EP0718471B1 - Containment ring for a turbomachine - Google Patents

Containment ring for a turbomachine Download PDF

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Publication number
EP0718471B1
EP0718471B1 EP95402879A EP95402879A EP0718471B1 EP 0718471 B1 EP0718471 B1 EP 0718471B1 EP 95402879 A EP95402879 A EP 95402879A EP 95402879 A EP95402879 A EP 95402879A EP 0718471 B1 EP0718471 B1 EP 0718471B1
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EP
European Patent Office
Prior art keywords
shield
stator
turbomachine
fairing
rotor
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP95402879A
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German (de)
French (fr)
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EP0718471A1 (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 Aerostructures
Hispano Suiza SA
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Publication of EP0718471A1 publication Critical patent/EP0718471A1/en
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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 turbomachine comprising a shield protection.
  • stator More precisely surrounding a padded area a rotor surrounded by the stator, that is to say surrounding a compressor or turbine section in the machine, and its function is to stop the pieces or debris from blades or rotor that would be thrown towards him under the action of centrifugal forces after a rupture due to an accident.
  • U.S. Patent 4,452,563 describes a shield formed by a continuous network of fibrous bands draped on the outer face, opposite the rotor, of the stator. This conception seems relatively little effective because the fibers should tear enough easily and therefore would not give protection sufficient. We could also lay layers of honeycomb material on this outer face of the stator, but despite the increased absorption of energy that such a structure would offer for slow or stop the projectiles, this absorption would be located at the point of shock and the shield would be pierced here too easily.
  • the patent European 0 626 502 describes a shield formed of juxtaposed plates which have the same disadvantages.
  • French patent 2,375,443 describes a continuous ring shield that breaks its attachments when a loose blade hits it; but the shield serves as a lining for the stator or replaces it, and does not can absorb the kinetic energy of the blade that taking a rotary motion; he doesn't have the possibility of absorbing energy by deforming, as in the invention, because it has no space surrounding to deform; it is finally effective that if the energy communicated is sufficient to break all its attachments, which limits its possibilities of employment.
  • the invention is based on the idea that it is advantageous to involve the whole shield in shock absorption allowing it to deform and to break its attachments to the stator in proportion to the energy received.
  • GB-A-1 466 385 a shield protective ring-shaped in which the ring is continuous, connected to the turbomachine by attachment means and extends into an annular space between the stator and an outer fairing of the turbomachine in being radially separated from the stator as from the fairing outside.
  • the attachment means comprise lugs extending the shield and comprising a smaller portion resistance provided with breaking primers.
  • Figure 1 shows a portion of turbomachine which comprises a rotor 1, a stator 2 under form of an envelope surrounding the rotor 1 and a exterior fairing 3 surrounding the stator 2; the stator 2 has a circular and planar flare 4 which ends upstream, and which ends in a flange 5 adjusted on the inner face of the fairing outside 3 and riveted to it.
  • the rotor 1 and the stator 2 carry alternating stages of respectively movable vanes 6 and fixed 7, as is usual to constitute turbines and compressors.
  • a closed annular space 8 exists between the stator 2 and the outer 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 exterior fairing 3 like stator 2, without necessarily be equidistant from them.
  • Shield 9 is a continuous ring of ductile, metallic or other material, whose advantage is to absorb large energies of shock. It is maintained by fastening means which unite it with the flare 4. Many designs are possible, and two will be illustrated.
  • the shield 9 has a curved flange end 10 flat and circular in holes of which there are engaged screws 11 of longitudinal orientation whose ends are retained in 12 drilled threads in the flare 4.
  • the screws 11 include a part thinned 13 of well determined diameter, constituting a breaking point, at the limit junction between the flare 4 and the flange 10.
  • the flange 10 is replaced by legs 14, in the extension of the shield 9, but significantly thinner than him, in the realization in Figure 3.
  • the flare 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 direction radial, join the legs 14 to the collar 15.
  • a breakthrough is also planned, in the form notches 19 which narrow the legs 14 to the limit shield 9 and collar 15.
  • Figure 4 illustrates what can happen occur after a shock due to a piece of rotor 17 accidentally detached in operation, such as turbine disc fragment.
  • the centrifugal force projects at high speed towards the outside: it bursts the stator 2 then dent the shield 9.
  • the deformation plastic which results in the appearance of the bump 18 on the part of the shield 9 which it reaches drives, if the kinetic energy of the rotor piece 17 the allows, partial or total destruction of the means of attachment.
  • the thinned part 13 of the screws 12 is sheared; in that in Figure 3, the legs 14 are broken, between the notches 19, again by shearing.
  • the broken fasteners are first those close to the bump 18. If the shock is sufficiently violent, all the elements of attachment can be hit and the shield 9 then becomes free, but as we took care to design it with sufficiently high resistance to piercing, it does not open in shock and continues to protect the outer fairing 3 of the direct contact of the piece of rotor 17, even if it strikes it or rolls over it. This resistance mainly depends on the thickness of shield 9 and the breaking strength of the material that forms it.
  • the behavior and benefits 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 much of its circumference, or even the whole of it.
  • the stator 2 and the fairing outside 3 are wide enough to allow this distortion.
  • the total energy that the system can capture is also increased by the breaking energy of 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.
  • the shield 9 is completely detached, it is projected against the outer fairing 3, but the figure 4 represents a particularly unfavorable situation, because only one 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)

Description

L'invention a pour sujet une turbomachine comportant un bouclier de protection.The subject of the invention is a turbomachine comprising a shield protection.

Il s'agit d'une enveloppe disposée autour d'un stator, plus précisément entourant une zone aubagée d'un rotor qu'entoure le stator, c'est-à-dire entourant 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 surrounding a padded area a rotor surrounded by the stator, that is to say surrounding a compressor or turbine section in the machine, and its function is to stop the pieces or debris from blades or rotor that would be thrown towards him 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 paraít 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.U.S. Patent 4,452,563 describes a shield formed by a continuous network of fibrous bands draped on the outer face, opposite the rotor, of the stator. This conception seems relatively little effective because the fibers should tear enough easily and therefore would not give protection sufficient. We could also lay layers of honeycomb material on this outer face of the stator, but despite the increased absorption of energy that such a structure would offer for slow or stop the projectiles, this absorption would be located at the point of shock and the shield would be pierced here too easily. The patent European 0 626 502 describes a shield formed of juxtaposed plates which have the same disadvantages.

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 that breaks its attachments when a loose blade hits it; but the shield serves as a lining for the stator or replaces it, and does not can absorb the kinetic energy of the blade that taking a rotary motion; he doesn't have the possibility of absorbing energy by deforming, as in the invention, because it has no space surrounding to deform; it is finally effective that if the energy communicated is sufficient to break all its attachments, which limits its possibilities of employment.

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. On connaít par GB-A-1 466 385 un bouclier de protection en forme d'anneau dans lequel l'anneau est continu, relié à la turbomachine par des moyens d'attache 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 shock absorption allowing it to deform and to break its attachments to the stator in proportion to the energy received. We know by GB-A-1 466 385 a shield protective ring-shaped in which the ring is continuous, connected to the turbomachine by attachment means and extends into an annular space between the stator and an outer fairing of the turbomachine in being radially separated from the stator as from the fairing outside.

Selon l'invention, les moyens d'attache comprennent des pattes prolongeant le bouclier et comprenant une portion de moindre résistance munie d'amorces de rupture.According to the invention, the attachment means comprise lugs extending the shield and comprising a smaller portion resistance provided with breaking primers.

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 feature allows, as we will see, transform energy much better kinetics of projectiles in deformation energy mechanical absorbed by the shield, which moreover is normally not punctured or pierced and therefore insulates always the exterior parts of the turbomachine of 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.Figure 1 shows a portion of turbomachine which comprises a rotor 1, a stator 2 under form of an envelope surrounding the rotor 1 and a exterior fairing 3 surrounding the stator 2; the stator 2 has a circular and planar flare 4 which ends upstream, and which ends in a flange 5 adjusted on the inner face of the fairing outside 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 vanes 6 and fixed 7, as is usual to constitute 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.A closed annular space 8 exists between the stator 2 and the outer 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 exterior fairing 3 like stator 2, without necessarily be equidistant from them. Shield 9 is a continuous ring of ductile, metallic or other material, whose advantage is to absorb large energies of shock. It is maintained by fastening means which unite it with the flare 4. Many designs are possible, and two will be illustrated. In Figure 2, the shield 9 has a curved flange end 10 flat and circular in holes of which there are engaged screws 11 of longitudinal orientation whose ends are retained in 12 drilled threads in the flare 4. The screws 11 include a part thinned 13 of well determined diameter, constituting a breaking point, 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 legs 14, in the extension of the shield 9, but significantly thinner than him, in the realization in Figure 3. The flare 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 direction radial, join the legs 14 to the collar 15. A breakthrough is also planned, in the form notches 19 which narrow the legs 14 to the limit shield 9 and collar 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 entraíne, 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.Figure 4 illustrates what can happen occur after a shock due to a piece of rotor 17 accidentally detached in operation, such as turbine disc fragment. The centrifugal force projects at high speed towards the outside: it bursts the stator 2 then dent the shield 9. The deformation plastic which results in the appearance of the bump 18 on the part of the shield 9 which it reaches drives, if the kinetic energy of the rotor piece 17 the allows, partial or total destruction of the means of attachment. In the embodiment of FIG. 2, the thinned part 13 of the screws 12 is sheared; in that in Figure 3, the legs 14 are broken, between the notches 19, again by shearing. We see that could also, in general, have used all known designs of rupture elements, too many screws, bolts, studs, rivets or other means that are severed, 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 fasteners are first those close to the bump 18. If the shock is sufficiently violent, all the elements of attachment can be hit and the shield 9 then becomes free, but as we took care to design it with sufficiently high resistance to piercing, it does not open in shock and continues to protect the outer fairing 3 of the direct contact of the piece of rotor 17, even if it strikes it or rolls over it. This resistance mainly depends on the thickness of shield 9 and the breaking strength of the material that 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 accroít 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 benefits 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 much of its circumference, or even the whole of it. The stator 2 and the fairing outside 3 are wide enough to allow this distortion. The total energy that the system can capture is also increased by the breaking energy of 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 projected against the outer fairing 3, but the figure 4 represents a particularly unfavorable situation, because only one large piece torn from the rotor 1 intervenes in the accident. In practice, it is common for several pieces more or less of the same weight be projected on different parts of shield 9, with the favorable consequence that their energy kinetics is more fully absorbed (their balancing movements) and that the shield 9 is projected at a much higher speed low which further reduces the risk of seeing the damaged outer pipe 3. Even if the energy projectile kinetics is only imperfectly transformed and a significant part is communicated to the shield 9 when it is detached, we must still expect a significant slowdown in the moving mass and less damage to the outer fairing 3 thanks regularity of shape and roundness of the shield 9.

Claims (1)

  1. A turbomachine comprising a containment shield (9) in the form of a continuous ductile ring disposed around a stator (2) and extending around a bladed zone of a rotor (1) around which the stator (2) extends, the ring being connected to the turbomachine by connecting means (11,14) calculated to rupture below an impact rupture limit of the shield (9) and extending in an annular gap (8) between the stator (2) and an outer fairing (3) of the turbomachine and being separated radially from both the stator (2) and the fairing (3), characterised in that the connecting means comprise lugs (14) which extend the shield and which comprise a weakened portion having rupture leaders (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
FR9415382A FR2728619B1 (en) 1994-12-21 1994-12-21 PROTECTIVE SHIELD OF A TURBOMACHINE
FR9415382 1994-12-21

Publications (2)

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

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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)

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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
GB9307288D0 (en) * 1993-04-07 1993-06-02 Rolls Royce Plc Gas turbine engine casing construction
GB2288639B (en) * 1994-04-20 1998-10-21 Rolls Royce Plc Ducted fan gas turbine engine nacelle assembly

Also Published As

Publication number Publication date
US5622472A (en) 1997-04-22
FR2728619A1 (en) 1996-06-28
EP0718471A1 (en) 1996-06-26
DE69509053D1 (en) 1999-05-20
DE69509053T2 (en) 1999-10-07
WO1996019641A1 (en) 1996-06-27
JP2967045B2 (en) 1999-10-25
FR2728619B1 (en) 1997-01-24
CA2165511A1 (en) 1996-06-22
RU2122124C1 (en) 1998-11-20
JPH08232683A (en) 1996-09-10

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