EP0222654B1 - Strahltriebwerk mit Nachverbrennung und radial angeordneten einzelnen Injektoren - Google Patents

Strahltriebwerk mit Nachverbrennung und radial angeordneten einzelnen Injektoren Download PDF

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Publication number
EP0222654B1
EP0222654B1 EP86402356A EP86402356A EP0222654B1 EP 0222654 B1 EP0222654 B1 EP 0222654B1 EP 86402356 A EP86402356 A EP 86402356A EP 86402356 A EP86402356 A EP 86402356A EP 0222654 B1 EP0222654 B1 EP 0222654B1
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EP
European Patent Office
Prior art keywords
fuel
stream
chamber
injector
apertures
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
Application number
EP86402356A
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English (en)
French (fr)
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EP0222654A1 (de
Inventor
René Alain Benoist
Guy Jean-Louis Lapergue
Jacques Albert Legueux
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
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Publication of EP0222654A1 publication Critical patent/EP0222654A1/de
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Publication of EP0222654B1 publication Critical patent/EP0222654B1/de
Expired legal-status Critical Current

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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
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/60—Fluid transfer
    • F05B2260/602—Drainage

Definitions

  • the technical sector of the present invention is that of fuel injection devices in an air flow stream and more particularly of post-combustion fuel injection devices for aviation turbojet engines having a device for heating or post-combustion.
  • This device had the same drawbacks as the previous one concerning the poor spraying of the fuel, the heterogeneity of the fuel mixture downstream of the injection device and the problems of coking of the injectors.
  • a third embodiment provided, as disclosed in patent FR 1 454 312, the combination of pressurized fuel injectors and catalytic igniters using a mixture of compressor air from a pipe bypassing the turbine and fuel to create a homogeneous mixture.
  • Such an arrangement requires the presence in the vein of two types of organs, injectors and igniters, which complicates the production of the post-combustion system, increases their cost and complicates their maintenance.
  • the present invention therefore aims to solve the problems of injecting post-combustion fuel in modern engines with high turbine outlet temperature by combining in a new way fuel injection and spraying means.
  • Another object of the invention is to provide a device for injecting post-combustion fuel with the shortest possible response time.
  • Another object of the invention is to provide an injection device that is not very sensitive to coking and therefore reduces maintenance measures, as well as an easily removable device in order to further minimize maintenance operations.
  • the subject of the invention is therefore a turbojet engine having a post-combustion device downstream of its turbine comprising at least one device for injecting fuel into the vein, connected to a circuit for distributing pressurized fuel and a flame holder.
  • the injection device consists of a set of individual tubular injectors regularly repaired tis radially in the vein, perpendicular to the direction of flow and each connected through openings made in the wall forming the vein to the pressurized fuel distribution circuit, each injector being supplied separately from the others and comprising, associated with its tubular part, a fuel spray chamber using a fraction of air from the vein to inject therein a finely sprayed and widely distributed fuel mixture, said spray chamber communicating with the tubular part of the injector by at least one calibrated nozzle and comprising on an upstream face with respect to the vein at least one air inlet orifice taken from the vein and on a downstream side at least one orifice for expulsion towards the vein of the fuel mixture constituted by the sprayed fuel suspended in the
  • the spray chamber is arranged at the end of the tubular part of the injector, said end being narrowed to form the fuel outlet nozzle and the chamber comprises, facing the outlet nozzle, a spherical cap disposed on the wall of the chamber between its upstream and downstream faces, on which the fuel jet explodes to carry out a first spraying of fuel, the part of the air flow admitted in the chamber through the upstream orifices ensuring a second finer atomization of the fuel, the finely atomized fuel mixture being expelled from the chamber through the downstream orifices towards the vein.
  • the spraying chamber is constituted by a tubular sheath closed at each of its ends, surrounding the tubular part of the injector and being integral with it, the tubular sheath forming the chamber comprising at least one orifice air inlet upstream and an orifice downstream for expelling the fuel mixture, orifices with axes parallel to the flow axis of the air flow.
  • the tubular part of the injector is also closed at its end and has on its wall at least two nozzles opening into the spraying chamber, the axes of the nozzles being perpendicular to the plane containing the axes of the upstream and downstream orifices of the chamber.
  • FIG. 1 the rear part of a post-combustion turbojet engine 1 is shown diagrammatically, the last turbine wheel 2 and the nozzle 3 being simply shown.
  • the post-combustion device comprises a set of injectors arranged radially (FIG. 7) in the air flow upstream of known flame catchers 4.
  • each injector 8 consists of a tubular part 5 passing through the external wall 3 to which it is fixed by any known means, this tubular part comprising an internal conduit 6 connected to the fuel distribution circuit 7 comprising a pump 9 and a regulation of known type 10.
  • Each injector has the end of its tubular part constricted in order to form a calibrated nozzle 11 for injecting fuel into a spray chamber 12 integral with the injector and constituted in this embodiment by a cylinder 13 welded to the end of the tubular part 5 of the injector, the cylinder having, opposite the outlet nozzle, a bottom 14 in the form of a spherical cap against which the pressurized fuel is sprayed through the nozzle 11.
  • a large diameter orifice 16 is drilled while on the opposite part, therefore downstream of the flow 15, are pierced with small diameter orifices 17.
  • the orifices 16 allow part of the hot flow to be taken from the vein which, with the fuel coming from the nozzle 11 and sprayed against the bottom 14, will constitute a finely pulverized fuel mixture which will be expelled through the orifices 17 downstream of the vein where this mixture will be ignited by any known means, either by means of a candle for example or simply by self-ignition if the conditions of turbine outlet temperatures allow it.
  • the number of inlet ports and their respective diameters are calculated so that the diameter of the air inlets is 5 to 8 times greater than the diameter of the outlet ports so as to create a swirl in the spray chamber. significant air capable of promoting fuel spraying as much as possible.
  • each injector is connected, independently of the other injectors, to the fuel distribution circuit. This is important because it makes it possible to reduce the residence time of the fuel in each injector and therefore to reduce the risks of clogging of the fuel mixture outlet orifices and of the fuel outlet nozzle 11 by coking.
  • each injector is associated with an injector purge unit.
  • This box is constituted by a switching valve 18 making it possible to connect the line 6 of the injector to a source of compressed air at a temperature lower than the air of the stream in order to expel in the stream all the fuel and to prevent the deposition of coke in the nozzles 11 and outlet orifices 17, and this as soon as the PC operation is stopped and throughout the duration of the dry operation.
  • Each purge box can be made in the form of a diverter valve distributor (as shown in FIG. 1), controlled by hydromechanical post-combustion regulation 10.
  • the source of cold air 19 may consist of air taken from the fan or from the low pressure compressor.
  • the lowering of temperature thus achieved in the injector conduit can in this way reach fifty degrees, and this as soon as the fuel supply stops, thus avoiding the formation of coke.
  • the injector according to the invention consists of a tubular conduit 6 closed at its end 116 and having on its parts oriented perpendicular to the air flow, twice two fuel outlet nozzles 111 diametrically opposite.
  • the spraying chamber 112 is constituted by a tubular sheath closed at its two ends and welded to a flange 106 of the duct 6.
  • the sheath 112 has two orifices 16 for the entry of air taken from the flow and three longitudinal rows of outlet orifices (17, 17a, 17b) of the fuel mixture.
  • the middle row 17 (FIG. 6) of outlet openings is diametrically opposite to the inlet openings 16 while the rows 17a and 17b are inclined on either side of the plane of the axes of the openings 16, 17 by an angle between 30 and 50 degrees in order to obtain the widest and most homogeneous distribution of mixture in the flow.
  • FIG. 5 differs from that of FIG. 4 only by the arrangement of the sleeve 212 on the conduit 6 of the injector.
  • the end of the duct 6 is closed by a spacer 216 on which a cylindrical seat 214 of the sheath is centered, while the lower end of the sheath is also centered on a spacer 206 and is wedged in a cup 221 integral with channel 6.
  • the spray injectors thus produced are also supplied separately with fuel as previously by the pump 9 and each associated with a bleed box 18 (not shown in FIGS. 4 and 5).
  • the injectors produced according to the present invention are fixed directly to the external wall of the vein when they are used in a single-flow turbojet and this by any known means, for example by a threaded ring symbolized at 22 in FIG. 1.
  • the sheath 12, 112, 212 may comprise a spherical bead 25 bearing against the opening 23 to compensate for any positioning games of the two intermediate and external walls.
  • the injectors according to the invention are preferably positioned in the plane of the pins 26 (FIG. 2) serving to maintain the spacing of the two walls.
  • a spray chamber associated with each injector is based on the principle of a jet of fuel transverse to the air flow and bursting over an obstacle (spherical cap 14 or inner wall of sheath 114) then sprayed by the fraction of flow taken from the upstream orifices makes it possible to achieve a broad and homogeneous dilution of the fuel which allows, using a dozen spray injectors according to the invention arranged radially in the flow to advantageously replace the booms upstream currently used by simplifying the production of the post-combustion device as well as its maintenance and by reducing the problems of trails and wakes such as those caused by the current upstream ramps.
  • the type of injector according to the invention applies very particularly to modern engines with high outlet temperature.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Nozzles (AREA)
  • Exhaust Gas After Treatment (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)

Claims (7)

1. Flugzeug-Turboluftstrahltriebwerk mit einer stromabwärts der Turbine angeordneten Nachverbrennungsvorrichtung mit wenigstens einer Einspritzvorrichtung zur Kraftstoffeinspritzung in den Strahl, die mit einem Verteilerkreis für unter Druck stehenden Kraftstoff und einem Flammrohr verbunden ist, wobei die Einspritzvorrichtung aus einer Gruppe von individuellen rohrförmigen Einspritzdüsen besteht, die radial gleichmässig in dem Strahl senkrecht zur Strömungsrichtung verteilt angeordnet und jeweils über in der den Strahl bildenen Wandung (3, 24) angebrachte Löcher (23) mit dem Verteilerkreis (7, 9, 10) für den unter Druck stehenden Kraftstoff verbunden sind, dadurch gekennzeichnet, dass jede der Einspritzdüsen getrennt von den anderen Einspritzdüsen gespeist wird und an ihrem rohrförmigen Teil (6) eine Zerstäubungskammer (12, 112, 212) aufweist, die einen Anteil der Luft des Strahls entnimmt, um in letzteren ein fein zerstäubtes und breit verteiltes Kraftstoffgemisch einzuspritzen, und dass die Zerstäubungskammer (12, 112, 212) mit dem rohrförmigen Teil (5, 6) der Einspritzdüse über wenigstens eine kalibrierte Düsenöffnung (11, 111, 211) in Verbindung steht und auf einer in Bezug auf den Strahl stromaufwärtigen Seite wenigstens eine Lufteintrittsöffnung (16) für den Eintritt von in dem Strahl entnommener Luft und auf einer stromabwärtigen Seite wenigstens eine Ausgabeöffnung (17) für das Kraftstoffgemisch aufweist, das aus dem in der durch die Lufteintrittsöffnung zugeführten Luft suspendierten zerstäubten Kraftstoff besteht.
2. Turboluftstrahltriebwerk nach Anspruch 1, dadurch gekennzeichnet, dass der Durchmesser der stromaufwärtigen Öffnungen (16) der Zerstäubungskammer zwischen fünf und achtmal so gross ist wie der Durchmesser der stromabwärtigen Öffnungen (17), um in der Zerstäubungskammer eine die Zertäubung begünstigende Luftverwirbelung zu erzeugen.
3. Turboluftstrahltriebwerk nach einem der Ansprüche 1 oder 2, dadurch gekennzeichnet, dass die Zerstäubungskammer in dem Endbereich des rohrförmigen Teils (5) der Einspritzdüse angeordnet ist, wobei dieser Endbereich verengt ist und dadurch die genannte kalibrierte Düsenöffnung (11) für den Kraftstoffaustritt bildet, dass die Zerstäubungskammer eine auf der dieser Austrittsöffnung gegenüberliegenden Seite angeordnete sphärische Kalotte (14) aufweist, die an der zwischen der stromaufwärtigen und der stromabwärtigen Seite liegenden Wandung der Zerstäubungskammer angeordnet ist und auf der (14) der Kraftstoffstrahl zerbirst, wodurch eine erste Zerstäubung des Kraftstoffs bewirkt wird, dass der Teil des durch die stromaufwärtigen Lufteintrittsöffnungen (16) in die Zerstäubungskammer eintretenden Luftstroms eine zweite, feinere Zerstäubung des Kraftstoffs hervorruft, und dass das fein zerstäubte Kraftstoffgemisch durch die stromabwärtigen Öffnungen (17) aus der Zerstäubungskammer in den Strahl ausgestossen wird.
4. Turboluftstrahltriebwerk nach Anspruch 2, dadurch gekennzeichnet, dass die Zerstäubungskammer aus einer an beiden Enden geschlossenen ringförmigen Hülse (112, 212) besteht, die den rohrförmigen Teil (6) der Einspritzdüse umgibt und mit dieser fest verbunden ist, dass diese Hülse (112, 212) wenigstens eine Lufteintrittsöffnung (16) und wenigstens eine Öffnung (17) für den Ausstoss des Kraftstoffgemischs aufweist, wobei die Achsen dieser Öffnungen parallel zur Strömungsachse der Lufteintrittsöffnung verlaufen, dass der rohrförmige Teil der Einspritzdüse an seinem Ende (116, 216) geschlossen ist und an seiner Wandung wenigstens zwei Düsenöffnungen (111, 211) aufweist, die in die Zerstäubungskammer münden, und dass die Achsen dieser Düsenöffnungen (111, 211) auf der Ebene senkrecht stehen, die die Achsen der stromaufwärtigen Öffnungen (16) und der stromabwärtigen Öffnungen (17) der Zerstäubungskammer enthält.
5. Turboluftstrahltriebwerk nach Anspruch 4, dadurch gekennzeichnet, dass die Zerstäubungskammer zwei stromaufwärtige Öffnungen (16) mit grossem Durchmesser und drei Reihen (17, 17a, 17b) von stromabwärtigen Öffnungen für den Ausstoss des Kraftstoffgemischs aufweist, und dass die Achsen einer ersten Reihe (17) von stromabwärtigen Öffnungen parallel zur Strömungsachse verlaufen, während die Achsen der Öffnungen der beiden anderen Reihen (17a, 17b) gegenüber der Strömung um einen Winkel zwischen 30° und 50° geneigt sind.
6. Turboluftstrahltriebwerk nach einem der Ansprüche 1 bis 5, dessen Nachverbrennungsvorrichtung eine Einrichtung zur Zuführung von Spülluft für den Kraftstoffkreis aufweist, die wenigstens einen Spülkasten mit einem Ventil (18) umfasst, das den Durchtritt von Spülluft in die Einspritzdüsen ermöglicht, wenn die Zufuhr von Kraftstoff für die Nachverbrennung unterbrochen ist, dadurch gekennzeichnet, dass jeder Einspritzdüse (8) ein Spülkasten (18) zugeordnet ist, wodurch das gleichzeitige Spülen aller Einspritzdüsen ermöglicht ist.
7. Zweikreis-Turboluftstrahltriebwerk mit Vorverbrennung nach einem der Ansprüche 1 bis 6, mit einer Aussenwandung (3), die den Sekundärstrahl aussen begrenzt, und einer Zwischenwandung (24), die durch eine Gruppe von Befestigungsstiften (26) an der Aussenwandung befestigt ist und den Sekundärstrahl von dem Primärstrahl trennt, dadurch gekennzeichnet, dass jede Einspritzdüse (8) mit Hilfe bekannter Mittel am Ort der Befestigungsstifte (26) an der Aussenwandung des Sekundärstrahls befestigt ist und die Zwischenwandung in einer Öffnung durchdringt, und dass die Zerstäubungskammer vollständig im Innern des Primärstrahls enthalten ist.
EP86402356A 1985-10-23 1986-10-22 Strahltriebwerk mit Nachverbrennung und radial angeordneten einzelnen Injektoren Expired EP0222654B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8515713 1985-10-23
FR8515713A FR2588920B1 (fr) 1985-10-23 1985-10-23 Turboreacteur a postcombustion a injecteurs de postcombustion radiaux individuels

Publications (2)

Publication Number Publication Date
EP0222654A1 EP0222654A1 (de) 1987-05-20
EP0222654B1 true EP0222654B1 (de) 1989-03-29

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EP86402356A Expired EP0222654B1 (de) 1985-10-23 1986-10-22 Strahltriebwerk mit Nachverbrennung und radial angeordneten einzelnen Injektoren

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US (1) US4730453A (de)
EP (1) EP0222654B1 (de)
DE (1) DE3662623D1 (de)
FR (1) FR2588920B1 (de)

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EP0550126A1 (de) * 1992-01-02 1993-07-07 General Electric Company Hitzeschild für Nachbrenner
FR2689567B1 (fr) * 1992-04-01 1994-05-27 Snecma Injecteur de carburant pour chambre de post-combustion d'une turbomachine.
DE4309131A1 (de) * 1993-03-22 1994-09-29 Abb Management Ag Verfahren und Vorrichtung zur Nachlaufbeeinflussung bei Brennkammereinbauten
DE59409252D1 (de) * 1994-09-21 2000-05-04 Abb Alstom Power Ch Ag Brennkammer einer Gasturbogruppe
US5768886A (en) * 1995-09-29 1998-06-23 National Science Council Twin-plate flameholder construction
US5826429A (en) * 1995-12-22 1998-10-27 General Electric Co. Catalytic combustor with lean direct injection of gas fuel for low emissions combustion and methods of operation
US5927067A (en) * 1997-11-13 1999-07-27 United Technologies Corporation Self-cleaning augmentor fuel manifold
FR2871519B1 (fr) * 2004-06-10 2006-08-04 Snecma Moteurs Sa Procede et systeme de protection des injecteurs de carburant de turbine de gaz
US7805948B2 (en) * 2005-12-15 2010-10-05 Pratt & Whitney Canada Corp. Internally mounted device for a pressure vessel
US9291139B2 (en) * 2008-08-27 2016-03-22 Woodward, Inc. Dual action fuel injection nozzle
US9115897B2 (en) 2008-09-04 2015-08-25 United Technologies Corporation Gas turbine engine systems and methods involving enhanced fuel dispersion
FR3017445B1 (fr) * 2014-02-12 2019-05-24 Fives Pillard Module de bruleur en veine
FR3039220B1 (fr) * 2015-07-24 2017-08-11 Snecma Dipositif de postcombustion pour turboreacteur
CN111829009A (zh) * 2020-07-10 2020-10-27 中国空气动力研究与发展中心 一种基于楔形体的燃料组合喷注结构
CN114060851B (zh) * 2021-11-15 2022-09-20 中国航发沈阳发动机研究所 一种基于3d打印的分区分压加力喷油杆
CN114645799B (zh) * 2022-02-24 2024-04-26 哈尔滨工业大学 一种使用电动辅助增压的轴对称全速域冲压发动机

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Also Published As

Publication number Publication date
FR2588920A1 (fr) 1987-04-24
US4730453A (en) 1988-03-15
EP0222654A1 (de) 1987-05-20
FR2588920B1 (fr) 1987-12-04
DE3662623D1 (en) 1989-05-03

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