EP0689006B1 - 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
EP0689006B1
EP0689006B1 EP95401465A EP95401465A EP0689006B1 EP 0689006 B1 EP0689006 B1 EP 0689006B1 EP 95401465 A EP95401465 A EP 95401465A EP 95401465 A EP95401465 A EP 95401465A EP 0689006 B1 EP0689006 B1 EP 0689006B1
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EP
European Patent Office
Prior art keywords
injector
take
fuel
pipe
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.)
Expired - Lifetime
Application number
EP95401465A
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English (en)
French (fr)
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EP0689006A1 (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
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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
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Publication of EP0689006B1 publication Critical patent/EP0689006B1/de
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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 cool the take-off injector of a double injector fitted to a combustion chamber with two heads of a turbomachine, said injector takeoff with fuel injection ports.
  • dual-head combustion supplied with fuel by a double injector which comprises a first supply for the pilot head or idle head and a second power supply for the takeoff head.
  • the idle head In two-head combustion chambers, the idle head is permanently 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 injector properly. takeoff to avoid coking problems in the fuel system of this injector.
  • FR-2 441 725 provides a double injector comprising a single inlet for fuel in which each bypass line is connected directly to the idle injection nozzle, part of the fuel being diverted to the the take-off injector by means of a shut-off valve controlled by a regulating device located at the injector head, said regulating device being controlled by an external body. It is mentioned in this document that the fuel at relatively low temperature cools the valve stem and part surrounding, but the device proposed by FR-A-2 441 725 does not allow cool the take-off injector to its end.
  • the aim of the present invention is to propose a method and a device as mentioned above which allow a vigorous cooling of the takeoff injector in idle speeds with a lower number of fuel circulation tubes.
  • the take-off injector is circulated, including in the end nozzle, all of the total fuel flow supplying said double injector whatever the speed of the turbomachine, the take-off injector is supplied, in the modes of use of the take-off head, by taking off fuel in the entire flow, and the superfluous fuel which passes in takeoff injector to the idle injector.
  • the device comprises a first conduit intended to direct all of the total fuel flow supplying double injector to the end nozzle of the take-off injector whatever the regime of the turbomachine, means for supplying fuel to the orifices injection of the take-off injector from said first conduit into the regimes of use of the take-off head, and a second conduit for evacuating superfluous fuel which passes through a chamber formed in said injector nozzle.
  • 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 pressure prevailing in said first conduit 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 by a shoulder formed in said takeoff injector in the takeoff position.
  • 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 for supplying a double annular combustion chamber head of a turbomachine, which comprises a head 2, for its attachment to the casing exterior of the turbomachine, a take-off injector 3, distant from the head 2 and a idle injector 4 placed midway between head 2 and the injector take-off 3.
  • the take-off injector 3 has a nozzle at its end take-off 5 which surrounds an interior chamber 6 and which has on its wall peripheral 7 an annular row of fuel injection orifices 8.
  • the idle injector 4 also has a nozzle at its end. idle 9 having fuel injection orifices 9a.
  • the reference 10 represents, in the head, the arrival area of the total flow rate 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 nozzle take-off 5.
  • a second conduit 12 disposed inside the first conduit 11 connects the chamber 6 with a second chamber 13 arranged in the head 2 and communicating with the orifices 9a of the idle nozzle 9 by 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 slidably mounted 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 further 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 FIG. 2, the surface device of the radial wall 17 closes the fuel injection orifices 8 the take-off nozzle 5.
  • the return force of the spring 18 is calculated such that so 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 speed use of the combustion chamber lift-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 difference in pressure dP being function of the total fuel flow Q according to the curve shown in Figure 5.
  • a first part Q1 of the total fuel Q supplied by the first conduit 11 is injected into the combustion chamber by the fuel injection ports 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 to the idle injector 4 through the second conduit 12, the second chamber 13 and the third leads 14.
  • Figure 5 shows the distribution of fuel between the take-off injector 3 and the idle injector 4 beyond the minimum flow rate Qo as a function of the pressure feed.
  • the valve 16 moves downstream, when the flow Q is slightly higher than the minimum flow Qo, conversely, during the descent in speed, the valve 16 moves upstream, when the flow Q is slightly lower than the switching rate Qo.
  • the radial wall 17 is in abutment on the face front of the second duct 12, in idle speed, and is in abutment on the annular shoulder 22 in takeoff mode. This arrangement avoids the beats of the valve 16 in the vicinity of the corresponding switching speed at minimum flow Qo.
  • 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 take-off injector 3 can be the following:
  • the double injector 1 has only one fuel supply in the area 10.
  • the idle injector 4 is supplied directly by the third conduit 14 to from an external distributor.
  • Take-off injector 3 is supplied directly through the first conduit 11.
  • the valve 16 then has only one series of orifices 19 which are closed by the annular shoulder 22 at the speed of lift-off.
  • the second conduit 12 evacuates the fuel passing through to the outside by the inner chamber 6 of the take-off nozzle 5, at idle speed, which allows to take off the injector 3.

Claims (7)

  1. Verfahren zur Kraftstoffversorgung und Kühlung der Starteinspritzdüse (3) einer Doppeleinspritzdüse (1) für eine Zweikopfbrennkammer einer Turbomaschine,
       dadurch gekennzeichnet,
    daß man den gesamten die Doppeleinspritzdüse (1) speisenden Kraftstoffdurchsatz (Q) unabhängig von der Drehzahl der Turbomaschine, in die Starteinspritzdüse (3), einschließlich deren Enddüse (5), zirkulieren läßt
    daß man anschließend den gesamten Kraftstoffdurchsatz (Q) zu der Leerlaufeinspritzdüse (4) leitet, wenn die Drehzahl der Turbomaschine unter der minimalen Betriebsdrehzahl des Startkopfs liegt, und
    daß man in den Betriebsdrehzahlen des Startkopfes den gesamten Kraftstoffdurchsatz (Q) zwischen der Leerlaufeinspritzdüse (4) und der Starteinspritzdüse (3) aufteilt.
  2. Vorrichtung zur Kraftstoffversorgung und Kühlung der Starteinspritzdüse (3) einer Doppeleinspritzdüse (1) für eine Zweikopfbrennkammer einer Turbomaschine, wobei die Starteinspritzdüse (3) Kraftstoffeinspritzöffnungen (8) aufweist,
       gekennzeichnet durch
    eine erste Leitung (11) zur Hinführung des gesamten die Doppeleinspritzdüse (1) speisenden Kraftstoffdurchsatzes (Q) zu der Enddüse (5) der Starteinspritzdüse (3) unabhängig von der Drehzahl der Turbomaschine,
    Mittel (16, 17, 18) für die Kraftstoffversorgung der Kraftstoffeinspritzöffnungen (8) der Starteinspritzdüse (3) aus der genannten ersten Leitung (11) in den Betriebsdrehzahlen des Startkopfes
    und eine zweite Leitung (12) zum Abführen des überschüssigen Kraftstoffs, der in eine in der Enddüse (5) der Starteinspritzdüse (3) angebrachte Kammer (6) übergeht.
  3. Vorrichtung nach Anspruch 1,
       dadurch gekennzeichnet,
    daß die Mittel (16, 17, 18) für die Kraftstoffversorgung der Kraftstoffeinspritzöffnungen (8) der Starteinspritzdüse (3) aus der ersten Leitung (11) aufweisen:
    ein bewegliches Ventilglied (16), das an der Mündung der ersten Leitung (11) angeordnet ist und zwei extreme Positionen einnehmen kann, nämlich eine Leerlaufposition, in der es die Kraftstoffeinspritzöffnungen (8) der Starteinspritzdüse (3) verschließt, und eine Startposition, in der die Kraftstoffeinspritzöffnungen (8) frei sind,
    und gegen die in der ersten Leitung (11) und der genannten Kammer (6) herrschenden Druckkräfte wirkende elastische Mittel (18) zur Rückführung des Ventilglieds (16) in die Leerlaufposition, wenn die Drehzahl der Turbomaschine unter der minimalen Betriebsdrehzahl des Startkopfs liegt,
    wobei das Ventilglied (16) eine erste Reihe von Öffnungen (19) aufweist, die die erste Leitung (11) zumindest in der Leerlaufposition mit der genannten Kammer (6) in Verbindung setzen.
  4. Vorrichtung nach Anspruch 3,
       dadurch gekennzeichnet,
       daß die erste Reihe von Öffnungen (19) in der Startposition des Ventilglieds (16) von einer in der Starteinspritzdüse (3) ausgebildeten Schulter (22) verschlossen wird.
  5. Vorrichtung nach einem der Ansprüche 3 oder 4,
       dadurch gekennzeichnet,
       daß das Ventilglied (16) eine zweite Reihe von Öffnungen (20) aufweist, die die erste Leitung (11) permanent mit der genannten Kammer (6) verbinden.
  6. Vorrichtung nach Anspruch 5,
       dadurch gekennzeichnet,
       daß die zweite Leitung (12) den in die genannte Kammer (6) übergehenden Kraftstoff zu der Leerlaufeinspritzdüse (4) abführt.
  7. Vorrichtung nach einem der Ansprüche 4 bis 6,
       dadurch gekennzeichnet,
       daß die erste Leitung (11) und die zweite Leitung (12) zumindest in der Nachbarschaft der Starteinspritzdüse (3) koaxial verlaufen, wobei die erste Leitung (11) die zweite Leitung (12) umschließt.
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 EP0689006A1 (de) 1995-12-27
EP0689006B1 true EP0689006B1 (de) 1998-11-11

Family

ID=9464486

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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)

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DK32196A (da) * 1996-03-19 1997-07-04 Danfoss As Dyseenhed til en oliebrænder
DE19645961A1 (de) * 1996-11-07 1998-05-14 Bmw Rolls Royce Gmbh Kraftstoffeinspritzvorrichtung für eine Gasturbinen-Brennkammer mit einer flüssigkeitsgekühlten Einspritzdüse
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
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
US8141368B2 (en) * 2008-11-11 2012-03-27 Delavan Inc Thermal management for fuel injectors
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

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US3669354A (en) * 1970-09-08 1972-06-13 J & T Eng Ascot Ltd Fluid injectors
GB2036296B (en) * 1978-11-20 1982-12-01 Rolls Royce Gas turbine
US5423178A (en) * 1992-09-28 1995-06-13 Parker-Hannifin Corporation Multiple passage cooling circuit method and device for gas turbine engine fuel nozzle

Also Published As

Publication number Publication date
DE69505894T2 (de) 1999-05-12
DE69505894D1 (de) 1998-12-17
EP0689006A1 (de) 1995-12-27
US5568721A (en) 1996-10-29
JPH0828875A (ja) 1996-02-02
FR2721693A1 (fr) 1995-12-29
JP2847045B2 (ja) 1999-01-13
FR2721693B1 (fr) 1996-07-19

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