UNCOUPLING SYSTEM FOR AN AIRCRAFT TURBOJET ENGINE ROTARY SHAFT

The invention relates to an uncoupling system for an aircraft turbojet engine rotary shaft, comprising: a rolling bearing (22) having rolling elements (34) inserted between a first ring (38) fixed to a fixed bearing support (30) and a second ring (36) mounted in a mounting chamber (42) fixed to a ro...

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Bibliographische Detailangaben
Hauptverfasser:	JADCZAK, EDOUARD, JOSEPH, MAGRET, CEDRIC, QUENARDEL, ARNAUD, FABRICE, OLLIVIER, PIERRICK
Format:	Patent
Sprache:	eng ; fre
Schlagworte:	BEARINGS BLASTING CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION ELEMENTS OR CRANKSHAFT MECHANISMS ENGINE PLANTS IN GENERAL ENGINEERING ELEMENTS AND UNITS FLEXIBLE SHAFTS GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS HEATING INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04 LIGHTING MACHINES OR ENGINES IN GENERAL MEANS FOR DAMPING VIBRATION MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES ROTARY BODIES OTHER THAN GEARING ELEMENTS SHAFTS SHOCK-ABSORBERS SPRINGS STEAM ENGINES TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE THERMAL INSULATION IN GENERAL WEAPONS
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Beschreibung
Zusammenfassung:	The invention relates to an uncoupling system for an aircraft turbojet engine rotary shaft, comprising: a rolling bearing (22) having rolling elements (34) inserted between a first ring (38) fixed to a fixed bearing support (30) and a second ring (36) mounted in a mounting chamber (42) fixed to a rotary shaft (12); means (52, 54) of transmitting the rotational torque from the rotary shaft to the second ring; means (56) to allow relative radial movement of the second ring with respect to the mounting chamber when a static load associated with an imbalance affecting the rotary shaft exceeds a predetermined threshold; and a plurality of fluidtight flexible sacs (58) interposed between the second ring and the mounting chamber and each containing a heterogeneous structure (59) consisting of a porous capillary solid matrix and of an associated liquid with respect to which the matrix is lyophobic. L'invention concerne un système de découplage pour arbre rotatif d'un turboréacteur d'aéronef, comportant : un palier à roulement (22) ayant des éléments roulant (34) insérés entre une première bague (38) fixée sur un support de palier fixe (30) et une seconde bague (36) montée dans une chambre de montage (42) fixée sur un arbre rotatif (12); des moyens (52, 54) de transmission du couple de rotation de l'arbre rotatif à la seconde bague; des moyens (56) pour autoriser un déplacement radial relatif de la seconde bague par rapport à la chambre de montage lorsqu'un effort statique lié à un balourd affectant l'arbre rotatif dépasse un seuil prédéterminé; et une pluralité de sacs (58) souples étanches intercalés entre la seconde bague et la chambre de montage et renfermant chacun une structure hétérogène (59) constituée d'une matrice solide capillaire poreuse et d'un liquide associé au regard duquel la matrice est lyophobe.