EP0235031B1 - Flame holder for the reheating system of a turbo jet - Google Patents

Flame holder for the reheating system of a turbo jet Download PDF

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Publication number
EP0235031B1
EP0235031B1 EP87400347A EP87400347A EP0235031B1 EP 0235031 B1 EP0235031 B1 EP 0235031B1 EP 87400347 A EP87400347 A EP 87400347A EP 87400347 A EP87400347 A EP 87400347A EP 0235031 B1 EP0235031 B1 EP 0235031B1
Authority
EP
European Patent Office
Prior art keywords
flame
ring
fins
flow
section
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
EP87400347A
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German (de)
French (fr)
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EP0235031A1 (en
Inventor
Jacques Emile Jules Caruel
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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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 EP0235031A1 publication Critical patent/EP0235031A1/en
Application granted granted Critical
Publication of EP0235031B1 publication Critical patent/EP0235031B1/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

Definitions

  • the present invention relates to a flame holder structure for a turbojet heater system.
  • US-A-3,931,707 which describes a flame holder for a heating system in which an annular passage is formed upstream of a V-section ring between two rings placed inside. a turbojet channel in the flow of gases which have passed through the turbine. The air-fuel mixture is produced inside the annular enclosure thus formed inside which is arranged a row of swirling vanes in order to improve the air-fuel mixture and to favor vaporization before ignition .
  • US-A-4,445,339 also describes a flame catcher comprising a V-section ring, the two radially outer and inner faces of which each carry a grid of fins, providing rotation of the flows both on the radially outer side and on the radially internal side.
  • the invention aims to obtain a simplification of the structure used while seeking an improvement in heating performance.
  • the flame catching structure of the aforementioned kind and according to the invention is characterized in that only the radially external part of the ring carries said grid. In this way, a cylindrical slice of flow passing through the grid of fins is rotated, in a limited area, providing remarkable results.
  • This recirculation phenomenon also induces shear turbulence at the level of the mixing border between the flow in gyration and the main flow outside the flame catching device which is not subjected to this rotation. .
  • This improvement in performance can be taken into account in the dimensioning of the turbojet channel which can, under these conditions, be shorter, which brings about an interesting reduction in mass and size which are important parameters in aeronautical applications. concerned.
  • each fin in addition to the radially external part of the ring corresponding to a branch of the V-section also covers the adjacent front part of the ring corresponding to the rounded base of the V-shaped section.
  • the invention does not envisage extending each fin over the part of the flame catching device situated towards the axis of the motor, corresponding to the branch of the radially internal V-section.
  • This construction method would in particular have the drawback of creating a radially internal rotation flow which would lead to recirculation downstream of the flame catching device by the influence of a centrifugal speed component.
  • the radially outer edges of the fins can be joined by a continuous outer circular envelope which can be extended longitudinally by an upstream flange.
  • FIG. 1 shows a rear part of a turbojet engine in longitudinal section along the axis of rotation. 1 designates an internal ejection hood which delimits the flow stream for hot gases, the flow of which at the outlet of the turbine (not shown in the drawing) is symbolized by the arrow 2.
  • This stream is delimited externally by a wall 3 which performs the separation between this hot flow and an external secondary flow called “cold flow which circulates in the secondary annular channel, between said wall 3 and an external wall 4 which extends downstream.
  • a complete heating system 5 is schematically represented in FIG.
  • a radially external burner ring 6 composed of a flame catching ring 7 and an injection ramp 8 and arranged at the level of the cold flow
  • a burner ring 9 also composed of a catching ring flame 10 and an injection ramp 11 and disposed outside the hot flow, at the confluence between cold flow and hot flow
  • a burner ring 12 composed of a flame catch ring 13 and an injection ramp 14 and located at the level of the hot flow
  • a flame-catching ring 15 radially internal, inside the hot flow.
  • FIG. 2 represents an enlarged view of the flame holder 10 produced in accordance with the invention.
  • Fins 27 are attached to the outer face, on the radially outer branch 28 of the V-shaped section of the flame holder 10. Each fin covers this outer branch 28 and also the front part 29 forming the rounded base of the section in V.
  • the partial developed view of FIG. 3 shows that fins 27 are regularly distributed over the periphery of the flame holder and these fins 27 receive a profile and an orientation which ensure the rotation of the cylindrical section of flow which crosses the grid of fins.
  • the outer edge of the fins 27 is joined by a continuous outer casing 30 which is extended upstream of the fins by a flange 31.
  • This arrangement promotes the separation of the flow between a wafer according to the arrow 32 rotated and an external flow according to the arrow 33 which is not and the resulting shearing effect at the level of the mixture.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Combustion Of Fluid Fuel (AREA)

Description

La présente invention concerne une structure d'accroche-flamme pour système de réchauffe de turboréacteur.The present invention relates to a flame holder structure for a turbojet heater system.

Il est généralement bien connu de prévoir dans un turboréacteur un système de réchauffe placé dans un canal situé en aval du moteur proprement dit, par rapport au sens normal de circulation des gaz. Ce système est ainsi placé dans le flux qui a traversé la turbine et dans le cas fréquent d'application à un moteur à double flux, le système se développe à la fois dans le flux chaud et dans le flux froid radialement extérieur, à la hauteur et légèrement en aval de la confluence de ces deux flux. Ce système procure ainsi une augmentation de poussée en introduisant une carburation complémentaire.It is generally well known to provide in a turbojet engine a heating system placed in a channel located downstream of the engine proper, relative to the normal direction of gas flow. This system is thus placed in the flow which has passed through the turbine and in the frequent case of application to a double-flow motor, the system develops both in the hot flow and in the radially external cold flow, at the height and slightly downstream of the confluence of these two flows. This system thus provides an increase in thrust by introducing additional carburetion.

Diverses réalisations ont été essayées en vue d'assurer l'efficacité de ce genre de systèmes. Un exemple est fourni par US-A-3.931.707 qui décrit un dispositif d'accroche-flamme pour système de réchauffe dans lequel un passage annulaire est ménagé en amont d'un anneau à section en V entre deux anneaux placés à l'intérieur d'un canal de turboréacteur dans le flux des gaz qui ont traversé la turbine. Le mélange air-carburant est réalisé à l'intérieur de l'enceinte annulaire ainsi ménagée à l'intérieur de laquelle est disposée une rangée d'aubes de tourbillonnement en vue d'améliorer le mélange air-carburant et de favoriser la vaporisation avant inflammation.Various embodiments have been tried in order to ensure the effectiveness of this kind of systems. An example is provided by US-A-3,931,707 which describes a flame holder for a heating system in which an annular passage is formed upstream of a V-section ring between two rings placed inside. a turbojet channel in the flow of gases which have passed through the turbine. The air-fuel mixture is produced inside the annular enclosure thus formed inside which is arranged a row of swirling vanes in order to improve the air-fuel mixture and to favor vaporization before ignition .

US-A-4 445 339 décrit également un accroche-flamme comportant un anneau à section en V dont les deux faces radialement externe et interne portent chacune une grille d'ailettes, procurant une mise en rotation des écoulements à la fois du côté radialement externe et du côté radialement interne.US-A-4,445,339 also describes a flame catcher comprising a V-section ring, the two radially outer and inner faces of which each carry a grid of fins, providing rotation of the flows both on the radially outer side and on the radially internal side.

L'invention vise à obtenir une simplification de la structure utilisée tout en recherchant une amélioration des performances de réchauffe.The invention aims to obtain a simplification of the structure used while seeking an improvement in heating performance.

La structure d'accroche-flamme du genre précité et conforme à l'invention est caractérisée en ce que seulement la partie radialement externe de l'anneau porte ladite grille. De cette manière, une tranche cylindrique d'écoulement traversant la grille d'ailettes est mise en rotation, dans une zone limitée, procurant des résultats remarquables.The flame catching structure of the aforementioned kind and according to the invention is characterized in that only the radially external part of the ring carries said grid. In this way, a cylindrical slice of flow passing through the grid of fins is rotated, in a limited area, providing remarkable results.

La giration ainsi provoquée dans cette tranche d'écoulement crée un gradient radial de pression qui augmente la zone de recirculation située en aval du dispositif d'accroche-flamme proprement dit. L'augmentation de ce volume de recirculation est un facteur qui améliore directement le domaine de stabilité du système de réchauffe.The gyration thus caused in this flow slice creates a radial pressure gradient which increases the recirculation zone located downstream of the flame catching device proper. The increase in this recirculation volume is a factor which directly improves the stability range of the heating system.

Ce phénomène de recirculation induit également une turbulence de cisaillement au niveau de la frontière de mélange entre l'écoulement en giration et l'écoulement principal à l'extérieur du dispositif d'accroche-flamme qui n'est pas soumis à cette mise en rotation. Il en résulte une caractéristique de vitesse de propagation de flamme augmentée, ce qui amène une amélioration du rendement et surtout une valeur donnée de rendement est obtenue à une distance plus courte en aval du dispositif d'accroche-flamme. Cette amélioration des performances peut être prise en compte dans le dimensionnement du canal de turboréacteur qui peut, dans ces conditions, être plus court, ce qui amène une réduction intéressant de la masse et de l'encombrement qui sont des paramètres importants dans les applications aéronautiques concernées.This recirculation phenomenon also induces shear turbulence at the level of the mixing border between the flow in gyration and the main flow outside the flame catching device which is not subjected to this rotation. . This results in a characteristic of increased flame propagation speed, which leads to an improvement in efficiency and above all a given value of efficiency is obtained at a shorter distance downstream from the flame catching device. This improvement in performance can be taken into account in the dimensioning of the turbojet channel which can, under these conditions, be shorter, which brings about an interesting reduction in mass and size which are important parameters in aeronautical applications. concerned.

Avantageusement, dans la structure d'accroche-fiamme selon l'invention, chaque ailette en sus de la partie radialement externe de l'anneau correspondant à une branche de la section en V recouvre également la partie frontale adjacente de l'anneau correspondant à la base arrondie de la section en V.Advantageously, in the fiamme attachment structure according to the invention, each fin in addition to the radially external part of the ring corresponding to a branch of the V-section also covers the adjacent front part of the ring corresponding to the rounded base of the V-shaped section.

Par contre, l'invention ne prévoit pas d'étendre chaque ailette sur la partie du dispositif d'accroche-flamme située vers l'axe du moteur, correspondant à la branche de la section en V radialement interne. Ce mode de construction aurait en particulier l'inconvénient de créer un écoulement en rotation radialement interne qui gènerait la recirculation en aval du dispositif accroche-flamme par l'influence d'une composante de vitesse centrifuge.On the other hand, the invention does not envisage extending each fin over the part of the flame catching device situated towards the axis of the motor, corresponding to the branch of the radially internal V-section. This construction method would in particular have the drawback of creating a radially internal rotation flow which would lead to recirculation downstream of the flame catching device by the influence of a centrifugal speed component.

Avantageusement aussi, les bords radialement externes des ailettes peuvent être réunis par une enveloppe circulaire extérieure continue qui peut se prolonger longitudinalement par un rebord amont.Advantageously also, the radially outer edges of the fins can be joined by a continuous outer circular envelope which can be extended longitudinally by an upstream flange.

D'autres caractéristiques et avantages de l'invention seront mieux compris à l'aide de la description qui va suivre un mode de réalisation de l'invention, en référence aux dessins annexés dans lesquels :

  • la figure 1 représente une vue partielle schématique en coupe longitudinale d'une partie arrière de turboréacteur montrant un exemple de réalisation d'un système de réchauffe ;
  • la figure 2 représente une vue de détail agrandie de la figure 1 montrant une structure d'accroche-flamme conforme à l'invention ;
  • la figure 3 représente une vue partielle développée de la figure 2 selon la direction F montrant la disposition de grille d'ailettes sur accroche-flamme.
Other characteristics and advantages of the invention will be better understood with the aid of the description which follows an embodiment of the invention, with reference to the appended drawings in which:
  • FIG. 1 represents a schematic partial view in longitudinal section of a rear part of a turbojet engine showing an exemplary embodiment of a heating system;
  • Figure 2 shows an enlarged detail view of Figure 1 showing a flame holder structure according to the invention;
  • 3 shows a partial developed view of Figure 2 in the direction F showing the arrangement of fin grid on flame catch.

On a représenté sur la figure 1 une partie arrière de turboréacteur en coupe longitudinale selon l'axe de rotation. 1 désigne un capot intérieur d'éjection qui délimite la veine de circulation des gaz chauds dont le flux à la sortie de la turbine (non représentée au dessin) est symbolisé par la flèche 2. Cette veine est délimitée extérieurement par une paroi 3 qui effectue la séparation entre ce flux chaud et un flux secondaire externe dit « flux froid qui circule dans le canal annulaire secondaire, entre ladite paroi 3 et une paroi externe 4 qui se prolonge vers l'aval. Un système complet de réchauffe 5 est schématiquement représenté à la figure 1 et comporte un anneau brûleur 6 radialement externe composé d'un anneau accroche-flamme 7 et d'une rampe d'injection 8 et disposé au niveau du flux froid, un anneau brûleur 9 également composé d'un anneau accroche-flamme 10 et d'une rampe d'injection 11 et disposé à l'extérieur du flux chaud, au niveau de la confluence entre flux froid et flux chaud, un anneau brûleur 12 composé d'un anneau accroche-flamme 13 et d'une rampe d'injection 14 et situé au niveau du flux chaud, un anneau accroche-flamme 15 radialement interne, à l'intérieur du flux chaud. Ces différents anneaux sont montés sur la paroi fixe 3 de séparation entre les deux flux au moyen de différentes biellettes de liaison 16, 17, 18, 19 comportant à leurs extrémités des articulations 20, 21, 22, 23, 24, 25. Un dispositif 26 d'amenée de carburant disposé en amont complète le système. Un ou plusieurs des accroche-flammes du système peuvent être réalisés conformément à l'invention, mais l'application la plus avantageuse est faite au niveau de l'accroche-flamme 10 à l'extérieur du flux chaud.FIG. 1 shows a rear part of a turbojet engine in longitudinal section along the axis of rotation. 1 designates an internal ejection hood which delimits the flow stream for hot gases, the flow of which at the outlet of the turbine (not shown in the drawing) is symbolized by the arrow 2. This stream is delimited externally by a wall 3 which performs the separation between this hot flow and an external secondary flow called “cold flow which circulates in the secondary annular channel, between said wall 3 and an external wall 4 which extends downstream. A complete heating system 5 is schematically represented in FIG. 1 and comprises a radially external burner ring 6 composed of a flame catching ring 7 and an injection ramp 8 and arranged at the level of the cold flow, a burner ring 9 also composed of a catching ring flame 10 and an injection ramp 11 and disposed outside the hot flow, at the confluence between cold flow and hot flow, a burner ring 12 composed of a flame catch ring 13 and an injection ramp 14 and located at the level of the hot flow, a flame-catching ring 15 radially internal, inside the hot flow. These different rings are mounted on the fixed wall 3 of separation between the two flows by means of different connecting rods 16, 17, 18, 19 comprising at their ends joints 20, 21, 22, 23, 24, 25. A device 26 upstream fuel supply completes the system. One or more of the flame catchers of the system can be produced in accordance with the invention, but the most advantageous application is made at the flame catcher 10 outside the hot stream.

La figure 2 représente une vue agrandie de l'accroche-flamme 10 réalisé conformément à l'invention. Des ailettes 27 sont rapportées sur la face extérieure, sur la branche radialement externe 28 de la section en V de l'accroche-flamme 10. Chaque ailette recouvre cette branche externe 28 et également la partie frontale 29 formant la base arrondie de la section en V. La vue partielle développée de la figure 3 montre que des ailettes 27 sont régulièrement réparties sur la périphérie de l'accroche-flamme et ces ailettes 27 reçoivent un profil et une orientation qui assurent la mise en rotation de la tranche cylindrique d'écoulement qui traverse la grille d'ailettes.FIG. 2 represents an enlarged view of the flame holder 10 produced in accordance with the invention. Fins 27 are attached to the outer face, on the radially outer branch 28 of the V-shaped section of the flame holder 10. Each fin covers this outer branch 28 and also the front part 29 forming the rounded base of the section in V. The partial developed view of FIG. 3 shows that fins 27 are regularly distributed over the periphery of the flame holder and these fins 27 receive a profile and an orientation which ensure the rotation of the cylindrical section of flow which crosses the grid of fins.

Le bord externe des ailettes 27 est réuni par une enveloppe extérieure 30 continue qui se prolonge en amont des ailettes par un rebord 31. Cette disposition favorise la séparation du flux entre une tranche selon la flèche 32 mise en rotation et un flux extérieur selon la flèche 33 qui ne l'est pas et l'effet de cisaillement qui en résulte au niveau du mélange.The outer edge of the fins 27 is joined by a continuous outer casing 30 which is extended upstream of the fins by a flange 31. This arrangement promotes the separation of the flow between a wafer according to the arrow 32 rotated and an external flow according to the arrow 33 which is not and the resulting shearing effect at the level of the mixture.

Claims (4)

1. Flame-baffle structure for a reheating system of a turbo-jet engine, of the type comprising a ring (10) of V-shaped cross-section and a grating of fins (27) uniformly distributed in such a way that a cylindrical flow segment passing through the said grating is set in rotation, characterized in that only the radially outer part (28) of the ring (10) carries the said grating.
2. Flame-baffle structure according to Claim 1, characterized in that each fin (27) covers not only the radially outer part (28) of the ring (10) corresponding to one branch of the V-shaped cross-section, but also the adjacent front part (29) of the ring (10) corresponding to the rounded base of the V-shaped cross-section.
3. Flame-baffle structure according to one of Claims 1 and 2, characterized in that the radially outer edges of the fins (27) are connected by means of a continuous outer circular casing (30).
4. Flame-baffle structure according to Claim 3, characterized in that the said outer casing (30) projects by means of a rim (31) longitudinally upstream of the upstream edge of the fins (27), upstream being defined in relation to the normal direction of circulation of the gases towards ejection.
EP87400347A 1986-02-27 1987-02-18 Flame holder for the reheating system of a turbo jet Expired EP0235031B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8602699A FR2594939B1 (en) 1986-02-27 1986-02-27 FLAME-HANGING STRUCTURE FOR A TURBO-JET HEATER SYSTEM
FR8602699 1986-02-27

Publications (2)

Publication Number Publication Date
EP0235031A1 EP0235031A1 (en) 1987-09-02
EP0235031B1 true EP0235031B1 (en) 1989-09-20

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP87400347A Expired EP0235031B1 (en) 1986-02-27 1987-02-18 Flame holder for the reheating system of a turbo jet

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US (1) US4802337A (en)
EP (1) EP0235031B1 (en)
DE (1) DE3760599D1 (en)
FR (1) FR2594939B1 (en)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5095696A (en) * 1990-01-02 1992-03-17 General Electric Company Asymmetric flameholder for gas turbine engine afterburner
US5142858A (en) * 1990-11-21 1992-09-01 General Electric Company Compact flameholder type combustor which is staged to reduce emissions
US5179832A (en) * 1991-07-26 1993-01-19 United Technologies Corporation Augmenter flame holder construction
US5593301A (en) * 1993-07-09 1997-01-14 Alliant Techsystems, Inc. Apparatus and method for burning energetic material
US5768886A (en) * 1995-09-29 1998-06-23 National Science Council Twin-plate flameholder construction
US7954328B2 (en) * 2008-01-14 2011-06-07 United Technologies Corporation Flame holder for minimizing combustor screech
RU2682220C1 (en) * 2018-03-01 2019-03-15 Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") Bypass turbofan engine afterburner combustion chamber
CN115930261A (en) * 2022-12-02 2023-04-07 南昌航空大学 Flame stabilizer with ribs for wave tail edge support plate

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GB706698A (en) * 1951-01-10 1954-04-07 Rolls Royce Improvements relating to combustion equipment of gas turbine engines
US2935847A (en) * 1957-11-18 1960-05-10 United Aircraft Corp Flow control means for use with flameholders and flamespreaders
US3056261A (en) * 1959-09-01 1962-10-02 Gen Electric Flameholder configuration
US3154920A (en) * 1961-11-30 1964-11-03 Gen Electric Catalytic igniter
US3176465A (en) * 1962-08-27 1965-04-06 Gen Electric Vapor fuel injector flameholder
US3153324A (en) * 1963-05-29 1964-10-20 Robert E Meyer Simplified primary fuel system
US3931707A (en) * 1975-01-08 1976-01-13 General Electric Company Augmentor flameholding apparatus
US4064691A (en) * 1975-11-04 1977-12-27 General Electric Company Cooling of fastener means for a removable flameholder
FR2429326A1 (en) * 1978-06-22 1980-01-18 Snecma IMPROVEMENTS IN FLAME-HANGING DEVICES FOR COMBUSTION CHAMBERS, IN PARTICULAR FOR TURBO-JET POST-COMBUSTION CHANNELS
US4445339A (en) * 1980-11-24 1984-05-01 General Electric Co. Wingtip vortex flame stabilizer for gas turbine combustor flame holder
US4418531A (en) * 1981-11-05 1983-12-06 The United States Of America As Represented By The Secretary Of The Air Force Flameholder stabilization plate for an aircraft engine afterburner system
US4490973A (en) * 1983-04-12 1985-01-01 The United States Of America As Represented By The Secretary Of The Air Force Flameholder with integrated air mixer

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Publication number Publication date
FR2594939A1 (en) 1987-08-28
EP0235031A1 (en) 1987-09-02
FR2594939B1 (en) 1989-11-03
DE3760599D1 (en) 1989-10-26
US4802337A (en) 1989-02-07

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