[go: up one dir, main page]

EP0718471A1 - Containment ring for a turbomachine - Google Patents

Containment ring for a turbomachine Download PDF

Info

Publication number
EP0718471A1
EP0718471A1 EP95402879A EP95402879A EP0718471A1 EP 0718471 A1 EP0718471 A1 EP 0718471A1 EP 95402879 A EP95402879 A EP 95402879A EP 95402879 A EP95402879 A EP 95402879A EP 0718471 A1 EP0718471 A1 EP 0718471A1
Authority
EP
European Patent Office
Prior art keywords
shield
stator
turbomachine
attachment means
rupture
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
EP95402879A
Other languages
German (de)
French (fr)
Other versions
EP0718471B1 (en
Inventor
Pierre A. Glowacki
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 Nacelles SAS
Original Assignee
Hispano Suiza SA
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 Hispano Suiza SA filed Critical Hispano Suiza SA
Publication of EP0718471A1 publication Critical patent/EP0718471A1/en
Application granted granted Critical
Publication of EP0718471B1 publication Critical patent/EP0718471B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime 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 subject of the invention is a protective shield for a turbomachine.
  • stator More precisely in front of a bladed area of a rotor which the stator surrounds, that is to say in front of a compressor or turbine section in the machine, and its function is to stop the pieces or debris of blades or rotor which would be projected towards it under the action of centrifugal forces after a rupture due to an accident.
  • US Patent 4,452,563 describes a shield formed by a continuous network of fibrous bands draped over the external face, opposite the rotor, of the stator. This design seems relatively ineffective because the fibers should tear quite easily and therefore would not give sufficient protection. We could also lay layers of honeycomb material on this external face of the stator, but, despite the increased energy absorption that such a structure would offer to slow or stop projectiles, this absorption would be localized to the place of the shock and the shield would be pierced here also quite easily.
  • European patent 0 626 502 describes a shield formed from juxtaposed plates which have the same drawbacks.
  • French Patent 2,375,443 describes a continuous ring shield which breaks its attachments when a detached blade strikes it; but the shield serves as a lining for the stator or replaces it, and it can only absorb the kinetic energy of the blade by taking a rotary movement; he doesn't have the possibility of absorbing energy by deforming, as in the invention, since it has no surrounding space to deform; Finally, it is only effective if the energy communicated is sufficient to break all of its attachments, which limits its possibilities of use.
  • the invention is based on the idea that it is advantageous to involve the whole shield in absorbing the shock by allowing it to deform and break its attachments to the stator in proportion to the energy received, and it is original in that the ring is continuous, connected to the turbomachine by attachment means calculated to rupture below a rupture limit of the shield subjected to an impact and extends in an annular space comprised between the stator and an external fairing of the turbomachine being radially separated from the stator as from the external fairing.
  • FIG. 1 represents a portion of a turbomachine which comprises a rotor 1, a stator 2 in the form of an envelope surrounding the rotor 1 and an external fairing 3 surrounding the stator 2; the stator 2 has a circular and planar flaring 4 which terminates it upstream, and which itself ends with a flange 5 fitted on the internal face of the outer fairing 3 and riveted to it.
  • the rotor 1 and the stator 2 carry alternating stages of respectively movable 6 and stationary vanes 7, as is usual for constituting turbines and compressors.
  • the shield 9 occupies it and extends in its middle: this means that it is radially separated from the external fairing 3 as from stator 2, without necessarily being equidistant from them.
  • the shield 9 is a continuous ring of ductile, metallic or other material, the advantage of which is to absorb large impact energies. It is maintained by attachment means which unite it to the flare 4. Many designs are possible, and two will be illustrated.
  • the shield 9 has one end bent into a flat and circular flange 10 in the bores of which screws 11 of longitudinal orientation have been engaged, the ends of which are retained in threads 12 drilled in the flare 4.
  • the screws 11 comprise a thinned part 13 of well-defined diameter, constituting an initiation of rupture, at the limit junction between the flare 4 and the flange 10.
  • the flange 10 is replaced by lugs 14, in the extension of the shield 9, but substantially thinner than it, in the embodiment of FIG. 3.
  • the flaring 4 is provided with a flange 15 circular and continuous, extending the shield 9 and almost contiguous to it, on which the legs 14 rest. Screws 16, this time oriented in the radial direction, unite the tabs 14 with the flange 15.
  • a breaking point is also provided, in the form of notches 19 which narrow the tabs 14 at the limit of the shield 9 and the flange 15 .
  • FIG. 4 illustrates what can happen after an impact due to a piece of rotor 17 accidentally detached in operation, such as a fragment of a turbine disc.
  • the centrifugal force projects it at high speed towards the outside: it bursts the stator 2 then embosses the shield 9.
  • the plastic deformation which results in the appearance of the bump 18 on the part of the shield 9 which it reaches causes if the kinetic energy of the piece of rotor 17 allows it, a partial or total destruction of the attachment means.
  • the thinned portion 13 of the screws 12 is sheared; in that of FIG. 3, the tabs 14 are broken, between the notches 19, here again by shearing.
  • the broken fastening elements are first of all those which are close to the bump 18. If the shock is sufficiently violent, all the fastening elements can be touched and the shield 9 then becomes free, but as care has been taken to design it with a sufficiently high resistance to piercing, it does not open in shock and continues to protect the outer fairing 3 from direct contact with the piece of rotor 17, even if it strikes it or rolls over it. This resistance essentially depends on the thickness of the shield 9 and on the breaking strength of the material which forms it.
  • the behavior and advantages of the invention can be fairly easily grasped.
  • the shield 9 does not rest directly on any surface, it can absorb energy by freely deforming over a large part of its circumference, or even all of it.
  • the stator 2 and the outer fairing 3 are sufficiently spaced to allow this deformation.
  • the total energy that the system can capture is also increased by the rupture energy of the attachment means, at the same time as this rupture allows a more extensive deformation of the shield 9 and therefore increases its energy absorption capacity.
  • FIG. 4 represents a particularly unfavorable situation, since a single large piece torn from the rotor 1 intervenes in the accident.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Abstract

The shield (9) to protect a turbine housing from broken blades, consists of a ring of a ductile material around the turbine stator (2), attached to the engine by fixings which are calculated to shear below the force needed to break the shield. This allows the shield to deform with the annular space between the stator and outer housing (3), containing the broken blade(s) within the housing. The fixings can be in the form of shearing bolts, pins or lugs connecting the shield to the engine, or a zone of reduced strength with initial perforations.

Description

L'invention a pour sujet un bouclier de protection d'une turbomachine.The subject of the invention is a protective shield for a turbomachine.

Il s'agit d'une enveloppe disposée autour d'un stator, plus précisément devant une zone aubagée d'un rotor qu'entoure le stator, c'est-à-dire devant une section de compresseur ou de turbine dans la machine, et sa fonction est d'arrêter les morceaux ou les débris d'aubes ou de rotor qui seraient projetés vers lui sous l'action des forces centrifuges après une rupture due à un accident.It is an envelope arranged around a stator, more precisely in front of a bladed area of a rotor which the stator surrounds, that is to say in front of a compressor or turbine section in the machine, and its function is to stop the pieces or debris of blades or rotor which would be projected towards it under the action of centrifugal forces after a rupture due to an accident.

Le brevet américain 4 452 563 décrit un bouclier formé d'un réseau continu de bandes fibreuses drapées sur la face externe, opposée au rotor, du stator. Cette conception paraît relativement peu efficace car les fibres devraient se déchirer assez aisément et ne donneraient donc pas une protection suffisante. On pourrait aussi poser des couches de matière en nid d'abeilles sur cette face externe du stator, mais, malgré l'accroissement d'absorption d'énergie qu'une telle structure offrirait pour ralentir ou arrêter les projectiles, cette absorption serait localisée à l'endroit du choc et le bouclier serait transpercé ici aussi assez facilement. Le brevet européen 0 626 502 décrit un bouclier formé de plaquettes juxtaposées qui présentent les mêmes inconvénients.US Patent 4,452,563 describes a shield formed by a continuous network of fibrous bands draped over the external face, opposite the rotor, of the stator. This design seems relatively ineffective because the fibers should tear quite easily and therefore would not give sufficient protection. We could also lay layers of honeycomb material on this external face of the stator, but, despite the increased energy absorption that such a structure would offer to slow or stop projectiles, this absorption would be localized to the place of the shock and the shield would be pierced here also quite easily. European patent 0 626 502 describes a shield formed from juxtaposed plates which have the same drawbacks.

Enfin, le brevet français 2 375 443 décrit un bouclier en anneau continu qui rompt ses attaches quand une pale détachée le heurte ; mais le bouclier sert de doublure au stator ou le remplace, et il ne peut absorber l'énergie cinétique de la pale qu'en prenant un mouvement rotatif ; il n'a pas la possibilité d'absorber de l'énergie en se déformant, comme dans l'invention, car il ne dispose pas d'espace environnant pour se déformer ; il n'est enfin efficace que si l'énergie communiquée est suffisante pour rompre toutes ses attaches, ce qui limite ses possibilités d'emploi.Finally, French Patent 2,375,443 describes a continuous ring shield which breaks its attachments when a detached blade strikes it; but the shield serves as a lining for the stator or replaces it, and it can only absorb the kinetic energy of the blade by taking a rotary movement; he doesn't have the possibility of absorbing energy by deforming, as in the invention, since it has no surrounding space to deform; Finally, it is only effective if the energy communicated is sufficient to break all of its attachments, which limits its possibilities of use.

L'invention repose sur l'idée qu'il est avantageux de faire participer tout le bouclier à l'absorption du choc en lui permettant de se déformer et de rompre ses attaches au stator en proportion de l'énergie reçue, et elle est originale en ce que l'anneau est continu, relié à la turbomachine par des moyens d'attache calculés pour se rompre en deçà d'une limite de rupture du bouclier soumis à un choc et s'étend dans un espace annulaire compris entre le stator et un carénage extérieur de la turbomachine en étant séparé radialement du stator comme du carénage extérieur.The invention is based on the idea that it is advantageous to involve the whole shield in absorbing the shock by allowing it to deform and break its attachments to the stator in proportion to the energy received, and it is original in that the ring is continuous, connected to the turbomachine by attachment means calculated to rupture below a rupture limit of the shield subjected to an impact and extends in an annular space comprised between the stator and an external fairing of the turbomachine being radially separated from the stator as from the external fairing.

Cette caractéristique permet, comme on le verra, de transformer beaucoup mieux l'énergie cinétique des projectiles en énergie de déformation mécanique absorbée par le bouclier, qui de plus n'est normalement pas crevé ou transpercé et isole donc toujours les pièces extérieures de la turbomachine des projectiles.This characteristic allows, as we will see, to transform the kinetic energy of projectiles much better into energy of mechanical deformation absorbed by the shield, which moreover is not normally punctured or pierced and therefore always isolates the external parts of the turbomachine projectiles.

L'invention va maintenant être décrite à l'aide des figures suivantes, annexées à titre illustratif et non limitatif, qui illustrent ses différents aspects :

  • la figure 1 est une vue générale de la position du bouclier dans la machine,
  • la figure 2 et la figure 3 présentent deux systèmes d'attache du bouclier,
  • et la figure 4 représente l'état du bouclier après un choc.
The invention will now be described with the aid of the following figures, annexed by way of illustration and not limitation, which illustrate its various aspects:
  • FIG. 1 is a general view of the position of the shield in the machine,
  • FIG. 2 and FIG. 3 show two systems for attaching the shield,
  • and FIG. 4 represents the state of the shield after an impact.

La figure 1 représente une portion de turbomachine qui comprend un rotor 1, un stator 2 sous forme d'une enveloppe entourant le rotor 1 et un carénage extérieur 3 entourant le stator 2 ; le stator 2 possède un évasement 4 circulaire et plan qui le termine en amont, et qui se termine lui-même par une bride 5 ajustée sur la face interne du carénage extérieur 3 et rivetée à lui.FIG. 1 represents a portion of a turbomachine which comprises a rotor 1, a stator 2 in the form of an envelope surrounding the rotor 1 and an external fairing 3 surrounding the stator 2; the stator 2 has a circular and planar flaring 4 which terminates it upstream, and which itself ends with a flange 5 fitted on the internal face of the outer fairing 3 and riveted to it.

Le rotor 1 et le stator 2 portent des étages alternés d'aubes respectivement mobiles 6 et fixes 7, comme il est habituel pour constituer des turbines et des compresseurs.The rotor 1 and the stator 2 carry alternating stages of respectively movable 6 and stationary vanes 7, as is usual for constituting turbines and compressors.

Un espace annulaire clos 8 existe entre le stator 2 et le carénage extérieur 3 en aval de l'évasement 4. Le bouclier 9 l'occupe et s'étend en son milieu : cela signifie qu'il est séparé radialement du carénage extérieur 3 comme du stator 2, sans forcément être à égale distance d'eux. Le bouclier 9 est un anneau continu de matière ductile, métallique ou autre, dont l'avantage est d'absorber de grandes énergies de choc. Il est maintenu par des moyens d'attache qui l'unissent à l'évasement 4. Bien des conceptions sont possibles, et deux seront illustrées. Sur la figure 2, le bouclier 9 a une extrémité recourbée en collerette 10 plane et circulaire dans des perçages desquels on a engagé des vis 11 d'orientation longitudinale dont les extrémités sont retenues dans des taraudages 12 percées dans l'évasement 4. Les vis 11 comprennent une partie amincie 13 de diamètre bien déterminé, constituant une amorce de rupture, à la jonction de limite entre l'évasement 4 et la collerette 10.An enclosed annular space 8 exists between the stator 2 and the external fairing 3 downstream of the flare 4. The shield 9 occupies it and extends in its middle: this means that it is radially separated from the external fairing 3 as from stator 2, without necessarily being equidistant from them. The shield 9 is a continuous ring of ductile, metallic or other material, the advantage of which is to absorb large impact energies. It is maintained by attachment means which unite it to the flare 4. Many designs are possible, and two will be illustrated. In FIG. 2, the shield 9 has one end bent into a flat and circular flange 10 in the bores of which screws 11 of longitudinal orientation have been engaged, the ends of which are retained in threads 12 drilled in the flare 4. The screws 11 comprise a thinned part 13 of well-defined diameter, constituting an initiation of rupture, at the limit junction between the flare 4 and the flange 10.

La collerette 10 est remplacée par des pattes 14, dans le prolongement du bouclier 9, mais sensiblement plus minces que lui, dans la réalisation de la figure 3. L'évasement 4 est muni d'une collerette 15 circulaire et continue, prolongeant le bouclier 9 et presque jointive à lui, sur laquelle les pattes 14 reposent. Des vis 16, cette fois orientées en direction radiale, unissent les pattes 14 à la collerette 15. Une amorce de rupture est aussi prévue, sous forme d'encoches 19 qui étrécissent les pattes 14 à la limite du bouclier 9 et de la collerette 15.The flange 10 is replaced by lugs 14, in the extension of the shield 9, but substantially thinner than it, in the embodiment of FIG. 3. The flaring 4 is provided with a flange 15 circular and continuous, extending the shield 9 and almost contiguous to it, on which the legs 14 rest. Screws 16, this time oriented in the radial direction, unite the tabs 14 with the flange 15. A breaking point is also provided, in the form of notches 19 which narrow the tabs 14 at the limit of the shield 9 and the flange 15 .

La figure 4 illustre ce qui peut se produire après un choc dû à un morceau de rotor 17 accidentellement détaché en fonctionnement, tel qu'un fragment de disque de turbine. La force centrifuge le projette à grande vitesse vers l'extérieur : il crève le stator 2 puis bosselle le bouclier 9. La déformation plastique qui se traduit par l'apparition de la bosse 18 sur la partie du bouclier 9 qu'il atteint entraîne, si l'énergie cinétique du morceau de rotor 17 le permet, une destruction partielle ou totale des moyens d'attache. Dans la réalisation de la figure 2, la partie amincie 13 des vis 12 est cisaillée ; dans celle de la figure 3, les pattes 14 sont rompues, entre les encoches 19, ici encore par cisaillement. On voit qu'on aurait pu aussi, d'une façon générale, utiliser toutes les conceptions connues d'éléments de rupture, aussi bien des vis, des boulons, des goujons, des rivets ou d'autres moyens qui sont sectionnés, déchirés ou arrachés en traction, en compression ou en cisaillement.FIG. 4 illustrates what can happen after an impact due to a piece of rotor 17 accidentally detached in operation, such as a fragment of a turbine disc. The centrifugal force projects it at high speed towards the outside: it bursts the stator 2 then embosses the shield 9. The plastic deformation which results in the appearance of the bump 18 on the part of the shield 9 which it reaches causes if the kinetic energy of the piece of rotor 17 allows it, a partial or total destruction of the attachment means. In the embodiment of Figure 2, the thinned portion 13 of the screws 12 is sheared; in that of FIG. 3, the tabs 14 are broken, between the notches 19, here again by shearing. We see that we could also, in a general way, use all the known designs of rupture elements, as well screws, bolts, studs, rivets or other means which are cut, torn or torn in tension, compression or shear.

Les éléments d'attache rompus sont d'abord ceux qui sont proches de la bosse 18. Si le choc est suffisamment violent, tous les éléments d'attache peuvent être touchés et le bouclier 9 devient alors libre, mais comme on a pris soin de le concevoir avec une résistance au transpercement suffisamment élevée, il ne s'ouvre pas sous le choc et continue de protéger le carénage extérieur 3 du contact direct du morceau de rotor 17, même s'il le heurte ou roule ensuite sur lui. Cette résistance dépend essentiellement de l'épaisseur du bouclier 9 et de la résistance à la rupture du matériau qui le forme.The broken fastening elements are first of all those which are close to the bump 18. If the shock is sufficiently violent, all the fastening elements can be touched and the shield 9 then becomes free, but as care has been taken to design it with a sufficiently high resistance to piercing, it does not open in shock and continues to protect the outer fairing 3 from direct contact with the piece of rotor 17, even if it strikes it or rolls over it. This resistance essentially depends on the thickness of the shield 9 and on the breaking strength of the material which forms it.

Le comportement et les avantages de l'invention peuvent être assez facilement saisis. Comme le bouclier 9 ne repose directement sur aucune surface, il peut absorber de l'énergie en se déformant librement sur une grande partie de sa circonférence, ou même la totalité de celle-ci. Le stator 2 et le carénage extérieur 3 sont suffisamment écartés pour permettre cette déformation. L'énergie totale que le système peut capter est aussi augmentée de l'énergie de rupture des moyens d'attache, en même temps que cette rupture autorise une déformation plus étendue du bouclier 9 et accroît donc sa capacité d'absorption d'énergie. Enfin, si le bouclier 9 est complètement détaché, il est projeté contre le carénage extérieur 3, mais la figure 4 représente une situation spécialement défavorable, car un seul gros morceau arraché du rotor 1 intervient dans l'accident. En pratique, il est fréquent que plusieurs morceaux plus ou moins de même poids soient projetés sur des parties différentes du bouclier 9, avec la conséquence favorable que leur énergie cinétique est plus complètement absorbée (leurs quantités de mouvement s'équilibrant) et que le bouclier 9 est projeté à une vitesse beaucoup plus faible qui réduit encore les risques de voir le canérage extérieur 3 endommagé. Même si l'énergie cinétique des projectiles n'est qu'imparfaitement transformée et qu'une partie notable est communiquée au bouclier 9 quand il est détaché, on doit tout de même espérer un ralentissement sensible de la masse mobile et des dommages moindres au carénage extérieur 3 grâce à la régularité de forme et à la rotondité du bouclier 9.The behavior and advantages of the invention can be fairly easily grasped. As the shield 9 does not rest directly on any surface, it can absorb energy by freely deforming over a large part of its circumference, or even all of it. The stator 2 and the outer fairing 3 are sufficiently spaced to allow this deformation. The total energy that the system can capture is also increased by the rupture energy of the attachment means, at the same time as this rupture allows a more extensive deformation of the shield 9 and therefore increases its energy absorption capacity. Finally, if the shield 9 is completely detached, it is thrown against the outer fairing 3, but FIG. 4 represents a particularly unfavorable situation, since a single large piece torn from the rotor 1 intervenes in the accident. In practice, it is frequent that several pieces more or less of the same weight are projected onto different parts of the shield 9, with the favorable consequence that their kinetic energy is more completely absorbed (their amounts of movement are balanced) and that the shield 9 is projected at a much lower speed which further reduces the risk of seeing the outer canering 3 damaged. Even if the kinetic energy of the projectiles is only imperfectly transformed and that a significant part is communicated to the shield 9 when it is detached, we must still hope for a significant slowdown in the moving mass and less damage to the fairing outside 3 thanks regularity of shape and roundness of the shield 9.

Claims (4)

Bouclier (9) de protection d'une turbomachine en forme d'anneau en matière ductile disposé autour d'un stator (2) et devant une zone aubagée d'un rotor (1) qu'entoure le stator (2), caractérisé en ce que l'anneau est continu, relié à la turbomachine par des moyens d'attache (11, 14) calculés pour se rompre en deçà d'une limite de rupture du bouclier (9) soumis à un choc et s'étend dans un espace annulaire (8) compris entre le stator (2) et un carénage extérieur (3) de la turbomachine en étant séparé radialement du stator (2) comme du carénage extérieur (3).Shield (9) for protecting a ring-shaped turbomachine made of ductile material arranged around a stator (2) and in front of a bladed area of a rotor (1) which surrounds the stator (2), characterized in that the ring is continuous, connected to the turbomachine by attachment means (11, 14) calculated to rupture below a rupture limit of the shield (9) subjected to an impact and extends in a annular space (8) comprised between the stator (2) and an external fairing (3) of the turbomachine being radially separated from the stator (2) as from the external fairing (3). Bouclier de protection d'une turbomachine selon la revendication 1, caractérisé en ce que les moyens d'attache sont des vis (11), des goujons ou des pions de cisaillement ou de traction.Protective shield of a turbomachine according to claim 1, characterized in that the attachment means are screws (11), studs or shear or traction pins. Bouclier de protection d'une turbomachine selon la revendication 1, caractérisé en ce que les moyens d'attache comprennent des pattes (14) prolongeant le bouclier.Protective shield of a turbomachine according to claim 1, characterized in that the attachment means comprise lugs (14) extending the shield. Bouclier de protection d'une turbomachine selon la revendication 1, caractérisé en ce que les moyens d'attache comprennent une portion de moindre résistance (13) munie d'amorces de rupture (19).Protective shield of a turbomachine according to claim 1, characterized in that the attachment means comprise a portion of weaker resistance (13) provided with rupture initiators (19).
EP95402879A 1994-12-21 1995-12-20 Containment ring for a turbomachine Expired - Lifetime EP0718471B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9415382 1994-12-21
FR9415382A FR2728619B1 (en) 1994-12-21 1994-12-21 PROTECTIVE SHIELD OF A TURBOMACHINE

Publications (2)

Publication Number Publication Date
EP0718471A1 true EP0718471A1 (en) 1996-06-26
EP0718471B1 EP0718471B1 (en) 1999-04-14

Family

ID=9470037

Family Applications (1)

Application Number Title Priority Date Filing Date
EP95402879A Expired - Lifetime EP0718471B1 (en) 1994-12-21 1995-12-20 Containment ring for a turbomachine

Country Status (8)

Country Link
US (1) US5622472A (en)
EP (1) EP0718471B1 (en)
JP (1) JP2967045B2 (en)
CA (1) CA2165511A1 (en)
DE (1) DE69509053T2 (en)
FR (1) FR2728619B1 (en)
RU (1) RU2122124C1 (en)
WO (1) WO1996019641A1 (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1849964A3 (en) * 2006-04-27 2010-11-10 Pratt & Whitney Canada Corp. Gas turbine rotor containment element with frangible connections
CN102733868A (en) * 2012-07-06 2012-10-17 中国航空动力机械研究所 Power machine

Families Citing this family (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH11230094A (en) * 1997-12-16 1999-08-24 United Technol Corp <Utc> Gas turbine engine
US6120242A (en) * 1998-11-13 2000-09-19 General Electric Company Blade containing turbine shroud
US6206631B1 (en) * 1999-09-07 2001-03-27 General Electric Company Turbomachine fan casing with dual-wall blade containment structure
US6375410B2 (en) * 2000-02-07 2002-04-23 General Electric Company Frangible cover for turbofan engine blade removal and access
ES2283780T3 (en) * 2002-06-05 2007-11-01 Volvo Aero Corporation TURBINE AND COMPONENT.
US6695574B1 (en) * 2002-08-21 2004-02-24 Pratt & Whitney Canada Corp. Energy absorber and deflection device
FR2859002A1 (en) * 2003-08-18 2005-02-25 Snecma Moteurs Abradable surface for gas turbine engine housing surrounding fan, is made from a resin with glass balls over a layer of thermoformable foam
FR2869954B1 (en) 2004-05-05 2006-06-16 Snecma Moteurs Sa DEVICE FOR FIXING A BURNER RING IN A POSTCOMBUSTION CHAMBER OF A TURBOJETACTOR
RU2281414C1 (en) * 2005-01-19 2006-08-10 Открытое акционерное общество "Научно-исследовательский институт измерительных приборов" (ОАО "НИИИП") Device for moving object in gas or liquid
DE102006036648A1 (en) * 2006-08-03 2008-02-07 Rolls-Royce Deutschland Ltd & Co Kg Ice protection ring for the fan housing of an aircraft gas turbine
RU2376528C1 (en) * 2008-03-31 2009-12-20 Денис Сергеевич Легконогих Method of increasing survivability of gas turbine engine combustion chamber
GB2459646B (en) * 2008-04-28 2011-03-30 Rolls Royce Plc A fan assembly
RU2461719C2 (en) * 2010-12-14 2012-09-20 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" Protection of blade machine housing against penetration by parted blade, and protected housing
US11280271B2 (en) 2012-10-09 2022-03-22 Raytheon Technologies Corporation Operability geared turbofan engine including compressor section variable guide vanes
RU2519677C1 (en) * 2013-04-22 2014-06-20 Открытое акционерное общество "Авиадвигатель" Turbomachine stator
DE102013217503A1 (en) * 2013-09-03 2015-03-05 MTU Aero Engines AG Device for energy absorption, turbomachine and method for energy absorption
GB2539217B (en) 2015-06-09 2020-02-12 Rolls Royce Plc Fan casing assembly
FR3058757B1 (en) * 2016-11-14 2018-11-02 Safran Aircraft Engines DEVICE FOR DECOUPLING FIRST AND SECOND PIECES OF A TURBOMACHINE
US10487684B2 (en) 2017-03-31 2019-11-26 The Boeing Company Gas turbine engine fan blade containment systems
US10550718B2 (en) 2017-03-31 2020-02-04 The Boeing Company Gas turbine engine fan blade containment systems
DE102018113396A1 (en) * 2018-06-06 2019-12-12 Man Energy Solutions Se Burst protection device for a turbomachine
DE102023106999A1 (en) * 2023-03-21 2024-09-26 MTU Aero Engines AG Housing structure for a turbomachine

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1698514A (en) * 1927-05-20 1929-01-08 Westinghouse Electric & Mfg Co Restraining guard for rotors
US3093361A (en) * 1958-07-07 1963-06-11 Bristol Siddeley Engines Ltd Engines
US3602602A (en) * 1969-05-19 1971-08-31 Avco Corp Burst containment means
GB1466385A (en) * 1974-11-21 1977-03-09 Rolls Royce Containment shields for gas turbine engines
FR2375443A1 (en) * 1976-12-23 1978-07-21 Gen Electric TURBOMACHINE BLADE RETAINER
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
EP0358141A1 (en) * 1988-09-06 1990-03-14 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Containment ring made of fibrous material
WO1992007180A1 (en) * 1990-10-22 1992-04-30 Sundstrand Corporation Radial turbine containment ring system
GB2262313A (en) * 1991-12-14 1993-06-16 Rolls Royce Plc Gas turbine aerofoil blade containment structure
DE4223496A1 (en) * 1992-07-17 1994-01-20 Asea Brown Boveri Reducing kinetic energy of bursting parts in turbines - involves crumple zone between inner and outer rings set between housing and rotor to absorb energy and contain fractured parts
EP0626502A1 (en) * 1993-04-07 1994-11-30 ROLLS-ROYCE plc Gas turbine engine casing assembly

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3097824A (en) * 1958-11-26 1963-07-16 Bendix Corp Turbine, wheel containment
NL134135C (en) * 1964-01-15
SU1474287A1 (en) * 1987-02-16 1989-04-23 М. В. Коротков Device for holding turbomachine breaked blades
SU1703844A1 (en) * 1989-01-12 1992-01-07 М.В.Коротов Device for fixing broken-off blade of gas turbine engine
GB2288639B (en) * 1994-04-20 1998-10-21 Rolls Royce Plc Ducted fan gas turbine engine nacelle assembly

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1698514A (en) * 1927-05-20 1929-01-08 Westinghouse Electric & Mfg Co Restraining guard for rotors
US3093361A (en) * 1958-07-07 1963-06-11 Bristol Siddeley Engines Ltd Engines
US3602602A (en) * 1969-05-19 1971-08-31 Avco Corp Burst containment means
GB1466385A (en) * 1974-11-21 1977-03-09 Rolls Royce Containment shields for gas turbine engines
FR2375443A1 (en) * 1976-12-23 1978-07-21 Gen Electric TURBOMACHINE BLADE RETAINER
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
EP0358141A1 (en) * 1988-09-06 1990-03-14 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Containment ring made of fibrous material
WO1992007180A1 (en) * 1990-10-22 1992-04-30 Sundstrand Corporation Radial turbine containment ring system
GB2262313A (en) * 1991-12-14 1993-06-16 Rolls Royce Plc Gas turbine aerofoil blade containment structure
DE4223496A1 (en) * 1992-07-17 1994-01-20 Asea Brown Boveri Reducing kinetic energy of bursting parts in turbines - involves crumple zone between inner and outer rings set between housing and rotor to absorb energy and contain fractured parts
EP0626502A1 (en) * 1993-04-07 1994-11-30 ROLLS-ROYCE plc Gas turbine engine casing assembly

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1849964A3 (en) * 2006-04-27 2010-11-10 Pratt & Whitney Canada Corp. Gas turbine rotor containment element with frangible connections
US8166746B2 (en) 2006-04-27 2012-05-01 Pratt & Whitney Canada Corp. Rotor containment element with frangible connections
CN102733868A (en) * 2012-07-06 2012-10-17 中国航空动力机械研究所 Power machine

Also Published As

Publication number Publication date
FR2728619A1 (en) 1996-06-28
DE69509053D1 (en) 1999-05-20
US5622472A (en) 1997-04-22
JPH08232683A (en) 1996-09-10
RU2122124C1 (en) 1998-11-20
DE69509053T2 (en) 1999-10-07
WO1996019641A1 (en) 1996-06-27
JP2967045B2 (en) 1999-10-25
CA2165511A1 (en) 1996-06-22
FR2728619B1 (en) 1997-01-24
EP0718471B1 (en) 1999-04-14

Similar Documents

Publication Publication Date Title
EP0718471B1 (en) Containment ring for a turbomachine
EP0027756B1 (en) Safety device in case of rupture of a rotating turbomachine part
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
US7959405B2 (en) Blade containment structure
JP4119654B2 (en) Fluid machine with radial flow impeller
EP0184962B1 (en) Retention housing for a turbo fan
EP2088290B1 (en) Supporting abradable casing liner in a turbomachine
EP0128819B1 (en) Containment structure for the housing of a turbo machine
EP2373906B1 (en) Flexible flywheel, particularly for a motor vehicle
EP2622181B1 (en) Gasturbine engine with means of axial retention of the engine fan
EP2609296B1 (en) Method for mounting a retention shield on a turbine casing, and mounting assembly for implementing same
JPS62500950A (en) Turbine impeller containment structure
FR2871201A1 (en) FLUIDIC MACHINE WITH RADIAL COMPRESSOR ROTOR
CA2473088C (en) Breakable coupling system for a turbojet fan shaft
FR2859002A1 (en) Abradable surface for gas turbine engine housing surrounding fan, is made from a resin with glass balls over a layer of thermoformable foam
JP4880148B2 (en) Fluid machinery
EP2053199A1 (en) Turbomachine wheel
EP0552089B1 (en) Device for the spraying of a liquid, particularly of a liquid fuel in a burner
FR2574499A1 (en) Flywheel with rim supported by flexible straps
EP0688405B1 (en) Double flywheel, in particular for motor vehicles
FR2875850A1 (en) Fan casing for rotor of aircraft turbine engine, has case arranged around blades and filled with metallic, organic or ceramic foam to ensure retention of bodies projected by rotor, where case has stringer arranged around blades
EP0917628B1 (en) Clutch friction and ring for dry disk clutch, more particularly for motor vehicle
FR2770266A1 (en) Safety clutch for lawn tractor is positioned between inner and outer drive shaft
KR20190138751A (en) Burst protection device for a turbo machine
BE725433A (en)

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: 19960109

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): DE FR GB

17Q First examination report despatched

Effective date: 19970826

GRAG Despatch of communication of intention to grant

Free format text: ORIGINAL CODE: EPIDOS AGRA

GRAG Despatch of communication of intention to grant

Free format text: ORIGINAL CODE: EPIDOS AGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: HISPANO-SUIZA AEROSTRUCTURES

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

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

REF Corresponds to:

Ref document number: 69509053

Country of ref document: DE

Date of ref document: 19990520

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

Effective date: 19990507

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
REG Reference to a national code

Ref country code: GB

Ref legal event code: IF02

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

Ref country code: FR

Payment date: 20031127

Year of fee payment: 9

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

Ref country code: DE

Payment date: 20031205

Year of fee payment: 9

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

Ref country code: GB

Payment date: 20031219

Year of fee payment: 9

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

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20041220

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

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20050701

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

Effective date: 20041220

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

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20050831

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST