EP0184962A1 - Retention housing for a turbo fan - Google Patents

Retention housing for a turbo fan Download PDF

Info

Publication number
EP0184962A1
EP0184962A1 EP85402398A EP85402398A EP0184962A1 EP 0184962 A1 EP0184962 A1 EP 0184962A1 EP 85402398 A EP85402398 A EP 85402398A EP 85402398 A EP85402398 A EP 85402398A EP 0184962 A1 EP0184962 A1 EP 0184962A1
Authority
EP
European Patent Office
Prior art keywords
housing
zone
wall
retention
casing
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
EP85402398A
Other languages
German (de)
French (fr)
Other versions
EP0184962B1 (en
Inventor
Alain Marie Joseph Lardellier
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
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, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0184962A1 publication Critical patent/EP0184962A1/en
Application granted granted Critical
Publication of EP0184962B1 publication Critical patent/EP0184962B1/en
Expired legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor

Definitions

  • the invention relates to a retention casing for a turbojet fan, said casing comprising, opposite the area swept by the rotor, a sealing ring and a retention structure capable of stopping the blade or the broken blade part and evacuate it.
  • the patent application European No. 0028183 proposes a solution consisting in placing between the casing and the sealing ring a retention structure made up of hollow toroids, concentric with the rotor, held by locking elements.
  • the casing then only has to provide a function of resistance to dynamic forces and damping of vibrations.
  • the invention aims to produce a retention casing having a succession of structures adapted to the different types of aggression to which they are liable to be subjected and of a fixing common to at least one retention structure and to the fittings of attachment of the accessories provided on the outside of the housing.
  • the retention case for a turbojet fan according to the invention is remarkable in this. that it consists of an assembly comprising at least one metallic outer casing and an internal lining of composite material, concentric, removable, hooped at least partially in the casing, said assembly having in the direction of flow of the air stream at least three zones of different retention characteristics, the first zone surrounding the rotor blading of the fan.
  • the single figure shows, in half section, the blower compartment of a turbojet engine.
  • the retention casing 1 has at its ends flanges 2 and 3 by which it is fixed respectively to the inlet casing and to the outlet casing (not shown) of the fan.
  • the retention casing surrounds the fan rotor 4 and retains the stationary vanes 5 of the air flow rectifier.
  • the retention casing is formed from an exterior assembly consisting of a casing / metal 6 and an internal lining 7, the wall of which, delimiting the flow channel of the air stream, is constituted at least in part by 'a composite material.
  • the lining, concentric with the casing 6, is hooped there at least partially, as will be described later.
  • the assembly has, in the direction of the flow of the air stream, (from left to right in the figure) at least three successive zones having different retention characteristics according to their position relative to the rotor blading of the blower.
  • the first zone A is located directly above the rotor vane and comprises radially from the inside to the outside a sealing ring 8 of abradable material, fixed in a housing provided in the wall of the lining 6, a annular portion of the wall of the metal casing, at least part 9 of the outer wall of which lies between two circular ribs 10, 11, carries a retention ring 12 formed by a winding of aromatic polyamide fibers embedded in a synthetic resin.
  • This part 9 is provided approximately on the front half of the first zone and is capable of slowing down and retaining the blade fragments liable to come off during the impact of material sucked in by the fan.
  • the second zone B extending behind the zone swept by the rotor, comprises from the inside towards the outside an approximately annular portion 13 formed by at least the wall of the lining 7, this wall possibly being able to be formed from two skins between which a retention structure is maintained; a retention belt 14, consisting of at least two tori 15, 16 held on the internal surface of the wall of the metal casing by supports 17; an annular portion 18 of the metal casing.
  • the third zone C extending the second zone B, of a length roughly equal to that of zone A, comprises from the inside to the outside the wall 19 of the lining 7, an empty annular space 20 and a portion 21 of the metal casing. This third zone is intended to retain in the empty space 20 the significant debris which lost their energy in the preceding zone B.
  • the parts of the wall extending upstream and downstream of these three zones will have a thickness substantially equal to that of the third zone C.
  • the wall of the metal casing has, in zone B, three circumferential rows of holes 25, 26, 27, provided for fixing the supports 17 of the toroids forming the retention belt and the fittings 29, 30 for fixing accessories and auxiliaries.
  • Another circumferential row of holes 31 is provided at the end of zone C to receive the fixings of the straightening vanes 5.
  • the inner surface of the metal casing 6 is provided, approximately perpendicular to the zone A of two cylindrical bearings 32, 33, the bore of the first bearing (in the direction fluid flow) being greater than that of the second bearing.
  • These bearing surfaces are intended to retain by hooping the removable lining 7 which is introduced through the front of the casing after the retention belt 14 has been fixed in the latter.
  • the retention belt is made up as previously described of two toroids 15 , 16 held from place to place by supports 17. These supports have an approximately trapezoidal section, the large curvilinear base of which has two notches, intended to house the toroids defining two oblique lateral tabs and a central tab capable of cooperating with means clamp 25A, 26A, 27A.
  • the side tabs are each provided with a threaded hole into which a bolt will be screwed passing through the holes of the rows 25 and 26 which will optionally maintain on the outer surface of the housing fixing fittings 29 and 30, serving as supports of accessories.
  • the central tab carries an axial passage for a bolt 27A whose end of the thread passes through a hole 27 in the central circumferential row of holes provided on the casing and in an opening provided in the central tab of the fittings.
  • the end of the thread receives a support piece which distributes the tightening forces of the nut on the central tab and involves a large portion of the metal casing.
  • the support 14 and in particular the bolt 26A passing through a hole in the row 26 ensures the fixing of a retaining fitting 34 to which is fixed by the means 38 the downstream part of the lining.
  • the toroids 15, 16 are, for example, formed from glass fiber, carbon or polyamide tubes wound, linked by a polymerizable resin.
  • the supports 17 are provided in titanium but can be made of a composite material.
  • the lining 7 carries at its upstream end a flange 35 whose periphery forms a bearing cooperating with a corresponding bearing 36 provided on the inner surface of the upstream end of the metal casing 6.
  • the lining is extended downstream by the honeycomb coating 37 of the wall of the metal casing used for acoustic damping.
  • the lining constitutes a removable, mountable and dismountable assembly from the upstream or inlet end of the fan casing, held in the upstream part by three cylindrical bearings 35, 32, 33 of decreasing diameter from upstream to downstream, and in the downstream part by fixing screws 38 on the holding fittings 34 held at one of their ends by the clamping means of the supports 17.
  • the lining is constituted according to one embodiment by a winding of organic or mineral fibers such as glass, carbon, "KEVLAR” or others, embedded in a synthetic resin.
  • the lining comprises an inner skin and an outer skin of metal or fibers fixed on a filling or retention structure formed of honeycombs or of a composite resin-mineral or organic filler material.
  • this wall construction of the lining is used in the zones which must provide a retention and / or acoustic damping function.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Carter de rétention formé d'un ensemble comportant un carter extérieur (6) métallique et une garniture interne (7) en matériau composite, concentrique, amovible, frettée au moins partiellement dans le carter.Retention housing formed of an assembly comprising an external metal housing (6) and an internal lining (7) of composite material, concentric, removable, hooped at least partially in the housing.

L'ensemble présente au moins dans le sens de l'écoulement de la veine d'air trois zones à caractéristiques de rétention différentes: une première zone (A) comportant l'anneau d'étanchéité (8) entourant l'aubage rotorique, une deuxième zone (B) dans laquelle la garniture recouvre une ceinture de rétention (12), une troisième zone (C) dans laquelle la garniture délimite avec la paroi du carter un espace vide (20).

Figure imgaf001
The assembly has at least in the direction of flow of the air stream three zones with different retention characteristics: a first zone (A) comprising the sealing ring (8) surrounding the rotor vane, a second zone (B) in which the lining covers a retention belt (12), a third zone (C) in which the lining defines with the wall of the housing an empty space (20).
Figure imgaf001

Description

L'invention concerne un carter de rétention pour soufflante de turboréacteur, ledit carter comportant face à la zone balayée par le rotor un anneau d'étanchéité et une structure de rétention susceptible d'arrêter l'aube ou la partie d'aube cassée et de l'évacuer.The invention relates to a retention casing for a turbojet fan, said casing comprising, opposite the area swept by the rotor, a sealing ring and a retention structure capable of stopping the blade or the broken blade part and evacuate it.

Il est connu d'utiliser comme structure de rétention un carter en acier relativement mince sur lequel sont bobiné(e)s ou appliqué(e)s des fibres ou des rubans de matériau synthétique tel que des fibres de polyamide aromatique connu sous le nom de marque commerciale "KEVLAR". Cette solution ne permet pas, dans les petits moteurs, de réaliser des gains substantiels sur la masse par rapport à un carter tout acier.It is known to use as a retention structure a relatively thin steel casing on which are wound (s) or applied (s) fibers or ribbons of synthetic material such as aromatic polyamide fibers known as trademark "KEVLAR". This solution does not allow, in small engines, to achieve substantial gains in mass compared to an all-steel casing.

Les essais de rupture d'aube ont mis en évidence trois zones de vulnérabilité différente du carter :

  • - une première zone (zone A), immédiatement à l'aplomb de la zone balayée par le rotor de soufflante, qui n'est atteinte que par des fragments de petite taille et dans laquelle ne se produit généralement pas de perforation ;
  • - une deuxième zone (zone B), en aval de la précédente par rapport à la direction du flux d'air, subissant les impacts les plus sévères, en particulier ceux des talons d'aubes par suite du basculement qui suit immédiatement la séparation du ou des fragments d'aube. Cette zone peut être le siège de déformations et perforations importantes ;
  • - une troisième zone (zone C) en aval de la deuxième zone, dont la vulnérabilité est comparable à celle de la première zone et dans laquelle se produisent des défor- formations ou des perforations limitées. Les fragments peuvent y être retenus efficacement avec des structures de fibres bobinées par effet de "filet".
The blade failure tests highlighted three zones of different vulnerability of the housing:
  • - a first zone (zone A), immediately above the zone swept by the fan rotor, which is only reached by small fragments and in which generally no perforation occurs;
  • - a second zone (zone B), downstream from the previous one with respect to the direction of the air flow, undergoing the most severe impacts, in particular those of the blade stubs following the tilting which immediately follows the separation of the or dawn fragments. This area can be the site of major deformations and perforations;
  • - a third zone (zone C) downstream of the second zone, the vulnerability of which is comparable to that of the first zone and in which deformation or limited perforation occurs. The fragments can be effectively retained there with fiber structures wound by the "net" effect.

Comme le carter ne peut pas lui-même assurer efficacement la fonction de rétention, la demande de brevet européen N° 0028183 propose une solution consistant à disposer entre le carter et l'anneau d'étanchéité une structure de rétention constituée de tores creux, concentriques au rotor, maintenus par des éléments de blocage. Le carter n'a plus alors qu'à assurer une fonction de résistance aux efforts dynamiques et d'amortissement des vibrations.As the housing cannot itself effectively perform the retention function, the patent application European No. 0028183 proposes a solution consisting in placing between the casing and the sealing ring a retention structure made up of hollow toroids, concentric with the rotor, held by locking elements. The casing then only has to provide a function of resistance to dynamic forces and damping of vibrations.

C'est en partant de cette remarque, et de la répartition des zones de vulnérabilité différente du carter entourant la soufflante que s'est développée l'idée inventive d'une disposition de structure de rétention permettant un gain de masse par l'utilisation d'un carter en alliage léger. En effet, un carter en alliage léger, tel que celui connu sous la dénomination AU2GN d'épaisseur équivalente à celle d'un carter classique en acier, permettrait des gains de masse importants de l'ordre de 30 à 40 kg. Mais bien que la capacité de résistance aux efforts dynamiques et d'amortissement des vibrations soit approximativement la même que pour l'acier, les alliages légers sont plus vulnérables à l'effet de tronçonnage. Il convient donc de maintenir le carter en alliage léger à distance du rotor et d'interposer,entre ce carter et le rotor, des structures propres à absorber l'énergie des fragments et à les retenir à l'intérieur du moteur.It is on the basis of this remark, and the distribution of the different zones of vulnerability of the casing surrounding the fan that the inventive idea of a retention structure arrangement allowing mass gain by the use of '' a light alloy casing. Indeed, a light alloy casing, such as that known under the name AU2GN of thickness equivalent to that of a conventional steel casing, would allow significant mass gains of the order of 30 to 40 kg. But although the capacity to withstand dynamic forces and dampen vibrations is approximately the same as for steel, light alloys are more vulnerable to the cutting effect. It is therefore advisable to keep the light alloy casing away from the rotor and to interpose, between this casing and the rotor, structures capable of absorbing the energy of the fragments and of retaining them inside the engine.

L'invention vise à la réalisation d'un carter de rétention présentant une succession de structures adaptées aux différents types d'agression auxquelles elles sont susceptibles d'être soumises et d'une fixation commune à au moins une structure de rétention et aux ferrures de fixation des accessoires prévus à l'extérieur du carter. Le carter de rétention pour soufflante de turboréacteur selon l'invention est remarquable en ce. qu'il est constitué d'un ensemble comportant au moins un carter extérieur métallique et une garniture interne en matériau composite, concentrique, amovible, frettée au moins partiellement dans le carter, ledit ensemble présentant dans le sens d'écoulement de la veine d'air au moins trois zones de caractéristiques de rétention différentes, la première zone entourant l'aubage rotorique de la soufflante.The invention aims to produce a retention casing having a succession of structures adapted to the different types of aggression to which they are liable to be subjected and of a fixing common to at least one retention structure and to the fittings of attachment of the accessories provided on the outside of the housing. The retention case for a turbojet fan according to the invention is remarkable in this. that it consists of an assembly comprising at least one metallic outer casing and an internal lining of composite material, concentric, removable, hooped at least partially in the casing, said assembly having in the direction of flow of the air stream at least three zones of different retention characteristics, the first zone surrounding the rotor blading of the fan.

Les explications et figures données ci-après à titre d'exemple permettront de comprendre comment l'invention peut être réalisée.The explanations and figures given below by way of example will make it possible to understand how the invention can be implemented.

La figure unique représente, en demi coupe, le compartiment soufflante d'un turboréacteur. Le carter de rétention 1 comporte à ses extrémités des brides 2 et 3 par lesquelles il est fixé respectivement au carter d'entrée et au carter de sortie (non représentés) de la soufflante.The single figure shows, in half section, the blower compartment of a turbojet engine. The retention casing 1 has at its ends flanges 2 and 3 by which it is fixed respectively to the inlet casing and to the outlet casing (not shown) of the fan.

Le carter de rétention entoure le rotor de soufflante 4 et retient les aubes fixes 5 du redresseur de la veine d'air.The retention casing surrounds the fan rotor 4 and retains the stationary vanes 5 of the air flow rectifier.

Le carter de rétention est formé d'un extérieur ensemble constitué d'un carter/métallique 6 et d'une garniture interne 7 dont la paroi, délimitant le canal d'écoulement de la veine d'air, est constituée au moins en partie d'un matériau composite. La garniture, concentrique au carter 6, y est frettée au moins partiellement, comme il sera décrit ultérieurement.The retention casing is formed from an exterior assembly consisting of a casing / metal 6 and an internal lining 7, the wall of which, delimiting the flow channel of the air stream, is constituted at least in part by 'a composite material. The lining, concentric with the casing 6, is hooped there at least partially, as will be described later.

Selon l'invention, l'ensemble présente, dans le sens de l'écoulement de la veine d'air,(de gauche à droite sur la figure) au moins trois zones successives présentant des caractéristiques de rétention différentes selon leur position par rapport à l'aubage rotorique de la soufflante.According to the invention, the assembly has, in the direction of the flow of the air stream, (from left to right in the figure) at least three successive zones having different retention characteristics according to their position relative to the rotor blading of the blower.

La première zone A est située à l'aplomb de l'aubage rotorique et comporte radialement de l'intérieur vers l'extérieur un anneau d'étanchéité 8 en matériau abradable, fixé dans un logement prévu dans la paroi de la garniture 6, une portion annulaire de la paroi du carter métallique dont au moins une partie 9 de la paroi extérieure, comprise entre deux nervures circulaires 10, 11, porte un anneau de rétention 12 formé par un bobinage de fibres de polyamide aromatique noyé dans une résine synthétique. Cette partie 9 est prévue approximativement sur la moitié avant de la première zone et est susceptible de ralentir et retenir les fragments d'aube susceptibles de se détacher lors d'impact de matériau aspiré par la soufflante.The first zone A is located directly above the rotor vane and comprises radially from the inside to the outside a sealing ring 8 of abradable material, fixed in a housing provided in the wall of the lining 6, a annular portion of the wall of the metal casing, at least part 9 of the outer wall of which lies between two circular ribs 10, 11, carries a retention ring 12 formed by a winding of aromatic polyamide fibers embedded in a synthetic resin. This part 9 is provided approximately on the front half of the first zone and is capable of slowing down and retaining the blade fragments liable to come off during the impact of material sucked in by the fan.

La deuxième zone B, s'étendant en arrière de la zone balayée par le rotor, comporte de l'intérieur vers l'extérieur une portion approximativement annulaire 13 formée par au moins la paroi de la garniture 7, cette paroi pouvant éventuellement être formée de deux peaux entre lesquelles est maintenue une structure de rétention; une ceinture de rétention 14, constituée d'au moins deux tores 15, 16 maintenus sur la surface interne de la paroi du carter métallique par des supports 17; une portion annulaire 18 du carter métallique.The second zone B, extending behind the zone swept by the rotor, comprises from the inside towards the outside an approximately annular portion 13 formed by at least the wall of the lining 7, this wall possibly being able to be formed from two skins between which a retention structure is maintained; a retention belt 14, consisting of at least two tori 15, 16 held on the internal surface of the wall of the metal casing by supports 17; an annular portion 18 of the metal casing.

La troisième zone C, prolongeant la deuxième zone B, d'une longueur à peu près égale à celle de la zone A, comporte de l'intérieur vers l'extérieur la paroi19 de la garniture 7, un espace annulaire vide 20 et une portion 21 du carter métallique. Cette troisième zone est destinée à retenir dans l'espace vide 20 les débris importants qui ont perdus leur énergie dans la zone B précédente.The third zone C, extending the second zone B, of a length roughly equal to that of zone A, comprises from the inside to the outside the wall 19 of the lining 7, an empty annular space 20 and a portion 21 of the metal casing. This third zone is intended to retain in the empty space 20 the significant debris which lost their energy in the preceding zone B.

La paroi du carter métallique correspondant aux.zones A et B devant présenter une rigidité suffisante aux vibrations et aux efforts dynamiques, elle aura de préférence une épaisseur approximativement double de celle correspondant à la zone C. Les parties de paroi s'étendant en amont et en aval de ces trois zones auront une épaisseur sensiblement égale à celle de la troisième zone C.The wall of the metal casing corresponding to the zones A and B having to have sufficient rigidity for vibrations and dynamic forces, it will preferably have a thickness approximately twice that corresponding to the zone C. The parts of the wall extending upstream and downstream of these three zones will have a thickness substantially equal to that of the third zone C.

Outre les nervures 10 et 11 déjà décrites entre lesquelles se trouve l'anneau de rétention 12, d'autres.nervures circulaires 22, 23, 24 prévues sur la surface extérieure du carter métallique concourent à donner au carter une plus grande inertie.In addition to the ribs 10 and 11 already described between which is the retaining ring 12, other circular ribs 22, 23, 24 provided on the outer surface of the metal casing contribute to giving the casing greater inertia.

La paroi du carter métallique présente dans la zone B trois rangées 25, 26, 27 circonférentielles de trous, prévues pour la fixation des supports 17 des tores formant la ceinture de rétention et des ferrures 29, 30 de fixation des accessoires et auxilliaires.The wall of the metal casing has, in zone B, three circumferential rows of holes 25, 26, 27, provided for fixing the supports 17 of the toroids forming the retention belt and the fittings 29, 30 for fixing accessories and auxiliaries.

Une autre rangée 31 circonférentielle de trous est prévue à l'extrémité de la zone C pour recevoir les fixations des aubes redresseuses 5.Another circumferential row of holes 31 is provided at the end of zone C to receive the fixings of the straightening vanes 5.

Selon l'exemple de réalisation représenté sur la figure unique, la surface intérieure du carter métallique 6 est munie, approximativement à l'aplomb de la zone A de deux portées cylindriques 32, 33, l'alésage de la première portée (dans le sens d'écoulement du fluide) étant supérieur à celui de la deuxième portée. Ces portées sont destinées à retenir par frettage la garniture amovible 7 qui est introduite par l'avant du carter après que l'on ait fixé dans ce dernier la ceinture de rétention 14. La ceinture de rétention est constituée comme précédemment décrit de deux tores 15, 16 maintenus de place en place par des supports 17. Ces supports présentent une section approximativement trapézoïdale dont la grande base, curviligne, porte deux échancrures, destinées à loger les tores définissant deux pattes latérales obliques et une patte centrale susceptibles de coopérer avec des moyens de serrage 25A, 26A, 27A. Pour ce faire les pattes latérales sont munies chacune d'un trou taraudé dans lequel viendra se visser un boulon passant par les trous des rangees 25 et 26 qui maintiendra éventuellement sur la surface extérieure du carter des ferrures de fixation 29 et 30, servant de supports d'accessoires. La patte centrale porte un passage axial pour un boulon 27A dont l'extrémité du filetage passe dans un trou 27 de la rangée circonférentielle centrale des trous prévus sur le carter et dans une ouverture prévue dans la patte centrale des ferrures. L'extrémité du filetage reçoit une pièce d'appui qui répartit les-efforts de serrage de l'écrou sur la patte centrale et fait participer une large portion du carter métallique.According to the embodiment shown in the single figure, the inner surface of the metal casing 6 is provided, approximately perpendicular to the zone A of two cylindrical bearings 32, 33, the bore of the first bearing (in the direction fluid flow) being greater than that of the second bearing. These bearing surfaces are intended to retain by hooping the removable lining 7 which is introduced through the front of the casing after the retention belt 14 has been fixed in the latter. The retention belt is made up as previously described of two toroids 15 , 16 held from place to place by supports 17. These supports have an approximately trapezoidal section, the large curvilinear base of which has two notches, intended to house the toroids defining two oblique lateral tabs and a central tab capable of cooperating with means clamp 25A, 26A, 27A. To do this, the side tabs are each provided with a threaded hole into which a bolt will be screwed passing through the holes of the rows 25 and 26 which will optionally maintain on the outer surface of the housing fixing fittings 29 and 30, serving as supports of accessories. The central tab carries an axial passage for a bolt 27A whose end of the thread passes through a hole 27 in the central circumferential row of holes provided on the casing and in an opening provided in the central tab of the fittings. The end of the thread receives a support piece which distributes the tightening forces of the nut on the central tab and involves a large portion of the metal casing.

Le support 14 et en particulier le boulon 26A passant par un trou de la rangée 26 assure la fixation d'une ferrure de maintien 34 à laquelle est fixée par le moyen 38 la partie aval de la garniture.The support 14 and in particular the bolt 26A passing through a hole in the row 26 ensures the fixing of a retaining fitting 34 to which is fixed by the means 38 the downstream part of the lining.

Les tores 15, 16 sont, par exemple, formés de tubes de fibres de verre, de carbone ou de polyamide bobinées, liées par une résine polymérisable. Les supports 17 sont prévus en titane mais peuvent être en un matériau composite.The toroids 15, 16 are, for example, formed from glass fiber, carbon or polyamide tubes wound, linked by a polymerizable resin. The supports 17 are provided in titanium but can be made of a composite material.

La garniture, selon l'exemple, présente dans le sens de l'écoulement de la veine d'air :

  • - une partie,proche de l'entrée, portant des perforations et faisant office d'amortisseur acoustique;
  • -une partie correspondant à la zone A dans laquelle est prévue un logement recevant un anneau en matériau abradable. Cet anneau est par exemple constitué d'un nid d'abeilles fixé dans une virole en résine synthétique renforcée de fibres de verre;
  • -une partie correspondant à la zone B en prolongement aérodynamique de l'anneau abradable dont la paroi extérieure s'appuie sur la ceinture de rétention ou au moins sur les supports 14;
  • -une partie correspondant à la zone C, prolongeant aérodynamiquement la partie B, s'appuyant sur la ferrure de maintien 34 et présentant des perforations ayant une fonction d'amortisseur acoustique et de "filet" pour retenir les fragments d'aube dont l'énergie a été amortie dans la zone B.
The packing, according to the example, has in the direction of flow of the air stream:
  • - a part, close to the entrance, carrying perforations and acting as an acoustic damper;
  • a part corresponding to zone A in which is provided a housing receiving a ring of abradable material. This ring is for example made up of a honeycomb fixed in a ferrule made of synthetic resin reinforced with glass fibers;
  • a part corresponding to zone B in aerodynamic extension of the abradable ring whose outer wall is supported on the retention belt or at least on the supports 14;
  • a part corresponding to zone C, aerodynamically extending part B, resting on the retaining fitting 34 and having perforations having the function of an acoustic damper and of "net" to retain the fragments of dawn whose energy was damped in zone B.

La garniture 7 porte à son extrémité amont une collerette 35 dont la périphérie forme une portée coopérant avec une portée correspondante 36 prévue sur la surface intérieure de l'extrémité amont-du carter métallique 6.The lining 7 carries at its upstream end a flange 35 whose periphery forms a bearing cooperating with a corresponding bearing 36 provided on the inner surface of the upstream end of the metal casing 6.

La garniture est prolongée en aval par le revêtement en nid d'abeilles 37 de la paroi du carter métallique servant à l'amortissement acoustique.The lining is extended downstream by the honeycomb coating 37 of the wall of the metal casing used for acoustic damping.

La garniture constitue un ensemble amovible,montable et démontable à partir de l'extrémité amont ou d'entrée du carter de soufflante, maintenue dans la partie amont par trois portées cylindriques 35, 32, 33 de diamètre décroissant d'amont en aval, et dans la partie aval par des vis de fixation 38 sur les ferrures de maintien 34 maintenues à l'une de leurs extrémités par les moyens de serrage des supports 17.The lining constitutes a removable, mountable and dismountable assembly from the upstream or inlet end of the fan casing, held in the upstream part by three cylindrical bearings 35, 32, 33 of decreasing diameter from upstream to downstream, and in the downstream part by fixing screws 38 on the holding fittings 34 held at one of their ends by the clamping means of the supports 17.

La garniture est constituée selon une forme de réalisation par un bobinage de fibres organiques ou minérales telles que du verre, du carbone, du"KEVLAR" ou autres, noyées dans une résine synthétique.The lining is constituted according to one embodiment by a winding of organic or mineral fibers such as glass, carbon, "KEVLAR" or others, embedded in a synthetic resin.

Selon d'autres formes de réalisation, la garniture comporte une peau intérieure et une peau extérieure métallique ou en fibres fixées sur une structure de remplissage ou de rétention formée de nids d'abeilles ou d'un matériau composite résine-charge minérale ou organique.According to other embodiments, the lining comprises an inner skin and an outer skin of metal or fibers fixed on a filling or retention structure formed of honeycombs or of a composite resin-mineral or organic filler material.

De préférence, cette constitution de paroi de la garniture est utilisée dans les zones devant assurer une fonction de rétention et/ou d'amortissement acoustique.Preferably, this wall construction of the lining is used in the zones which must provide a retention and / or acoustic damping function.

Claims (10)

1. Carter de rétention pour soufflante de turboréacteur, ledit carter comportant, face à la zone balayée par le rotor, un anneau d'étanchéité et une structure de rétention susceptible d'arrêter l'aube ou la partie d'aube cassée et de l'évacuer, caractérisé en ce qu'il est constitué d'un ensemble comportant au moins un carter extérieur (6) métallique et une garniture interne (7) en matériau composite, concentrique, amovible, frettée au moins partiellement dans le carter, ledit ensemble présentant dans le sens d'écoulement de la veine d'air au moins trois zones (A, B, C) de caractéristiques de rétention différentes, la première zone (A) entourant l'aubage rotorique de la soufflante.1. Retention housing for a turbojet fan, said housing comprising, facing the area swept by the rotor, a sealing ring and a retention structure capable of stopping the blade or the portion of the blade that is broken and the '' discharge, characterized in that it consists of an assembly comprising at least one outer casing (6) of metal and an internal lining (7) of composite material, concentric, removable, hooped at least partially in the casing, said assembly having in the direction of flow of the air stream at least three zones (A, B, C) with different retention characteristics, the first zone (A) surrounding the rotor blading of the fan. 2. Carter selon la revendication 1, caractérisé en ce que : - la première zone (A) est formée, en allant de l'intérieur vers l'extérieur, de l'anneau d'étanchéité (8) fixé dans un logement prévu dans la paroi de la garniture (7), de la paroi de la garniture dans laquelle est fixé l'anneau d'étanchéité, d'une partie de la paroi du carter métallique (6), d'un anneau de rétention (1.2) en fibres à haute résistance bobiné sur au moins une partie de la surface extérieure du carter métallique; - la deuxième zone (B) est formée, en allant de l'intérieur vers l'extérieur, d'une partie (13) de la paroi de la garniture interne (7), d'une ceinture de rétention (14), d'une partie (18) de la paroi du carter métallique (6); - la troisième zone (C) est formée, de l'intérieur vers l'extérieur, d'une partie (19) de la paroi de la garniture (7), d'un espace annulaire vide(20) et d'une portion (21) du carter métallique (6). 2. Housing according to claim 1, characterized in that: - The first zone (A) is formed, going from the inside to the outside, of the sealing ring (8) fixed in a housing provided in the wall of the lining (7), of the wall of the lining in which the sealing ring is fixed, of a part of the wall of the metal casing (6), of a retention ring (1.2) made of high-strength fibers wound on at least part of the surface outside of the metal casing; - the second zone (B) is formed, going from the inside towards the outside, of a part (13) of the wall of the internal lining (7), of a retention belt (14), d 'a part (18) of the wall of the metal casing (6); - the third zone (C) is formed, from the inside towards the outside, of a part (19) of the wall of the lining (7), of an empty annular space (20) and of a portion (21) of the metal casing (6). 3. Carter selon la revendication 2, caractérisé en ce que la ceinture de rétention (14) est constituée d'au moins deux tores (15, 16) fixés sur la surface interne de la paroi du carter métallique (6) par des supports (17).3. Housing according to claim 2, characterized in that the retention belt (14) is consisting of at least two toroids (15, 16) fixed on the internal surface of the wall of the metal casing (6) by supports (17). 4. Carter selon la revendication 3, caractérisé en ce que les supports (17) ont une section approximativement trapézoïdale, dont la grande base, curviligne, porte deux échancrures, destinées à loger les tores, définissant deux pattes obliques et une patte centrale.4. Housing according to claim 3, characterized in that the supports (17) have an approximately trapezoidal section, the large base, curvilinear, carries two notches, intended to accommodate the toroids, defining two oblique legs and a central leg. 5. Carter selon la revendication 4, caractérisé en ce que les pattes des supports sont munies de trous susceptibles de coopérer avec des moyens de serrage (25A, 26A, 27A) traversant la paroi du carter métallique (6) et maintenant éventuellement des ferrures de fixation (29, 30) des accessoires et auxilliaires disposés à l'extérieur du carter.5. Housing according to claim 4, characterized in that the legs of the supports are provided with holes capable of cooperating with clamping means (25A, 26A, 27A) passing through the wall of the metal casing (6) and possibly holding fittings of fixing (29, 30) of the accessories and auxiliaries arranged outside the casing. 6. Carter selon l'une des revendications précédentes, caractérisé en ce que la garniture interne (7) est maintenue dans le carter en amont par trois portées cylindriques (32, 33, 35) de diamètre décroissant d'amont en aval et en aval par des moyens de fixation (38) sur des ferrures de maintien (34), elles-mêmes maintenues à l'une de leurs extrémités par un des moyens de serrage (26A) des supports (17).6. Housing according to one of the preceding claims, characterized in that the internal lining (7) is held in the housing upstream by three cylindrical bearings (32, 33, 35) of decreasing diameter from upstream to downstream and downstream by fixing means (38) on retaining fittings (34), themselves held at one of their ends by one of the clamping means (26A) of the supports (17). 7. Carter selon l'une des revendications précédentes, caractérisé en ce que la garniture interne (7) est formée d'un bobinage de fibres organiques ou minérales noyées dans une résine synthétique.7. Housing according to one of the preceding claims, characterized in that the internal lining (7) is formed by a winding of organic or mineral fibers embedded in a synthetic resin. 8. Carter selon l'une des revendications précédentes, caractérisé en ce que le carter métallique (6) porte sur sa surface extérieure des nervures circulaires (10, 11, 22, 23, 24).8. Housing according to one of the preceding claims, characterized in that the metal housing (6) carries on its outer surface circular ribs (10, 11, 22, 23, 24). 9. Carter selon la revendication 2, caraoté- risé en ce que l'anneau de rétention (12) est maintenu entre deux nervures circulaires (10, 11) prévues sur la surface extérieure du carter métallique (6).9. Housing according to claim 2, characterized in that the retention ring (12) is held between two circular ribs (10, 11) provided on the outer surface of the metal housing (6). 10. Carter selon l'une des revendications précédentes, caractérisé en ce que la partie de paroi du carter métallique (6) correspondant aux première et deuxième zones (A, B) a une épaisseur supérieure à celle des autres parties du carter.10. Housing according to one of the preceding claims, characterized in that the wall part of the metal housing (6) corresponding to the first and second zones (A, B) has a thickness greater than that of the other parts of the housing.
EP85402398A 1984-12-06 1985-12-04 Retention housing for a turbo fan Expired EP0184962B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8418593A FR2574476B1 (en) 1984-12-06 1984-12-06 RETENTION HOUSING FOR TURBOJET BLOWER
FR8418593 1984-12-06

Publications (2)

Publication Number Publication Date
EP0184962A1 true EP0184962A1 (en) 1986-06-18
EP0184962B1 EP0184962B1 (en) 1988-08-03

Family

ID=9310290

Family Applications (1)

Application Number Title Priority Date Filing Date
EP85402398A Expired EP0184962B1 (en) 1984-12-06 1985-12-04 Retention housing for a turbo fan

Country Status (5)

Country Link
US (1) US4648795A (en)
EP (1) EP0184962B1 (en)
JP (1) JPS61138864A (en)
DE (1) DE3564148D1 (en)
FR (1) FR2574476B1 (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1995030076A1 (en) * 1994-04-29 1995-11-09 United Technologies Corporation Fan blade containment assembly
WO1995030073A1 (en) * 1994-04-29 1995-11-09 United Technologies Corporation Aircraft fan containment structure
WO2000046489A1 (en) * 1999-02-04 2000-08-10 Pratt & Whitney Canada Corp. Hardwall fan case with structured bumper
US6497550B2 (en) 2000-04-05 2002-12-24 Rolls-Royce Plc Gas turbine engine blade containment assembly
FR2925118A1 (en) * 2007-12-14 2009-06-19 Snecma Sa ABRADABLE SUPPORT PANEL IN A TURBOMACHINE
US7918215B2 (en) 2006-05-08 2011-04-05 Honeywell International Inc. Compressor stage assembly lock
FR3054526A1 (en) * 2016-07-26 2018-02-02 Safran Aircraft Engines AIRCRAFT COMPRISING AN INTEGRATED REAR-FUSELAGE TURBOREACTOR COMPRISING A FITTING FOR EJECTING OF BLADES

Families Citing this family (36)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4955192A (en) * 1988-12-12 1990-09-11 Sundstrand Corporation Containment ring for radial inflow turbine
US5188505A (en) * 1991-10-07 1993-02-23 General Electric Company Structural ring mechanism for containment housing of turbofan
GB2262313B (en) * 1991-12-14 1994-09-21 Rolls Royce Plc Aerofoil blade containment
US5259724A (en) * 1992-05-01 1993-11-09 General Electric Company Inlet fan blade fragment containment shield
US5267828A (en) * 1992-11-13 1993-12-07 General Electric Company Removable fan shroud panel
US5486086A (en) * 1994-01-04 1996-01-23 General Electric Company Blade containment system
US5485723A (en) * 1994-04-29 1996-01-23 United Technologies Corporation Variable thickness isogrid case
US5409349A (en) * 1994-04-29 1995-04-25 United Technologies Corporation Turbofan containment structure
US6206631B1 (en) * 1999-09-07 2001-03-27 General Electric Company Turbomachine fan casing with dual-wall blade containment structure
GB9922619D0 (en) * 1999-09-25 1999-11-24 Rolls Royce Plc A gas turbine engine blade containment assembly
US6290455B1 (en) * 1999-12-03 2001-09-18 General Electric Company Contoured hardwall containment
GB0107970D0 (en) * 2001-03-30 2001-05-23 Rolls Royce Plc A gas turbine engine blade containment assembly
GB0117550D0 (en) * 2001-07-19 2001-09-12 Rolls Royce Plc Joint arrangement
GB0403941D0 (en) * 2004-02-21 2004-03-24 Rolls Royce Plc A gas turbine engine blade containment assembly
US8191254B2 (en) 2004-09-23 2012-06-05 Carlton Forge Works Method and apparatus for improving fan case containment and heat resistance in a gas turbine jet engine
AU2005335919A1 (en) * 2005-09-20 2007-04-05 Carlton Forge Works Fan case reinforcement in a gas turbine jet engine
FR2913053B1 (en) * 2007-02-23 2009-05-22 Snecma Sa PROCESS FOR MANUFACTURING A GAS TURBINE CASE OF COMPOSITE MATERIAL AND CARTER THUS OBTAINED
GB2459646B (en) * 2008-04-28 2011-03-30 Rolls Royce Plc A fan assembly
GB0813821D0 (en) * 2008-07-29 2008-09-03 Rolls Royce Plc A fan casing for a gas turbine engine
FR2935017B1 (en) * 2008-08-13 2012-11-02 Snecma INTERNAL WALL OF A TURBOMACHINE NACELLE
GB2471466A (en) * 2009-06-30 2011-01-05 Rolls Royce Plc Fan casing for a turbofan gas turbine engine
GB2471465A (en) * 2009-06-30 2011-01-05 Rolls Royce Plc Fan casing for a turbofan gas turbine engine
FR2964145B1 (en) * 2010-08-26 2018-06-15 Safran Helicopter Engines TURBINE HOOD SHIELDING METHOD AND HITCH ASSEMBLY FOR ITS IMPLEMENTATION
GB201020143D0 (en) 2010-11-29 2011-01-12 Rolls Royce Plc A gas turbine engine blade containment arrangement
GB201103682D0 (en) * 2011-03-04 2011-04-20 Rolls Royce Plc A turbomachine casing assembly
WO2014151097A1 (en) * 2013-03-15 2014-09-25 United Technologies Corporation Reinforced composite case
GB201417416D0 (en) * 2014-10-02 2014-11-19 Rolls Royce Plc Fan track liner assembly
EP3173587B1 (en) * 2015-11-30 2021-03-31 MTU Aero Engines GmbH Housing for a fluid flow engine, securing device and fluid flow engine
DE102016105957A1 (en) * 2016-04-01 2017-10-05 Rolls-Royce Deutschland Ltd & Co Kg Fan housing and engine assembly with fan housing
US10260522B2 (en) * 2016-05-19 2019-04-16 Rolls-Royce Corporation Liner system
FR3060052B1 (en) * 2016-12-14 2020-10-09 Safran Helicopter Engines PROCESS FOR MANUFACTURING AN ARMOR CARTRIDGE FOR A TURBOMACHINE ELEMENT AND CORRESPONDING SHIELDING CARTRIDGE AND TURBOMACHINE ELEMENT
US10550718B2 (en) 2017-03-31 2020-02-04 The Boeing Company Gas turbine engine fan blade containment systems
US10487684B2 (en) 2017-03-31 2019-11-26 The Boeing Company Gas turbine engine fan blade containment systems
GB201816990D0 (en) * 2018-10-18 2018-12-05 Rolls Royce Plc Debris retention
GB201816989D0 (en) * 2018-10-18 2018-12-05 Rolls Royce Plc Debris retention
US11008887B2 (en) 2018-12-21 2021-05-18 Rolls-Royce Corporation Fan containment assembly having a nesting cavity

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH460450A (en) * 1964-01-15 1968-07-31 United Aircraft Corp Gas turbine
EP0028183A1 (en) * 1979-10-23 1981-05-06 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Containment device for the compressor housing of a turbomachine
EP0030179A1 (en) * 1979-11-27 1981-06-10 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Retaining structure for the compressor housing of a turbo engine
GB2112349A (en) * 1981-12-21 1983-07-20 United Technologies Corp Containment structure
GB2114233A (en) * 1982-02-01 1983-08-17 United Technologies Corp Containment shell for a fan section of a gas turbine engine

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1485032A (en) * 1974-08-23 1977-09-08 Rolls Royce Gas turbine engine casing
FR2452601A1 (en) * 1979-03-30 1980-10-24 Snecma REMOVABLE SEALING COVER FOR TURBOJET BLOWER HOUSING
JPS57126572A (en) * 1981-01-30 1982-08-06 Toshiba Corp Operation controlling method for water wheel and pump water wheel
US4452563A (en) * 1981-12-21 1984-06-05 United Technologies Corporation Containment structure

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH460450A (en) * 1964-01-15 1968-07-31 United Aircraft Corp Gas turbine
EP0028183A1 (en) * 1979-10-23 1981-05-06 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Containment device for the compressor housing of a turbomachine
EP0030179A1 (en) * 1979-11-27 1981-06-10 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Retaining structure for the compressor housing of a turbo engine
GB2112349A (en) * 1981-12-21 1983-07-20 United Technologies Corp Containment structure
GB2114233A (en) * 1982-02-01 1983-08-17 United Technologies Corp Containment shell for a fan section of a gas turbine engine

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1995030076A1 (en) * 1994-04-29 1995-11-09 United Technologies Corporation Fan blade containment assembly
WO1995030073A1 (en) * 1994-04-29 1995-11-09 United Technologies Corporation Aircraft fan containment structure
WO2000046489A1 (en) * 1999-02-04 2000-08-10 Pratt & Whitney Canada Corp. Hardwall fan case with structured bumper
US6497550B2 (en) 2000-04-05 2002-12-24 Rolls-Royce Plc Gas turbine engine blade containment assembly
US7918215B2 (en) 2006-05-08 2011-04-05 Honeywell International Inc. Compressor stage assembly lock
FR2925118A1 (en) * 2007-12-14 2009-06-19 Snecma Sa ABRADABLE SUPPORT PANEL IN A TURBOMACHINE
EP2088290A1 (en) * 2007-12-14 2009-08-12 Snecma Supporting abradable casing liner in a turbomachine
US8061967B2 (en) 2007-12-14 2011-11-22 Snecma Panel for supporting abradable material in a turbomachine
CN101457771B (en) * 2007-12-14 2012-10-10 斯奈克玛 Abradable support panel in a turbine engine
RU2477805C2 (en) * 2007-12-14 2013-03-20 Снекма Base panel for worn-out coating in gas turbine engine
FR3054526A1 (en) * 2016-07-26 2018-02-02 Safran Aircraft Engines AIRCRAFT COMPRISING AN INTEGRATED REAR-FUSELAGE TURBOREACTOR COMPRISING A FITTING FOR EJECTING OF BLADES
US10746044B2 (en) 2016-07-26 2020-08-18 Safran Aircraft Engines Aircraft comprising a turbojet engine integrated into the rear fuselage comprising a fairing allowing the ejection of blades

Also Published As

Publication number Publication date
JPH0363669B2 (en) 1991-10-02
JPS61138864A (en) 1986-06-26
EP0184962B1 (en) 1988-08-03
FR2574476B1 (en) 1987-01-02
FR2574476A1 (en) 1986-06-13
US4648795A (en) 1987-03-10
DE3564148D1 (en) 1988-09-08

Similar Documents

Publication Publication Date Title
EP0184962B1 (en) Retention housing for a turbo fan
FR3026134B1 (en) DEVICE FOR FIXING AN AIR INLET ON A BLOWER HOUSING OF AN AIRCRAFT TURBOJET AIRCRAFT
CA2746249C (en) Fan for a turbine engine including a balancing system with blind holes for housing bodies, and related turbine engine
CA2206154C (en) Process and bearing mount allowing a turbine engine for aircraft to be maintained in operation after the occurrence of accidental imbalance in a rotor
FR2565629A1 (en) IMPROVED BLOWER DUCT ENCLOSURE
EP0017546A1 (en) Exchangeable support for the tipsealing layer in a turbofan housing
EP1357279A2 (en) Noise reducing attachment for a turbofan engine
WO2009144300A1 (en) Assembly including a turbine disc for a gas turbine engine and a bearing-supporting journal, and cooling circuit for the turbine disc of such an assembly
CA2594259A1 (en) Cooling system for a centrifugal compressor impeller
EP1881179A2 (en) System for ventilating the wall of a combustion chamber in a turbomachine
FR2636375A1 (en) REINFORCEMENT RING FOR LOW PRESSURE STAGE OF A COMPRESSOR
EP2811121A1 (en) Composite casing for axial turbomachine compressor with metal flange
WO2008006961A1 (en) Turbine engine for aircraft
WO2015110751A1 (en) Rotor disk having a centripetal air collection device, compressor comprising said disc and turbomachine with such a compressor
FR2491545A1 (en) BANDAGE FOR THE RADIAL CLAMPING OF SEGMENTS OF A SEGMENTED TURBINE FIN WHEEL
EP2096357A1 (en) Flame holder for reheat duct of a jet engine with separating flange, reheat duct and jet engine comprising a reheat duct
EP2795068A1 (en) Turbomachine compressor guide vanes assembly
CA2478788A1 (en) Abradable device on fan case for gas turbine engine
FR2470269A1 (en) RETENTION STRUCTURE FOR A COMPRESSOR CASE OF A TURBOMACHINE
FR2932227A1 (en) Double body turbofan engine, has high pressure compressor provided with external case, and internal inner fan duct cowl fixed on downstream end of external case, where air flow is circulated between external cowl and internal cowl
FR3038654A1 (en) ASSEMBLY OF A REPORTED PLATFORM OF BLOWER BLADE ON A BLOWER DISK
FR2536460A1 (en) IMPROVED COMPACT DIFFUSER, PARTICULARLY SUITABLE FOR HIGH-GAS GAS TURBINES
FR3005693A1 (en) DOUBLE-FLOW AIRCRAFT TURBOMACHINE COMPRISING AN INTER-VEIN VIOLINE WITH SIMPLIFIED HOLD
FR2672943A1 (en) Turbomachine compressor equipped with a device for drawing off air
FR2997470A1 (en) Holding device for holding brush seal of lubrication enclosure of turbojet engine, has cylindrical part formed by cylindrical face and thread that is engaged with another thread to ensure axial translation of lock with respect to cover

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 19851227

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): DE FR GB

17Q First examination report despatched

Effective date: 19870626

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)
REF Corresponds to:

Ref document number: 3564148

Country of ref document: DE

Date of ref document: 19880908

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed
PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 19921120

Year of fee payment: 8

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 19921123

Year of fee payment: 8

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 19930226

Year of fee payment: 8

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Effective date: 19931204

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 19931204

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Effective date: 19940831

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Effective date: 19940901

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST