EP1921274A1 - Overspeed limitation device for the turbine of a turbomachine and corresponding turbomachine - Google Patents

Overspeed limitation device for the turbine of a turbomachine and corresponding turbomachine Download PDF

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Publication number
EP1921274A1
EP1921274A1 EP07291199A EP07291199A EP1921274A1 EP 1921274 A1 EP1921274 A1 EP 1921274A1 EP 07291199 A EP07291199 A EP 07291199A EP 07291199 A EP07291199 A EP 07291199A EP 1921274 A1 EP1921274 A1 EP 1921274A1
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EP
European Patent Office
Prior art keywords
turbine
cylinder
pin
overspeed
turbomachine
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
EP07291199A
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German (de)
French (fr)
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EP1921274B1 (en
Inventor
Jacques René Bart
Didier René André Escure
Stéphane Rousselin
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Safran Aircraft Engines SAS
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SNECMA SAS
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Publication of EP1921274A1 publication Critical patent/EP1921274A1/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
    • F01D21/02—Shutting-down responsive to overspeed
    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0292—Stop safety or alarm devices, e.g. stop-and-go control; Disposition of check-valves
    • 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
    • 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
    • F05D2270/04—Purpose of the control system to control acceleration (u)
    • F05D2270/042—Purpose of the control system to control acceleration (u) by keeping it below damagingly high values
    • 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
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/304—Spool rotational speed
    • 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
    • F05D2270/60—Control system actuates means
    • F05D2270/62—Electrical actuators

Definitions

  • the present invention relates to a device for limiting overspeed in a turbomachine such as an aircraft turbojet, to counteract a rupture of the turbine shaft, a rare phenomenon but whose consequences can be disastrous.
  • the rotor of the turbine is found uncoupled from the fan which limited its speed of rotation but the blades of the turbine continue to be rotated by the gas leaving the combustion chamber of the turbine engine .
  • the turbine then passes "overspeed", which subjects the rotor to excessive centrifugal forces likely to cause it to burst, with risks of perforation of the outer casing of the turbine and also of the cabin of the aircraft equipped with this turbomachine.
  • the overspeed limitation is therefore a mandatory constraint to be respected in the turbomachines.
  • the known overspeed limiting devices generally exploit the downstream displacement of the rotor of the turbine which results from the rupture of the turbine shaft and the pressure of the gases on the vanes of the rotor.
  • the known devices have the disadvantage of being relatively slow, which affects their efficiency. This is particularly disadvantageous in the case of small engines, whose lower inertia of the turbine rotor induces a risk of starting in faster overspeed.
  • the devices requiring a frank contact between parts may prove to be inoperative in case of rebound of the rotor on a fixed part or in case of orbiting of this rotor.
  • Braking devices based on friction between parts have an efficiency that is difficult to predict because they involve multiple uncertain parameters such as the temperature or the force exerted between the parts.
  • the invention aims in particular to provide a simple, economical and effective solution to these problems, to avoid the disadvantages of the known technique.
  • the invention also aims to respond more satisfactorily to the reliability and speed requirements of a device for limiting the overspeed of a turbine in a turbomachine.
  • a device for limiting turbine overspeed in a turbine engine in the event of rupture of the turbine shaft comprising shearing means for moving blades of at least one stage of the turbine, characterized in that these shearing means comprise means for projecting a pin on the path of the blades, these projection means being mounted on a casing of the turbine or turbomachine and controlled by means of detecting an overspeed of rotation of the blade; turbine or detection of a rupture of the shaft of this turbine.
  • the essential advantage of this device is that it is not dependent on the recoil of the rotor and can be triggered without waiting for this recoil to occur, which guarantees a greater speed of reaction, the speed of the device does not depend more than the response time of the projection means.
  • the operation of this device will not be penalized, unlike some previous devices, in case of rebound of the turbine or rotor orbiting.
  • the projection means comprise an explosive material capsule housed in a cylinder capable of guiding the pin during the explosion of the capsule.
  • pellets of a material capable of generating a gas under the effect of a detonation such as, for example, sodium acid, are placed near the explosive material capsule in this cylinder.
  • the cylinder is mounted outside the housing in alignment with an orifice of this casing opening on the path of the blades, and comprises an open end by which it is fixed. on the housing, its other end being closed and containing the capsule of explosive material.
  • the pin extends completely inside the cylinder when it is in rest condition, before detecting an overspeed departure or before detecting a rupture of the low pressure turbine shaft, and it comprises a body cylindrical whose one end is slidably guided in the end of the cylinder fixed on the housing, the other end of the cylindrical body having a head whose diameter is greater than that of the cylindrical body and the diameter of the open end of the cylinder; cylinder, so as to form a retaining member of the pin in the cylinder.
  • the pin in rest condition, does not disturb the flow of gas in the turbine and therefore does not affect the performance of the engine.
  • the casing orifice is closed by a cover of material resistant to the operating temperatures of the turbomachine and capable of being broken by the pin in the event of detection of a departure in overspeed, the pin preferably comprising a tip suitable for pierce this operculum, formed at the end of the cylindrical body opposite the head.
  • the pin is locked inside the cylinder in the rest position, and only the explosion and the release of gas, following an overspeed departure detection or rupture of the low pressure turbine shaft. , can, by the violent thrust exerted on the pin, bring this one to pierce the operculum to leave the cylinder.
  • this seal prevents gases passing through the turbine from entering the cylinder containing the pin and the explosive capsule.
  • the cylinder advantageously comprises a lateral fastening flange on the housing and electrical connection means of the explosive charge means for detecting an overspeed of rotation of the turbine or a rupture of the shaft of this turbine.
  • the present invention also relates to a turbomachine, such as an aircraft turbojet, equipped with an overspeed limitation device of the type described above.
  • FIG 1 shows a low pressure turbine rotor comprising four discs 12, 14, 16, 18 assembled axially to each other by annular flanges 20 and carrying blades 22 which are mounted by means of blade roots at their radially inner end in grooves in the outer periphery of the discs 12, 14, 16, 18.
  • the rotor is connected to the turbine shaft 24 via a fixed drive cone 26 by means of an annular flange 28 between the annular flanges 20 of the discs 14 and 16.
  • a device 40 for limiting the speed of the turbine according to the invention is mounted on the outer surface of an exhaust casing 34 to which is connected the turbine casing 32.
  • the device 40 thus positioned is associated on the top floor of the turbine, it is possible to use it for any floor.
  • the turbine is furthermore equipped with means for detecting an overspeed of rotation of the rotor or a rupture of the shaft 24 of this turbine, shown schematically at 36.
  • the overspeed limiting device 40 comprises a pin 42 made of very hard metal housed in a cylinder 44, which has at its end applied to the casing 34 a lateral rim 46 fixed by one or more screws 48 to a plate 50 formed on the outer surface of the housing 34, the cylinder 44 being open at its end fixed on the housing and closed at its other end.
  • the pin 42 comprises a cylindrical body 52 respectively comprising, at its two ends, a tip 56 and a head 54, the latter having a diameter greater than that of the cylindrical body 52, so as to form a retaining member of the pin in the cylinder.
  • the head 54 is in the vicinity of the closed end of the cylinder 44 while the tip 56 faces its open end.
  • An explosive charge shown schematically at 38 and optionally sodium acid pellets or other gas generating material are placed inside the cylinder, in the free space 58 between the head 54 of the pin and the closed end of the cylinder.
  • the cylinder 44 is mounted in alignment with an orifice 60 of the housing 34 which opens on the path of the blades 22 of the last stage of the rotor of the turbine.
  • This orifice 60 has a diameter slightly greater than that of the cylindrical body 52, and smaller than that of the head 54.
  • the pin 42 In the rest position shown in Figure 2, the pin 42 is housed entirely in the cylinder 44 and the orifice 60 is obstructed by a seal of a material, such as a resin or putty, resistant to operating temperatures the turbomachine and adapted to be perforated by the tip 56 of the pin 42 under the effect of a strong thrust.
  • a seal of a material such as a resin or putty
  • Electrical connection means 64 are mounted on a lateral support 62 connected to the cylinder 44 and to the lateral attachment flange 46, to enable the control of the explosive charge by the means 36 for detecting an overspeed of rotation of the turbine or of a rupture of the shaft 24 of this turbine.
  • the pin Under the effect of the strong thrust exerted by the gas on its head 54, the pin then pierces through its point 56 the seal obstructing the orifice 60, and is projected inwardly of the turbine through the orifice 60 , until the head 54 abuts against the edge of the orifice 60, as shown in FIG.
  • Part of the pin 42 is then in the path of the aforementioned moving blades 22, so that these vanes are broken against it.
  • the response time of the device according to the invention is very short: about 40 milliseconds (10 ms for the detection of the overspeed and 30 ms for the explosion of the load and the projection of the pin), while the response time devices known from the prior art is greater than 100 ms.

Abstract

The device (40) has a shearing unit for shearing bearing blades (22) of stages (30) of a turbine. The shearing unit includes a cylinder for propelling a pin (42) into a path of the blades. An explosive charge is mounted on an exhaust casing (34) of the turbine or of the turbo-machine and controlled by a detecting unit that detect that the turbine is experiencing overspeed or that a turbine shaft (24) has broken. The cylinder is mounted on an outside of the casing in a line with an orifice of the casing that opens onto the path of the blades.

Description

La présente invention concerne un dispositif de limitation de survitesse dans une turbomachine telle qu'un turboréacteur d'avion, pour parer à une rupture de l'arbre de turbine, phénomène rarissime mais dont les conséquences peuvent être désastreuses.The present invention relates to a device for limiting overspeed in a turbomachine such as an aircraft turbojet, to counteract a rupture of the turbine shaft, a rare phenomenon but whose consequences can be disastrous.

A la rupture de cet arbre, le rotor de la turbine se retrouve désaccouplé de la soufflante qui limitait sa vitesse de rotation mais les aubes mobiles de la turbine continuent d'être entraînées en rotation par les gaz sortant de la chambre de combustion de la turbomachine. La turbine passe alors en « survitesse », ce qui soumet le rotor à des forces centrifuges excessives susceptibles de provoquer son éclatement, avec des risques de perforation du carter externe de la turbine et aussi de la carlingue de l'avion équipé de cette turbomachine. La limitation de survitesse est donc une contrainte impérative à respecter dans les turbomachines.At the rupture of this shaft, the rotor of the turbine is found uncoupled from the fan which limited its speed of rotation but the blades of the turbine continue to be rotated by the gas leaving the combustion chamber of the turbine engine . The turbine then passes "overspeed", which subjects the rotor to excessive centrifugal forces likely to cause it to burst, with risks of perforation of the outer casing of the turbine and also of the cabin of the aircraft equipped with this turbomachine. The overspeed limitation is therefore a mandatory constraint to be respected in the turbomachines.

Les dispositifs connus de limitation de survitesse exploitent en général le déplacement vers l'aval du rotor de la turbine qui résulte de la rupture de l'arbre de turbine et de la pression des gaz sur les aubes du rotor.The known overspeed limiting devices generally exploit the downstream displacement of the rotor of the turbine which results from the rupture of the turbine shaft and the pressure of the gases on the vanes of the rotor.

On a ainsi déjà proposé des dispositifs de freinage mécanique du rotor de la turbine, comprenant des moyens portés par le rotor et destinés à venir en appui sur des moyens correspondants du stator de manière à freiner le rotor, suite à son déplacement vers l'aval après la rupture de l'arbre de turbine.It has thus already been proposed mechanical braking devices of the rotor of the turbine, comprising means carried by the rotor and intended to bear on corresponding means of the stator so as to brake the rotor, following its downstream movement after the rupture of the turbine shaft.

On a également proposé de monter les aubes directrices du stator de façon amovible ou basculante pour que le rotor, du fait de son déplacement vers l'aval après la rupture de l'arbre de turbine, vienne s'appuyer sur ces aubes et les fasse basculer sur la trajectoire des aubes mobiles pour les détruire et ainsi ralentir la rotation de la turbine. Cette solution connue est toutefois relativement complexe et coûteuse.It has also been proposed to mount the guide vanes of the stator in a removable or tilting manner so that the rotor, because of its downstream displacement after the breakage of the turbine shaft, comes to rest on these vanes and makes them switch on the path of the blades to destroy them and thus slow down the rotation of the turbine. This However, the known solution is relatively complex and expensive.

Les dispositifs connus ont l'inconvénient d'être relativement lents, ce qui nuit à leur efficacité. Ceci est particulièrement pénalisant dans le cas des petits moteurs, dont l'inertie plus faible du rotor de turbine induit un risque de départ en survitesse plus rapide.The known devices have the disadvantage of being relatively slow, which affects their efficiency. This is particularly disadvantageous in the case of small engines, whose lower inertia of the turbine rotor induces a risk of starting in faster overspeed.

Par ailleurs, les dispositifs nécessitant un contact franc entre des pièces, peuvent se révéler inopérants en cas de rebond du rotor sur une pièce fixe ou en cas d'orbitage de ce rotor.Furthermore, the devices requiring a frank contact between parts, may prove to be inoperative in case of rebound of the rotor on a fixed part or in case of orbiting of this rotor.

Les dispositifs de freinage fondés sur le frottement entre des pièces ont une efficacité difficilement prévisible du fait qu'ils font intervenir de multiples paramètres incertains tels que la température ou l'effort exercé entre les pièces.Braking devices based on friction between parts have an efficiency that is difficult to predict because they involve multiple uncertain parameters such as the temperature or the force exerted between the parts.

En outre, certains dispositifs connus ont l'inconvénient d'augmenter la masse totale de la turbine et de modifier le profil aérodynamique de ses composants au détriment des performances du moteur.In addition, some known devices have the disadvantage of increasing the total mass of the turbine and changing the aerodynamic profile of its components at the expense of engine performance.

L'invention a notamment pour but d'apporter une solution simple, économique et efficace à ces problèmes, permettant d'éviter les inconvénients de la technique connue.The invention aims in particular to provide a simple, economical and effective solution to these problems, to avoid the disadvantages of the known technique.

L'invention a aussi pour but de répondre de façon plus satisfaisante aux exigences de fiabilité et de rapidité d'un dispositif de limitation de survitesse d'une turbine dans une turbomachine.The invention also aims to respond more satisfactorily to the reliability and speed requirements of a device for limiting the overspeed of a turbine in a turbomachine.

Elle propose à cet effet un dispositif de limitation de survitesse de turbine dans une turbomachine en cas de rupture de l'arbre de turbine, comprenant des moyens de cisaillement des aubes mobiles d'au moins un étage de la turbine, caractérisé en ce que ces moyens de cisaillement comprennent des moyens de projection d'une goupille sur le trajet des aubes mobiles, ces moyens de projection étant montés sur un carter de la turbine ou de la turbomachine et commandés par des moyens de détection d'une survitesse de rotation de la turbine ou de détection d'une rupture de l'arbre de cette turbine.To this end, it proposes a device for limiting turbine overspeed in a turbine engine in the event of rupture of the turbine shaft, comprising shearing means for moving blades of at least one stage of the turbine, characterized in that these shearing means comprise means for projecting a pin on the path of the blades, these projection means being mounted on a casing of the turbine or turbomachine and controlled by means of detecting an overspeed of rotation of the blade; turbine or detection of a rupture of the shaft of this turbine.

Les aubes mobiles interceptées par la goupille sont détruites sous l'effet de la collision avec cette goupille et leurs fragments sont projetés sur les autres aubes du rotor et sur celles du stator de la turbine et provoquent leur destruction. Le rotor, qui n'est plus entraîné par les aubes, ne risque plus de destruction pour cause de survitesse.Mobile blades intercepted by the pin are destroyed under the effect of the collision with this pin and their fragments are projected on the other blades of the rotor and those of the stator of the turbine and cause their destruction. The rotor, which is no longer driven by the blades, no longer risk destruction because of overspeed.

L'avantage essentiel de ce dispositif est qu'il n'est pas tributaire du recul du rotor et peut être déclenché sans attendre que ce recul se produise, ce qui garantit une plus grande vitesse de réaction, la rapidité du dispositif ne dépendant plus que du temps de réponse des moyens de projection. De plus, le fonctionnement de ce dispositif ne se trouvera pas pénalisé, contrairement à certains dispositifs antérieurs, en cas de rebond de la turbine ou d'orbitage du rotor.The essential advantage of this device is that it is not dependent on the recoil of the rotor and can be triggered without waiting for this recoil to occur, which guarantees a greater speed of reaction, the speed of the device does not depend more than the response time of the projection means. In addition, the operation of this device will not be penalized, unlike some previous devices, in case of rebound of the turbine or rotor orbiting.

Selon un mode de réalisation préféré de l'invention, les moyens de projection comprennent une capsule de matière explosive logée dans un cylindre apte à guider la goupille lors de l'explosion de la capsule.According to a preferred embodiment of the invention, the projection means comprise an explosive material capsule housed in a cylinder capable of guiding the pin during the explosion of the capsule.

Avantageusement, des pastilles d'une matière susceptible de générer un gaz sous l'effet d'une détonation, telle par exemple de l'acide de sodium, sont placées à proximité de la capsule de matière explosive dans ce cylindre.Advantageously, pellets of a material capable of generating a gas under the effect of a detonation, such as, for example, sodium acid, are placed near the explosive material capsule in this cylinder.

Ainsi, c'est le souffle produit par l'explosion de la capsule et, le cas échéant, par le dégagement gazeux produit par les pastilles précitées, qui projette la goupille sur le trajet des aubes pour les détruire. L'utilisation de pastilles d'acide de sodium, déjà connue dans le domaine des coussins gonflables d'automobiles, permet une vitesse de réaction optimale.Thus, it is the breath produced by the explosion of the capsule and, where appropriate, by the gassing produced by the above-mentioned pellets, which projects the pin on the path of the blades to destroy them. The use of sodium acid pellets, already known in the field of automobile airbags, allows an optimal reaction rate.

En variante, il est possible de recourir à une amenée de gaz sous pression prélevé sur le moteur ou fourni par une réserve de gaz sous pression.Alternatively, it is possible to use a supply of pressurized gas taken from the engine or provided by a pressurized gas reserve.

Dans le mode de réalisation préféré de l'invention, le cylindre est monté à l'extérieur du carter dans l'alignement d'un orifice de ce carter débouchant sur le trajet des aubes mobiles, et comprend une extrémité ouverte par laquelle il est fixé sur le carter, son autre extrémité étant fermée et contenant la capsule de matière explosive.In the preferred embodiment of the invention, the cylinder is mounted outside the housing in alignment with an orifice of this casing opening on the path of the blades, and comprises an open end by which it is fixed. on the housing, its other end being closed and containing the capsule of explosive material.

La goupille s'étend entièrement à l'intérieur du cylindre lorsqu'elle est en condition de repos, avant détection d'un départ en survitesse ou avant détection d'une rupture de l'arbre de turbine basse pression, et elle comporte un corps cylindrique dont une extrémité est guidée en coulissement dans l'extrémité du cylindre fixée sur le carter, l'autre extrémité du corps cylindrique comportant une tête dont le diamètre est supérieur à celui du corps cylindrique ainsi qu'au diamètre de l'extrémité ouverte du cylindre, de manière à former un organe de retenue de la goupille dans le cylindre.The pin extends completely inside the cylinder when it is in rest condition, before detecting an overspeed departure or before detecting a rupture of the low pressure turbine shaft, and it comprises a body cylindrical whose one end is slidably guided in the end of the cylinder fixed on the housing, the other end of the cylindrical body having a head whose diameter is greater than that of the cylindrical body and the diameter of the open end of the cylinder; cylinder, so as to form a retaining member of the pin in the cylinder.

Ainsi, en condition de repos, la goupille ne perturbe en rien le flux des gaz dans la turbine et ne pénalise donc pas les performances du moteur.Thus, in rest condition, the pin does not disturb the flow of gas in the turbine and therefore does not affect the performance of the engine.

En cas de détection d'un départ en survitesse ou d'une rupture de l'arbre de turbine basse pression, la poussée de l'explosion et des gaz libérés s'exerce sur la tête de la goupille et pousse violemment la goupille en coulissement au travers de l'extrémité ouverte du cylindre, jusqu'à ce que la tête de la goupille vienne buter contre le bord de l'ouverture du cylindre, retenant ainsi la goupille dans le cylindre.If an overspeed departure or a rupture of the low pressure turbine shaft is detected, the thrust of the explosion and the released gases is exerted on the pin head and pushes the pin slid violently. through the open end of the cylinder, until the pin head abuts against the edge of the cylinder opening, thereby retaining the pin in the cylinder.

Avantageusement, l'orifice du carter est fermé par un opercule de matière résistant aux températures de fonctionnement de la turbomachine et propre à être rompue par la goupille en cas de détection d'un départ en survitesse, la goupille comportant de préférence une pointe apte à percer cet opercule, formée à l'extrémité du corps cylindrique opposée à la tête.Advantageously, the casing orifice is closed by a cover of material resistant to the operating temperatures of the turbomachine and capable of being broken by the pin in the event of detection of a departure in overspeed, the pin preferably comprising a tip suitable for pierce this operculum, formed at the end of the cylindrical body opposite the head.

Grâce à cet opercule, la goupille est bloquée à l'intérieur du cylindre en position de repos, et seule l'explosion et la libération de gaz, consécutives à une détection de départ en survitesse ou de rupture de l'arbre de turbine basse pression, peuvent, par la violente poussée exercée sur la goupille, amener celle-ci à percer l'opercule pour sortir du cylindre. En outre, cet opercule interdit aux gaz passant dans la turbine de pénétrer à l'intérieur du cylindre contenant la goupille et la capsule explosive.Thanks to this cover, the pin is locked inside the cylinder in the rest position, and only the explosion and the release of gas, following an overspeed departure detection or rupture of the low pressure turbine shaft. , can, by the violent thrust exerted on the pin, bring this one to pierce the operculum to leave the cylinder. In addition, this seal prevents gases passing through the turbine from entering the cylinder containing the pin and the explosive capsule.

Le cylindre comprend avantageusement un rebord latéral de fixation sur le carter et des moyens de connexion électrique de la charge explosive aux moyens de détection d'une survitesse de rotation de la turbine ou d'une rupture de l'arbre de cette turbine.The cylinder advantageously comprises a lateral fastening flange on the housing and electrical connection means of the explosive charge means for detecting an overspeed of rotation of the turbine or a rupture of the shaft of this turbine.

La présente invention concerne également une turbomachine, telle qu'un turboréacteur d'avion, équipée d'un dispositif de limitation de survitesse du type décrit ci-dessus.The present invention also relates to a turbomachine, such as an aircraft turbojet, equipped with an overspeed limitation device of the type described above.

D'autres avantages et caractéristiques de l'invention apparaîtront à la lecture de la description suivante faite à titre d'exemple non limitatif et en référence aux dessins annexés dans lesquels :

  • la figure 1 est une demi-vue schématique partielle en coupe axiale d'une turbine basse-pression de turboréacteur équipée d'un dispositif selon l'invention ;
  • la figure 2 est une vue schématique agrandie d'une partie de la figure 1 illustrant le dispositif de limitation de survitesse de la turbine selon l'invention en position de repos ;
  • la figure 3 est une vue semblable à la figure 2 illustrant le dispositif de limitation de survitesse de la turbine en position active.
Other advantages and characteristics of the invention will appear on reading the following description given by way of nonlimiting example and with reference to the appended drawings in which:
  • FIG. 1 is a partial schematic half-view in axial section of a low-pressure turbojet turbine equipped with a device according to the invention;
  • Figure 2 is an enlarged schematic view of a portion of Figure 1 illustrating the overspeed limitation device of the turbine according to the invention in the rest position;
  • Figure 3 is a view similar to Figure 2 illustrating the overspeed limitation device of the turbine in the active position.

On se réfère d'abord à la figure 1 qui représente un rotor de turbine basse-pression comprenant quatre disques 12, 14, 16, 18 assemblés axialement les uns aux autres par des brides annulaires 20 et portant des aubes 22 qui sont montées par des pieds d'aube à leur extrémité radialement interne dans des rainures de la périphérie extérieure des disques 12, 14, 16, 18. Le rotor est relié à l'arbre de turbine 24 par l'intermédiaire d'un cône d'entraînement 26 fixé au moyen d'une bride annulaire 28 entre les brides annulaires 20 des disques 14 et 16.Referring first to Figure 1 which shows a low pressure turbine rotor comprising four discs 12, 14, 16, 18 assembled axially to each other by annular flanges 20 and carrying blades 22 which are mounted by means of blade roots at their radially inner end in grooves in the outer periphery of the discs 12, 14, 16, 18. The rotor is connected to the turbine shaft 24 via a fixed drive cone 26 by means of an annular flange 28 between the annular flanges 20 of the discs 14 and 16.

Entre les étages d'aubes mobiles 22 se trouvent des étages d'aubes fixes 30 qui sont montées par des moyens appropriés à leurs extrémités radialement externes sur un carter 32 de la turbine basse-pression.Between the stages of moving blades 22 are fixed blade stages 30 which are mounted by appropriate means at their radially outer ends on a housing 32 of the low-pressure turbine.

Un dispositif 40 de limitation de vitesse de la turbine selon l'invention est monté sur la surface extérieure d'un carter d'échappement 34 auquel est lié le carter de turbine 32. Le dispositif 40 ainsi positionné est associé au dernier étage de la turbine, mail il est possible de l'utiliser pour n'importe quel étage.A device 40 for limiting the speed of the turbine according to the invention is mounted on the outer surface of an exhaust casing 34 to which is connected the turbine casing 32. The device 40 thus positioned is associated on the top floor of the turbine, it is possible to use it for any floor.

La turbine est en outre équipée de moyens de détection d'une survitesse de rotation du rotor ou d'une rupture de l'arbre 24 de cette turbine, représentés schématiquement en 36.The turbine is furthermore equipped with means for detecting an overspeed of rotation of the rotor or a rupture of the shaft 24 of this turbine, shown schematically at 36.

Comme on le voit mieux en figure 2, le dispositif de limitation de survitesse 40 comprend une goupille 42 en métal très dur logée dans un cylindre 44, qui comporte à son extrémité appliqué sur le carter 34 un rebord latéral 46 fixé par une ou des vis 48 à une platine 50 formée sur la surface extérieure du carter 34, le cylindre 44 étant ouvert à son extrémité fixée sur le carter et fermé à son autre extrémité.As best seen in FIG. 2, the overspeed limiting device 40 comprises a pin 42 made of very hard metal housed in a cylinder 44, which has at its end applied to the casing 34 a lateral rim 46 fixed by one or more screws 48 to a plate 50 formed on the outer surface of the housing 34, the cylinder 44 being open at its end fixed on the housing and closed at its other end.

La goupille 42 comprend un corps cylindrique 52 comportant respectivement, à ses deux extrémités, une pointe 56 et une tête 54, cette dernière présentant un diamètre supérieur à celui du corps cylindrique 52, de manière à former un organe de retenue de la goupille dans le cylindre. La tête 54 est au voisinage de l'extrémité fermée du cylindre 44 tandis que la pointe 56 fait face à son extrémité ouverte.The pin 42 comprises a cylindrical body 52 respectively comprising, at its two ends, a tip 56 and a head 54, the latter having a diameter greater than that of the cylindrical body 52, so as to form a retaining member of the pin in the cylinder. The head 54 is in the vicinity of the closed end of the cylinder 44 while the tip 56 faces its open end.

Une charge explosive représentée schématiquement en 38 et éventuellement des pastilles d'acide de sodium ou d'une autre matière génératrice de gaz sont placées à l'intérieur du cylindre, dans l'espace libre 58 entre la tête 54 de la goupille et l'extrémité fermée du cylindre.An explosive charge shown schematically at 38 and optionally sodium acid pellets or other gas generating material are placed inside the cylinder, in the free space 58 between the head 54 of the pin and the closed end of the cylinder.

Le cylindre 44 est monté dans l'alignement d'un orifice 60 du carter 34 qui débouche sur le trajet des aubes 22 du dernier étage du rotor de la turbine. Cet orifice 60 a un diamètre légèrement supérieur à celui du corps cylindrique 52, et inférieur à celui de la tête 54.The cylinder 44 is mounted in alignment with an orifice 60 of the housing 34 which opens on the path of the blades 22 of the last stage of the rotor of the turbine. This orifice 60 has a diameter slightly greater than that of the cylindrical body 52, and smaller than that of the head 54.

Dans la position de repos représentée à la figure 2, la goupille 42 est logée entièrement dans le cylindre 44 et l'orifice 60 est obstrué par un opercule d'une matière, telle qu'une résine ou un mastic, résistant aux températures de fonctionnement de la turbomachine et propre à être perforée par la pointe 56 de la goupille 42 sous l'effet d'une forte poussée.In the rest position shown in Figure 2, the pin 42 is housed entirely in the cylinder 44 and the orifice 60 is obstructed by a seal of a material, such as a resin or putty, resistant to operating temperatures the turbomachine and adapted to be perforated by the tip 56 of the pin 42 under the effect of a strong thrust.

Des moyens de connexion électrique 64 sont montés sur un support latéral 62 lié au cylindre 44 et au rebord latéral de fixation 46, pour permettre la commande de la charge explosive par les moyens 36 de détection d'une survitesse de rotation de la turbine ou d'une rupture de l'arbre 24 de cette turbine.Electrical connection means 64 are mounted on a lateral support 62 connected to the cylinder 44 and to the lateral attachment flange 46, to enable the control of the explosive charge by the means 36 for detecting an overspeed of rotation of the turbine or of a rupture of the shaft 24 of this turbine.

Le dispositif décrit ci-dessus fonctionne de la façon suivante :

  • lorsqu'un départ en survitesse du rotor de la turbine est détecté, suite à une rupture de l'arbre de turbine 24, ou lorsqu'une rupture de l'arbre de turbine 24 est détectée, les moyens de détection 36 engendrent un signal appliqué aux moyens de connexion 64 pour déclencher l'explosion de la charge explosive 38, ce qui provoque une libération brutale d'azote par les pastilles d'acide de sodium. Le signal peut aussi déclencher l'ouverture d'une vanne entraînant une alimentation en gaz sous pression provenant d'un réservoir de stockage ou prélevé sur le moteur.
The device described above operates as follows:
  • when an overspeed departure of the rotor of the turbine is detected, following a rupture of the turbine shaft 24, or when a rupture of the turbine shaft 24 is detected, the detection means 36 generate an applied signal the connection means 64 for triggering the explosion of the explosive charge 38, which causes a sudden release of nitrogen by the sodium acid pellets. The signal can also trigger the opening of a valve causing a supply of pressurized gas from a storage tank or taken from the engine.

Sous l'effet de la forte poussée exercée par les gaz sur sa tête 54, la goupille perce alors par sa pointe 56 l'opercule obstruant l'orifice 60, et est projetée vers l'intérieur de la turbine à travers l'orifice 60, jusqu'à ce que la tête 54 vienne buter contre le bord de l'orifice 60, comme montré en figure 3.Under the effect of the strong thrust exerted by the gas on its head 54, the pin then pierces through its point 56 the seal obstructing the orifice 60, and is projected inwardly of the turbine through the orifice 60 , until the head 54 abuts against the edge of the orifice 60, as shown in FIG.

Une partie de la goupille 42 se trouve alors sur le trajet des aubes mobiles 22 précitées, de telle sorte que ces aubes viennent se briser contre elle.Part of the pin 42 is then in the path of the aforementioned moving blades 22, so that these vanes are broken against it.

La destruction des aubes mobiles empêche tout risque de survitesse du rotor de la turbine.The destruction of the blades prevents any risk of overspeed of the rotor of the turbine.

Le temps de réponse du dispositif selon l'invention est très court : environ 40 millisecondes (10 ms pour la détection de la survitesse et 30 ms pour l'explosion de la charge et la projection de la goupille), alors que le temps de réponse des dispositifs connus de la technique antérieure est supérieur à 100 ms.The response time of the device according to the invention is very short: about 40 milliseconds (10 ms for the detection of the overspeed and 30 ms for the explosion of the load and the projection of the pin), while the response time devices known from the prior art is greater than 100 ms.

Claims (12)

Dispositif (40) de limitation de survitesse dans une turbomachine en cas de rupture de l'arbre de turbine (24), comprenant des moyens de cisaillement des aubes mobiles (22) d'au moins un étage de la turbine, caractérisé en ce que ces moyens de cisaillement comprennent des moyens de projection (38, 44) d'une goupille (42) sur le trajet des aubes mobiles (22), ces moyens de projection étant montés sur un carter (32, 34) de la turbine ou de la turbomachine et commandés par des moyens (36) de détection d'une survitesse de rotation de la turbine ou de détection d'une rupture de l'arbre de cette turbine.Device (40) for limiting overspeed in a turbomachine in case of rupture of the turbine shaft (24), comprising shearing means of the blades (22) of at least one stage of the turbine, characterized in that these shearing means comprise means (38, 44) for projecting a pin (42) on the path of the blades (22), said projection means being mounted on a casing (32, 34) of the turbine or of the turbomachine and controlled by means (36) for detecting an overspeed of rotation of the turbine or for detecting a rupture of the shaft of this turbine. Dispositif selon la revendication 1, caractérisé en ce que les moyens de projection comprennent une capsule (38) de matière explosive logée dans un cylindre (44) de guidage de la goupille (42).Device according to claim 1, characterized in that the projection means comprise a capsule (38) of explosive material housed in a cylinder (44) for guiding the pin (42). Dispositif selon la revendication 2, caractérisé en ce que le cylindre (44) contient également des pastilles d'une matière de génération de gaz, telle par exemple que de l'acide de sodium.Device according to claim 2, characterized in that the cylinder (44) also contains pellets of a gas generating material, such as, for example, sodium acid. Dispositif selon la revendication 1, caractérisé en ce que les moyens de projection de la goupille (42) sont reliés à une source de gaz sous pression.Device according to claim 1, characterized in that the projection means of the pin (42) are connected to a source of gas under pressure. Dispositif selon l'une des revendications 1 à 3, caractérisé en ce que le cylindre (44) est monté à l'extérieur du carter (32, 34) dans l'alignement d'un orifice (60) de ce carter débouchant sur le trajet des aubes mobiles (22), et comprend une extrémité ouverte par laquelle il est fixé sur le carter, son autre extrémité étant fermée et contenant la capsule (38) de matière explosive.Device according to one of claims 1 to 3, characterized in that the cylinder (44) is mounted outside the housing (32, 34) in alignment with an orifice (60) of this casing opening on the moving blade path (22), and includes an open end by which it is fixed to the housing, its other end being closed and containing the capsule (38) of explosive material. Dispositif selon la revendication 5, caractérisé en ce qu'en condition de repos avant détection d'un départ en survitesse, la goupille (42) est logée entièrement à l'intérieur du cylindre (44) et comporte une tête (54) située du côté de l'extrémité fermée du cylindre et reliée à un corps cylindrique (52) ayant un diamètre inférieur à celui de la tête (54), l'extrémité du corps opposé à la tête (54) étant guidée en coulissement dans l'extrémité du cylindre (44) fixée sur le carter (32, 34).Device according to Claim 5, characterized in that, in a rest condition before detecting an overspeed start, the pin (42) is housed entirely inside the cylinder (44) and comprises a head (54) located side of the closed end of the cylinder and connected to a cylindrical body (52) having a diameter smaller than that of the head (54), the end of the body opposite the head (54) being slidably guided in the end of the cylinder (44) fixed on the housing (32, 34). Dispositif selon la revendication 6, caractérisé en ce que la tête (54) de la goupille (42) a un diamètre supérieur à celui de l'extrémité ouverte du cylindre (44) et forme un organe de retenue de la goupille dans le cylindre.Device according to claim 6, characterized in that the head (54) of the pin (42) has a diameter greater than that of the open end of the cylinder (44) and forms a retaining member of the pin in the cylinder. Dispositif selon l'une des revendications 5 à 7, caractérisé en ce que l'orifice (60) du carter (32, 34) est fermé par un opercule de matière résistant aux températures de fonctionnement de la turbomachine et propre à être rompue par la goupille (42) en cas de détection d'un départ en survitesse.Device according to one of claims 5 to 7, characterized in that the orifice (60) of the housing (32, 34) is closed by a cover of material resistant to the operating temperatures of the turbomachine and capable of being broken by the pin (42) in case of detection of an overspeed departure. Dispositif selon l'une des revendications 5 à 8, caractérisé en ce que la goupille (42) comporte une pointe (56) formée à l'extrémité de son corps cylindrique en regard de l'orifice (60) du carter.Device according to one of claims 5 to 8, characterized in that the pin (42) has a tip (56) formed at the end of its cylindrical body facing the orifice (60) of the housing. Dispositif selon l'une des revendications 5 à 9, caractérisé en ce que le cylindre (44) comprend, à son extrémité ouverte, un rebord latéral (46) de fixation au carter.Device according to one of claims 5 to 9, characterized in that the cylinder (44) comprises at its open end, a lateral flange (46) for attachment to the housing. Dispositif selon l'une des revendications 5 à 10, caractérisé en ce que le cylindre (44) comporte un support (62) de moyens de connexion électrique (64) de la charge explosive (38) aux moyens (36) de détection de survitesse de rotation de la turbine ou de rupture de l'arbre (24) de cette turbine.Device according to one of Claims 5 to 10, characterized in that the cylinder (44) comprises a support (62) for electrical connection means (64) for the explosive charge (38) to the overspeed detection means (36). rotating the turbine or breaking the shaft (24) of this turbine. Turbomachine, telle qu'un turboréacteur d'avion, caractérisée en ce qu'elle est équipée d'un dispositif de limitation de survitesse décrit dans l'une des revendications précédentes.Turbomachine, such as an aircraft turbojet, characterized in that it is equipped with an overspeed limitation device described in one of the preceding claims.
EP07291199A 2006-10-30 2007-10-02 Overspeed limitation device for the turbine of a turbomachine and corresponding turbomachine Active EP1921274B1 (en)

Applications Claiming Priority (1)

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FR0609502A FR2907840B1 (en) 2006-10-30 2006-10-30 DEVICE FOR LIMITING TURBINE OVERVIEW IN A TURBOMACHINE

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JP5114797B2 (en) 2013-01-09
CA2608267C (en) 2014-08-05
JP2008111436A (en) 2008-05-15
FR2907840A1 (en) 2008-05-02
RU2451188C2 (en) 2012-05-20
FR2907840B1 (en) 2008-12-26
CA2608267A1 (en) 2008-04-30
US8057160B2 (en) 2011-11-15
DE602007002248D1 (en) 2009-10-15
RU2007139920A (en) 2009-05-10
EP1921274B1 (en) 2009-09-02

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