EP1770333B1 - Anti-Verkokungsinjektorarm - Google Patents

Anti-Verkokungsinjektorarm Download PDF

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Publication number
EP1770333B1
EP1770333B1 EP06121357A EP06121357A EP1770333B1 EP 1770333 B1 EP1770333 B1 EP 1770333B1 EP 06121357 A EP06121357 A EP 06121357A EP 06121357 A EP06121357 A EP 06121357A EP 1770333 B1 EP1770333 B1 EP 1770333B1
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EP
European Patent Office
Prior art keywords
fuel
distributor
central
duct
injection system
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.)
Active
Application number
EP06121357A
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English (en)
French (fr)
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EP1770333A1 (de
Inventor
Didier Hernandez
Thomas Noel
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
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SNECMA SAS
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Publication of EP1770333A1 publication Critical patent/EP1770333A1/de
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Publication of EP1770333B1 publication Critical patent/EP1770333B1/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
    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00016—Preventing or reducing deposit build-up on burner parts, e.g. from carbon
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23K—FEEDING FUEL TO COMBUSTION APPARATUS
    • F23K2900/00—Special features of, or arrangements for fuel supplies
    • F23K2900/05003—Non-continuous fluid fuel supply

Definitions

  • the invention relates to a fuel injector fitted to the combustion chamber of a gas turbine engine, more particularly in an aircraft turbojet engine. It relates in particular to an improvement to avoid fuel coking in the arm of the injector where are formed two coaxial ducts belonging to different fuel supply circuits, respectively a primary circuit and a secondary circuit.
  • the combustion chamber is provided with a plurality of injectors regularly distributed circumferentially at the bottom of the annular combustion chamber.
  • Each injector comprises a curved arm terminated by a spray head.
  • the fuel flows in this arm, attached to the outer casing surrounding the combustion chamber, to the spray head.
  • Compressed air from a high pressure compressor circulates in this housing. The fuel is mixed with the air in the bottom of the combustion chamber before igniting in it.
  • the so-called primary circuit or idle circuit is designed to obtain a particularly fine spraying of the fuel. Its flow is limited but permanent.
  • the so-called secondary circuit or full-gas circuit is designed to complete the fuel flow to the full-throttle point allowing, in particular, to achieve all the power required for take-off.
  • this secondary circuit is not used continuously and its flow is sometimes very low at certain speeds.
  • the fuel from these two circuits reaches the spray head by flowing in coaxial conduits defined within the arm.
  • the central duct belongs to the primary circuit and the tubular duct that surrounds it belongs to the secondary circuit.
  • most of the injector, including the arm can be subjected to high temperatures (300 ° K to 950 ° K for a full throttle) since such an arm is installed in a hot air stream from the last stage of the high pressure compressor.
  • the secondary circuit may not be used or have a very low flow rate, as mentioned above.
  • a conventional dual circuit mechanical injector has a reinforced thermal insulation around the arm of the injector.
  • Such an arm is therefore complex and expensive to manufacture and its mass is increased by the thermal insulation elements.
  • the document WO03 / 054447A discloses a gas turbine fuel system dual fuel injection system, in which the fuel line of a fuel system crosses in the injector spray head the conduit of an additional combustion air circuit. This additional air flows in an annular peripheral duct from the injector to the head to cool the injector per se. Coking of the fuel is avoided only in the event that only one fuel circuit is in use.
  • the invention proposes a novel design of a gas turbine two-circuit fuel injection system according to claim 1, which makes it possible to eliminate or at least considerably reduce the static thermal insulation in favor of cooling by the circulation of the fuel itself.
  • Said spray head may comprise a splitter connected to the ends of the two ducts defined in the arm.
  • This distributor is housed in a spray nozzle extending said arm and said channel arrangement is formed essentially in said distributor.
  • the central duct is extended by an axial blind hole of said distributor and bores extend between said blind hole and respective grooves made, for example longitudinally, to the surface of said distributor.
  • These grooves form, with the inner surface of the nozzle, outer channels opening into an open annular cavity defined at the free end of this nozzle.
  • a nozzle extending said distributor inside said nozzle externally comprises substantially helical ribs and in contact with the inner wall of the nozzle.
  • the nozzle defines with said inner wall of the nozzle rotational channels arranged between the outer channels of the distributor and the annular cavity. The rotation of the fuel makes it possible to obtain a divergent jet.
  • the nozzle is hollowed to define with the end of said distributor, a cavity central having a central orifice for spraying the fuel.
  • the peripheral duct defined in the arm communicates with holes made in the distributor and opening into this central cavity. These bores extend at least partly obliquely to an axis of the distributor, to cause a rotation of the fuel in the central cavity and therefore a divergent ejection of the spray of fuel sprayed.
  • the figure 1 is partially in half section, a combustion chamber 11 of an aircraft turbojet engine 10.
  • the chamber of generally annular geometry combustion comprises a chamber bottom 12 inside which are engaged the spray heads 14 of a number of injectors 15 carried by a casing 16 surrounding the combustion chamber.
  • the injectors 15 are spaced regularly circumferentially.
  • Air under relatively hot pressure from an upstream high pressure compressor is introduced into the housing by an annular diffuser 18.
  • the hot air is divided into two streams; one passes through the housing 16 bypassing the combustion chamber 11 and the other engages in the combustion chamber through holes in the chamber bottom 12, to mix with the fuel projected by the spray heads 14 in the chamber of combustion.
  • the fuel ignites to provide gas supplying a downstream high pressure turbine.
  • Each injector 15 comprises an injector arm 22 with two coaxial ducts, supporting and supplying the spray head 14 which is of the double jet type.
  • the arm 22 is bent to maintain the spray head perpendicular to the chamber bottom.
  • the structure of the arm is very simple. It comprises an outer tube 24 surrounded by a protective casing 25 and an inner tube 26 engaged co-axially in the outer tube so as to define two coaxial ducts, a central duct 28 delimited by said inner tube and a sectional duct 29 with section annular surrounding the central duct and defined by the two tubes 24, 26 inside and outside.
  • the injector arm is installed in a stream of relatively hot compressed air, that is to say, the air which bypasses the combustion chamber 11 and partly the air entering the combustion chamber.
  • each injector 15 is connected to two fuel supply circuits for adapting the supply conditions to different engine speeds.
  • the two circuits, outside the housing 16 are symbolized in broken lines.
  • the peripheral duct 29 is part of the so-called primary fuel circuit 32 while the central duct 28 is part of the so-called secondary fuel circuit 33.
  • the fuel circulating in the peripheral duct (at a temperature much lower than that of the air circulating in the crankcase) does not have time to coke due to a flow rate sufficient and is on the other hand an effective thermal protection for the fuel that is in the central conduit 28.
  • the fuel flowing in the peripheral duct continuously cools the inner tube 26 and prevents the heating of fuel that stagnates eventually, at certain times, in the central duct. Therefore, the coking of the fuel in the central duct is avoided.
  • the spray head comprises an arrangement of channels for ejecting the circulating fuel in said central duct 28 in a divergent jet located outside the fuel jet coming from the peripheral duct 29.
  • the spray head 14 comprises, at the end of the arm 22: a distributor 35, a nozzle 37 extending said distributor and a nozzle 39 connected to the end of the arm 22 and surrounding the distributor and the nozzle.
  • the distributor 35 is connected to the ends of the two ducts 28, 29. It is approximately cylindrical and has an axis xx which merges with the axis of the divergent double jet produced by the spray head 14.
  • the above-mentioned channel arrangement is provided essentially in this distributor.
  • the central duct 28 is extended by a blind hole 39 of said axial distributor. Holes 41 perpendicular to the blind hole (here four holes at 90 ° relative to each other) extend between the blind hole and respective grooves 42 made here, longitudinally, to the surface of the distributor.
  • the grooves 42 form with the inner surface of this nozzle outer channels 43 opening into an open annular cavity 45 defined at the free end of the nozzle. It comprises a conical orifice 47 which delimits the outer contour of the outlet of said open annular cavity 45.
  • This annular cavity is internally limited by the outer surface, here conical, of the nozzle 37. This extends the distributor 35 to the inside of the nozzle and it has externally substantially helical ribs 60 themselves in contact with the inner wall of the nozzle 39. They therefore define with them rotating channels which are arranged between the channels. 43 and the annular cavity 45.
  • the fuel supplied by the central duct 28 passes through the blind hole 39, then into the holes 41 and into the outer channels before engaging in the rotation channels. This gives a divergent jet which surrounds the jet from the peripheral duct.
  • the nozzle 37 is hollowed to define, with the end of the distributor 35, a central cavity 50 opening axially through a central orifice 52 for spraying the fuel of the primary circuit.
  • the annular cavity 45 opens all around this central orifice 52.
  • the peripheral duct 29 communicates with holes 55 formed in the distributor and opening into this central cavity 50. As shown, these bores extend at first substantially longitudinally, that is to say, parallel to the axis and then obliquely relative to this axis to generate a rotation of the fuel in the central cavity. In this way, the spray that emerges from the central orifice 52 is divergent.
  • the invention relates primarily to the anti-coking arrangement.
  • Such a structure can be used with other types of spray heads designed to be powered by a primary circuit and a secondary circuit as defined above.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)

Claims (7)

  1. System mit zwei Kreisläufen zum Einspritzen von Kraftstoff in eine Brennkammer eines Gasturbinenmotors, wobei das System einen sogenannten Hauptkraftstoffkreislauf (32) mit ununterbrochenem Durchfluß, einen sogenannten Nebenkraftstoffkreislauf (33) mit im wesentlichen variablem Durchfluß, und einen Einspritzarm (22) mit zwei koaxialen Leitungen (28, 29), die einen Doppelstrahl-Sprühkopf (14), jeweils eine zentrale Leitung (28) und eine Umfangsleitung (29) mit ringförmigem Querschnitt, die die zentrale Leitung umgibt, stützen und versorgen, aufweist, wobei der Einspritzarm in einer relativ warmen Druckluftzunge installiert ist, dadurch gekennzeichnet, daß die Umfangsleitung (29) an den sogenannten Hauptkraftstoffkreislauf (32) angeschlossen ist, während die zentrale Leitung (28) an den sogenannten Nebenkraftstoffkreislauf (33) angeschlossen ist, und daß der Sprühkopf (14) eine Anordnung von Kanälen aufweist, die es erlauben, den Kraftstoff, der in der zentralen Leitung zirkuliert, als einen divergenten Strahl auszustoßen, der sich außerhalb des Kraftstoffstrahls befindet, der in der Umfangsleitung zirkuliert.
  2. Einspritzsystem nach Anspruch 1, dadurch gekennzeichnet, daß der Sprühkopf (14) einen Verteiler (35) aufweist, der an den Enden der beiden Leitungen (28, 29) angeschlossen und in einem Sprühansatz (39) untergebracht ist, der den Arm verlängert, und daß die Anordnung der Kanäle im wesentlichen in dem Verteiler eingerichtet ist.
  3. Einspritzsystem nach Anspruch 2, dadurch gekennzeichnet, daß die zentrale Leitung (28) durch ein Sackloch (39) des Verteilers verlängert ist, daß sich Bohrungen (41) zwischen dem Sackloch und Rillen (42), die an der Oberfläche des Verteilers angebracht sind, erstrecken, und daß diese Rillen mit der Innenfläche des Ansatzes Außenkanäle (43) bilden, die in einen offenen ringförmigen Hohlraum (45), der an dem freien Ende des Ansatzes definiert ist, münden.
  4. Einspritzsystem nach Anspruch 3, dadurch gekennzeichnet, daß es eine Düse (37) aufweist, die den Verteiler im Inneren des Ansatzes (39) verlängert, wobei der offene Hohlraum (45) zwischen der Düse und der Innenwand des Ansatzes definiert ist, daß diese Düse ausgehöhlt ist, um einen zentralen Hohlraum (50) mit dem Ende des Verteilers zu definieren, und daß die Umfangsleitung (29) mit Bohrungen (55) kommuniziert, die in dem Verteiler ausgeführt sind und in den zentralen Hohlraum münden, wobei dieser Letztere eine zentrale Öffnung (52) für das Ausstoßen des Kraftstoffs aus dem Hauptkreislauf aufweist, und wobei der ringförmige Hohlraum (45) ganz um diese zentrale Öffnung für das Sprühen des Kraftstoffs des Nebenkreislaufs mündet.
  5. Einspritzsystem nach Anspruch 4, dadurch gekennzeichnet, daß sich diese Bohrungen (55) mindestens zum Teil schräg in bezug zu einer Achse des Verteilers erstrecken, um ein Indrehungversetzen des Kraftstoffs in dem zentralen Hohlraum (50) zu bewirken.
  6. Einspritzsystem nach Anspruch 4, dadurch gekennzeichnet, daß die Düse außen im wesentlichen schraubenförmige Rippen (60) aufweist, die mit der Innenwand des Ansatzes in Berührung sind, um mit dieser Kanäle zum Indrehungversetzen zu definieren, die zwischen den Außenkanälen (43) und dem ringförmigen Hohlraum (45) eingerichtet sind.
  7. Einspritzsystem nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, daß die zentrale Leitung (28) und die Umfangsleitung (29) von koaxialen Röhren (24, 26) definiert sind.
EP06121357A 2005-09-28 2006-09-27 Anti-Verkokungsinjektorarm Active EP1770333B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0509879A FR2891314B1 (fr) 2005-09-28 2005-09-28 Bras d'injecteur anti-cokefaction.

Publications (2)

Publication Number Publication Date
EP1770333A1 EP1770333A1 (de) 2007-04-04
EP1770333B1 true EP1770333B1 (de) 2010-07-21

Family

ID=36228821

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06121357A Active EP1770333B1 (de) 2005-09-28 2006-09-27 Anti-Verkokungsinjektorarm

Country Status (7)

Country Link
US (1) US20070068164A1 (de)
EP (1) EP1770333B1 (de)
JP (1) JP2007093200A (de)
CA (1) CA2561225A1 (de)
DE (1) DE602006015580D1 (de)
FR (1) FR2891314B1 (de)
RU (1) RU2006134688A (de)

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7762070B2 (en) * 2006-05-11 2010-07-27 Siemens Energy, Inc. Pilot nozzle heat shield having internal turbulators
US8448881B2 (en) * 2006-10-13 2013-05-28 Rolls-Royce Power Engineering Plc Fuel injector
FR2922995B1 (fr) 2007-10-31 2009-12-04 Snecma Chambre de combustion annulaire de moteur a turbine a gaz.
US8443608B2 (en) * 2008-02-26 2013-05-21 Delavan Inc Feed arm for a multiple circuit fuel injector
FR2927949B1 (fr) * 2008-02-27 2010-03-26 Snecma Diffuseur de turbomachine comportant des voiles annulaires echancres
BR112013028196B1 (pt) * 2011-05-17 2021-06-22 Snecma Câmara anular de combustão para uma turbomáquina e turbomáquina
FR2975466B1 (fr) * 2011-05-17 2013-05-24 Snecma Chambre annulaire de combustion pour une turbomachine
BR112016003574B1 (pt) 2013-08-20 2021-10-13 Snecma Sistema de injeção de combustível, método de injeção de combustível, produto de programa de computador e mídia de armazenamento
FR3010139B1 (fr) * 2013-09-04 2019-05-17 Safran Aircraft Engines Dispositif et procede d'estimation de colmatage dans un systeme d'injection de carburant dans une chambre de combustion d'un moteur
FR3011318B1 (fr) 2013-10-01 2018-01-05 Safran Aircraft Engines Injecteur de carburant dans une turbomachine
US10228140B2 (en) * 2016-02-18 2019-03-12 General Electric Company Gas-only cartridge for a premix fuel nozzle
FR3091332B1 (fr) * 2018-12-27 2021-01-29 Safran Aircraft Engines Nez d’injecteur pour turbomachine comprenant une vrille secondaire de carburant à section évolutive
FR3091333B1 (fr) * 2018-12-27 2021-05-14 Safran Aircraft Engines Nez d’injecteur pour turbomachine comprenant un circuit primaire de carburant agencé autour d’un circuit secondaire de carburant
FR3106373B1 (fr) * 2020-01-20 2021-12-10 Safran Aircraft Engines Injecteur pour une turbomachine

Citations (1)

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Publication number Priority date Publication date Assignee Title
WO2003054447A1 (de) * 2001-12-20 2003-07-03 Alstom Technology Ltd Brennstofflanze

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US6446439B1 (en) * 1999-11-19 2002-09-10 Power Systems Mfg., Llc Pre-mix nozzle and full ring fuel distribution system for a gas turbine combustor
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FR2817016B1 (fr) * 2000-11-21 2003-02-21 Snecma Moteurs Procede d'assemblage d'un injecteur de combustible pour chambre de combustion de turbomachine
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Also Published As

Publication number Publication date
FR2891314B1 (fr) 2015-04-24
FR2891314A1 (fr) 2007-03-30
DE602006015580D1 (de) 2010-09-02
US20070068164A1 (en) 2007-03-29
JP2007093200A (ja) 2007-04-12
RU2006134688A (ru) 2008-04-10
CA2561225A1 (fr) 2007-03-28
EP1770333A1 (de) 2007-04-04

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