EP0142389B1 - Flame holder burner ring for a post combuster of a jet engine - Google Patents

Flame holder burner ring for a post combuster of a jet engine Download PDF

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Publication number
EP0142389B1
EP0142389B1 EP84401726A EP84401726A EP0142389B1 EP 0142389 B1 EP0142389 B1 EP 0142389B1 EP 84401726 A EP84401726 A EP 84401726A EP 84401726 A EP84401726 A EP 84401726A EP 0142389 B1 EP0142389 B1 EP 0142389B1
Authority
EP
European Patent Office
Prior art keywords
ring
limb
burner
flows
burner ring
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
EP84401726A
Other languages
German (de)
French (fr)
Other versions
EP0142389A1 (en
Inventor
René Alain Benoist
Michel Robert Clauzel
Roger Alfred Jules Vandenbroucke
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
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0142389A1 publication Critical patent/EP0142389A1/en
Application granted granted Critical
Publication of EP0142389B1 publication Critical patent/EP0142389B1/en
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

Definitions

  • the invention relates to a burner ring for afterburning of a jet engine, in particular for a heating system of a turbofan engine, said system being placed behind the wall separating the two streams and comprising a stabilizing ring for approximately V-shaped section flame containing a circular fuel injection ramp flowing against the current through openings provided at the tip of the V.
  • Certain multiflux military engines equipped with a heating system on the two flows, have a very reduced master torque. They may include one or more burner rings used for post-combustion proper and for heating the secondary cold flow. Generally one of the afterburner rings is located at the confluence of the two streams, just behind the conical wall separating them.
  • the burner ring includes a V-section flame stabilizing ring containing a circular fuel injection ramp flowing counter-current through openings made at the tip of the V.
  • the stabilizing ring As a result of the position of the stabilizing ring, its wings are subjected to very different temperatures.
  • the external wing is bathed by the secondary air flow, the temperature of which does not exceed 200 ° C. while the internal wing is subjected to the temperature of the gas leaving the turbine, of the order of 850 ° C.
  • French patent application 2,186,608 proposes a solution to the problem of overheating by arranging, at a certain distance upstream from the burner ring, an annular member called an anvil, against which the jets emitted by the holes provided in the ramp.
  • the mixture of gas and pulverized fuel thus produced, penetrates through the openings surrounding the jets and provided in the stabilizing ring, in the space surrounding the ramp in the ring and protects the latter against the heat of the flame.
  • the layers of fog are uniformly charged with sprayed fuel and wet the outer surface of the stabilizing ring which avoids hot spots and excessive deformation.
  • the device described does not, however, avoid stresses in the ring, which adversely affects its mechanical strength.
  • the main purpose of the anvil is to obtain a uniform spraying of the fuel into the air stream and better flame stability.
  • the invention proposes to remedy the constraints arising in the stabilizing ring by dissociating the two wings and allowing them to expand freely separately, each wing being held by a device articulated to the wall separating the two flows.
  • the invention is remarkable in that the flame stabilizing ring is formed by two independent parts, each of these parts constituting a wing of the V, and in that articulated support means are provided at the end of the partition wall flows to maintain each of the parts of the stabilizing ring.
  • the burner ring 3 comprises an injection ramp 5, pierced with orifices 6 for injecting fuel, against the flow of the primary and secondary air streams, a flame stabilizing ring 7 located upstream of the ramp and surrounding it.
  • the stabilizing ring has a section approximately in V, the point of the V being directed upstream of the current.
  • the stabilizing ring is formed by two independent parts 8 and 9, each of these parts constituting a wing of the V.
  • the two adjacent ends of the wings leave between them a continuous annular slot 10 allowing passage fuel jets emitted by the rail 5.
  • the burner ring 3 is held on the conical flow separation wall 4 by articulated support means 11.
  • the outer 8 and inner 9 wings are suspended from the conical wall 4 by bent levers 12, by means of welded yokes 13 and 14 respectively on the wings 8 and 9, arranged in the same axial planes and distributed uniformly along the wings.
  • the levers 12 have two arms 15 and 16 of unequal length.
  • the shortest arm 16 ends in a double yoke 16a which cooperates by means of a link 17 being articulated to the double yokes 16a and 14 by two axes 18 and 19 (see also Figure 4).
  • the elbow formed by the arms 15 and 16 comprises a bore which receives the axis 20 now in an articulated manner the yoke 13 welded to the outer wing 8.
  • the free end of the longest arm 15 carries a bore cooperating via a pin 21 with a yoke 22 fixed on the external surface of the wall 4.
  • the injection ramp 5 is fixed from place to place along the wing by lugs 23 and rivets 24 to the outer wing 8 of the ring.
  • the outer wing 8 immersed in the secondary air flow at low temperature, exhibits low thermal expansion and its dimensional characteristics vary little.
  • the injection ramp 5 which is integral with it will not undergo any significant displacement capable of modifying the direction of the jets and will make it possible to maintain a reasonable width of the annular slot 10 despite the relatively large expansion of the internal wing 9.
  • the continuous slot 10 of the burner ring according to the invention will optionally allow the use of an anvil ring as described in French patent application 2 186 608.
  • the removal of the partitions separating the openings surrounding the jets as described in the cited patent prevents the deformation of this relatively small area and improves the passage of the mixture of gas and fuel sprayed into the space surrounding the ramp 5 in the stabilizing ring 7 and protects the ramp against the heat of the flame.

Description

L'invention concerne un anneau-brûleur pour postcombustion de moteur à réaction en particulier pour système de réchauffe d'un turboréacteur à double flux, ledit système étant placé à l'arrière de la paroi de séparation des deux flux et comprenant un anneau stabiliseur de flamme de section approximativement en V contenant une rampe circulaire d'injection de carburant débitant à contre-courant à travers des ouvertures prévues à la pointe du V.The invention relates to a burner ring for afterburning of a jet engine, in particular for a heating system of a turbofan engine, said system being placed behind the wall separating the two streams and comprising a stabilizing ring for approximately V-shaped section flame containing a circular fuel injection ramp flowing against the current through openings provided at the tip of the V.

Certains moteurs militaires multiflux, équipés d'un système de réchauffe sur les deux flux, ont un maître couple très réduit. Ils peuvent comporter un ou plusieurs anneaux brûleurs servant à la postcombustion proprement dite et à la chauffe du flux froid secondaire. Généralement un des anneaux de postcombustion est situé à la confluence des deux flux, juste derrière la paroi conique les séparant.Certain multiflux military engines, equipped with a heating system on the two flows, have a very reduced master torque. They may include one or more burner rings used for post-combustion proper and for heating the secondary cold flow. Generally one of the afterburner rings is located at the confluence of the two streams, just behind the conical wall separating them.

L'anneau-brûleur comprend un anneau stabilisateur de flamme à section en V contenant une rampe circulaire d'injection de carburant débitant à contre-courant à travers des ouvertures pratiquées à la pointe du V.The burner ring includes a V-section flame stabilizing ring containing a circular fuel injection ramp flowing counter-current through openings made at the tip of the V.

Par suite de la position de l'anneau stabilisateur, ses ailes sont soumises à des températures très différentes. L'aile externe est baignée par le flux d'air secondaire dont la température ne dépasse pas 200 °C tandis que l'aile interne est soumise à la température du gaz sortant de la turbine, de l'ordre de 850 °C.As a result of the position of the stabilizing ring, its wings are subjected to very different temperatures. The external wing is bathed by the secondary air flow, the temperature of which does not exceed 200 ° C. while the internal wing is subjected to the temperature of the gas leaving the turbine, of the order of 850 ° C.

De telles différences de température entraînent des contraintes très sévères et des déformations de l'anneau préjudiciables à son bon fonctionnement et à sa tenue mécanique.Such temperature differences cause very severe stresses and deformations of the ring which are detrimental to its proper functioning and to its mechanical strength.

La demande de brevet français 2 186 608 propose une solution au problème de l'échauffement en disposant à une certaine distance en amont de l'anneau-brûleur un organe annulaire appelé enclume, contre lequel viennent se pulvériser les jets émis par les trous prévus dans la rampe. Le mélange de gaz et de carburant pulvérisé ainsi produit, pénètre par les ouvertures entourant les jets et prévues dans l'anneau stabilisateur, dans l'espace entourant la rampe dans l'anneau et protège celle-ci contre la chaleur de la flamme. En outre, les nappes de brouillard sont uniformément chargées en carburant pulvérisé et mouillent la surface extérieure de l'anneau stabilisateur ce qui évite les points chauds et les déformations trop importantes.French patent application 2,186,608 proposes a solution to the problem of overheating by arranging, at a certain distance upstream from the burner ring, an annular member called an anvil, against which the jets emitted by the holes provided in the ramp. The mixture of gas and pulverized fuel thus produced, penetrates through the openings surrounding the jets and provided in the stabilizing ring, in the space surrounding the ramp in the ring and protects the latter against the heat of the flame. In addition, the layers of fog are uniformly charged with sprayed fuel and wet the outer surface of the stabilizing ring which avoids hot spots and excessive deformation.

Le dispositif décrit ne permet toutefois pas d'éviter les contraintes dans l'anneau, ce qui influe défavorablement sur sa tenue mécanique. Le but principal de l'enclume est l'obtention d'une pulvérisation uniforme du carburant dans le courant d'air et une meilleure stabilité de la flamme.The device described does not, however, avoid stresses in the ring, which adversely affects its mechanical strength. The main purpose of the anvil is to obtain a uniform spraying of the fuel into the air stream and better flame stability.

L'invention se propose de remédier aux contraintes prenant naissance dans l'anneau stabilisateur en dissociant les deux ailes et en leur permettant de se dilater librement séparément, chaque aile étant maintenue par un dispositif articulé à la paroi séparant les deux flux.The invention proposes to remedy the constraints arising in the stabilizing ring by dissociating the two wings and allowing them to expand freely separately, each wing being held by a device articulated to the wall separating the two flows.

L'invention est remarquable en ce que l'anneau stabilisateur de flamme est formé de deux parties indépendantes, chacune de ces parties constituant une aile du V, et en ce que des moyens supports articulés sont prévus à l'extrémité de la paroi de séparation des flux pour maintenir cha- ' cune des parties de l'anneau stabilisateur.The invention is remarkable in that the flame stabilizing ring is formed by two independent parts, each of these parts constituting a wing of the V, and in that articulated support means are provided at the end of the partition wall flows to maintain each of the parts of the stabilizing ring.

Les explications et figures données ci-après à titre d'exemple, permettront de comprendre comment l'invention peut être réalisée.

  • La figure 1 représente une coupe longitudinale partielle d'un anneau brûleur selon l'invention.
  • La figure 2 est une vue en coupe longitudinale de l'anneau passant par une fixation de la rampe d'injection.
  • La figure 3 est une vue en bout partielle du réacteur montrant l'anneau-brûleur et la fixation de la rampe d'injection.
  • La figure 4 est une vue en coupe selon IV-IV de l'anneau-brûleur selon la figure 1.
  • La figure 1 est une vue en coupe partielle et longitudinale de la partie de turboréacteur située à la sortie du canal du flux secondaire 1 et à l'extrémité du canal du flux primaire 2. L'anneau-brûleur 3 est fixé à la confluence des deux flux, juste derrière la paroi conique 4 les séparant et sur laquelle il est fixé.
The explanations and figures given below by way of example will make it possible to understand how the invention can be implemented.
  • Figure 1 shows a partial longitudinal section of a burner ring according to the invention.
  • Figure 2 is a longitudinal sectional view of the ring passing through a fixing of the injection rail.
  • FIG. 3 is a partial end view of the reactor showing the burner ring and the fixing of the injection manifold.
  • Figure 4 is a sectional view along IV-IV of the burner ring according to Figure 1.
  • FIG. 1 is a view in partial and longitudinal section of the turbojet engine part located at the outlet of the secondary flow channel 1 and at the end of the primary flow channel 2. The burner ring 3 is fixed at the confluence of the two streams, just behind the conical wall 4 separating them and on which it is fixed.

L'anneau-brûleur 3 comporte une rampe d'injection 5, percée d'orifices 6 pour injecter du carburant, à contre-courant des veines d'air primaire et secondaire, un anneau stabilisateur de flamme 7 situé en amont de la rampe et entourant celle-ci. De manière connue, l'anneau stabilisateur présente une section approximativement en V, la pointe du V étant dirigé vers l'amont du courant.The burner ring 3 comprises an injection ramp 5, pierced with orifices 6 for injecting fuel, against the flow of the primary and secondary air streams, a flame stabilizing ring 7 located upstream of the ramp and surrounding it. In known manner, the stabilizing ring has a section approximately in V, the point of the V being directed upstream of the current.

Selon la réalisation conforme à l'invention, l'anneau stabilisateur est formé de deux parties indépendantes 8 et 9, chacune de ces parties constituant une aile du V. Les deux extrémités voisines des ailes laissent entre elles une fente annulaire continue 10 laissant le passage aux jets de carburant émis par la rampe 5.According to the embodiment according to the invention, the stabilizing ring is formed by two independent parts 8 and 9, each of these parts constituting a wing of the V. The two adjacent ends of the wings leave between them a continuous annular slot 10 allowing passage fuel jets emitted by the rail 5.

L'anneau brûleur 3 est maintenu sur la paroi conique de séparation des flux 4 par des moyens supports articulés 11.The burner ring 3 is held on the conical flow separation wall 4 by articulated support means 11.

Les ailes externe 8 et interne 9 sont suspendues à la paroi conique 4 par des leviers coudés 12, par l'intermédiaire des chapes soudées 13 et 14 respectivement sur les ailes 8 et 9, disposées dans des mêmes plans axiaux et réparties uniformément le long des ailes.The outer 8 and inner 9 wings are suspended from the conical wall 4 by bent levers 12, by means of welded yokes 13 and 14 respectively on the wings 8 and 9, arranged in the same axial planes and distributed uniformly along the wings.

Les leviers 12 présentent deux bras 15 et 16 d'inégales longueurs. Le bras le plus court 16 se termine par une double chape 16a qui coopère par l'intermédiaire d'une biellette 17 étant articulée aux doubles chapes 16a et 14 par deux axes 18 et 19 (voir aussi la figure 4).The levers 12 have two arms 15 and 16 of unequal length. The shortest arm 16 ends in a double yoke 16a which cooperates by means of a link 17 being articulated to the double yokes 16a and 14 by two axes 18 and 19 (see also Figure 4).

Le coude formé par les bras 15 et 16 comporte un alésage qui reçoit l'axe 20 maintenant de manière articulée la chape 13 soudée sur l'aile externe 8.The elbow formed by the arms 15 and 16 comprises a bore which receives the axis 20 now in an articulated manner the yoke 13 welded to the outer wing 8.

L'extrémité libre du bras le plus long 15 porte un alésage coopérant par l'intermédiaire d'un axe 21 avec une chape 22 fixée sur la surface externe de la paroi 4.The free end of the longest arm 15 carries a bore cooperating via a pin 21 with a yoke 22 fixed on the external surface of the wall 4.

Les mouvements relatifs des ailes 8 et 9 dus aux dilatations différentielles, n'ont d'autre effet que d'ouvrir ou fermer plus ou moins l'angle formé par les axes 18, 19 et 18, 20 sans mise en contrainte de l'anneau.The relative movements of the wings 8 and 9 due to differential expansions, have no other effect than to open or close more or less the angle formed by the axes 18, 19 and 18, 20 without stressing the ring.

Selon le détail de réalisation montré figures 2 et 3 du dispositif conforme à l'invention, la rampe d'injection 5 est fixée de place en place le long de l'aile par des pattes 23 et des rivets 24 à l'aile externe 8 de l'anneau.According to the embodiment shown in Figures 2 and 3 of the device according to the invention, the injection ramp 5 is fixed from place to place along the wing by lugs 23 and rivets 24 to the outer wing 8 of the ring.

L'aile externe 8, plongée dans le flux d'air secondaire à faible température, présente une dilatation thermique faible et ses caractéristiques dimensionnelles varient peu.The outer wing 8, immersed in the secondary air flow at low temperature, exhibits low thermal expansion and its dimensional characteristics vary little.

La rampe d'injection 5 qui lui est solidaire ne subira pas de déplacement sensible susceptible de modifier la direction des jets et permettra de maintenir une largeur raisonnable de la fente annulaire 10 malgré la dilatation relativement importante de l'aile interne 9.The injection ramp 5 which is integral with it will not undergo any significant displacement capable of modifying the direction of the jets and will make it possible to maintain a reasonable width of the annular slot 10 despite the relatively large expansion of the internal wing 9.

La fente continue 10 de l'anneau-brûleur selon l'invention permettra éventuellement l'utilisation d'un anneau enclume tel que décrit dans la demande de brevet français 2 186 608. La suppression des cloisons séparant les ouvertures entourant les jets telles que décrites dans le brevet cité empêche la déformation de cette zone relativement faible et améliore le passage du mélange de gaz et de carburant pulvérisé dans l'espace entourant la rampe 5 dans l'anneau stabilisateur 7 et protège la rampe contre la chaleur de la flamme.The continuous slot 10 of the burner ring according to the invention will optionally allow the use of an anvil ring as described in French patent application 2 186 608. The removal of the partitions separating the openings surrounding the jets as described in the cited patent prevents the deformation of this relatively small area and improves the passage of the mixture of gas and fuel sprayed into the space surrounding the ramp 5 in the stabilizing ring 7 and protects the ramp against the heat of the flame.

Claims (5)

1. Burner ring for post-combustion in a jet engine in particular for the re-heat of a turbo jet engine with twin flows, the said system being disposed at the rear of the separating wall of the two flows and comprising a flame stabilising ring of approximately V section containing a circular manifold for the injection of fuel discharging in countercurrent through openings provided at the point of the V, characterized in that the annular flame stabiliser (7) is in the form of two independent parts (8, 9) each of the parts constituting one limb of the V, and in that pivotal support means (11) are provided at the end of the separation wall of the flows (4) in order to support each of the parts of the annular stabiliser.
2. Burner ring according to claim 1, characterized in this that the pivotal support means (11) comprise a bell crank lever (12) secured in a pivotal manner by the end of one of its arms (15) to the separating wall of the flows (4), the other arm (16) supporting in a pivotal manner and through the intermediary of a rod (17), one of the limbs (9) of the annular stabiliser. the other limb (8) being secured in a pivotal manner to the elbow of the lever (12).
3. Burner ring according to claim 2, characterized in this that the limbs (8, 9) of the stabilising ring carry clevises (13, 14) disposed approximately in the same axial planes, distributed uniformly along the limbs, the said clevices (13, 14) cooperating respectively in a pivotal manner with the elbow of the lever (12) and with one end of the rod (17).
4. Burner ring according to one of the preceding claims characterized in that the limb (8) disposed on the outside with the respect to the other limb (9) carries securing means (23. 24) of the fuel injection manifold (5).
5. Ring burner according to claim 4, characterized in that the securing means are constituted by tabs (23) secured at intervals along the limb (8).
EP84401726A 1983-09-07 1984-08-29 Flame holder burner ring for a post combuster of a jet engine Expired EP0142389B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8314249 1983-09-07
FR8314249A FR2551500B1 (en) 1983-09-07 1983-09-07 BURNER RING FOR POSTCOMBUSTION OF A REACTION ENGINE

Publications (2)

Publication Number Publication Date
EP0142389A1 EP0142389A1 (en) 1985-05-22
EP0142389B1 true EP0142389B1 (en) 1986-10-01

Family

ID=9292032

Family Applications (1)

Application Number Title Priority Date Filing Date
EP84401726A Expired EP0142389B1 (en) 1983-09-07 1984-08-29 Flame holder burner ring for a post combuster of a jet engine

Country Status (6)

Country Link
US (1) US4592200A (en)
EP (1) EP0142389B1 (en)
JP (1) JPS60155827A (en)
DE (1) DE3460874D1 (en)
FR (1) FR2551500B1 (en)
IL (1) IL72744A (en)

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FR2869953B1 (en) * 2004-05-05 2008-07-04 Snecma Moteurs Sa DEVICE FOR SUPPLYING AIR AND FUEL FROM A RING-BURNER IN A POSTCOMBUSTION CHAMBER
JP5625585B2 (en) * 2010-07-27 2014-11-19 株式会社Ihi Afterburner and aircraft engine
GB201013723D0 (en) 2010-08-17 2010-09-29 Rolls Royce Plc Manifold mounting arrangement
CN104439634B (en) * 2014-11-07 2016-03-30 沈阳黎明航空发动机(集团)有限责任公司 A kind of prevent annular V groove stabilizer welding to be out of shape device and using method
FR3032519B1 (en) * 2015-02-10 2017-02-24 Herakles APPARATUS-FLAME DEVICE
CN113883549B (en) * 2021-12-08 2022-02-22 中国航发沈阳发动机研究所 Flame stabilizer considering radar stealth
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FR2404111A1 (en) * 1977-09-27 1979-04-20 Snecma FUEL DISTRIBUTION DEVICE

Also Published As

Publication number Publication date
FR2551500A1 (en) 1985-03-08
FR2551500B1 (en) 1985-11-08
JPS60155827A (en) 1985-08-15
US4592200A (en) 1986-06-03
EP0142389A1 (en) 1985-05-22
IL72744A0 (en) 1984-11-30
JPH0366570B2 (en) 1991-10-17
DE3460874D1 (en) 1986-11-06
IL72744A (en) 1992-03-29

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