Safran Aircraft Engines

Snecma

Alexandre Jean-Marie Tan-Kim

Julien Fabien Patrick Becoulet

Paul Ghislain Albert Levisse

Emmanuel Fabrice Marie Baret

Michel Gilbert Roland Brault

Yanis Benslama

Arnaud Nicolas Negri

Olivier Formica

Patrice Jean-Marc Rosset

Serge Benyamin

Maxime Paul Numa Givert

Jérémy Dievart

Sylvain Bories

Nicolas Auguste Marcel Pommier

Disclosed is an assembly for a turbomachine that includes connection elements having respective radial flexibilities, wherein a ratio of a first of the respective radial flexibilities to a third of the respective radial flexibilities is strictly lower than 10% and/or a ratio of the first of the respective radial flexibilities to a second of the respective radial flexibilities is strictly lower than 4%.

Flexibilities in a gas turbine engine with speed reducer

A device for centering and guiding a shaft of an aircraft turbine engine is provided. The device includes an outer ring of a rolling bearing extending about an axis and having orifices, an annular bearing support extending about the axis and at least partially about the ring, the support having orifices and a series of studs for connecting the ring to the support. The studs can be distributed about the axis and extend parallel to the axis. The ends of first studs can be engaged without clearance in the orifices, and ends of second studs can be engaged with clearances in the orifices of the ring and/or of the support, the clearances being configured so that the device has different stiffnesses in at least two directions perpendicular to the axis.

Device for centering and guiding a shaft of an aircraft turbine engine

A device for centering and guiding a shaft of an aircraft turbine engine, the device including an outer ring of a rolling bearing, the ring extending about an axis; an annular bearing support extending about the axis and at least partially about the ring; at least one series of connecting elements for linking the ring to the support, the connecting elements being interposed between an inner cylindrical rim of the ring and an outer cylindrical rim of the support that extends about the inner rim, and each having a first radially outer end for linking to the outer cylindrical rim and a second radially inner end for linking to the inner cylindrical rim, the ring, the support and the connecting elements being integrally formed, the connecting elements being enclosed in an annular housing that is radially delimited by the rims and laterally enclosed by an annular web.

A device for centering and guiding a shaft of an aircraft turbine engines. The device includes an outer ring of a rolling bearing, the ring extending about a main axis and having orifices arranged around the axis axis; an annular bearing support extending about the main axis and at least partially about the ring, the support having orifices and openings arranged about the axis; and a series of studs for linking the ring to the support, the studs being distributed about the main axis and having elongation axes substantially parallel to the main axis, the body of each of the studs passing through one of the openings. Some of the studs, have bodies that pass with a first positive clearance and a second virtually zero clearance through the first openings, the first and second clearances being configured so that the device has different displacement amplitudes.

An enclosure for a turbomachine includes a turbomachine drive shaft rotating about a longitudinal axis (X) by means of two roller bearings, an upstream bearing and a downstream bearing, each having an inner ring carried by the drive shaft. The two bearings share a single integral outer ring that has an upstream end and a downstream end connected to one another by a section of studs. The single outer ring is carried by an upstream base plate and a downstream base plate of a bearing support configured to be attached to a stationary structure of the turbomachine.

Fused soft and hard bearing rings

A device for centring and rotationally guiding a turbomachine shaft includes a rolling-element bearing outer ring; a bearing support having a radially inner annular surface surrounding the outer ring; a connection structure connecting the outer ring to the bearing support and including an elastically deformable structure; a first cavity formed between the radially inner annular surface and the outer ring to receive a first damping fluid film; at least one second cavity formed between the bearing support and the connection structure which is arranged radially outside the radially inner annular surface to receive a second respective damping fluid film. Such an arrangement allows for the coexistence of damping fluid films having very different damping properties.

Device for centring and rotationally guiding a turbomachine shaft comprising several optimised damping fluid films

A dual-flow turbojet engine having a central shaft surrounded by a high-pressure body which rotate about the same longitudinal axis while being independent in rotation, and including a fan driven by the central pressure shaft; a high-pressure compressor and a high-pressure turbine mounted on the high-pressure body; an inter-turbine casing; a low-pressure turbine mounted on a low-pressure rotor surrounding the central shaft; an exhaust casing on which an output cone is mounted; a reduction gear with which the low-pressure rotor drives the central pressure shaft; two bearings mounted on the exhaust casing and respectively receiving the central shaft and the low-pressure rotor; a bearing mounted on the inter-turbine casing and receiving the low-pressure rotor.

Dual-flow turbojet engine arrangement with epicyclic or planetary reduction gear

An aircraft turbomachine with a reduction gear has a first shaft and a second shaft having one same axis of rotation, the second shaft being rotationally driven by the first shaft via the reduction gear, the first shaft having elastically deformable means having bellows section(s) and being connected to the reduction gear by a connecting system likewise having elastically deformable means involving a hairpin or bellows section(s).

Aircraft turbomachine with reduction gear

A geared turbomachine includes: a fan, a low pressure shaft which drives the fan rotationally around the main axis of the turbomachine, a speed reducer interposed between the fan and the low pressure shaft, and an alternator driven by the low pressure shaft. The alternator includes an inductor and an armature of which one of the inductor and the armature is integral with the fan and the other of the inductor and the armature is integral with the low pressure shaft.

Turbomachine comprising an alternator between two counter-rotating elements

A bearing suspension device includes first and second elastically flexible members extending in an axial direction; and first and second thrust points that are movable in the axial direction and that are in radial contact respectively with the first and second elastically flexible members. The bearing suspension device is configured to transmit a radial force by the first elastically flexible member bending between the first thrust point and a first end of the first elastically flexible member, and also to transmit the radial force by the second elastically flexible member bending between the second thrust point and a first end of the second elastically flexible member.

Variable stiffness bearing suspension device

A propulsive assembly including a turbine engine configured to be fastened to an aircraft by means of a suspension, having certain casing portions suitable for being decoupled so as to attenuate certain bending modes of the turbine engine in the event of an incident, the propulsive assembly comprising at least first and second casing portions () extending axially one after another, one of said casing portions being cantilevered out relative to said suspension, wherein a first casing portion () possesses a first fastener portion () connected rigidly to the body () of the first casing portion () and a second fastener portion () connected more flexibly to the body () of the first casing portion (), and wherein the second casing portion () is fastened to the second fastener portion () of the first casing portion () in a manner that is permanent, and to the first fastener portion () of the first casing portion () in a manner that is releasable.

Propulsive assembly having decouplable casing portions

The invention relates to a turbine engine comprising a fixed structure (), a fan () rotor (), having an axis (XX) of rotation, and emergency braking means () of the rotor (), in particular in the event of the loss of a blade of the fan (), characterized in that said emergency braking means () comprise a first () and a second () member supported by the fixed structure (), said members () respectively being configured so as to interact frictionally with a first () element which is complementary to the rotor (), by forming a stop of the rotor () towards the rear along the axis (XX), and a second () element which is complementary to the rotor (), by forming a stop of the rotor () towards the front along the axis (XX), when the emergency braking means () are active.

Growing community of inventors

Moissy-Cramayel, France

Alexandre Jean-Marie Tan-Kim