EP1770333A1 - Anti-Verkokungsinjektorarm - Google Patents

Anti-Verkokungsinjektorarm Download PDF

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Publication number
EP1770333A1
EP1770333A1 EP06121357A EP06121357A EP1770333A1 EP 1770333 A1 EP1770333 A1 EP 1770333A1 EP 06121357 A EP06121357 A EP 06121357A EP 06121357 A EP06121357 A EP 06121357A EP 1770333 A1 EP1770333 A1 EP 1770333A1
Authority
EP
European Patent Office
Prior art keywords
fuel
duct
nozzle
central
distributor
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
EP06121357A
Other languages
English (en)
French (fr)
Other versions
EP1770333B1 (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
Original Assignee
SNECMA SAS
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Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP1770333A1 publication Critical patent/EP1770333A1/de
Application granted granted Critical
Publication of EP1770333B1 publication Critical patent/EP1770333B1/de
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Anticipated expiration legal-status Critical

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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 invention proposes a new design of the injector, including the arm thereof, to remove or at least significantly reduce the static thermal insulation in favor of cooling by the circulation of the fuel itself.
  • the invention relates to a fuel injector for a gas turbine engine combustion chamber of the type comprising a coaxial two-pipe injector arm supporting and supplying a double-jet spray head, respectively a central duct and a nozzle.
  • annular section peripheral duct surrounding said central duct, said injector arm being installed in a stream of relatively hot compressed air, characterized in that said peripheral duct is able to be connected to a so-called primary, permanent flow fuel circuit , while said central duct is adapted to be connected to a fuel circuit said secondary substantially variable flow rate and in that said spray head comprises an arrangement of channels for ejecting the fuel flowing in said central duct in a divergent jet located outside the fuel jet from said peripheral duct.
  • 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 invention also relates to a fuel injection system in a gas turbine engine combustion chamber of the type comprising a so-called primary fuel circuit, with a constant flow rate, a so-called secondary fuel system with essentially variable flow rate and an arm coaxial two-pipe injector unit supporting and supplying a double jet spray head, respectively a central duct and an annular section peripheral duct surrounding said central duct, said injector arm being installed in a stream of relatively hot compressed air , characterized in that said peripheral duct is connected to the so-called primary fuel circuit, while said central duct is connected to the so-called secondary fuel circuit and in that said spray head comprises an arrangement of channels making it possible to eject the circulating fuel in said central duct in a divergent jet located on the outside of the carburettone jet originating from said peripheral duct.
  • FIG. 1 partially shows 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, partly the air that bypasses the combustion chamber 11 and partially the air that enters the combustion chamber. this 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 first extend 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, that is to say substantially the structure of the arm 22.
  • Such a structure can be used with other types of spray head designed to be fed by a circuit primary and secondary circuit as defined above.
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 true EP1770333A1 (de) 2007-04-04
EP1770333B1 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)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2056023A1 (de) 2007-10-31 2009-05-06 Snecma Ringförmige Brennkammer eines Gasturbinenmotors
WO2015025109A1 (fr) 2013-08-20 2015-02-26 Snecma Procédé et système d'injection de carburant dans une chambre de combustion d'un moteur
FR3010139A1 (fr) * 2013-09-04 2015-03-06 Snecma Dispositif et procede d'estimation de colmatage dans un systeme d'injection de carburant dans une chambre de combustion d'un moteur
WO2020136359A1 (fr) * 2018-12-27 2020-07-02 Safran Aircraft Engines Nez d'injecteur pour turbomachine comprenant un circuit primaire de carburant agencé autour d'un circuit secondaire de carburant
FR3091332A1 (fr) * 2018-12-27 2020-07-03 Safran Aircraft Engines Nez d’injecteur pour turbomachine comprenant une vrille secondaire de carburant à section évolutive
FR3106373A1 (fr) * 2020-01-20 2021-07-23 Safran Aircraft Engines Injecteur pour une turbomachine

Families Citing this family (8)

* 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
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
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

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3638865A (en) * 1970-08-31 1972-02-01 Gen Electric Fuel spray nozzle
GB2088037A (en) * 1980-11-25 1982-06-03 Gen Electric Fuel Nozzle for a Gas Turbine Engine
US5570580A (en) * 1992-09-28 1996-11-05 Parker-Hannifin Corporation Multiple passage cooling circuit method and device for gas turbine engine fuel nozzle
US5934555A (en) * 1996-03-05 1999-08-10 Abb Research Ltd. Pressure atomizer nozzle
US6256995B1 (en) * 1999-11-29 2001-07-10 Pratt & Whitney Canada Corp. Simple low cost fuel nozzle support
US20020073707A1 (en) * 2000-11-21 2002-06-20 Snecma Moteurs Full cooling of main injectors in a two-headed combustion chamber

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3013732A (en) * 1959-09-01 1961-12-19 Parker Hannifin Corp Fuel injection nozzle
US4491272A (en) * 1983-01-27 1985-01-01 Ex-Cell-O Corporation Pressure atomizing fuel injection assembly
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
US6272840B1 (en) * 2000-01-13 2001-08-14 Cfd Research Corporation Piloted airblast lean direct fuel injector
US6389815B1 (en) * 2000-09-08 2002-05-21 General Electric Company Fuel nozzle assembly for reduced exhaust emissions
FR2817016B1 (fr) * 2000-11-21 2003-02-21 Snecma Moteurs Procede d'assemblage d'un injecteur de combustible pour chambre de combustion de turbomachine
EP1456583B1 (de) * 2001-12-20 2007-10-10 Alstom Technology Ltd Verfahren zum Eindüsen eines Brennstoff-/Luftgemisches in eine Brennkammer
US6675587B2 (en) * 2002-03-21 2004-01-13 United Technologies Corporation Counter swirl annular combustor

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3638865A (en) * 1970-08-31 1972-02-01 Gen Electric Fuel spray nozzle
GB2088037A (en) * 1980-11-25 1982-06-03 Gen Electric Fuel Nozzle for a Gas Turbine Engine
US5570580A (en) * 1992-09-28 1996-11-05 Parker-Hannifin Corporation Multiple passage cooling circuit method and device for gas turbine engine fuel nozzle
US5934555A (en) * 1996-03-05 1999-08-10 Abb Research Ltd. Pressure atomizer nozzle
US6256995B1 (en) * 1999-11-29 2001-07-10 Pratt & Whitney Canada Corp. Simple low cost fuel nozzle support
US20020073707A1 (en) * 2000-11-21 2002-06-20 Snecma Moteurs Full cooling of main injectors in a two-headed combustion chamber

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2056023A1 (de) 2007-10-31 2009-05-06 Snecma Ringförmige Brennkammer eines Gasturbinenmotors
WO2015025109A1 (fr) 2013-08-20 2015-02-26 Snecma Procédé et système d'injection de carburant dans une chambre de combustion d'un moteur
US10072578B2 (en) 2013-08-20 2018-09-11 Safran Aircraft Engines Method and system for injecting fuel into an engine combustion chamber
FR3010139A1 (fr) * 2013-09-04 2015-03-06 Snecma Dispositif et procede d'estimation de colmatage dans un systeme d'injection de carburant dans une chambre de combustion d'un moteur
WO2020136359A1 (fr) * 2018-12-27 2020-07-02 Safran Aircraft Engines Nez d'injecteur pour turbomachine comprenant un circuit primaire de carburant agencé autour d'un circuit secondaire de carburant
FR3091333A1 (fr) * 2018-12-27 2020-07-03 Safran Aircraft Engines Nez d’injecteur pour turbomachine comprenant un circuit primaire de carburant agencé autour d’un circuit secondaire de carburant
FR3091332A1 (fr) * 2018-12-27 2020-07-03 Safran Aircraft Engines Nez d’injecteur pour turbomachine comprenant une vrille secondaire de carburant à section évolutive
US11168886B2 (en) 2018-12-27 2021-11-09 Safran Aircraft Engines Injector nose for turbomachine including a secondary fuel swirler with changing section
US11788727B2 (en) 2018-12-27 2023-10-17 Safran Aircraft Engines Injector nose for turbomachine comprising a primary fuel circuit arranged around a secondary fuel circuit
FR3106373A1 (fr) * 2020-01-20 2021-07-23 Safran Aircraft Engines Injecteur pour une turbomachine

Also Published As

Publication number Publication date
FR2891314B1 (fr) 2015-04-24
US20070068164A1 (en) 2007-03-29
EP1770333B1 (de) 2010-07-21
CA2561225A1 (fr) 2007-03-28
RU2006134688A (ru) 2008-04-10
JP2007093200A (ja) 2007-04-12
FR2891314A1 (fr) 2007-03-30
DE602006015580D1 (de) 2010-09-02

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