EP1605139A1 - Turbomachine with axial retention means for the rotor - Google Patents

Turbomachine with axial retention means for the rotor Download PDF

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Publication number
EP1605139A1
EP1605139A1 EP05105129A EP05105129A EP1605139A1 EP 1605139 A1 EP1605139 A1 EP 1605139A1 EP 05105129 A EP05105129 A EP 05105129A EP 05105129 A EP05105129 A EP 05105129A EP 1605139 A1 EP1605139 A1 EP 1605139A1
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EP
European Patent Office
Prior art keywords
bearing
turbomachine
fixed structure
decoupling
support
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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
EP05105129A
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German (de)
French (fr)
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EP1605139B1 (en
Inventor
Guy Lapergue
Régis Servant
Gael Bouchy
Alain Baum
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Safran Aircraft Engines SAS
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SNECMA SAS
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Publication of EP1605139A1 publication Critical patent/EP1605139A1/en
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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
    • F01D21/04—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
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings

Definitions

  • the invention relates to the field of turbomachines and in particular turbofan engines with fan attached to a drive shaft which is supported by at least a first landing.
  • Such a turbojet engine comprises, from upstream to downstream in the direction of the flow gases, a blower, one or more stages of compressors, a chamber of compression, one or more stages of turbines and a gas exhaust nozzle.
  • the fan comprises a rotor provided with vanes at its periphery which, when they are rotated, drive the air in the turbojet engine.
  • the fan rotor is supported by the low pressure rotor shaft of the motor. It is centered on the axis of turbojet engine by a first bearing which is upstream of a second bearing connected to the fixed structure, in particular the intermediate casing.
  • blower is mounted integral with the compressor shaft, which is the low pressure rotor shaft in a double-body engine, this shaft is designated by the single term compressor shaft.
  • the first bearing is supported by a support piece, forming a envelope around the compressor shaft, facing downstream of the first landing and fixed to a fixed structure of the turbojet engine.
  • the second tier is supported by a support piece also fixed to a fixed structure of the turbojet engine.
  • the support piece of the first landing is attached to the structure of the turbojet engine by said fusible screws, comprising a portion weakened causing their breakage in case of excessive effort. So, at the appearance of unbalance on the compressor shaft, the forces induced on the first bearing are transmitted to the fusible screws which break, uncoupling the support part of the first bearing of the turbojet engine structure.
  • the support of second tier is associated with that of the first landing to accompany him in case of decoupling, or includes its own decoupling system, independent of that of the first landing. After decoupling, the forces caused by the unbalance are no longer transmitted to the fixed structure of the turbojet engine by the support parts of the bearing or bearings.
  • the patent FR 2, 752, 024 proposes in this case to provide, on the fixed structure of turbojet, a rib surrounding the support part of the first bearing, of which here is solidary that of the second bearing, and fulfilling a function of limiter of movements or emergency landing.
  • the rib proposed in the patent FR 2, 752, 024 can however ensure, in case of rupture of the compressor shaft, a function of axial retention of the rotor of the fan, the fixing flange of the support part of the first bearing to the fixed structure the turbojet then abutting on a radial wall of this rib.
  • the present invention aims to overcome these disadvantages.
  • the invention relates to a turbomachine, extending longitudinally along an axis, comprising a rotor, integral with a drive shaft, arranged to rotate about an axis, supported by at least a first bearing, mounted on the fixed structure of the turbomachine by a bearing support piece, characterized in that it comprises a stop ring, mounted on the fixed structure of the turbomachine to cooperate with the support part of the first bearing and ensure, in case of displacement of the rotor relative to the fixed structure, a function axially retaining the rotor, homogeneously, without effect of angle between the axis of the turbomachine and the axis of the drive shaft.
  • the axial retention of the rotor for example in the case of a rupture of the compressor shaft following the loss of a blade of the fan, if the rotor is a fan rotor, is homogeneous regardless of the angle between the axis of the compressor and the axis of the turbomachine at the time of retention. This angle, which can vary due to the unbalance suffered by the tree, does not affect the restraint axial rotor.
  • the support part of the first bearing has a bearing intended to cooperate with the surface of a bead of the stop ring.
  • the scope is of frustoconical shape.
  • the surface of the bead of the stop ring presents in axial section a curved shape, symmetrical of revolution around the axis of the turbine engine.
  • the curved shape is an arc of a circle.
  • the stop ring longitudinally belts the downstream portion of the bearing part of the first bearing, without contact in normal operating mode of the turbomachine.
  • the drive shaft being supported by a second bearing
  • the second bearing being mounted on the fixed structure of the turbomachine by a bearing support part
  • the support part of the first bearing is attached to the supporting part of the second bearing by means of fusible screws allowing its decoupling of the support part of the second bearing.
  • the drive shaft being supported by a second bearing
  • the second bearing being mounted on the fixed structure of the turbomachine by a bearing support part, fixed by screws
  • the stop ring has longitudinal recesses allowing the passage of said screws to ensure fixing the stop ring to the fixed structure of the turbomachine.
  • the support piece of the first bearing being mounted on the fixed structure of the turbomachine by a device allowing its decoupling with respect to the fixed structure of the turbomachine, the stop ring is arranged so as not to interfere with the decoupling phase.
  • the support part of the first bearing being mounted on the fixed structure of the turbomachine by a device allowing its decoupling with respect to the fixed structure of the turbomachine, the stop ring is arranged to limit the deflections of the compressor shaft during the phase of decoupling.
  • the second bearing is mounted on the fixed structure of the turbomachine by a device allowing its decoupling by relative to the fixed structure of the turbomachine.
  • the stop ring ensures in particular the axial retention of the rotor in case of breakage of the drive shaft after decoupling the first landing.
  • the invention is particularly applicable to a double-body turbojet engine, whose second bearing is a bearing supporting the low pressure rotor, but the applicant does not intend to limit the scope of its rights to this application.
  • the turbojet engine 1 of the invention comprises a blower 2, whose rotor comprises blades 3 extending radially around the axis 4 of the turbojet.
  • the fan shaft 2 is fixed, downstream of the blades 3, to the shaft of the compressor 5. This is the low pressure compressor shaft.
  • the compressor shaft 5 is supported by a first bearing 6 and a second bearing 7, located downstream of the first bearing 6.
  • the first bearing 6 comprises an inner ring 8 and an outer ring 9, between which are mounted balls 10 or other rolling members.
  • the ring internal 8 is mounted integral with the compressor shaft 5 and the integral outer ring a bearing support member 11, referred to in the following support of the first bearing 11.
  • the balls 10 allow the rotation of the inner ring 8, therefore of the shaft of the compressor 5, with respect to the outer ring 9, thus to the support of the first bearing 11.
  • the support of the first bearing 11 extends, from the first step 6, towards the downstream; it is of slightly frustoconical shape, its diameter increasing downstream.
  • the second bearing 7 comprises an inner ring 14 and an outer ring 15, between which are mounted rollers 16 or other rolling members.
  • the ring internal 14 is mounted integral with the compressor shaft 5 and the outer ring 15 is fixed mounting of the fixed structure of the turbojet engine 1.
  • the rollers 16 are mounted parallel to the axis 4 of the turbojet engine 1, in a groove extending at the circumference of the inner ring 14, and are held spaced from each other by a cage, although known to those skilled in the art. They allow the rotation of the inner ring 14 by relative to the outer ring 15, and therefore via the compressor shaft 5 with respect to the fixed structure of the turbojet engine 1.
  • the second bearing 7 is supported by a bearing support piece 19, named thereafter support of the second bearing 19, presenting generally in the form a flange extending transversely to the axis 4 of the turbojet engine 1.
  • the outer ring 15 of the second bearing 7 comprises, on its outer face, a radial flange 20 fixed to the supporting the second bearing 19 by screws 21.
  • the support of the second bearing 19 is fixed by a radial flange 22, to the fixed structure of the turbojet engine 1, here to a housing 23 said crankcase intermediate 23, by screws 24.
  • the support of the first bearing 11 has at its downstream end a portion stop 26, here of greater thickness than its upstream portion.
  • This stop portion 26 presents in axial section a section in the shape of a right triangle.
  • the inner wall 27 of this stop portion 26 is of cylindrical shape, its downstream wall 28 extends transversely to the axis 4 of the turbojet engine, the inner 27 and downstream 28 walls being connected by a wall 29 having a generally frustoconical surface, the diameter of which increases downstream, and which corresponds to the hypotenuse of the right triangle defined by the portion stop 26 in axial section.
  • the support of the first landing 11 thus presents, in its downstream part, a frustoconical bearing surface 29 constituted by the frustoconical wall 29.
  • the stop portion 26 has longitudinal recesses 26 'allowing the passage of fusible screws 25 for fixing the support of the first bearing 11 to the flange 22 of the support of the second bearing 19.
  • These fusible screws 25 are radially located between the axis 4 of the turbojet engine 1 and the screws 24 for fixing the support of the second bearing 19 to the intermediate housing 23.
  • These fusible screws 25 comprise a portion of lower section 25 ', having a determined tensile strength which causes them to break in cases of excessive effort, especially when an imbalance appears on the tree of the compressor 5, following for example the loss of a blade 3.
  • the intermediate casing 23 supports a stop ring 30, which extends around the stop portion 26 of the support of the first bearing 11, longitudinally encircling it, without any contact between them during normal operation of the turbojet engine 1.
  • This stop ring 30 is of frustoconical shape, its diameter increasing towards the rear, its inner walls 30 'and outer 30 "being here approximately parallel over the majority of its length. It comprises, at its downstream end, a radial flange 31 by which it is fixed to the intermediate casing 23, here by the screws 24 for fixing the support of the second bearing 19 to intermediate casing 23.
  • the stop ring 30 has, at its upstream end, a bead 32 making protruding radially inwards.
  • the inner surface 33 of the bead 32 is of a shape convex curve, in axial section, according to a curve schematized in FIG. curve portion 33 '.
  • the stop ring 30 is arranged so that the surface of the reach frustoconical 29 of the support of the first bearing 11 can abut on the surface 33 of its bead 32, if the support of the first bearing 11 is made to be driven axially forward.
  • the function of the stop ring 30 is to block axially, through the support of the first bearing 11, the compressor shaft 5 into case of rupture, so that the blower 2 which is attached to it is not driven towards forward in this case, as will be explained later.
  • the induced forces cause the fusible screws to rupture. fixing the support of the first bearing 11 to the support of the second bearing 19, level of their weakened portion 25 '.
  • the fusible screws 25 do not all break at the same time time, but usually gradually.
  • a fusible screw 25 is broken, on the underside of the figure, while the fusible screw 25 on the higher is still intact.
  • the unbalance induced a flexion of the compressor shaft 5, whose axis 5 'is inclined relative to the axis 4 of the turbojet engine 1. This bending of the compressor shaft 5 is allowed by a sliding of rolls of the second bearing 7 on their outer ring 15, with that said a probable deterioration of this level 7.
  • the support of the first bearing 11, integral with the compressor shaft 5, is same stroke also inclined with respect to the axis 4 of the turbojet engine 1.
  • the surface of the frustoconical bearing 29 of the first bearing 11 can then abut on the surface of the wall 33 of the bead 32 of the stop ring 30, in the regions where the fusible screws 25 broke. Due to the duly optimized shape of the surface 33 of the bead 32, the angle has no effect on this contact, which is homogeneous regardless the angle considered.
  • the stop ring 30 allows, in the form of described here, to limit somewhat the bending of the compressor shaft 5, homogeneous way. This flexion can also be limited, as is generally the case, because of the consumption of the game between the ends of the blades 3 of the blower 2 and their retention housing.
  • the longitudinal distance between the span frustoconical 29 of the support of the first bearing 11 and the bead 32 of the stop ring 30 can be dimensioned so that the surfaces of the frustoconical wall 29 and the bead 32 never come into contact during the decoupling phase, in order not to not interfere with it. It is besides this form of realization which will be preferred, in which the stop ring 30 provides only an axial stop function and not Radial movement limitation function.
  • the support of the first bearing 11 is decoupled from the support of the second bearing 19, therefore of the intermediate casing 23, that is to say that it is decoupled from the fixed structure of the turbojet engine 1.
  • the forces are no longer transmitted to the fixed structure of the turbojet by the support of the first bearing 11 and the compressor shaft 5 can freely rotate on its axis 5 ', the frustoconical bearing surface 29 of the support of the first bearing 11 and the bead 32 of the stop ring 30 not being in contact.
  • the support of the first bearing 11 is then also driven forward, and the rollers 16 of the second bearing 7, which slide on their outer ring 15.
  • this forward leakage is stopped thanks to the stop ring 30, integral with the fixed structure of the turbojet engine 1.
  • the frustoconical bearing surface 29 of the support of the first bearing 11 abuts on the wall 33 of the bead 32 of the stop ring 30, which thus ensures the axial stop of the support of the first bearing 11 and therefore of the fan 2, which is not expelled from the turbojet.
  • the rotation of the blower 2 can be prolonged somewhat, before stopping by friction.
  • the curve 33 'defining the inner surface 33 of the bead 32 is optimized so that the abutment of the bearing surface 29 of the first bearing 11 on this surface 33, and therefore the axial stop of the blower 2, is done homogeneously, independent of the angle that can exist between the axis 5 'of the compressor shaft 5 with the axis 4 of the turbojet engine 1.
  • This curved shape of the inner surface 33 of the bead 32 is a meridian curve, in an axial plane, symmetrical of revolution around the axis 4 of the turbojet.
  • the curve 33 ' is here, in axial sectional view, of circular shape.
  • This curve 33 'could be of more complex shape, for example to respect the different phases of decoupling - with or without contact depending on the steps.
  • the invention has been described in connection with the support of the first level fixed to the fixed structure of the turbojet engine via the support of the second bearing, while the stop ring is fixed to the fixed structure of the turbojet engine by the fixing screws of the second bearing support to this fixed structure. It goes without saying that the first support of bearing, the second bearing support and the stop ring could be attached to the fixed structure of the turbojet independently of one another and to fill the same functions that have been described.
  • the support of the second bearing could be fixed at this structure by fusible screws.
  • the decoupling of the two levels would be possible, the axial stop by the stop ring intervenes only in case of breakage of the shaft of the compressor.
  • the downstream bearing 29 of the first bearing 11 has here been described with a frustoconical shape. It goes without saying that it could also have a curved shape, in sectional view axial shape, this shape being optimized in correlation with the curve 33 'that the 33 surface of the bead 33 of the stop ring 30 so that the stop of the blower is do it in a homogeneous way, without angle effect.
  • stop ring 30 could also provide a function an emergency bearing, acting as a bearing for the compressor shaft 5, in case of rupture of the latter after decoupling of the first bearing 6.
  • turbojet engine in particular a double-body turbojet engine, the second bearing of which is a bearing supporting the rotor low pressure.
  • turbomachines such as a turboprop, an industrial turbocharger or an industrial turbine, the rotor not being then a fan rotor but simply a rotor.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Supercharger (AREA)
  • Mounting Of Bearings Or Others (AREA)

Abstract

The turbomachine has an air blower (2) integral to a compressor shaft (5) supported by a bearing (6) mounted on turbomachine`s fixed structure by a bearing support part (11). A spring retaining ring (30) is mounted on the structure to cooperate with the part and ensure, when the blower`s rotor is displaced relative to the structure, axial retaining function of the rotor independent of an angle between axes of the turbomachine and shaft.

Description

L'invention concerne le domaine des turbomachines et en particulier des turboréacteurs avec soufflante solidaire d'un arbre d'entraínement qui est supporté par au moins un premier palier.The invention relates to the field of turbomachines and in particular turbofan engines with fan attached to a drive shaft which is supported by at least a first landing.

Un tel turboréacteur comprend, d'amont en aval dans le sens de l'écoulement des gaz, une soufflante, un ou plusieurs étages de compresseurs, une chambre de compression, un ou plusieurs étages de turbines et une tuyère d'échappement des gaz. La soufflante comporte un rotor pourvu d'aubes à sa périphérie qui, lorsqu'elles sont mises en rotation, entraínent l'air dans le turboréacteur. Le rotor de soufflante est supporté par l'arbre du rotor basse pression du moteur. Il est centré sur l'axe du turboréacteur par un premier palier qui est en amont d'un deuxième palier relié à la structure fixe, notamment le carter intermédiaire.Such a turbojet engine comprises, from upstream to downstream in the direction of the flow gases, a blower, one or more stages of compressors, a chamber of compression, one or more stages of turbines and a gas exhaust nozzle. The fan comprises a rotor provided with vanes at its periphery which, when they are rotated, drive the air in the turbojet engine. The fan rotor is supported by the low pressure rotor shaft of the motor. It is centered on the axis of turbojet engine by a first bearing which is upstream of a second bearing connected to the fixed structure, in particular the intermediate casing.

Dans la suite de la description, dans la mesure où la soufflante est montée solidaire de l'arbre du compresseur, qui est l'arbre du rotor basse pression dans un moteur à double corps, on désigne cet arbre par l'unique terme arbre du compresseur.In the remainder of the description, to the extent that the blower is mounted integral with the compressor shaft, which is the low pressure rotor shaft in a double-body engine, this shaft is designated by the single term compressor shaft.

Le premier palier est supporté par une pièce de support, formant une enveloppe autour de l'arbre du compresseur, orientée vers l'aval du premier palier et fixée à une structure fixe du turboréacteur. Le deuxième palier est supporté par une pièce de support fixée également à une structure fixe du turboréacteur.The first bearing is supported by a support piece, forming a envelope around the compressor shaft, facing downstream of the first landing and fixed to a fixed structure of the turbojet engine. The second tier is supported by a support piece also fixed to a fixed structure of the turbojet engine.

Il peut se produire, accidentellement, la perte d'une aube de soufflante. Il s'ensuit un balourd important sur l'arbre du compresseur, qui entraíne des charges et des vibrations sur les paliers, transmises par leurs pièces de support aux structures fixes du turboréacteur, qui peuvent de ce fait être endommagées.It can happen, accidentally, the loss of a fan blade. he a major imbalance ensues on the compressor shaft, which causes loads and vibrations on the bearings, transmitted by their supporting parts to the structures turbojet engines, which can therefore be damaged.

Pour prévenir un risque de détérioration trop important du turboréacteur, on peut sur-dimensionner la structure ou, comme dans le brevet FR 2, 752, 024, proposer un système de découplage du premier palier. La pièce de support du premier palier est fixée à la structure du turboréacteur par des vis dites fusibles, comportant une portion affaiblie entraínant leur rupture en cas d'efforts trop importants. Ainsi, à l'apparition du balourd sur l'arbre du compresseur, les efforts induits sur le premier palier sont transmis aux vis fusibles qui cassent, découplant la pièce de support du premier palier de la structure du turboréacteur. Selon d'autres modes de réalisation, le support du deuxième palier est associé à celui du premier palier pour l'accompagner en cas de découplage, ou comprend son propre système de découplage, indépendant de celui du premier palier. Après découplage, les efforts provoqués par le balourd ne sont plus transmis à la structure fixe du turboréacteur par les pièces de support du ou des paliers.To prevent a risk of excessive deterioration of the turbojet engine, can over-size the structure or, as in the patent FR 2, 752, 024, propose a decoupling system of the first stage. The support piece of the first landing is attached to the structure of the turbojet engine by said fusible screws, comprising a portion weakened causing their breakage in case of excessive effort. So, at the appearance of unbalance on the compressor shaft, the forces induced on the first bearing are transmitted to the fusible screws which break, uncoupling the support part of the first bearing of the turbojet engine structure. According to other embodiments, the support of second tier is associated with that of the first landing to accompany him in case of decoupling, or includes its own decoupling system, independent of that of the first landing. After decoupling, the forces caused by the unbalance are no longer transmitted to the fixed structure of the turbojet engine by the support parts of the bearing or bearings.

Toutefois, après le découplage d'un ou des deux paliers, la soufflante continue de tourner et l'arbre du compresseur peut ne plus tourner sur son axe et subir des débattements importants pouvant endommager la structure fixe du turboréacteur. Le brevet FR 2, 752, 024 propose dans ce cas de prévoir, sur la structure fixe du turboréacteur, une nervure entourant la pièce de support du premier palier, dont est ici solidaire celle du deuxième palier, et remplissant une fonction de limiteur de mouvements ou de palier de secours.However, after the decoupling of one or both bearings, the blower continues turn and the compressor shaft may no longer rotate on its axis and suffer large deflections that can damage the fixed structure of the turbojet engine. The patent FR 2, 752, 024 proposes in this case to provide, on the fixed structure of turbojet, a rib surrounding the support part of the first bearing, of which here is solidary that of the second bearing, and fulfilling a function of limiter of movements or emergency landing.

La poursuite de la rotation de la soufflante peut néanmoins entraíner des contraintes sur l'arbre de compresseur et l'arbre de turbine, qui sont solidaires, et provoquer la rupture de l'un des deux, ou des deux. On parlera quel que soit le cas de rupture de l'arbre de compresseur. Dans ce cas, la rotation de la soufflante entraíne cette dernière, ainsi que l'arbre de compresseur dont elle est solidaire, vers l'avant. La soufflante est alors expulsée hors du turboréacteur, ce qui doit être évité.Continued rotation of the blower may nevertheless lead to constraints on the compressor shaft and the turbine shaft, which are integral, and cause the rupture of one or both of them. We will talk about whatever the case rupture of the compressor shaft. In this case, the rotation of the fan causes the latter, as well as the compressor shaft which it is secured, forward. The The blower is then expelled from the turbojet, which must be avoided.

La nervure proposée dans le brevet FR 2, 752, 024 peut toutefois assurer, en cas de rupture de l'arbre de compresseur, une fonction de retenue axiale du rotor de la soufflante, la bride de fixation de la pièce support du premier palier à la structure fixe du turboréacteur venant alors en butée sur une paroi radiale de cette nervure. Toutefois, du fait de la flexion à laquelle peut être soumis l'arbre de compresseur dans cette situation, un angle peut exister entre la paroi de la bride et la paroi de la nervure destinées à venir en butée, impliquant, soit un arrêt peu efficace de l'arbre avec dégradation des éléments par frottement, soit même, si l'angle est trop important, un passage de la bride, inclinée radialement vers l'axe du turboréacteur, au-delà de la nervure et donc l'impossibilité d'endiguer l'avancée de l'arbre de compresseur et du rotor de la soufflante, qui se trouve alors expulsée ou coincée en travers de son carter de rétention, détériorant de ce fait toute la structure du turboréacteur.The rib proposed in the patent FR 2, 752, 024 can however ensure, in case of rupture of the compressor shaft, a function of axial retention of the rotor of the fan, the fixing flange of the support part of the first bearing to the fixed structure the turbojet then abutting on a radial wall of this rib. However, because of the bending to which the compressor shaft can be subjected in this situation, an angle can exist between the wall of the flange and the wall of the rib intended to come to a stop, implying either an inefficient stop of the tree with degradation of the elements by friction, or even, if the angle is too important, a passage of the flange, inclined radially towards the axis of the turbojet engine, beyond the rib and therefore the impossibility of stemming the advance of the compressor shaft and the rotor of the blower, which is then expelled or stuck across its crankcase retention, thereby deteriorating the entire structure of the turbojet engine.

La présente invention vise à pallier ces inconvénients.The present invention aims to overcome these disadvantages.

A cet effet, l'invention concerne une turbomachine, s'étendant longitudinalement suivant un axe, comprenant un rotor, solidaire d'un arbre d'entraínement, agencé pour tourner autour d'un axe, supporté par au moins un premier palier, monté sur la structure fixe de la turbomachine par une pièce support de palier,
caractérisée par le fait qu'elle comprend un anneau d'arrêt, monté sur la structure fixe de la turbomachine pour coopérer avec la pièce de support du premier palier et assurer, en cas de déplacement du rotor par rapport à la structure fixe, une fonction de retenue axiale du rotor, de façon homogène, sans effet d'angle entre l'axe de la turbomachine et l'axe de l'arbre d'entraínement.For this purpose, the invention relates to a turbomachine, extending longitudinally along an axis, comprising a rotor, integral with a drive shaft, arranged to rotate about an axis, supported by at least a first bearing, mounted on the fixed structure of the turbomachine by a bearing support piece,
characterized in that it comprises a stop ring, mounted on the fixed structure of the turbomachine to cooperate with the support part of the first bearing and ensure, in case of displacement of the rotor relative to the fixed structure, a function axially retaining the rotor, homogeneously, without effect of angle between the axis of the turbomachine and the axis of the drive shaft.

Grâce à l'invention, la retenue axiale du rotor, par exemple dans le cas d'une rupture de l'arbre de compresseur faisant suite à la perte d'une aube de la soufflante, si le rotor est un rotor de soufflante, se fait de façon homogène quel que soit l'angle entre l'axe du compresseur et l'axe de la turbomachine au moment de la retenue. Cet angle, qui peut varier en raison du balourd subi par l'arbre, n'influe donc pas sur la retenue axiale du rotor.Thanks to the invention, the axial retention of the rotor, for example in the case of a rupture of the compressor shaft following the loss of a blade of the fan, if the rotor is a fan rotor, is homogeneous regardless of the angle between the axis of the compressor and the axis of the turbomachine at the time of retention. This angle, which can vary due to the unbalance suffered by the tree, does not affect the restraint axial rotor.

De préférence, la pièce de support du premier palier présente une portée destinée à coopérer avec la surface d'un bourrelet de l'anneau d'arrêt.Preferably, the support part of the first bearing has a bearing intended to cooperate with the surface of a bead of the stop ring.

Avantageusement dans ce cas, la portée est de forme tronconique.Advantageously in this case, the scope is of frustoconical shape.

Avantageusement encore, la surface du bourrelet de l'anneau d'arrêt présente en coupe axiale une forme courbe, à symétrie de révolution autour de l'axe de la turbomachine.Advantageously, the surface of the bead of the stop ring presents in axial section a curved shape, symmetrical of revolution around the axis of the turbine engine.

De préférence dans ce cas, la forme courbe est un arc de cercle.In this case, preferably, the curved shape is an arc of a circle.

De préférence, l'anneau d'arrêt ceinture longitudinalement la partie aval de la pièce de support du premier palier, sans contact en mode de fonctionnement normal de la turbomachine.Preferably, the stop ring longitudinally belts the downstream portion of the bearing part of the first bearing, without contact in normal operating mode of the turbomachine.

Selon une forme de réalisation, l'arbre d'entraínement étant supporté par un deuxième palier, le deuxième palier étant monté sur la structure fixe de la turbomachine par une pièce support de palier, la pièce de support du premier palier est fixée à la pièce de support du deuxième palier par des vis fusibles permettant son découplage de la pièce de support du deuxième palier.According to one embodiment, the drive shaft being supported by a second bearing, the second bearing being mounted on the fixed structure of the turbomachine by a bearing support part, the support part of the first bearing is attached to the supporting part of the second bearing by means of fusible screws allowing its decoupling of the support part of the second bearing.

Selon une forme de réalisation, l'arbre d'entraínement étant supporté par un deuxième palier, le deuxième palier étant monté sur la structure fixe de la turbomachine par une pièce support de palier, fixée par des vis, l'anneau d'arrêt comporte des évidements longitudinaux permettant le passage desdites vis pour assurer la fixation de l'anneau d'arrêt à la structure fixe de la turbomachine.According to one embodiment, the drive shaft being supported by a second bearing, the second bearing being mounted on the fixed structure of the turbomachine by a bearing support part, fixed by screws, the stop ring has longitudinal recesses allowing the passage of said screws to ensure fixing the stop ring to the fixed structure of the turbomachine.

Selon un mode de fonctionnement, la pièce de support du premier palier étant montée sur la structure fixe de la turbomachine par un dispositif permettant son découplage par rapport à la structure fixe de la turbomachine, l'anneau d'arrêt est agencé pour ne pas interférer sur la phase de découplage.According to one mode of operation, the support piece of the first bearing being mounted on the fixed structure of the turbomachine by a device allowing its decoupling with respect to the fixed structure of the turbomachine, the stop ring is arranged so as not to interfere with the decoupling phase.

Selon un autre mode de fonctionnement, la pièce de support du premier palier étant montée sur la structure fixe de la turbomachine par un dispositif permettant son découplage par rapport à la structure fixe de la turbomachine, l'anneau d'arrêt est agencé pour limiter les débattements de l'arbre de compresseur lors de la phase de découplage.According to another mode of operation, the support part of the first bearing being mounted on the fixed structure of the turbomachine by a device allowing its decoupling with respect to the fixed structure of the turbomachine, the stop ring is arranged to limit the deflections of the compressor shaft during the phase of decoupling.

Selon un mode de réalisation particulier, le deuxième palier est monté sur la structure fixe de la turbomachine par un dispositif permettant son découplage par rapport à la structure fixe de la turbomachine.According to a particular embodiment, the second bearing is mounted on the fixed structure of the turbomachine by a device allowing its decoupling by relative to the fixed structure of the turbomachine.

De préférence enfin, la pièce de support du premier palier étant montée sur la structure fixe de la turbomachine par un dispositif permettant son découplage par rapport à la structure fixe de la turbomachine, l'anneau d'arrêt assure en particulier la retenue axiale du rotor en cas de rupture de l'arbre d'entraínement après découplage du premier palier.Preferably, finally, the support part of the first bearing being mounted on the fixed structure of the turbomachine by a device allowing its decoupling by compared to the fixed structure of the turbomachine, the stop ring ensures in particular the axial retention of the rotor in case of breakage of the drive shaft after decoupling the first landing.

L'invention s'applique particulièrement à un turboréacteur à double corps, dont le deuxième palier est un palier supportant le rotor basse pression, mais la demanderesse n'entend pas limiter la portée de ses droits à cette application.The invention is particularly applicable to a double-body turbojet engine, whose second bearing is a bearing supporting the low pressure rotor, but the applicant does not intend to limit the scope of its rights to this application.

L'invention sera mieux comprise grâce à la description suivante de la forme de réalisation préférée du turboréacteur de l'invention, en référence aux dessins annexés, sur lesquels :

  • la figure 1 représente une vue en coupe axiale, de profil, de la forme de réalisation préférée de l'invention ;
  • la figure 2 représente une vue agrandie de la zone de la figure 1 contenue dans le cadre C ;
  • la figure 3 représente une vue en coupe axiale, de profil, de la zone du deuxième palier du turboréacteur de la forme de réalisation préférée de l'invention, pendant une phase de découplage, et
  • la figure 4 représente une vue en coupe axiale, de profil, de la zone du deuxième palier du turboréacteur de la forme de réalisation préférée de l'invention, après rupture de l'arbre de compresseur.
The invention will be better understood thanks to the following description of the preferred embodiment of the turbojet engine of the invention, with reference to the appended drawings, in which:
  • Figure 1 shows an axial sectional view, in profile, of the preferred embodiment of the invention;
  • FIG. 2 represents an enlarged view of the area of FIG. 1 contained in frame C;
  • FIG. 3 represents an axial sectional view, in profile, of the zone of the second bearing of the turbojet engine of the preferred embodiment of the invention during a decoupling phase, and
  • FIG. 4 represents an axial sectional view, in profile, of the zone of the second bearing of the turbojet engine of the preferred embodiment of the invention, after rupture of the compressor shaft.

En référence à la figure 1, le turboréacteur 1 de l'invention comprend une soufflante 2, dont le rotor comporte des aubes 3 s'étendant radialement autour de l'axe 4 du turboréacteur. L'arbre de soufflante 2 est fixé, en aval des aubes 3, à l'arbre du compresseur 5. Il s'agit ici de l'arbre du compresseur basse pression. On désignera dans la suite l'ensemble de l'arbre de la soufflante 2 et de l'arbre du compresseur 5 par arbre du compresseur 5, ou arbre d'entraínement 5. L'arbre du compresseur 5 est supporté par un premier palier 6 et un deuxième palier 7, situé en aval du premier palier 6.With reference to FIG. 1, the turbojet engine 1 of the invention comprises a blower 2, whose rotor comprises blades 3 extending radially around the axis 4 of the turbojet. The fan shaft 2 is fixed, downstream of the blades 3, to the shaft of the compressor 5. This is the low pressure compressor shaft. We will designate in following the entire shaft of the blower 2 and the compressor shaft 5 per shaft compressor 5, or drive shaft 5. The compressor shaft 5 is supported by a first bearing 6 and a second bearing 7, located downstream of the first bearing 6.

Le premier palier 6 comporte une bague interne 8 et une bague externe 9, entre lesquelles sont montés des billes 10 ou autres organes de roulement. La bague interne 8 est montée solidaire de l'arbre du compresseur 5 et la bague externe solidaire d'une pièce support de palier 11, appelée dans la suite support du premier palier 11. Les billes 10 autorisent la rotation de la bague interne 8, donc de l'arbre du compresseur 5, par rapport à la bague externe 9, donc au support du premier palier 11.The first bearing 6 comprises an inner ring 8 and an outer ring 9, between which are mounted balls 10 or other rolling members. The ring internal 8 is mounted integral with the compressor shaft 5 and the integral outer ring a bearing support member 11, referred to in the following support of the first bearing 11. The balls 10 allow the rotation of the inner ring 8, therefore of the shaft of the compressor 5, with respect to the outer ring 9, thus to the support of the first bearing 11.

Le support du premier palier 11 s'étend, à partir du premier palier 6, vers l'aval ; il est de forme légèrement tronconique, son diamètre augmentant vers l'aval.The support of the first bearing 11 extends, from the first step 6, towards the downstream; it is of slightly frustoconical shape, its diameter increasing downstream.

Le deuxième palier 7 comporte une bague interne 14 et une bague externe 15, entre lesquelles sont montés des rouleaux 16 ou autres organes de roulement. La bague interne 14 est montée solidaire de l'arbre du compresseur 5 et la bague externe 15 est montée solidaire de la structure fixe du turboréacteur 1. Les rouleaux 16 sont montés parallèles à l'axe 4 du turboréacteur 1, dans une rainure s'étendant à la circonférence de la bague interne 14, et sont tenus espacés les uns des autres par une cage, bien connue de l'homme du métier. Ils permettent la rotation de la bague interne 14 par rapport à la bague externe 15, et donc par leur intermédiaire de l'arbre du compresseur 5 par rapport à la structure fixe du turboréacteur 1.The second bearing 7 comprises an inner ring 14 and an outer ring 15, between which are mounted rollers 16 or other rolling members. The ring internal 14 is mounted integral with the compressor shaft 5 and the outer ring 15 is fixed mounting of the fixed structure of the turbojet engine 1. The rollers 16 are mounted parallel to the axis 4 of the turbojet engine 1, in a groove extending at the circumference of the inner ring 14, and are held spaced from each other by a cage, although known to those skilled in the art. They allow the rotation of the inner ring 14 by relative to the outer ring 15, and therefore via the compressor shaft 5 with respect to the fixed structure of the turbojet engine 1.

Le deuxième palier 7 est supporté par une pièce support de palier 19, nommée par la suite support du deuxième palier 19, se présentant globalement sous la forme d'un flasque s'étendant transversalement à l'axe 4 du turboréacteur 1. La bague externe 15 du deuxième palier 7 comporte, sur sa face externe, une bride radiale 20, fixée au support du deuxième palier 19 par des vis 21. The second bearing 7 is supported by a bearing support piece 19, named thereafter support of the second bearing 19, presenting generally in the form a flange extending transversely to the axis 4 of the turbojet engine 1. The outer ring 15 of the second bearing 7 comprises, on its outer face, a radial flange 20 fixed to the supporting the second bearing 19 by screws 21.

En référence à la figure 2, le support du deuxième palier 19 est fixé, par une bride radiale 22, à la structure fixe du turboréacteur 1, ici à un carter 23 dit carter intermédiaire 23, par des vis 24.With reference to FIG. 2, the support of the second bearing 19 is fixed by a radial flange 22, to the fixed structure of the turbojet engine 1, here to a housing 23 said crankcase intermediate 23, by screws 24.

Le support du premier palier 11 présente à son extrémité aval une portion d'arrêt 26, ici d'épaisseur supérieure à sa partie amont. Cette portion d'arrêt 26 présente en coupe axiale une section en forme de triangle rectangle. La paroi interne 27 de cette portion d'arrêt 26 est de forme cylindrique, sa paroi aval 28 s'étend transversalement à l'axe 4 du turboréacteur, les parois interne 27 et aval 28 étant reliées par une paroi 29 présentant une surface de forme globalement tronconique, dont le diamètre augmente vers l'aval, et qui correspond à l'hypoténuse du triangle rectangle que définit la portion d'arrêt 26 en coupe axiale. Le support du premier palier 11 présente donc, dans sa partie aval, une portée tronconique 29 constituée par la paroi tronconique 29.The support of the first bearing 11 has at its downstream end a portion stop 26, here of greater thickness than its upstream portion. This stop portion 26 presents in axial section a section in the shape of a right triangle. The inner wall 27 of this stop portion 26 is of cylindrical shape, its downstream wall 28 extends transversely to the axis 4 of the turbojet engine, the inner 27 and downstream 28 walls being connected by a wall 29 having a generally frustoconical surface, the diameter of which increases downstream, and which corresponds to the hypotenuse of the right triangle defined by the portion stop 26 in axial section. The support of the first landing 11 thus presents, in its downstream part, a frustoconical bearing surface 29 constituted by the frustoconical wall 29.

La portion d'arrêt 26 comporte des évidements longitudinaux 26' permettant le passage de vis fusibles 25 de fixation du support du premier palier 11 à la bride 22 du support du deuxième palier 19. Ces vis fusibles 25 sont radialement situées entre l'axe 4 du turboréacteur 1 et les vis 24 de fixation du support du deuxième palier 19 au carter intermédiaire 23. Ces vis fusibles 25 comprennent une portion de plus faible section 25', présentant une résistance à la traction déterminée entraínant leur rupture en cas d'efforts trop importants, notamment lors de l'apparition d'un balourd sur l'arbre du compresseur 5, suite par exemple à la perte d'une aube 3.The stop portion 26 has longitudinal recesses 26 'allowing the passage of fusible screws 25 for fixing the support of the first bearing 11 to the flange 22 of the support of the second bearing 19. These fusible screws 25 are radially located between the axis 4 of the turbojet engine 1 and the screws 24 for fixing the support of the second bearing 19 to the intermediate housing 23. These fusible screws 25 comprise a portion of lower section 25 ', having a determined tensile strength which causes them to break in cases of excessive effort, especially when an imbalance appears on the tree of the compressor 5, following for example the loss of a blade 3.

Le carter intermédiaire 23 supporte un anneau d'arrêt 30, qui s'étend autour de la portion d'arrêt 26 du support du premier palier 11, le ceinturant longitudinalement, sans qu'il n'y ait de contact entre eux en fonctionnement normal du turboréacteur 1. Cet anneau d'arrêt 30 est de forme tronconique, son diamètre augmentant vers l'arrière, ses parois interne 30' et externe 30" étant ici à peu près parallèles sur la majorité de sa longueur. Il comporte, à son extrémité aval, une bride radiale 31 par laquelle il est fixé au carter intermédiaire 23, ici par les vis 24 de fixation du support du deuxième palier 19 au carter intermédiaire 23.The intermediate casing 23 supports a stop ring 30, which extends around the stop portion 26 of the support of the first bearing 11, longitudinally encircling it, without any contact between them during normal operation of the turbojet engine 1. This stop ring 30 is of frustoconical shape, its diameter increasing towards the rear, its inner walls 30 'and outer 30 "being here approximately parallel over the majority of its length. It comprises, at its downstream end, a radial flange 31 by which it is fixed to the intermediate casing 23, here by the screws 24 for fixing the support of the second bearing 19 to intermediate casing 23.

L'anneau d'arrêt 30 comporte, à son extrémité amont, un bourrelet 32 faisant saillie radialement vers l'intérieur. La surface interne 33 du bourrelet 32 est de forme courbe convexe, en coupe axiale, suivant une courbe schématisée sur la figure 2 par la portion de courbe 33'. The stop ring 30 has, at its upstream end, a bead 32 making protruding radially inwards. The inner surface 33 of the bead 32 is of a shape convex curve, in axial section, according to a curve schematized in FIG. curve portion 33 '.

L'anneau d'arrêt 30 est agencé de façon à ce que la surface de la portée tronconique 29 du support du premier palier 11 puisse venir en butée sur la surface interne 33 de son bourrelet 32, si le support du premier palier 11 est amené à être entraíné axialement vers l'avant. La fonction de l'anneau d'arrêt 30 est de bloquer axialement, par le biais du support du premier palier 11, l'arbre du compresseur 5 en cas de rupture, afin que la soufflante 2 qui lui est solidaire ne soit pas entraínée vers l'avant dans ce cas, comme il sera expliqué plus loin.The stop ring 30 is arranged so that the surface of the reach frustoconical 29 of the support of the first bearing 11 can abut on the surface 33 of its bead 32, if the support of the first bearing 11 is made to be driven axially forward. The function of the stop ring 30 is to block axially, through the support of the first bearing 11, the compressor shaft 5 into case of rupture, so that the blower 2 which is attached to it is not driven towards forward in this case, as will be explained later.

Le fonctionnement du turboréacteur 1 de l'invention lors de la perte d'une aube 3 de soufflante 2 va maintenant être expliqué plus en détails.The operation of the turbojet engine 1 of the invention during the loss of a Blower dawn 3 will now be explained in more detail.

La perte d'une aube 3 en cours de fonctionnement du turboréacteur 1, donc en cours de rotation de la soufflante 2, provoque un balourd sur l'arbre du compresseur 5. En référence à la figure 3, les efforts induits provoquent la rupture des vis fusibles 25 de fixation du support du premier palier 11 au support du deuxième palier 19, au niveau de leur portion affaiblie 25'. Les vis fusibles 25 ne cassent pas toutes en même temps, mais en général de proche en proche. Sur la figure 3, une vis fusible 25 est représentée cassée, du côté inférieur de la figure, tandis que la vis fusible 25 du côté supérieur est encore intacte. Dans cette situation, le balourd a induit une flexion de l'arbre du compresseur 5, dont l'axe 5' est incliné par rapport à l'axe 4 du turboréacteur 1. Cette flexion de l'arbre du compresseur 5 est autorisée par un glissement des rouleaux du deuxième palier 7 sur leur bague externe 15, avec cela dit une probable détérioration de ce palier 7.The loss of a blade 3 during operation of the turbojet engine 1, so in rotation of the fan 2, causes an unbalance on the compressor shaft 5. With reference to FIG. 3, the induced forces cause the fusible screws to rupture. fixing the support of the first bearing 11 to the support of the second bearing 19, level of their weakened portion 25 '. The fusible screws 25 do not all break at the same time time, but usually gradually. In FIG. 3, a fusible screw 25 is broken, on the underside of the figure, while the fusible screw 25 on the higher is still intact. In this situation, the unbalance induced a flexion of the compressor shaft 5, whose axis 5 'is inclined relative to the axis 4 of the turbojet engine 1. This bending of the compressor shaft 5 is allowed by a sliding of rolls of the second bearing 7 on their outer ring 15, with that said a probable deterioration of this level 7.

Le support du premier palier 11, solidaire de l'arbre du compresseur 5, est du même coup également incliné par rapport à l'axe 4 du turboréacteur 1. La surface de la portée tronconique 29 du premier palier 11 peut alors venir en butée sur la surface de la paroi 33 du bourrelet 32 de l'anneau d'arrêt 30, dans les régions où les vis fusibles 25 ont cassé. Du fait de la forme dûment optimisée de la surface 33 du bourrelet 32, l'angle n'a aucun effet sur ce contact, qui se fait de façon homogène quel que soit l'angle considéré. Ainsi, pendant la phase de découplage du support du premier palier 11 de la structure fixe du turboréacteur 1, l'anneau d'arrêt 30 permet, dans la forme de réalisation ici décrite, de limiter quelque peu la flexion de l'arbre du compresseur 5, de façon homogène. Cette flexion peut par ailleurs être limitée, comme c'est généralement le cas, du fait de la consommation du jeu entre les extrémités des aubes 3 de la soufflante 2 et leur carter de rétention. The support of the first bearing 11, integral with the compressor shaft 5, is same stroke also inclined with respect to the axis 4 of the turbojet engine 1. The surface of the frustoconical bearing 29 of the first bearing 11 can then abut on the surface of the wall 33 of the bead 32 of the stop ring 30, in the regions where the fusible screws 25 broke. Due to the duly optimized shape of the surface 33 of the bead 32, the angle has no effect on this contact, which is homogeneous regardless the angle considered. Thus, during the decoupling phase of the support of the first level 11 of the fixed structure of the turbojet engine 1, the stop ring 30 allows, in the form of described here, to limit somewhat the bending of the compressor shaft 5, homogeneous way. This flexion can also be limited, as is generally the case, because of the consumption of the game between the ends of the blades 3 of the blower 2 and their retention housing.

Selon une autre forme de réalisation, la distance longitudinale entre la portée tronconique 29 du support du premier palier 11 et le bourrelet 32 de l'anneau d'arrêt 30 peut être dimensionnée de façon à ce que les surfaces de la paroi tronconique 29 et du bourrelet 32 ne viennent jamais en contact pendant la phase de découplage, afin de ne pas interférer sur cette dernière. C'est d'ailleurs cette forme de réalisation qui sera préférée, dans laquelle l'anneau d'arrêt 30 n'assure qu'une fonction d'arrêt axial et pas de fonction de limitation de mouvements radiaux.According to another embodiment, the longitudinal distance between the span frustoconical 29 of the support of the first bearing 11 and the bead 32 of the stop ring 30 can be dimensioned so that the surfaces of the frustoconical wall 29 and the bead 32 never come into contact during the decoupling phase, in order not to not interfere with it. It is besides this form of realization which will be preferred, in which the stop ring 30 provides only an axial stop function and not Radial movement limitation function.

Quelle que soit la forme de réalisation, une fois l'ensemble des vis fusibles 25 cassées, le support du premier palier 11 est découplé du support du deuxième palier 19, donc du carter intermédiaire 23, c'est-à-dire qu'il est découplé de la structure fixe du turboréacteur 1. Les efforts ne sont plus alors transmis à la structure fixe du turboréacteur par le support du premier palier 11 et l'arbre du compresseur 5 peut librement tourner sur son axe 5', la portée tronconique 29 du support du premier palier 11 et le bourrelet 32 de l'anneau d'arrêt 30 n'étant pas en contact.Whatever the embodiment, once the set of fusible screws 25 broken, the support of the first bearing 11 is decoupled from the support of the second bearing 19, therefore of the intermediate casing 23, that is to say that it is decoupled from the fixed structure of the turbojet engine 1. The forces are no longer transmitted to the fixed structure of the turbojet by the support of the first bearing 11 and the compressor shaft 5 can freely rotate on its axis 5 ', the frustoconical bearing surface 29 of the support of the first bearing 11 and the bead 32 of the stop ring 30 not being in contact.

Toutefois, la poursuite de la rotation de la soufflante 2 peut entraíner des contraintes sur l'arbre du compresseur 5 et l'arbre de turbine, qui sont solidaires, et provoquer la rupture de l'un des deux, ou des deux. On parle alors, comme il a été vu précédemment, de rupture de l'arbre du compresseur 5. Dans ce cas, la rotation de la soufflante 2 entraíne cette dernière, ainsi que l'arbre du compresseur 5 qui lui est solidaire, vers l'avant.However, the continued rotation of the blower 2 can lead to constraints on the compressor shaft 5 and the turbine shaft, which are integral, and cause the rupture of one or both of them. We speak then, as it was seen previously, breakage of the compressor shaft 5. In this case, the rotation of the blower 2 drives the latter, and the compressor shaft 5 which is solidary, forward.

Le support du premier palier 11 est alors également entraíné vers l'avant, ainsi que les rouleaux 16 du deuxième palier 7, qui glissent sur leur bague externe 15. En référence à la figure 4, cette fuite en avant est arrêtée grâce à l'anneau d'arrêt 30, solidaire de la structure fixe du turboréacteur 1. En effet, lors de la fuite vers l'avant du support du premier palier 11, la portée tronconique 29 du support du premier palier 11 vient en butée sur la paroi 33 du bourrelet 32 de l'anneau d'arrêt 30, qui assure ainsi l'arrêt axial du support du premier palier 11 et donc de la soufflante 2, qui n'est pas expulsée hors du turboréacteur. La rotation de la soufflante 2 peut se prolonger quelque peu, avant de s'arrêter par frottements.The support of the first bearing 11 is then also driven forward, and the rollers 16 of the second bearing 7, which slide on their outer ring 15. In reference to FIG. 4, this forward leakage is stopped thanks to the stop ring 30, integral with the fixed structure of the turbojet engine 1. Indeed, during the flight towards the front of the support of the first bearing 11, the frustoconical bearing surface 29 of the support of the first bearing 11 abuts on the wall 33 of the bead 32 of the stop ring 30, which thus ensures the axial stop of the support of the first bearing 11 and therefore of the fan 2, which is not expelled from the turbojet. The rotation of the blower 2 can be prolonged somewhat, before stopping by friction.

La courbe 33' définissant la surface interne 33 du bourrelet 32 est optimisée de façon à ce que la butée de la portée 29 du premier palier 11 sur cette surface 33, et donc l'arrêt axial de la soufflante 2, se fasse de façon homogène, indépendante de l'angle pouvant exister entre l'axe 5' de l'arbre du compresseur 5 avec l'axe 4 du turboréacteur 1. Cette forme courbe de la surface interne 33 du bourrelet 32 est une courbe méridienne, dans un plan axial, à symétrie de révolution autour de l'axe 4 du turboréacteur. La courbe 33' est ici, en vue en coupe axiale, de forme circulaire. Cette courbe 33' pourrait être de forme plus complexe, afin par exemple de respecter les différentes phases du découplage - avec ou sans contact selon les étapes.The curve 33 'defining the inner surface 33 of the bead 32 is optimized so that the abutment of the bearing surface 29 of the first bearing 11 on this surface 33, and therefore the axial stop of the blower 2, is done homogeneously, independent of the angle that can exist between the axis 5 'of the compressor shaft 5 with the axis 4 of the turbojet engine 1. This curved shape of the inner surface 33 of the bead 32 is a meridian curve, in an axial plane, symmetrical of revolution around the axis 4 of the turbojet. The curve 33 'is here, in axial sectional view, of circular shape. This curve 33 'could be of more complex shape, for example to respect the different phases of decoupling - with or without contact depending on the steps.

De fait, la poursuite de la rotation de la soufflante 2 après découplage du support du premier palier 11 ne se fait pas forcément autour de l'axe 4 du turboréacteur 1, puisque justement l'arbre du compresseur 5 n'est plus centré par le premier palier 6. Au moment de la rupture de l'arbre du compresseur 5 et de sa fuite en avant, l'angle de son axe 5' avec l'axe 4 du turboréacteur 1 est aléatoire. Cet aléa ne perturbe pas l'arrêt de la soufflante 2 par l'anneau de retenue 30 du fait de la forme optimisée de la paroi 33 de son bourrelet 32. Cette dernière permet d'ailleurs, avec la continuation de la rotation de la soufflante 2 liée à son avancée, de remettre la soufflante 2 et l'arbre du compresseur 5 dans l'axe 4 du turboréacteur 1, comme c'est le cas sur la figure 4.In fact, the continued rotation of the fan 2 after decoupling the support of the first bearing 11 is not necessarily around the axis 4 of the turbojet engine 1, since precisely the compressor shaft 5 is no longer centered by the first bearing 6. At the moment of rupture of the compressor shaft 5 and its forward leakage, the angle of its axis 5 'with the axis 4 of the turbojet 1 is random. This hazard does not disturb the shutdown of the blower 2 by the retaining ring 30 due to the optimized shape of the wall 33 This allows, moreover, with the continuation of the rotation of the fan 2 related to its advance, to put the blower 2 and the shaft of the compressor 5 in the axis 4 of the turbojet 1, as is the case in FIG.

L'invention a été décrite en lien avec le support du premier palier fixé à la structure fixe du turboréacteur par le biais du support du deuxième palier, tandis que l'anneau d'arrêt est fixé à la structure fixe du turboréacteur par les vis de fixation du support du deuxième palier à cette structure fixe. Il va de soi que le premier support de palier, le deuxième support de palier et l'anneau d'arrêt pourraient être fixés à la structure fixe du turboréacteur indépendamment les uns des autres et remplir les mêmes fonctions qui ont été décrites.The invention has been described in connection with the support of the first level fixed to the fixed structure of the turbojet engine via the support of the second bearing, while the stop ring is fixed to the fixed structure of the turbojet engine by the fixing screws of the second bearing support to this fixed structure. It goes without saying that the first support of bearing, the second bearing support and the stop ring could be attached to the fixed structure of the turbojet independently of one another and to fill the same functions that have been described.

En outre, dans le cas où l'anneau d'arrêt est fixé à la structure fixe du turboréacteur de façon indépendante, le support du deuxième palier pourrait être fixé à cette structure par des vis fusibles. Ainsi, le découplage des deux paliers seraient possible, l'arrêt axial par l'anneau d'arrêt n'intervenant qu'en cas de rupture de l'arbre du compresseur.In addition, in the case where the stop ring is attached to the fixed structure of the turbojet engine independently, the support of the second bearing could be fixed at this structure by fusible screws. Thus, the decoupling of the two levels would be possible, the axial stop by the stop ring intervenes only in case of breakage of the shaft of the compressor.

La portée aval 29 du premier palier 11 a ici été décrite de forme tronconique. Il va de soi qu'elle pourrait également présenter une forme courbe, en vue en coupe axiale, cette forme étant optimisée en corrélation avec la courbe 33' que présente la surface 33 du bourrelet 33 de l'anneau d'arrêt 30 pour que l'arrêt de la soufflante se fasse de façon homogène, sans effet d'angle.The downstream bearing 29 of the first bearing 11 has here been described with a frustoconical shape. It goes without saying that it could also have a curved shape, in sectional view axial shape, this shape being optimized in correlation with the curve 33 'that the 33 surface of the bead 33 of the stop ring 30 so that the stop of the blower is do it in a homogeneous way, without angle effect.

On peut noter que l'anneau d'arrêt 30 pourrait également assurer une fonction de palier de secours, faisant office de palier pour l'arbre de compresseur 5, en cas de rupture de ce dernier après découplage du premier palier 6. It may be noted that the stop ring 30 could also provide a function an emergency bearing, acting as a bearing for the compressor shaft 5, in case of rupture of the latter after decoupling of the first bearing 6.

L'invention a été décrite en relation avec un turboréacteur, en particulier un turboréacteur à double corps dont le deuxième palier est un palier supportant le rotor basse pression. L'invention s'applique à d'autres types de turbomachines, telles qu'un turbopropulseur, un turbocompresseur industriel ou une turbine industrielle, le rotor n'étant pas alors un rotor de soufflante mais tout simplement un rotor.The invention has been described in relation with a turbojet engine, in particular a double-body turbojet engine, the second bearing of which is a bearing supporting the rotor low pressure. The invention applies to other types of turbomachines, such as a turboprop, an industrial turbocharger or an industrial turbine, the rotor not being then a fan rotor but simply a rotor.

Claims (13)

Turbomachine, s'étendant longitudinalement suivant un axe (4), comprenant un rotor (2), solidaire d'un arbre d'entraínement (5), agencé pour tourner autour d'un axe (5'), supporté par au moins un premier palier (6), monté sur la structure fixe de la turbomachine par une pièce support de palier (11), caractérisée par le fait qu'elle comprend un anneau d'arrêt (30), monté sur la structure fixe de la turbomachine pour coopérer avec la pièce de support du premier palier (11) et assurer, en cas de déplacement du rotor (2) par rapport à la structure fixe, une fonction de retenue axiale du rotor (2), de façon homogène, sans effet d'angle entre l'axe (4) de la turbomachine et l'axe (5') de l'arbre d'entraínement (5).Turbomachine, extending longitudinally along an axis (4), comprising a rotor (2), integral with a drive shaft (5), arranged to rotate about an axis (5 '), supported by at least one first bearing (6), mounted on the fixed structure of the turbomachine by a bearing support member (11), characterized in that it comprises a stop ring (30), mounted on the fixed structure of the turbomachine for cooperate with the support part of the first bearing (11) and ensure, in case of movement of the rotor (2) relative to the fixed structure, an axial retention function of the rotor (2), homogeneously, without effect of angle between the axis (4) of the turbomachine and the axis (5 ') of the drive shaft (5). Turbomachine selon la revendication 1, dans laquelle la pièce de support du premier palier (11) présente une portée (29) destinée à coopérer avec la surface (33) d'un bourrelet (32) de l'anneau d'arrêt (30).A turbomachine according to claim 1, wherein the support piece the first bearing (11) has a bearing surface (29) intended to cooperate with the surface (33) a bead (32) of the stop ring (30). Turbomachine selon la revendication 2, dans laquelle la portée (29) est de forme tronconique.A turbomachine according to claim 2, wherein the span (29) is frustoconical shape. Turbomachine selon l'une des revendications 2 ou 3, dans laquelle la surface (33) du bourrelet (32) de l'anneau d'arrêt (30) présente en coupe axiale une forme courbe (33'), à symétrie de révolution autour de l'axe (4) de la turbomachine.Turbomachine according to one of claims 2 or 3, in which the surface (33) of the bead (32) of the stop ring (30) has in axial section a curved shape (33 '), symmetrical of revolution about the axis (4) of the turbomachine. Turbomachine selon la revendication 4, dans laquelle la forme courbe (33') est un arc de cercle.Turbomachine according to Claim 4, in which the curved shape (33 ') is an arc of a circle. Turbomachine selon l'une des revendications 1 à 5, dans laquelle l'anneau d'arrêt ceinture longitudinalement la partie aval de la pièce de support du premier palier (11), sans contact en mode de fonctionnement normal de la turbomachine.Turbomachine according to one of claims 1 to 5, wherein the ring stopping longitudinally the downstream part of the support part of the first bearing (11), without contact in normal operating mode of the turbomachine. Turbomachine selon l'une des revendications 1 à 6 dans laquelle, l'arbre d'entraínement (5) étant supporté par un deuxième palier (7), le deuxième palier (7) étant monté sur la structure fixe de la turbomachine par une pièce support de palier (19), la pièce de support du premier palier (11) est fixée à la pièce de support du deuxième palier (19) par des vis fusibles (25) permettant son découplage de la pièce de support du deuxième palier (19). Turbomachine according to one of claims 1 to 6 wherein the shaft drive (5) being supported by a second bearing (7), the second bearing (7) being mounted on the fixed structure of the turbomachine by a bearing support piece (19), the support part of the first bearing (11) is fixed to the support part of the second bearing (19) by fusible screws (25) allowing its decoupling of the piece of support of the second bearing (19). Turbomachine selon l'une des revendications 1 à 7 dans laquelle, la pièce de support du premier palier (11) étant montée sur la structure fixe de la turbomachine par un dispositif (25) permettant son découplage par rapport à la structure fixe de la turbomachine, l'anneau d'arrêt (30) est agencé pour ne pas interférer sur la phase de découplage.Turbomachine according to one of claims 1 to 7 wherein the piece supporting the first bearing (11) being mounted on the fixed structure of the turbomachine by a device (25) allowing its decoupling with respect to the fixed structure of the turbomachine, the stop ring (30) is arranged not to interfere with the phase of decoupling. Turbomachine selon l'une des revendications 1 à 7 dans laquelle, la pièce de support du premier palier (11) étant montée sur la structure fixe de la turbomachine par un dispositif (25) permettant son découplage par rapport à la structure fixe de la turbomachine, l'anneau d'arrêt (30) est agencé pour limiter les débattements de l'arbre de compresseur (5) lors de la phase de découplage.Turbomachine according to one of claims 1 to 7 wherein the piece supporting the first bearing (11) being mounted on the fixed structure of the turbomachine by a device (25) allowing its decoupling with respect to the fixed structure of the turbomachine, the stop ring (30) is arranged to limit the deflections of the shaft compressor (5) during the decoupling phase. Turbomachine selon l'une des revendications 1 à 9 dans laquelle, l'arbre d'entraínement (5) étant supporté par un deuxième palier (7), le deuxième palier est monté sur la structure fixe de la turbomachine par un dispositif permettant son découplage par rapport à la structure fixe de la turbomachine.Turbomachine according to one of claims 1 to 9 wherein the shaft drive (5) being supported by a second bearing (7), the second bearing is mounted on the fixed structure of the turbomachine by a device allowing its decoupling with respect to the fixed structure of the turbomachine. Turbomachine selon l'une des revendications 1 à 9 dans laquelle, l'arbre d'entraínement (5) étant supporté par un deuxième palier (7), le deuxième palier (7) étant monté sur la structure fixe de la turbomachine par une pièce support de palier (19), fixée par des vis (24), l'anneau d'arrêt (30) comporte des évidements longitudinaux (26') permettant le passage desdites vis (24) pour assurer la fixation de l'anneau d'arrêt (30) à la structure fixe de la turbomachine.Turbomachine according to one of claims 1 to 9 wherein the shaft drive (5) being supported by a second bearing (7), the second bearing (7) being mounted on the fixed structure of the turbomachine by a bearing support piece (19), fixed by screws (24), the locking ring (30) has recesses longitudinal members (26 ') allowing the passage of said screws (24) to ensure the fixing of the stop ring (30) to the fixed structure of the turbomachine. Turbomachine selon l'une des revendications 1 à 11, qui est un élément de l'ensemble constitué par un turboréacteur à double corps, comprenant un deuxième palier (7) qui est un palier supportant le rotor basse pression, un turbopropulseur, un turbocompresseur et une turbine.Turbomachine according to one of claims 1 to 11, which is an element of the assembly consisting of a double-body turbojet, comprising a second bearing (7) which is a bearing supporting the low pressure rotor, a turboprop, a turbocharger and a turbine. Turbomachine selon l'une des revendications 1 à 12 dans laquelle, la pièce de support du premier palier (11) étant montée sur la structure fixe de la turbomachine par un dispositif (25) permettant son découplage par rapport à la structure fixe de la turbomachine, l'anneau d'arrêt (30) assure en particulier la retenue axiale du rotor (2) en cas de rupture de l'arbre d'entraínement après découplage du premier palier (6).Turbomachine according to one of claims 1 to 12 wherein the piece supporting the first bearing (11) being mounted on the fixed structure of the turbomachine by a device (25) allowing its decoupling with respect to the fixed structure of the turbomachine, the stop ring (30) ensures in particular the axial retention of the rotor (2) in case of breakage of the drive shaft after decoupling the first bearing (6).
EP05105129.0A 2004-06-11 2005-06-10 Turbomachine with axial retention means for the rotor Active EP1605139B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0406306 2004-06-11
FR0406306A FR2871517B1 (en) 2004-06-11 2004-06-11 TURBOMACHINE WITH AXIAL ROTOR RETENTION MEANS

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EP1605139A1 true EP1605139A1 (en) 2005-12-14
EP1605139B1 EP1605139B1 (en) 2014-07-30

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US (1) US7340882B2 (en)
EP (1) EP1605139B1 (en)
CN (1) CN1740523B (en)
CA (1) CA2509489C (en)
FR (1) FR2871517B1 (en)
RU (1) RU2382886C2 (en)
UA (1) UA89021C2 (en)

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Also Published As

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UA89021C2 (en) 2009-12-25
CN1740523B (en) 2011-07-20
FR2871517A1 (en) 2005-12-16
EP1605139B1 (en) 2014-07-30
CN1740523A (en) 2006-03-01
RU2005118145A (en) 2006-12-20
US7340882B2 (en) 2008-03-11
US20050276683A1 (en) 2005-12-15
FR2871517B1 (en) 2006-09-01
RU2382886C2 (en) 2010-02-27
CA2509489A1 (en) 2005-12-11
CA2509489C (en) 2012-08-07

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