EP0235031A1 - 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
EP0235031A1
EP0235031A1 EP87400347A EP87400347A EP0235031A1 EP 0235031 A1 EP0235031 A1 EP 0235031A1 EP 87400347 A EP87400347 A EP 87400347A EP 87400347 A EP87400347 A EP 87400347A EP 0235031 A1 EP0235031 A1 EP 0235031A1
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EP
European Patent Office
Prior art keywords
fins
flow
flame
section
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.)
Granted
Application number
EP87400347A
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German (de)
French (fr)
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EP0235031B1 (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
SNECMA SAS
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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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    • 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.
  • USA 3.931.707 describes a flame catching device 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 .
  • the invention aims to obtain a simplification of the structure used while seeking an improvement in heating performance.
  • the flame holder structure of the aforementioned type and in accordance with the invention is characterized in that the radially outer part of a V-section ring carries a grid of regularly distributed fins. In this way, a cylindrical slice of flow passing through the grid of fins is rotated.
  • 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 inner ejection cover which delimits the hot gas circulation stream whose flow 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 stream and a stream secondary external said "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 disposed at the level of the cold flow
  • a burner ring 9 also composed of a flame catching ring 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 catch 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 V-shaped section.
  • the partial view developed in 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 ensures 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)

Abstract

Un anneau d'accroche-flamme (10) à section en V comporte des ailettes (27) rapportées sur la face extérieure de branche (28) radialement externe de la section en V. Cette grille d'ailettes (27) provoque une mise en rotation d'une tranche cylindrique d'écoulement qui la traverse, ce qui a pour effet d'améliorer la stabilité en augmentant le volume de zone de recirculation aval sous l'influence d'un gradient radial de pression et d'augmenter la vitesse de propagation de flamme en créant une turbulence de cisaillement au niveau du mélange entre l'écoulement en rotation et l'écoulement non affecté.A V-section flame catch ring (10) has fins (27) attached to the outer face of the branch (28) radially external to the V section. This grid of fins (27) causes rotation of a cylindrical slice of flow which crosses it, which has the effect of improving stability by increasing the volume of downstream recirculation zone under the influence of a radial pressure gradient and of increasing the speed of flame spread by creating shear turbulence at the mixture between the rotating flow and the unaffected flow.

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 USA 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 USA 3.931.707 which describes a flame catching device 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 .

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 la partie radialement externe d'un anneau à section en V porte une grille d'ailettes régulièrement réparties. De cette manière, une tranche cylindrique d'écoulement traversant la grille d'ailettes est mise en rotation.The flame holder structure of the aforementioned type and in accordance with the invention is characterized in that the radially outer part of a V-section ring carries a grid of regularly distributed fins. In this way, a cylindrical slice of flow passing through the grid of fins is rotated.

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-flamme 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 flame holder 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 d'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 of an embodiment of the invention, with reference to the appended drawings in which:
  • - Figure 1 shows 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;
  • - Figure 3 shows a partial developed view of Figure 2 in direction F showing the arrangement of fin grid on flame holder.

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 inner ejection cover which delimits the hot gas circulation stream whose flow 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 stream and a stream secondary external said "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 disposed at the level of the cold flow, a burner ring 9 also composed of a flame catching ring 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 catch 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 V-shaped section. The partial view developed in 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 ensures 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. Structure d'accroche-flamme pour système de réchauffe de turboréacteur, du genre comportant un anneau (10) à section en V caractérisée en ce que la partie radialement externe (28) de l'anneau (10) porte une grille d'ailettes (27) régulièrement réparties de telle sorte qu'une tranche cylindrique d'écoulement traversant ladite grille est mise en rotation.1. Structure of flame holder for turbojet heater system, of the type comprising a ring (10) with a V section, characterized in that the radially external part (28) of the ring (10) carries a grid of fins (27) regularly distributed so that a cylindrical section of flow passing through said grid is rotated. 2. Structure d'accroche-flamme selon la revendication 1 caractérisée en ce que chaque ailette (27) en sus de la partie radialement externe (28) de l'anneau (10) correspondant à une branche de la section en V recouvre également la partie frontale (29) adjacente de l'anneau (10) correspondant à la base arrondie de la section en V.2. flame holder structure according to claim 1 characterized in that each fin (27) in addition to the radially outer part (28) of the ring (10) corresponding to a branch of the V-section also covers the frontal part (29) adjacent to the ring (10) corresponding to the rounded base of the V-shaped section. 3. Structure d'accroche-flamme selon l'une des revendications 1 et 2 caractérisée en ce que les bords radialement externes des ailettes (27) sont réunis par une enveloppe (30) circulaire extérieure continue.3. flame-holding structure according to one of claims 1 and 2 characterized in that the radially outer edges of the fins (27) are joined by a continuous outer circular envelope (30). 4. Structure d'accroche-flamme selon la revendication 3 caractérisée en ce que ladite enveloppe extérieure (30) déborde par un rebord (31), longitudinalement en amont du bord amont des ailettes (27), l'amont étant défini par rapport au sens normal de circulation des gaz vers l'éjection.4. flame holder structure according to claim 3 characterized in that said outer casing (30) projects by a flange (31), longitudinally upstream of the upstream edge of the fins (27), the upstream being defined relative to the normal direction of gas flow to 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
FR8602699 1986-02-27
FR8602699A FR2594939B1 (en) 1986-02-27 1986-02-27 FLAME-HANGING STRUCTURE FOR A TURBO-JET HEATER SYSTEM

Publications (2)

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

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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)

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WO1995002155A1 (en) * 1993-07-09 1995-01-19 Alliant Techsystems Inc. Apparatus and method for burning energetic material

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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
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

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US2935847A (en) * 1957-11-18 1960-05-10 United Aircraft Corp Flow control means for use with flameholders and flamespreaders
US3931707A (en) * 1975-01-08 1976-01-13 General Electric Company Augmentor flameholding apparatus
US4445339A (en) * 1980-11-24 1984-05-01 General Electric Co. Wingtip vortex flame stabilizer for gas turbine combustor flame holder

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US3154920A (en) * 1961-11-30 1964-11-03 Gen Electric Catalytic igniter
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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
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

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
US3931707A (en) * 1975-01-08 1976-01-13 General Electric Company Augmentor flameholding apparatus
US4445339A (en) * 1980-11-24 1984-05-01 General Electric Co. Wingtip vortex flame stabilizer for gas turbine combustor flame holder

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1995002155A1 (en) * 1993-07-09 1995-01-19 Alliant Techsystems Inc. Apparatus and method for burning energetic material
US5593301A (en) * 1993-07-09 1997-01-14 Alliant Techsystems, Inc. Apparatus and method for burning energetic material
US5649325A (en) * 1993-07-09 1997-07-15 Alliant Techsystems, Inc. Apparatus and method for burning energetic material

Also Published As

Publication number Publication date
FR2594939A1 (en) 1987-08-28
DE3760599D1 (en) 1989-10-26
EP0235031B1 (en) 1989-09-20
US4802337A (en) 1989-02-07
FR2594939B1 (en) 1989-11-03

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