EP4004442B1 - Kraftstoffinjektor mit einem spülkreis für ein flugzeugtriebwerk - Google Patents

Kraftstoffinjektor mit einem spülkreis für ein flugzeugtriebwerk Download PDF

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Publication number
EP4004442B1
EP4004442B1 EP20751616.2A EP20751616A EP4004442B1 EP 4004442 B1 EP4004442 B1 EP 4004442B1 EP 20751616 A EP20751616 A EP 20751616A EP 4004442 B1 EP4004442 B1 EP 4004442B1
Authority
EP
European Patent Office
Prior art keywords
injector
axis
elongation
fins
fuel
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
EP20751616.2A
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English (en)
French (fr)
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EP4004442A1 (de
Inventor
Thomas Jean Olivier Lederlin
Denis Luc Alain Chanteloup
Simon Arthur MEILLEURAT
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 Helicopter Engines SAS
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Safran Helicopter Engines SAS
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Publication of EP4004442A1 publication Critical patent/EP4004442A1/de
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Classifications

    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • 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
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances

Definitions

  • the present invention relates to a purge circuit fuel injector for an aircraft turbomachine.
  • the state of the art includes in particular the documents FR-A1-2 971 039 , FR-A 1-3 013 805 And FR-A1-3 067 792 .
  • a mixture of compressed air and suitable fuel is generally injected into a turbomachine combustion chamber using one or more injectors.
  • the injectors are, for example, fixed to a casing and pass through orifices in a chamber wall to eject fuel into the chamber in the form of a jet of fuel droplets.
  • a fuel injector 10 for example a flat jet, such as that shown in figures 1 to 5 , conventionally comprises a body 12 of generally elongated shape having an elongation axis A.
  • the body 12 comprises a first longitudinal end 14 for supplying fuel and a second longitudinal end 16 for ejecting a flat jet of fuel.
  • the body 12 is tubular and comprises an internal bore 18 which opens axially at the end 14 and which is connected to a nozzle 20 for projecting the jet of fuel at the end 16.
  • the body may include an air cooling circuit coaxial with the fuel circuit, as described in the documents DE-10.2017. 200106- A1 , DE-10.2013.208069-A1 And JP-2003.247425 -A .
  • the body 12 may also comprise at least one integrated air purge circuit which comprises an internal cavity 22 connected on the one hand to air inlet orifices 24 located on the body and to at least one air outlet 26 located on the level of end 16, as described in the document EP-2.244.014 -A2
  • This air circuit has only a purge function and the present invention proposes an improvement to this technology which makes it possible to optimize the operation of a fuel injector, in a simple, efficient and economical manner.
  • the present invention provides a fuel injector according to the subject matter of claim 1.
  • Flow disruptors can provide the air circuit with at least one additional function beyond the purge function.
  • flow disruptors can promote heat exchange between the air and the injector body and thus contribute to cooling the injector body. They can also facilitate the propagation of the fuel jet and thus optimize the performance of the combustion chamber equipped with this injector.
  • the present invention also relates to an aircraft turbomachine, comprising a combustion chamber equipped with at least one injector
  • FIG. 6 shows an environment in which a fuel injector 110 according to the invention can be used.
  • This is a combustion chamber 130 of an aircraft turbomachine such as a helicopter.
  • the combustion chamber 130 is arranged inside a casing 132 of the turbomachine and comprises a wall 134 internally defining a combustion space into which a mixture of air and fuel is injected and burned.
  • the fuel is injected into the chamber 130 via one or more injectors 110 which are here fixed to the casing 132 and which pass through an orifice 136 in the wall 134.
  • a body 112 of generally elongated shape having an elongation axis A this body 112 comprising a first longitudinal end 114 for supplying fuel and a second longitudinal end 116 for ejecting a jet of fuel.
  • This second end 116 comprises a nozzle formed by a tubular portion 120 of generally elongated shape having an elongation axis B substantially perpendicular to the elongation axis A ( Figure 5 in particular).
  • the tubular portion has its two open longitudinal ends configured to respectively form two separate fuel flow inlets (arrows 121) intended to meet substantially in the middle of the tubular portion which comprises at least one slot 125 for ejecting the fuel jet (arrow 127).
  • the body 112 and the tubular portion 120 are made of metal and they are obtained in a single piece by machining a metal block, preferably by additive manufacturing.
  • This fixing base 138 comprises a collar extending around the axis A and pierced with holes for the passage of screws for fixing the injector to the casing 132.
  • the body 112 includes an internal longitudinal bore 118 extending along and at the axis A, between the first and second longitudinal ends, and in fluid communication with the ends of the tubular portion 120.
  • the body 112 also comprises an internal air passage cavity 122, which comprises an annular portion 139 extending around the bore 118 and channels 140 which open at the end 116 to form the aforementioned purge air outlets.
  • the portion of the cavity 122 extends over a part of the length of the body 112. It extends to the second longitudinal end 116 of the body 112 and is connected to two channels 140 diametrically opposite relative to the axis A, which open at this end 116 so that air is expelled from the injector.
  • a jet of fuel is ejected by the injector, this jet is surrounded by the air expelled by the same injector.
  • the injector is not expelling fuel, the expelled air purges the injector fuel system.
  • the air then expels the last drops of fuel and cleans the fuel ejection slot 125 of the tubular portion 120.
  • the air passage cavity 122 is thus likened to a purge circuit.
  • the cavity 122 is in fluid communication with an annular row of air supply orifices 124 formed at the periphery of the body and extending around the axis of elongation A.
  • THE figures 7 and 8 illustrate a first embodiment of the invention in which air flow disruptors 150 are provided in the cavity 122, and more particularly in its annular portion 139.
  • This annular portion 139 is here defined between two cylindrical surfaces 152, 154 extending around each other and around the axis A.
  • the fins 150a are axially spaced from each other along the axis A.
  • the fins 150b are also axially spaced from each other along this axis A and extend in transverse planes passing substantially between the fins 150a.
  • the fins 150a, 150b may have a rectangular, triangular or trapezoidal shape in axial section.
  • the fins 150a may have a different shape in section from the fins 150b, as in the example shown. They may have a thickness or axial dimension substantially equal to their height or radial dimension (measured from the axis A).
  • the air which enters the portion 139 of the cavity 122, through the orifices 124, must bypass the fins 150a, 150b and undergoes pressure losses due to the baffle effect. This phenomenon contributes to the cooling of the body 112 of the injector 110.
  • Each of the channels 140 has protruding disruptors 156.
  • the disruptors 156 of each of the channels 140 comprise several partitions, which are here parallel to each other and substantially parallel to the axis A.
  • the number of disruptors 156 or partitions per channel 140 is for example between 3 and 10.
  • the air leaving the purge circuit is guided by the partitions so as to optimize the formation and diffusion of the fuel jet, for example in the direction of a spark plug of the combustion chamber 130 equipped with the injector 110.
  • the injector 110 according to the invention can be produced by additive manufacturing for example, and is advantageously a single piece.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Organic Low-Molecular-Weight Compounds And Preparation Thereof (AREA)

Claims (8)

  1. Kraftstoffinjektor (110) für ein Flugzeug-Turbotriebwerk, der einen rohrförmigen Körper (112) umfasst, der eine Ausdehnungsachse (A) aufweist und ein erstes Längsende (114) zum Zuführen von Kraftstoff und ein zweites Längsende (116) zum Ausstoßen eines Kraftstoffstrahls umfasst, wobei der Körper weiter einen integrierten Spülluftkreis umfasst, der einen inneren Hohlraum (122) umfasst, der mit Luftzufuhröffnungen (124), die sich am Körper (112) befinden, in strömungstechnischer Kommunikation steht und der einen ringförmigen Abschnitt (139) umfasst, der sich um die Ausdehnungsachse (A) herum erstreckt und mit Luftauslasskanälen (140), die im Bereich des zweiten Endes (116) münden, verbunden ist, dadurch gekennzeichnet, dass Luftströmungsstörer (150, 156) vorgesehen sind, die im ringförmigen Abschnitt (139) des inneren Hohlraums (122) und in den Kanälen (140) vorspringen, wobei die Störer (156) jedes der Kanäle (140) mehrere Trennwände umfassen, wobei die Trennwände parallel zueinander und im Wesentlichen parallel zur Ausdehnungsachse (A) sind.
  2. Injektor (110) nach Anspruch 1, wobei die Störer (150) vorspringende ringförmige Rippen (150a, 150b) umfassen, die sich im ringförmigen Abschnitt (139) um die Ausdehnungsachse herum erstrecken.
  3. Injektor (110) nach Anspruch 2, wobei die Störer (150) erste ringförmige Rippen (150a), die an einer zylindrischen Außenfläche (152), welche den Abschnitt definiert, vorspringen, und zweite ringförmige Rippen (150b) umfassen, die an einer zylindrischen Innenfläche (154), welche sich um die Außenfläche herum erstreckt, vorspringen.
  4. Injektor (110) nach Anspruch 3, wobei die ersten ringförmigen Rippen (150a) entlang der Ausdehnungsachse axial voneinander beabstandet sind, wobei die zweiten Rippen (150b) ebenfalls entlang dieser Achse axial voneinander beabstandet sind und sich in Querebenen, die im Wesentlichen zwischen den ersten Rippen verlaufen, erstrecken.
  5. Injektor (110) nach einem der vorstehenden Ansprüche, wobei der Hohlraum (122) zwei Kanäle (140) umfasst, die sich in Bezug auf die Ausdehnungsachse (A) diametral gegenüberliegen und jeweils einen Luftauslass im Bereich des zweiten Endes (116) definieren.
  6. Injektor (110) nach einem der vorstehenden Ansprüche, wobei der Körper (112) einstückig gebildet ist.
  7. Injektor (110) nach einem der vorstehenden Ansprüche, wobei das erste Längsende (114) des Körpers (112) mit einer Befestigungsbasis (138) verbunden ist, die mit dem Körper einstückig gebildet ist.
  8. Flugzeug-Turbotriebwerk, das eine Brennkammer umfasst, die mit mindestens einem Injektor (110) nach einem der vorstehenden Ansprüche ausgestattet ist.
EP20751616.2A 2019-07-24 2020-07-16 Kraftstoffinjektor mit einem spülkreis für ein flugzeugtriebwerk Active EP4004442B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1908419A FR3099231B1 (fr) 2019-07-24 2019-07-24 Injecteur de carburant a circuit de purge pour une turbomachine d’aeronef
PCT/FR2020/051274 WO2021014074A1 (fr) 2019-07-24 2020-07-16 Injecteur de carburant a circuit de purge pour une turbomachine d'aeronef

Publications (2)

Publication Number Publication Date
EP4004442A1 EP4004442A1 (de) 2022-06-01
EP4004442B1 true EP4004442B1 (de) 2025-04-02

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Application Number Title Priority Date Filing Date
EP20751616.2A Active EP4004442B1 (de) 2019-07-24 2020-07-16 Kraftstoffinjektor mit einem spülkreis für ein flugzeugtriebwerk

Country Status (7)

Country Link
US (1) US11892166B2 (de)
EP (1) EP4004442B1 (de)
CN (1) CN114222889B (de)
CA (1) CA3144907A1 (de)
FR (1) FR3099231B1 (de)
PL (1) PL4004442T3 (de)
WO (1) WO2021014074A1 (de)

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE200106C (de)
JP2003247425A (ja) * 2002-02-25 2003-09-05 Mitsubishi Heavy Ind Ltd 燃料ノズル、燃焼器およびガスタービン
FR2875584B1 (fr) * 2004-09-23 2009-10-30 Snecma Moteurs Sa Injecteur a effervescence pour systeme aeromecanique d'injection air/carburant dans une chambre de combustion de turbomachine
US8015815B2 (en) * 2007-04-18 2011-09-13 Parker-Hannifin Corporation Fuel injector nozzles, with labyrinth grooves, for gas turbine engines
US8286433B2 (en) * 2007-10-26 2012-10-16 Solar Turbines Inc. Gas turbine fuel injector with removable pilot liquid tube
US8256226B2 (en) * 2009-04-23 2012-09-04 General Electric Company Radial lean direct injection burner
US9151227B2 (en) * 2010-11-10 2015-10-06 Solar Turbines Incorporated End-fed liquid fuel gallery for a gas turbine fuel injector
FR2971039B1 (fr) 2011-02-02 2013-01-11 Turbomeca Injecteur de chambre de combustion de turbine a gaz a double circuit de carburant et chambre de combustion equipee d'au moins un tel injecteur
RU2618801C2 (ru) * 2013-01-10 2017-05-11 Дженерал Электрик Компани Топливная форсунка, концевой узел топливной форсунки и газовая турбина
DE102013208069A1 (de) * 2013-05-02 2014-11-06 Siemens Aktiengesellschaft Brennerlanze für einen Brenner einer Gasturbine
FR3013805B1 (fr) 2013-11-26 2018-01-26 Safran Helicopter Engines Ensemble de combustion a acces facilite des cannes de prevaporisation.
US9528705B2 (en) * 2014-04-08 2016-12-27 General Electric Company Trapped vortex fuel injector and method for manufacture
US20170328568A1 (en) * 2014-11-26 2017-11-16 Siemens Aktiengesellschaft Fuel lance with means for interacting with a flow of air and improve breakage of an ejected liquid jet of fuel
JP6100295B2 (ja) * 2015-03-02 2017-03-22 三菱日立パワーシステムズ株式会社 燃料ノズル、これを備えた燃焼器及びガスタービン
FR3059047B1 (fr) * 2016-11-21 2020-08-28 Safran Helicopter Engines Injecteur de chambre de combustion pour une turbomachine et son procede de fabrication
DE102017200106A1 (de) * 2017-01-05 2018-07-05 Siemens Aktiengesellschaft Brennerspitze mit einem Luftkanalsystem und einem Brennstoffkanalsystem für einen Brenner und Verfahren zu deren Herstellung
FR3067792B1 (fr) 2017-06-16 2021-05-21 Safran Helicopter Engines Injecteur de carburant a jet plat pour une turbomachine d'aeronef et son procede de fabrication

Also Published As

Publication number Publication date
EP4004442A1 (de) 2022-06-01
CN114222889A (zh) 2022-03-22
PL4004442T3 (pl) 2025-05-26
FR3099231B1 (fr) 2022-08-12
US11892166B2 (en) 2024-02-06
WO2021014074A1 (fr) 2021-01-28
FR3099231A1 (fr) 2021-01-29
CN114222889B (zh) 2024-08-23
CA3144907A1 (en) 2021-01-28
US20220282869A1 (en) 2022-09-08

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