EP1995414B1 - Braking device for a turbine in a gas turbine engine in the event of shaft breakage - Google Patents

Braking device for a turbine in a gas turbine engine in the event of shaft breakage Download PDF

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Publication number
EP1995414B1
EP1995414B1 EP08156695A EP08156695A EP1995414B1 EP 1995414 B1 EP1995414 B1 EP 1995414B1 EP 08156695 A EP08156695 A EP 08156695A EP 08156695 A EP08156695 A EP 08156695A EP 1995414 B1 EP1995414 B1 EP 1995414B1
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EP
European Patent Office
Prior art keywords
braking member
braking
turbine
rim
rotor
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EP08156695A
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German (de)
French (fr)
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EP1995414A1 (en
Inventor
Jacques René Bart
Didier René André Escure
Claude Marcel Mons
Stéphane Rousselin
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Safran Aircraft Engines SAS
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SNECMA SAS
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    • 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
    • F01D21/006—Arrangements of brakes
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/02—Purpose of the control system to control rotational speed (n)
    • F05D2270/021—Purpose of the control system to control rotational speed (n) to prevent overspeed

Definitions

  • the present invention relates to the field of gas turbine engines, in particular multiflux turbojet engines, and relates to a system which makes it possible, in the event of the breakage of a shaft of the machine, to stop it as quickly as possible. .
  • a turbojet turbojet turbofan In a turbojet turbojet turbofan, the latter is driven by the low pressure turbine.
  • the shaft connecting the fan rotor to that of the turbine breaks, the resistance torque on the turbine is abruptly canceled while the flow of engine gas continues to transmit energy to the rotor. This results in a rapid increase in the rotational speed of the rotor which is likely to reach its limit of resistance and burst with the resulting catastrophic consequences.
  • the present invention aims at a simple, effective and inexpensive solution for reducing the speed of rotation, in a gas turbine engine, of a turbine comprising a rotor driving a shaft and movable in rotation inside a stator, in case of rupture of said shaft.
  • the braking device in a gas turbine engine a turbine comprising a rotor, having at least one disc with a rim, driving a shaft and mobile in rotation with respect to a stator, is characterized by the fact that it comprises a first braking member, integral with said rim and provided with at least one cutting element, and a second braking member, integral with the stator downstream of the rim, comprising a shaped element; ring made of a material capable of being cut by the cutting element of the first braking member, the two braking members coming into contact by axial displacement of the rotor after rupture of the shaft, the cutting element of the first member braking system cutting off the ring-shaped element of the second braking member.
  • the solution of the invention therefore consists in dissipating the energy of the rotor between two members which are arranged specifically for braking. These means make it possible to increase the contact surface according to the objective aimed at and to ensure a high coefficient of friction.
  • the advantage is also to reduce the maximum speed at which the rotor must resist without bursting.
  • This diet is the one that is likely to be reached when the tree breaks.
  • the blades are preserved and the zone where this energy dissipation occurs can be located.
  • the first member is advantageously secured to the last turbine stage of the rotor and the second member of the exhaust casing.
  • the first member comprises a plurality of cutting elements distributed around the axis of the motor, and the elements are made by machining with the rim.
  • the cutting elements are knife-shaped arranged to dig the ring-shaped element with removal of material.
  • the ring-shaped element is attached to a flange mounted on the stator.
  • the invention also relates to a dual-body gas turbine engine with a low-pressure turbine section whose section is equipped with such a braking device.
  • the turbine section 1 comprises a high-pressure turbine upstream and not visible in the figure, which receives the hot gases from the combustion chamber.
  • the gases after having passed through the vane of the high-pressure turbine wheel are directed, through a fixed distributor wheel 3, onto the low-pressure turbine section 5.
  • This section 5 is composed of a rotor 6 formed here in a drum the assembly of several disks 61, 62, 63 bladed, three in this example.
  • the blades, comprising a blade and a foot, are mounted, generally individually, at the periphery of the discs in housings formed on the rim.
  • Stationary distributor wheels 7 are interposed between the turbine stages, each to properly orient the gas flow relative to the downstream moving blade.
  • This assembly forms the low pressure turbine section 5.
  • the rotor 6 of the low-pressure turbine is mounted on a shaft 8, concentric with the high-pressure shaft 9, which extends axially towards the front of the engine where it is integral with the fan rotor.
  • the rotating assembly is supported by appropriate bearings located in the front and rear parts of the engine.
  • the shaft 8, supported by a bearing 81 is seen in the structural casing, designated exhaust casing 10.
  • the exhaust casing is provided with fastening means for mounting on an aircraft.
  • the turbine rotor is racing and its speed reaches the maximum permitted speed before bursting, a braking device is incorporated in the turbine section.
  • This device 100 is represented on the figure 2 which is a partial perspective view of the turbine disk 63 'and the exhaust casing.
  • the disk 63 ' corresponds to the disk 63 of the figure 1 modified according to the invention.
  • the disc 63 ' has a conventional shape or the like, according to this example with a hub 63'A, a rim 63'B at its periphery and a thin radial sail 63'C between the hub and the rim.
  • the rim 63'B is provided with means for attaching the vanes which extend in a radial direction in the annular channel traversed by the engine gas.
  • the vanes and their attachment means are not part of the invention and have not been represented in their entirety in the figure a single silhouette in the section plane is visible.
  • the exhaust casing 10 is shown in its part which is vis-à-vis the disc 63 '.
  • annular platform 10A forming the inner wall of the gas channel in the extension of the platforms at the periphery of the disk 63 'of the last turbine stage.
  • Rectifier vanes 10B extend radially in the annular channel.
  • the platform 10A extends axially upstream towards the disc 63 'by an annular sealing tongue 10A'.
  • the braking device 100 of the invention comprises a first braking member 110 which consists of cutting elements 110A.
  • the first braking member 110 is secured to the rim 63'B. More precisely for this example, the member 110 is secured to a radial flange 63'B1 downstream at the rim.
  • the elements 110A are, according to the example shown, teeth inclined in the direction of rotation of the disc. Their distal end is bevel-shaped and is cut to form a cutting means, such as a chisel.
  • the cutting edge is here radial or substantially radial.
  • This first braking member (110) can be attached to the flange 63'B1 of the rim 63'B but it can also be obtained by machining together with the rim from a cast blank. In this case it is made of the same metal as the rim. Its hardness corresponds to it.
  • the second braking member 120 is mounted on the stator formed by the exhaust casing 10. It comprises an annular pool 120B bolted to an annular rib of the housing 10 under the tongue 10A '.
  • the flange 120B comprises a radial flange 120B1 positioned downstream of the first braking member 110.
  • a ring-shaped element 120A is integral with the flange 120B1. This ring element 120A is of rectangular section with a radial face perpendicular to the axis of rotation, maintained at a short distance downstream from the edges of the cutting elements (110A) forming the first braking member (110).
  • the material constituting the ring-shaped element 120A is of lower hardness than that of the cutting elements 110A. It may consist of a piece with the flange 120B but may also have been attached to the flange.
  • the turbine disk rotates about its axis and the cutting elements 110A move in rotation about the motor axis, parallel to the front face of the ring member 120A without touching it preferably.
  • the combination of the elements 110A and 120A should allow, when the disc moves axially downstream due to the breakage of the shaft 8, the cutting elements 110A to rub against the ring member 120A.
  • the rotation associated with the pressure leads to the cutting of the element 120A by the cutting elements 110A in the manner of a conventional cutting tool.
  • the energy is supplied by the rotating rotor and is thus dissipated.
  • the geometry of the cutting elements 110A; angle of the bevel, length of the cutting edge, and the material constituting them are determined jointly and in relation to the material of the annular element 120A.

Description

La présente invention concerne le domaine des moteurs à turbine à gaz, en particulier des turboréacteurs multiflux, et porte sur un système permettant en cas de rupture d'un arbre de la machine d'en obtenir l'arrêt dans un délai aussi bref que possible.The present invention relates to the field of gas turbine engines, in particular multiflux turbojet engines, and relates to a system which makes it possible, in the event of the breakage of a shaft of the machine, to stop it as quickly as possible. .

Dans un turboréacteur multiflux à turbo soufflante, cette dernière est entraînée par la turbine basse pression. Lorsque l'arbre reliant le rotor de soufflante à celui de la turbine se rompt, le couple résistant sur la turbine est brutalement annulé alors que le flux de gaz moteur continue à transmettre son énergie au rotor. Il s'ensuit une augmentation rapide de la vitesse de rotation du rotor qui est susceptible d'atteindre sa limite de résistance et d'éclater avec les conséquences catastrophiques qui en résultent.In a turbojet turbojet turbofan, the latter is driven by the low pressure turbine. When the shaft connecting the fan rotor to that of the turbine breaks, the resistance torque on the turbine is abruptly canceled while the flow of engine gas continues to transmit energy to the rotor. This results in a rapid increase in the rotational speed of the rotor which is likely to reach its limit of resistance and burst with the resulting catastrophic consequences.

On a proposé d'interrompre l'arrivée de carburant alimentant la chambre de combustion afin d'éliminer la source d'énergie par laquelle le rotor est accéléré. Une solution consiste à surveiller la vitesse de rotation des arbres par des moyens de mesure redondants et à commander l'interruption de l'alimentation en carburant lorsqu'une survitesse est détectée. Selon le brevet US6494046 , on mesure les fréquences de rotation aux deux extrémités de l'arbre au niveau des paliers et on les compare en continue et en temps réel.It has been proposed to interrupt the fuel supply to the combustion chamber in order to eliminate the energy source by which the rotor is accelerated. One solution is to monitor the speed of rotation of the shafts by redundant measuring means and to control the interruption of the fuel supply when an overspeed is detected. According to the patent US6494046 the rotation frequencies at both ends of the shaft are measured at the bearings and are continuously and real-time compared.

Des moyens assurant le freinage du rotor lorsque survient un tel incident ont aussi été proposés. Le déplacement axial du rotor consécutif à la rupture de l'arbre déclenche l'actionnement de mécanismes visant à en dissiper l'énergie cinétique. Il s'agit par exemple d'ailettes fixes de la roue adjacente de distributeurs qui sont basculées en direction des aubes du rotor de manière à venir s'interposer entre elles et couper leur trajectoire. L'énergie cinétique est dissipée par le frottement des pièces entre elles, leur déformation, voire leur rupture. Une solution 'de ce type est décrite dans la demande de brevet EP 1640564 au nom du présent déposant. Selon cette solution des moyens de destruction sont montés sur une roue fixe adjacente à une roue de la turbine à freiner et sont agencés pour cisailler les échasses des aubes du rotor amont en début de déplacement vers l'aval du rotor.Means for braking the rotor when such an incident occurs have also been proposed. The axial displacement of the rotor following the rupture of the shaft triggers the actuation of mechanisms to dissipate the kinetic energy. It is for example fixed fins of the adjacent wheel distributors that are tilted towards the blades of the rotor so as to come between them and cut their path. The kinetic energy is dissipated by the friction of the parts between them, their deformation, even their rupture. A solution of this type is described in the patent application EP 1640564 on behalf of the present applicant. According to this solution destruction means are mounted on a fixed wheel adjacent to a wheel of the turbine to be braked and are arranged to shear the stilts of the blades of the upstream rotor at the beginning of displacement downstream of the rotor.

Cette solution quoique efficace, entraîne des coûts de réparation importants en raison des dégâts occasionnés sur les aubages.This solution, although effective, entails significant repair costs because of damage to the blades.

La présente invention vise une solution simple, efficace et peu onéreuse pour réduire la vitesse de rotation, dans un moteur à turbine à gaz, d'une turbine comprenant un rotor entraînant un arbre et mobile en rotation à l'intérieur d'un stator, en cas de rupture dudit arbre.The present invention aims at a simple, effective and inexpensive solution for reducing the speed of rotation, in a gas turbine engine, of a turbine comprising a rotor driving a shaft and movable in rotation inside a stator, in case of rupture of said shaft.

Conformément à l'invention le dispositif de freinage dans un moteur à turbine à gaz, d'une turbine comprenant un rotor, ayant au moins un disque avec une jante, entraînant un arbre et mobile en rotation par rapport à un stator, est caractérisé par le fait qu'il comprend un premier organe de freinage, solidaire de ladite jante et pourvu d'au moins un élément de coupe, et un second organe de freinage, solidaire du stator en aval de la jante, comprenant un élément en forme d'anneau réalisé en un matériau susceptible d'être découpé par l'élément de coupe du premier organe de freinage, les deux organes de freinage venant en contact par déplacement axial du rotor après rupture de l'arbre, l'élément de coupe du premier organe de freinage découpant l'élément en forme d'anneau du second organe de freinage.According to the invention the braking device in a gas turbine engine, a turbine comprising a rotor, having at least one disc with a rim, driving a shaft and mobile in rotation with respect to a stator, is characterized by the fact that it comprises a first braking member, integral with said rim and provided with at least one cutting element, and a second braking member, integral with the stator downstream of the rim, comprising a shaped element; ring made of a material capable of being cut by the cutting element of the first braking member, the two braking members coming into contact by axial displacement of the rotor after rupture of the shaft, the cutting element of the first member braking system cutting off the ring-shaped element of the second braking member.

La solution de l'invention consiste donc à dissiper l'énergie du rotor entre deux organes qui sont agencés spécifiquement pour le freinage. Ces moyens permettent d'augmenter la surface de contact en fonction de l'objectif visé et d'assurer un coefficient de frottement important.The solution of the invention therefore consists in dissipating the energy of the rotor between two members which are arranged specifically for braking. These means make it possible to increase the contact surface according to the objective aimed at and to ensure a high coefficient of friction.

L'avantage est aussi de permettre de réduire le régime maximal auquel le rotor doit résister sans éclater. Ce régime est celui qui est susceptible d'être atteint lors de la rupture de l'arbre.The advantage is also to reduce the maximum speed at which the rotor must resist without bursting. This diet is the one that is likely to be reached when the tree breaks.

En disposant les organes de freinage en dehors de la veine de gaz, on préserve les aubes et on peut localiser la zone où se produit cette dissipation d'énergie.By arranging the braking members outside the gas stream, the blades are preserved and the zone where this energy dissipation occurs can be located.

Pour un moteur comprenant un carter d'échappement, le premier organe est avantageusement solidaire du dernier étage de turbine du rotor et le second organe du carter d'échappement.For an engine comprising an exhaust casing, the first member is advantageously secured to the last turbine stage of the rotor and the second member of the exhaust casing.

Conformément à un mode de réalisation, le premier organe comprend une pluralité d'éléments de coupe répartis autour de l'axe du moteur, et les éléments sont réalisés par usinage avec la jante. Les éléments de coupe sont en forme de couteaux agencés pour creuser l'élément en forme d'anneau avec enlèvement de matière.According to one embodiment, the first member comprises a plurality of cutting elements distributed around the axis of the motor, and the elements are made by machining with the rim. The cutting elements are knife-shaped arranged to dig the ring-shaped element with removal of material.

Conformément à une autre caractéristique, l'élément en forme d'anneau est rapporté sur un flasque monté sur le stator.According to another characteristic, the ring-shaped element is attached to a flange mounted on the stator.

L'invention porte également sur un moteur à turbine à gaz à double corps avec une section de turbine basse pression dont ladite section est équipée d'un tel dispositif de freinage.The invention also relates to a dual-body gas turbine engine with a low-pressure turbine section whose section is equipped with such a braking device.

D'autres caractéristiques et avantages ressortiront de la description d'un mode de réalisation non limitatif de l'invention en référence aux dessins sur lesquels

  • La figure 1 montre une demi-coupe axiale de la section de turbine d'un moteur à turbine à gaz double corps,
  • La figure 2 montre un dispositif de freinage aménagé sur la section de turbine basse pression du moteur à turbine à gaz.
Other features and advantages will emerge from the description of a non-limiting embodiment of the invention with reference to the drawings in which
  • The figure 1 shows an axial half-section of the turbine section of a double-body gas turbine engine,
  • The figure 2 shows a braking device arranged on the low-pressure turbine section of the gas turbine engine.

On voit sur la figure 1, une partie de la section de turbine 1 d'un moteur à turbine à gaz. Dans un moteur à double corps et double flux, la section de turbine 1 comprend une turbine haute pression en amont et non visible sur la figure, qui reçoit les gaz chauds de la chambre de combustion. Les gaz après avoir traversé l'aubage de la roue de turbine haute pression sont dirigés, à travers une roue de distributeurs 3 fixes, sur la section de turbine basse pression 5. Cette section 5 est composée d'un rotor 6 formé ici en tambour de l'assemblage de plusieurs disques 61, 62, 63 aubagés, trois dans cet exemple. Les aubes, comprenant une pale et un pied, sont montées, généralement individuellement, à la périphérie des disques dans des logements ménagés sur la jante. Des roues de distributeurs 7 fixes sont interposées entre les étages de turbine, chacune pour orienter convenablement le flux gazeux par rapport à l'aubage mobile aval. Cet ensemble forme la section 5 de turbine basse pression. Le rotor 6 de la turbine basse pression est monté sur un arbre 8, concentrique à l'arbre haute pression 9, qui se prolonge axialement vers l'avant du moteur où il est solidaire du rotor de soufflante. L'ensemble tournant est supporté par des paliers appropriés situés dans les parties avant et arrière du moteur. Sur la figure 1, on voit l'arbre 8 supporté par un palier 81, dans le carter structural, désigné carter d'échappement 10. Le carter d'échappement est pourvu de moyens d'attaches pour un montage sur un aéronef.We see on the figure 1 , part of the turbine section 1 of a gas turbine engine. In a double-body, double-flow motor, the turbine section 1 comprises a high-pressure turbine upstream and not visible in the figure, which receives the hot gases from the combustion chamber. The gases after having passed through the vane of the high-pressure turbine wheel are directed, through a fixed distributor wheel 3, onto the low-pressure turbine section 5. This section 5 is composed of a rotor 6 formed here in a drum the assembly of several disks 61, 62, 63 bladed, three in this example. The blades, comprising a blade and a foot, are mounted, generally individually, at the periphery of the discs in housings formed on the rim. Stationary distributor wheels 7 are interposed between the turbine stages, each to properly orient the gas flow relative to the downstream moving blade. This assembly forms the low pressure turbine section 5. The rotor 6 of the low-pressure turbine is mounted on a shaft 8, concentric with the high-pressure shaft 9, which extends axially towards the front of the engine where it is integral with the fan rotor. The rotating assembly is supported by appropriate bearings located in the front and rear parts of the engine. On the figure 1 the shaft 8, supported by a bearing 81, is seen in the structural casing, designated exhaust casing 10. The exhaust casing is provided with fastening means for mounting on an aircraft.

Lorsque l'arbre 8 se rompt accidentellement, l'ensemble mobile de la turbine basse pression se déplace vers l'arrière, vers la droite sur la figure, en raison de la pression exercée par les gaz. Par ailleurs, il est accéléré en rotation en raison de la disparition de son couple résistant combinée à la poussée tangentielle que les gaz chauds continuent d'exercer sur les aubages mobiles pendant leur traversée de la turbine.When the shaft 8 breaks accidentally, the movable assembly of the low pressure turbine moves backwards, to the right in the figure, due to the pressure exerted by the gases. Moreover, it is accelerated in rotation due to the disappearance of its resistant torque combined with the tangential thrust that the hot gases continue to exert on the mobile blades during their crossing of the turbine.

Pour empêcher, conformément à l'invention, que le rotor de turbine s'emballe et que sa vitesse atteigne le régime maximal autorisé avant d'éclater, un dispositif de freinage est incorporé à la section de turbine.To prevent, according to the invention, the turbine rotor is racing and its speed reaches the maximum permitted speed before bursting, a braking device is incorporated in the turbine section.

Ce dispositif 100 est représenté sur la figure 2 qui est une vue partielle en perspective du disque de turbine 63' et du carter d'échappement.This device 100 is represented on the figure 2 which is a partial perspective view of the turbine disk 63 'and the exhaust casing.

Le disque 63' correspond au disque 63 de la figure 1 modifié conformément à l'invention. Le disque 63' a une forme conventionnelle ou autre, selon cet exemple avec un moyeu 63'A, une jante 63'B à sa périphérie et un voile radial 63'C de faible épaisseur entre le moyeu et la jante. La jante 63'B est pourvue de moyens d'attache des aubes qui s'étendent en direction radiale dans le canal annulaire parcouru par le gaz moteur. Les aubes et leur moyen d'attache ne font pas partie de l'invention et n'ont pas été représentés dans leur ensemble sur la figure une silhouette seule dans le plan de coupe est visible. Le carter d'échappement 10 est représenté dans sa partie qui est en vis-à-vis du disque 63'. Il comprend une plateforme annulaire 10A formant la paroi intérieure du canal des gaz dans le prolongement des plateformes à la périphérie du disque 63' du dernier étage de turbine. Des aubes de redresseur 10B s'étendent radialement dans le canal annulaire. La plateforme 10A s'étend axialement en amont vers le disque 63' par une languette annulaire 10A' d'étanchéité.The disk 63 'corresponds to the disk 63 of the figure 1 modified according to the invention. The disc 63 'has a conventional shape or the like, according to this example with a hub 63'A, a rim 63'B at its periphery and a thin radial sail 63'C between the hub and the rim. The rim 63'B is provided with means for attaching the vanes which extend in a radial direction in the annular channel traversed by the engine gas. The vanes and their attachment means are not part of the invention and have not been represented in their entirety in the figure a single silhouette in the section plane is visible. The exhaust casing 10 is shown in its part which is vis-à-vis the disc 63 '. It comprises an annular platform 10A forming the inner wall of the gas channel in the extension of the platforms at the periphery of the disk 63 'of the last turbine stage. Rectifier vanes 10B extend radially in the annular channel. The platform 10A extends axially upstream towards the disc 63 'by an annular sealing tongue 10A'.

Le dispositif de freinage 100 de l'invention est décrit ci-après. Il comprend un premier organe de freinage 110 qui est constitué d'éléments de coupe 110A. Le premier organe de freinage 110 est solidaire de la jante 63'B. Plus précisément pour cet exemple, l'organe 110 est solidaire d'une bride radiale 63'B1 en aval au niveau de la jante. Les éléments 110A sont, selon l'exemple représenté, des dents inclinées dans le sens de rotation du disque. Leur extrémité distale est en forme de biseau et est taillée de manière à former un moyen de coupe, tel un ciseau. L'arête de coupe est ici radiale ou bien sensiblement radiale.The braking device 100 of the invention is described below. It comprises a first braking member 110 which consists of cutting elements 110A. The first braking member 110 is secured to the rim 63'B. More precisely for this example, the member 110 is secured to a radial flange 63'B1 downstream at the rim. The elements 110A are, according to the example shown, teeth inclined in the direction of rotation of the disc. Their distal end is bevel-shaped and is cut to form a cutting means, such as a chisel. The cutting edge is here radial or substantially radial.

Ce premier organe de freinage (110) peut être rapporté sur la bride 63'B1 de la jante 63'B mais il peut être aussi obtenu par usinage ensemble avec la jante à partir d'une ébauche venue de fonderie. Dans ce cas il est constitué du même métal que la jante. Sa dureté lui correspond.This first braking member (110) can be attached to the flange 63'B1 of the rim 63'B but it can also be obtained by machining together with the rim from a cast blank. In this case it is made of the same metal as the rim. Its hardness corresponds to it.

Le second organe de freinage 120 est monté sur le stator formé par le carter d'échappement 10. Il comprend un flaque annulaire 120B boulonné sur une nervure annulaire du carter 10 sous la languette 10A'. Le flasque 120B comprend une bride radiale 120B1 positionnée en aval du premier organe de freinage 110. Un élément en forme d'anneau 120A est solidaire de la bride 120B1. Cet élément en anneau 120A est à section rectangulaire avec une face radiale perpendiculaire à l'axe de rotation, maintenue à faible distance en aval des arêtes des éléments de coupe (110A) formant le premier organe de freinage (110).The second braking member 120 is mounted on the stator formed by the exhaust casing 10. It comprises an annular pool 120B bolted to an annular rib of the housing 10 under the tongue 10A '. The flange 120B comprises a radial flange 120B1 positioned downstream of the first braking member 110. A ring-shaped element 120A is integral with the flange 120B1. This ring element 120A is of rectangular section with a radial face perpendicular to the axis of rotation, maintained at a short distance downstream from the edges of the cutting elements (110A) forming the first braking member (110).

Le matériau constituant l'élément en forme d'anneau 120A est de dureté inférieure à celle des éléments de coupe 110A. Il peut être constitué d'une pièce avec le flasque 120B mais peut aussi bien avoir été rapporté sur la bride.The material constituting the ring-shaped element 120A is of lower hardness than that of the cutting elements 110A. It may consist of a piece with the flange 120B but may also have been attached to the flange.

En fonctionnement normal, le disque de turbine tourne autour de son axe et les éléments de coupe 110A se déplacent en rotation autour de l'axe moteur, parallèlement à la face avant de l'élément en anneau 120A sans le toucher de préférence.In normal operation, the turbine disk rotates about its axis and the cutting elements 110A move in rotation about the motor axis, parallel to the front face of the ring member 120A without touching it preferably.

La combinaison des éléments 110A et 120A doit permettre, lorsque le disque se déplace axialement vers l'aval en raison de la rupture de l'arbre 8, aux éléments de coupe 110A de frotter contre l'élément en anneau 120A. La rotation associée à la pression conduit à la découpe de l'élément 120A par les éléments de coupe 110A à l'instar d'un outil de coupe conventionnel. L'énergie est fournie par le rotor en rotation et est ainsi dissipée.The combination of the elements 110A and 120A should allow, when the disc moves axially downstream due to the breakage of the shaft 8, the cutting elements 110A to rub against the ring member 120A. The rotation associated with the pressure leads to the cutting of the element 120A by the cutting elements 110A in the manner of a conventional cutting tool. The energy is supplied by the rotating rotor and is thus dissipated.

La géométrie des éléments de coupe 110A ; angle du biseau, longueur de l'arête de coupe, et le matériau qui les constitue sont déterminés conjointement et en relation avec le matériau de l'élément annulaire 120A.The geometry of the cutting elements 110A; angle of the bevel, length of the cutting edge, and the material constituting them are determined jointly and in relation to the material of the annular element 120A.

Claims (8)

  1. A device for, in a gas turbine engine, braking a turbine comprising a rotor, having at least one disk (63') with a rim (63'B), driving a shaft and capable of rotating with respect to a stator, this device being for the event of said shaft breaking characterized by the fact that it comprises a first braking member (110), secured to said rim and provided with at least one cutting element (110A), and a second braking member (120) secured to the stator downstream of the rim (63'B), comprising a ring-shaped (120A) element made of a material that can be cut by the cutting element (110A), the two braking members coming into contact with one another through axial displacement of the rotor once the shaft has broken, the cutting element (110A) of the first braking member (110) cutting the ring-shaped (120A) element of the second braking member (120).
  2. The device as claimed in claim 1, the engine comprising an exhaust casing (10), in which the first braking member (110) is secured to the last turbine stage of the rotor and the second braking member (120) is secured to the exhaust casing (10).
  3. The device as claimed in claim 1 or 2, in which the first braking member (110) comprises a plurality of cutting elements (110A) distributed about the axis of the engine.
  4. The device as claimed in claim 1 in which the cutting elements (110A) of the first braking member (110) are produced by a machining operation with the rim (63'B).
  5. The device as claimed in claim 1 in which the cutting elements (110A) of the first braking member (110) are produced by a machining operation on an additional element attached to the rim (63'B).
  6. The device as claimed in claim 4 or 5 in which the cutting elements (110A) are in the form of cutters designed to cut into the ring-shaped element (120A) of the second braking member, removing material.
  7. The device as claimed in one of claims 1 and 2 in which the ring-shaped element (120A) of the second braking member is added on to a flange (120B) mounted on the stator.
  8. A twin spool gas turbine engine with a low-pressure turbine section in which said section is equipped with a braking device as claimed in one of the preceding claims.
EP08156695A 2007-05-25 2008-05-21 Braking device for a turbine in a gas turbine engine in the event of shaft breakage Active EP1995414B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0703759A FR2916483B1 (en) 2007-05-25 2007-05-25 SYSTEM FOR DISSIPATING ENERGY IN THE EVENT OF TURBINE SHAFT BREAKAGE IN A GAS TURBINE ENGINE

Publications (2)

Publication Number Publication Date
EP1995414A1 EP1995414A1 (en) 2008-11-26
EP1995414B1 true EP1995414B1 (en) 2010-07-07

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Application Number Title Priority Date Filing Date
EP08156695A Active EP1995414B1 (en) 2007-05-25 2008-05-21 Braking device for a turbine in a gas turbine engine in the event of shaft breakage

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US (1) US8127525B2 (en)
EP (1) EP1995414B1 (en)
CA (1) CA2631620C (en)
DE (1) DE602008001684D1 (en)
FR (1) FR2916483B1 (en)
RU (1) RU2469194C2 (en)

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DE102011086775A1 (en) 2011-07-20 2013-01-24 Mtu Aero Engines Gmbh Method for producing an inlet lining, inlet system, turbomachine and vane
FR2987085B1 (en) * 2012-02-20 2014-03-21 Snecma METHOD FOR SECURING THE OPERATION OF A TURBOMACHINE
FR3026774B1 (en) * 2014-10-07 2020-07-17 Safran Aircraft Engines TURBOMACHINE COMPRISING A BLOWER ROTOR BRAKING DEVICE.
US10190440B2 (en) 2015-06-10 2019-01-29 Rolls-Royce North American Technologies, Inc. Emergency shut-down detection system for a gas turbine
FR3049646B1 (en) * 2016-03-31 2019-04-12 Safran Aircraft Engines DEVICE FOR LIMITING THE OVERVIEW OF A TURBINE ROTOR ROTOR
RU2647944C1 (en) * 2017-03-07 2018-03-21 Акционерное общество "ОДК-Авиадвигатель" Gas turbine engine with birotate fan
FR3079550B1 (en) 2018-03-27 2020-10-23 Safran Aircraft Engines TURBINE SHAFT OF A TURBOMACHINE AND PROCESS FOR PROTECTING AGAINST OVERSPEED OF THE SHAFT
CN108742350B (en) * 2018-06-28 2021-04-06 芜湖泰领信息科技有限公司 Automatic cleaning brush head replacement method and intelligent sweeper
GB201820823D0 (en) * 2018-12-20 2019-02-06 Rolls Royce Plc Gas turbine engine
FR3107318B1 (en) 2020-02-17 2022-01-14 Safran Aircraft Engines Dual-flow aircraft turbomachine equipped with a rotor overspeed shutdown device

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FR2916482B1 (en) * 2007-05-25 2009-09-04 Snecma Sa BRAKE SYSTEM IN CASE OF TURBINE SHAFT RUPTURE IN A GAS TURBINE ENGINE

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RU2008120784A (en) 2009-11-27
DE602008001684D1 (en) 2010-08-19
EP1995414A1 (en) 2008-11-26
US20080289315A1 (en) 2008-11-27
CA2631620A1 (en) 2008-11-25
RU2469194C2 (en) 2012-12-10
FR2916483A1 (en) 2008-11-28
FR2916483B1 (en) 2013-03-01
CA2631620C (en) 2015-02-24
US8127525B2 (en) 2012-03-06

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