Snecma

Safran Aircraft Engines

Laurent Leeder

Arnaud Bessy

Bernard Adrien Edmond Souart

Hubert Thomas

Francois Pierre Andre Bergerot

Jacques Pierre Felix Malterre

Jacques Pierre Malterre

Bernard Adrien Souart

Francois Pierre Bergerot

Guy Frank Paul Dusserre-Telmon

Guy Frank Dusserre-Telmon

François Bergerot

Jacques Malterre

M Bernard Souart

An assembly for supporting and guiding a drive shaft for an aircraft turbine engine includes a bearing support having a cylindrical housing for receiving an outer ring of a bearing, and a device for rotationally retaining a first portion of the outer ring which is detached from its attachment to the bearing support. When the detachment occurs, the free outer peripheries of the first teeth of the first portion cooperate by wedge effect in the tangential direction with complementary inner surfaces of the housing of the bearing support and/or the free inner peripheries of the second teeth inside the housing cooperate by wedge effect in the tangential direction with complementary outer surfaces of the outer ring.

Assembly for supporting and guiding a drive shaft for an aircraft turbine engine

A device for centring and rotationally guiding a turbomachine shaft, including a rolling bearing including an outer ring, a bearing mount, a band interposed between the outer ring and the bearing mount and a device for connecting the outer ring to the bearing mount, including a device for the axial retention of the outer ring including an axial thrust flange downstream of and in contact with the fixing flange of the connecting device, and including a fixing hole for fixing together the fixing flange, the bearing mount and the axial thrust flange, which latter further includes a lug extending between two successive tabs of the elastically deformable device.

Device for centring and rotationally guiding a turbomachine shaft comprising means for an axial retention of outer ring of a bearing

An assembly for a turbomachine includes a fan rotor drive shaft, a rolling element and a support of an exterior rolling-element bearing ring including an exterior annular element as well as an interior annular element coupled through a decoupling interface in the shape of a truncated sphere and configured to be retained by friction under normal operating conditions of the turbomachine, and to move with respect to one another in the event of a fan blade loss. The rolling-element bearing is designed so that each rolling element has four points of contact with the rings, and so that the interface between the ring and the support has a hollowed space for deformation routed around a central portion of the exterior ring.

Aircraft turbomachine assembly having an improved decoupling system in the event of a fan blade loss

A device for heating a cylindrical component of given diameter is disclosed. The device includes at least two heaters each delivering a stream of hot gas and emerging in an annular chamber. The inside diameter of the annular chamber is slightly greater than the diameter of the cylindrical component. The device may be used for heating a metal journal in which a bearing ring for an inter-shaft bearing in a double-body turbomachine is mounted.

Device for heating a cylindrical component and use in assembling an inter-shaft bearing in a turbomachine

A method of assembly of a turbomachine that includes a first module and a second module with a second shaft assembled by a bearing, the bearing including an outer ring shrink-fitted inside a journal integral with the first module and an inner ring integral with the second shaft. The second module is assembled on the first module by engagement of the second shaft, with the inner ring, inside the journal. The method includes a step of inserting the second module in the first module up to a determined distance such that the first and second modules are only partially assembled. The second shaft is centered with respect to the journal, the centering being controlled on the basis of measuring distance deviations with respect to a reference on the journal. The journal is expanded by heating its outer surface. After the step of expanding, the second module is displaced inside the first module so as to complete the assembly. This displacement step is started based on a predetermined temperature.

Method of assembling a turbomachine

A method of inspecting the profile of the connection zone between the cylindrical portion and the taper of a roller for a turbomachine roller bearing. The method includes taking a measurement of the surface profile of the roller; on the basis of a calculation of the first derivative of the measured profile, calculating straight line segments for each of the geometrical zones of the roller, where the straight line segments model the first derivative of the measured profile; calculating the radii of curvature of the surface profile of the roller by taking the first derivative of the straight line segments; and comparing the calculated radii of curvature with predefined threshold values in order to verify continuity thereof.

Growing community of inventors

Saint Germain Les Corbeil, France

Laurent Leeder