reduction into a space
    • F23D11/26—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space by pressurisation of the fuel before a nozzle through which it is sprayed by a substantial pressure reduction into a space with provision for varying the rate at which the fuel is sprayed
    • F23D11/28—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space by pressurisation of the fuel before a nozzle through which it is sprayed by a substantial pressure reduction into a space with provision for varying the rate at which the fuel is sprayed with flow-back of fuel at the burner, e.g. using by-pass
    • 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 a method and device for supplying fuel and cooling the take-off injector of a double injector fitted to a combustion chamber with two heads of a turbomachine, said take-off injector having fuel injection orifices.
  • 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 maximum speed. In idle phase it is therefore necessary to cool the take-off injector correctly in order to avoid coking problems in the fuel circuit of this injector.
  • FR-2 441 725 provides a double injector comprising a single fuel inlet in which each bypass line is connected directly to the nozzle of the idling injection, a part of the fuel being diverted to the nozzle of the take-off injector at by means of a shut-off valve controlled by a regulator device located at the injector head, said regulator device being controlled by an external member. It is mentioned in this document that the fuel at relatively low temperature cools the valve stem and the surrounding part, but the device proposed by FR-A-2 441 725 does not cool the take-off injector to its end .
  • the object of the present invention is to provide a method and a device such as mentioned above which allow vigorous cooling of the take-off injector in idle speeds with a smaller number of fuel circulation tubes.
  • At least part of the total fuel flow supplying said double injector is circulated in the take-off injector, whatever the speed of the turbomachine, the take-off injector is supplied, in the speeds of use of the take-off head, by taking fuel from said flow portion, and the superfluous fuel which passes through the take-off injector is discharged.
  • all of the fuel flow supplying said double injector is circulated in the take-off injector whatever the speed of the turbomachine, said total flow is then directed to the idle injector, when the speed of the the turbomachine is less than the minimum speed of use of the take-off head and said total flow is distributed between the idle injector and the take-off injector in the modes of use of the take-off head.
  • the device according to the invention comprises a first conduit intended to direct at least part of the total flow of fuel supplying the double injector to a chamber formed in the take-off injector, whatever the speed of the turbomachine, means for supplying fuel the injection ports of the take-off injector from said first conduit in the operating conditions of the take-off head, and a second conduit for discharging the superfluous fuel which passes through said chamber.
  • the means for supplying fuel to the fuel injection orifices of the take-off injector from the first conduit comprise a movable valve disposed at the mouth of the first conduit and which can take two extreme positions: an idle position in which it closes the fuel injection orifices of said take-off injector and a take-off position in which the injection orifices are released, and elastic means 18 acting against the forces of the pressures prevailing in said first duct and said chamber and intended to return said valve to the idle position, when the speed of the turbomachine is lower than the minimum speed of use of the take-off head, said valve comprising a first series of orifices which places the first conduit in communication with said chamber at least in the idle position.
  • Said first series of orifices is closed off by a shoulder formed in said take-off injector in the take-off position.
  • the second conduit evacuates the fuel passing through the chamber to the outside of the double injector, the idle injector having its own fuel supply circuit.
  • the valve comprises a second series of orifices which places the first conduit in permanent communication with said chamber, and the second conduit evacuates the fuel passing through said chamber to the idle injector.
  • the reference 1 represents, according to a preferred embodiment, 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 from the head 2 and an idle injector 4 disposed midway between the head 2 and the take-off injector 3.
  • the take-off injector 3 has at its end a take-off nozzle 5 which surrounds an interior chamber 6 and which has on its peripheral wall 7 an annular row of orifices 8 for injecting fuel.
  • the idle injector 4 also includes at its end an idle nozzle 9 having orifices 9a for injecting fuel.
  • the reference 10 represents, in the head, the arrival area of the total flow Q of fuel used to supply the take-off injector 3 and the idle injector 4.
  • a first conduit 11 connects the zone 10 to the chamber 6 of the take-off nozzle 5.
  • a second conduit 12 disposed inside the first conduit 11 connects the chamber 6 with a second chamber 13 disposed in the head 2 and communicating with the orifices 9a of the idle nozzle 9 through a third conduit 14.
  • the end 15 of the second conduit 12, located in the interior chamber 6 of the take-off nozzle 5 carries an annular valve 16 whose radial wall 17 closes the mouth of the first conduit 11.
  • This valve 16 is mounted to slide on the end 15 and is connected to the internal wall of the second conduit by a spring 18.
  • the radial wall 17 comprises a first series of axial orifices 19 and a second series of axial orifices 20.
  • the orifices 19 and 20 are distributed circumferentially around the axis 21 of the take-off nozzle 5, the orifices 19 being more distant from the axis 21 than the orifices 20.
  • the spring 18 applies the radial wall 17 of the valve 16 against the end 15 of the second conduit 12. In this position, called idling, shown in Figure 2, the peripheral surface of the radial wall 17 closes the fuel injection orifices 8 of the take-off nozzle 5.
  • the return force of the spring 18 is calculated in such a way that the valve 16 remains in the idle position, when the total flow of fuel Q is less than the flow rate Qo corresponding to the minimum operating speed of the combustion chamber take-off head.
  • the orifices 19 and 20 of the valve 16 cause a pressure difference dP on the two faces of the radial wall 17, this pressure difference dP being a function of the total fuel flow rate Q according to the curve shown in FIG. 5.
  • the pressure difference dP acts on the valve 16, against the force of the spring 18 and displaces the valve. 16 downstream from a distance do.
  • take-off position shown in FIG. 3
  • the valve 16 is in abutment on an annular abutment shoulder 22 of the take-off nozzle 5, said shoulder 22 being formed in the interior chamber 6 opposite the first series orifices 19 of the valve 16, the fuel injection orifices 8 are released upstream of the radial wall 17 and the orifices 19 are closed.
  • a first part Q1 of the total fuel Q supplied by the first conduit 11 is injected into the combustion chamber through the fuel injection orifices 8 of the take-off nozzle 5, and the second part Q2 of fuel passes through the second series of orifices 20 of the valve 16 and is directed towards the idle injector 4 by the second conduit 12, the second chamber 13 and the third conduit 14.
  • FIG. 5 shows the distribution of the fuel between the take-off injector 3 and the idle injector 4 beyond the minimum flow rate Qo as a function of the supply pressure.
  • the maximum displacement do of the valve 16 may be small.
  • the number N and the diameter D of the different orifices 8, 9a, 19, 20 of the takeoff injector 3 can be:
  • the double injector 1 has only one fuel supply in zone 10.
  • the idle injector 4 is supplied directly by the third conduit 14 from an external distributor.
  • the take-off injector 3 is supplied directly by the first conduit 11.
  • the valve 16 then comprises only a single series of orifices 19 which are closed by the annular shoulder 22 at take-off speed.
  • the second conduit 12 evacuates the fuel which passes through the interior chamber 6 of the take-off nozzle 5, at idle speed, which makes it possible to cool the take-off injector 3.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)
EP95401465A 1994-06-22 1995-06-21 Verfahren und Vorrichtung zur Kraftstoffversorgung und zur Kühlung der Abflugdüse in einer Brennkammer mit zwei Brennerköpfen Expired - Lifetime EP0689006B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9407623A FR2721693B1 (fr) 1994-06-22 1994-06-22 Procédé et dispositif pour alimenter en carburant et refroidir l'injecteur de décollage d'une chambre de combustion à deux têtes.
FR9407623 1994-06-22

Publications (2)

Publication Number Publication Date
EP0689006A1 true EP0689006A1 (de) 1995-12-27
EP0689006B1 EP0689006B1 (de) 1998-11-11

Family

ID=9464486

Family Applications (1)

Application Number Title Priority Date Filing Date
EP95401465A Expired - Lifetime EP0689006B1 (de) 1994-06-22 1995-06-21 Verfahren und Vorrichtung zur Kraftstoffversorgung und zur Kühlung der Abflugdüse in einer Brennkammer mit zwei Brennerköpfen

Country Status (5)

Country Link
US (1) US5568721A (de)
EP (1) EP0689006B1 (de)
JP (1) JP2847045B2 (de)
DE (1) DE69505894T2 (de)
FR (1) FR2721693B1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1997035148A1 (en) * 1996-03-19 1997-09-25 Danfoss A/S Nozzle unit for oil burner
EP0841517A2 (de) 1996-11-07 1998-05-13 BMW Rolls-Royce GmbH Kraftstoffeinspritzvorrichtung für eine Gasturbinen-Brennkammer mit einer flüssigkeitsgekühlten Einspritzdüse
FR2938300A1 (fr) * 2008-11-11 2010-05-14 Delavan Inc Gestion thermique pour injecteurs de carburant

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6321541B1 (en) * 1999-04-01 2001-11-27 Parker-Hannifin Corporation Multi-circuit multi-injection point atomizer
US6711898B2 (en) 1999-04-01 2004-03-30 Parker-Hannifin Corporation Fuel manifold block and ring with macrolaminate layers
US6351948B1 (en) * 1999-12-02 2002-03-05 Woodward Fst, Inc. Gas turbine engine fuel injector
FR2817016B1 (fr) * 2000-11-21 2003-02-21 Snecma Moteurs Procede d'assemblage d'un injecteur de combustible pour chambre de combustion de turbomachine
JP4495179B2 (ja) * 2007-02-28 2010-06-30 三菱重工業株式会社 燃料ノズル装置、ガスタービンおよび燃料ノズル装置の制御方法
EP2520858A1 (de) * 2011-05-03 2012-11-07 Siemens Aktiengesellschaft Brennstoffgekühlte Pilot-Brennstoff-Lanze für eine Gasturbine
CN102380464B (zh) * 2011-10-31 2015-07-22 昆明理工大学 一种喷油油冷氧枪
US10619855B2 (en) * 2012-09-06 2020-04-14 United Technologies Corporation Fuel delivery system with a cavity coupled fuel injector
US11421883B2 (en) 2020-09-11 2022-08-23 Raytheon Technologies Corporation Fuel injector assembly with a helical swirler passage for a turbine engine
US11754287B2 (en) 2020-09-11 2023-09-12 Raytheon Technologies Corporation Fuel injector assembly for a turbine engine
US11649964B2 (en) 2020-12-01 2023-05-16 Raytheon Technologies Corporation Fuel injector assembly for a turbine engine
CN113108313B (zh) * 2021-04-01 2022-09-13 中国科学院工程热物理研究所 一种单路供油及压力自适应双膜燃油雾化装置
US11808455B2 (en) 2021-11-24 2023-11-07 Rtx Corporation Gas turbine engine combustor with integral fuel conduit(s)
US11846249B1 (en) 2022-09-02 2023-12-19 Rtx Corporation Gas turbine engine with integral bypass duct

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1451416A1 (de) * 1962-09-05 1969-02-20 Peabody Ltd OElbrenner fuer oelbeheizte Kessel,OEfen od.dgl.
US3669354A (en) * 1970-09-08 1972-06-13 J & T Eng Ascot Ltd Fluid injectors
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

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1451416A1 (de) * 1962-09-05 1969-02-20 Peabody Ltd OElbrenner fuer oelbeheizte Kessel,OEfen od.dgl.
US3669354A (en) * 1970-09-08 1972-06-13 J & T Eng Ascot Ltd Fluid injectors
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 (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1997035148A1 (en) * 1996-03-19 1997-09-25 Danfoss A/S Nozzle unit for oil burner
EP0841517A2 (de) 1996-11-07 1998-05-13 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
FR2938300A1 (fr) * 2008-11-11 2010-05-14 Delavan Inc Gestion thermique pour injecteurs de carburant

Also Published As

Publication number Publication date
JPH0828875A (ja) 1996-02-02
DE69505894T2 (de) 1999-05-12
FR2721693A1 (fr) 1995-12-29
US5568721A (en) 1996-10-29
FR2721693B1 (fr) 1996-07-19
DE69505894D1 (de) 1998-12-17
EP0689006B1 (de) 1998-11-11
JP2847045B2 (ja) 1999-01-13

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