EP1605139A1 - Turbomachine avec moyens de retenue axiale du rotor - Google Patents
Turbomachine avec moyens de retenue axiale du rotor Download PDFInfo
- 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
- Authority
- EP
- European Patent Office
- Prior art keywords
- bearing
- turbomachine
- fixed structure
- decoupling
- support
- 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
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
- F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
-
- 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
Description
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.
- 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.
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 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).
- Turbomachine selon la revendication 2, dans laquelle la portée (29) est de forme tronconique.
- 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 selon la revendication 4, dans laquelle la forme courbe (33') est un arc de cercle.
- 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 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 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 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 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 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 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 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).
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0406306A FR2871517B1 (fr) | 2004-06-11 | 2004-06-11 | Turbomachine avec moyens de retenue axiale du rotor |
FR0406306 | 2004-06-11 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1605139A1 true EP1605139A1 (fr) | 2005-12-14 |
EP1605139B1 EP1605139B1 (fr) | 2014-07-30 |
Family
ID=34940148
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP05105129.0A Active EP1605139B1 (fr) | 2004-06-11 | 2005-06-10 | Turbomachine avec moyens de retenue axiale du rotor |
Country Status (7)
Country | Link |
---|---|
US (1) | US7340882B2 (fr) |
EP (1) | EP1605139B1 (fr) |
CN (1) | CN1740523B (fr) |
CA (1) | CA2509489C (fr) |
FR (1) | FR2871517B1 (fr) |
RU (1) | RU2382886C2 (fr) |
UA (1) | UA89021C2 (fr) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2965298A1 (fr) * | 2010-09-28 | 2012-03-30 | Snecma | Moteur a turbine a gaz comprenant des moyens de retention axiale d'une soufflante dudit moteur |
Families Citing this family (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2866069A1 (fr) * | 2004-02-06 | 2005-08-12 | Snecma Moteurs | Turboreacteur a soufflante solidaire d'un arbre d'entrainement supporte par un premier et un deuxieme paliers |
FR2866068B1 (fr) * | 2004-02-06 | 2006-07-07 | Snecma Moteurs | Turboreacteur a soufflante solidaire d'un arbre d'entrainement supporte par un premier et un deuxieme paliers |
FR2925123A1 (fr) * | 2007-12-14 | 2009-06-19 | Snecma Sa | Etancheite de fixation de support de palier dans une turbomachine |
FR2960026B1 (fr) * | 2010-05-11 | 2014-05-16 | Snecma | Turboreacteur a montage frangible et moyen de retenue axiale de la soufflante |
US8845277B2 (en) | 2010-05-24 | 2014-09-30 | United Technologies Corporation | Geared turbofan engine with integral gear and bearing supports |
FR2966208B1 (fr) * | 2010-10-13 | 2012-12-28 | Snecma | Boitier de liaison entre un arbre d'entrainement de soufflante de moteur et un palier de roulement |
CN103775212B (zh) * | 2012-10-25 | 2016-11-23 | 中航商用航空发动机有限责任公司 | 一种航空发动机的风扇失效制动装置 |
US9909451B2 (en) | 2015-07-09 | 2018-03-06 | General Electric Company | Bearing assembly for supporting a rotor shaft of a gas turbine engine |
US10316742B2 (en) * | 2016-05-13 | 2019-06-11 | Garrett Transportation I Inc. | Turbocharger assembly |
FR3063310B1 (fr) * | 2017-02-28 | 2019-04-26 | Safran Aircraft Engines | Moteur d'aeronef comprenant un palier entre deux arbres concentriques |
US10550718B2 (en) | 2017-03-31 | 2020-02-04 | The Boeing Company | Gas turbine engine fan blade containment systems |
US10487684B2 (en) | 2017-03-31 | 2019-11-26 | The Boeing Company | Gas turbine engine fan blade containment systems |
CN108343512B (zh) * | 2018-01-24 | 2019-11-12 | 深圳意动航空科技有限公司 | 一种发动机转子支架 |
CN111238355B (zh) * | 2020-02-14 | 2021-09-03 | 中国航发沈阳发动机研究所 | 一种发动机高压涡轮转子轴向位移测量方法 |
FR3129174A1 (fr) * | 2021-11-15 | 2023-05-19 | Safran Aircraft Engines | Module de turbomachine comprenant un dispositif d’amortissement et turbomachine correspondante |
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US4475869A (en) * | 1981-11-12 | 1984-10-09 | Rolls-Royce Limited | Gas turbine engine and shaft |
FR2752024A1 (fr) | 1996-08-01 | 1998-02-06 | Snecma | Support d'arbre cassant a l'apparition d'un balourd |
US5791789A (en) | 1997-04-24 | 1998-08-11 | United Technologies Corporation | Rotor support for a turbine engine |
EP1308602A1 (fr) | 2001-10-31 | 2003-05-07 | Snecma Moteurs | Système d'accouplement cassable pour l'arbre soufflante de turboréacteur |
Family Cites Families (3)
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FR2749883B1 (fr) * | 1996-06-13 | 1998-07-31 | Snecma | Procede et support de palier permettant de maintenir en fonctionnement un turbomoteur pour aeronef apres apparition d'un balourd accidentel sur un rotor |
GB2320526B (en) * | 1996-12-20 | 2000-09-20 | Rolls Royce Plc | Ducted fan gas turbine engine |
GB2322165B (en) * | 1997-02-15 | 2001-02-28 | Rolls Royce Plc | Ducted fan gas turbine engine |
-
2004
- 2004-06-11 FR FR0406306A patent/FR2871517B1/fr not_active Expired - Lifetime
-
2005
- 2005-06-09 UA UAA200505538A patent/UA89021C2/ru unknown
- 2005-06-09 CA CA2509489A patent/CA2509489C/fr active Active
- 2005-06-10 RU RU2005118145/06A patent/RU2382886C2/ru active
- 2005-06-10 US US11/149,214 patent/US7340882B2/en active Active
- 2005-06-10 EP EP05105129.0A patent/EP1605139B1/fr active Active
- 2005-06-10 CN CN200510091324.1A patent/CN1740523B/zh active Active
Patent Citations (4)
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---|---|---|---|---|
US4475869A (en) * | 1981-11-12 | 1984-10-09 | Rolls-Royce Limited | Gas turbine engine and shaft |
FR2752024A1 (fr) | 1996-08-01 | 1998-02-06 | Snecma | Support d'arbre cassant a l'apparition d'un balourd |
US5791789A (en) | 1997-04-24 | 1998-08-11 | United Technologies Corporation | Rotor support for a turbine engine |
EP1308602A1 (fr) | 2001-10-31 | 2003-05-07 | Snecma Moteurs | Système d'accouplement cassable pour l'arbre soufflante de turboréacteur |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2965298A1 (fr) * | 2010-09-28 | 2012-03-30 | Snecma | Moteur a turbine a gaz comprenant des moyens de retention axiale d'une soufflante dudit moteur |
WO2012042161A1 (fr) * | 2010-09-28 | 2012-04-05 | Snecma | Moteur a turbine a gaz comprenant des moyens de retention axiale d'une soufflante dudit moteur |
US9341116B2 (en) | 2010-09-28 | 2016-05-17 | Snecma | Gas turbine engine comprising means for axially retaining a fan of the engine |
RU2592154C2 (ru) * | 2010-09-28 | 2016-07-20 | Снекма | Газотурбинный двигатель, содержащий средства осевого удерживания вентилятора упомянутого двигателя |
Also Published As
Publication number | Publication date |
---|---|
FR2871517A1 (fr) | 2005-12-16 |
EP1605139B1 (fr) | 2014-07-30 |
US7340882B2 (en) | 2008-03-11 |
RU2005118145A (ru) | 2006-12-20 |
RU2382886C2 (ru) | 2010-02-27 |
CN1740523B (zh) | 2011-07-20 |
CN1740523A (zh) | 2006-03-01 |
UA89021C2 (ru) | 2009-12-25 |
CA2509489A1 (fr) | 2005-12-11 |
US20050276683A1 (en) | 2005-12-15 |
FR2871517B1 (fr) | 2006-09-01 |
CA2509489C (fr) | 2012-08-07 |
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