Safran Helicopter Engines

Safran

Safran Aircraft Engines

Benjamin Fulleringer

Arnaud Georges Nifenecker

Yannick Cazaux

Antoine Pascal Moutaux

Romain Jean Gilbert Thiriet

Rémi Lanquetin

Nicolas Maurice Marcel Herran

Jean-Pierre Pajard

Pierre Gaymu

Armand Bueno

Rémi Joseph Lanquetin

Xavier Roger Betbeder-laüque

Philippe Olharan

Damien Paul Antonin Lecouvreur

Cédric Lempegnat

Samuel Jousselin

Laurent Jean Crabos

Cédric Georget

Cédric Jean Daniel Plaino

Frédéric Bonnet

Damien Lecouvreur

An assembly for measuring a torque transmitted between a first member and a second member of a turbomachine includes a pinion having a first annular portion and a second annular portion joining together at a connecting portion carrying a gearing of the pinion, said first and second annular portions extending axially in opposite directions, from the connecting portion. The pinion also includes an axial power shaft with a first area coupled to the first annular portion, and a second area for coupling to the second member, and a device for measuring the torsion between the first and second areas. The device includes a first phonic wheel on the power shaft, a second phonic wheel equipping the second annular portion of the pinion and axially aligned with the first phonic wheel, and an acquisition means axially aligned with and opposite to the first phonic wheel and the second phonic wheel and outputting a signal representative of an angular variation.

Torque transmission and measurement assembly for a turbomachine

Rolling bearing with three contact points, wherein the inner raceway, the third contact point being located in a sector of the outer raceway delimited by a proximal end of the outer raceway on the one hand, and by the rolling plane on the other hand, characterized in that the outer ring comprises a drain provided in the outer raceway, and opening from an outer surface of the outer ring, said drain opening eccentrically on the outer raceway with respect to the rolling plane, in a sector of the outer raceway delimited by the rolling plane on the one hand, and a distal end of the outer raceway on the other hand, the drain and the third contact point being disjoint.

Three-point contact rolling bearing with improved drain

A propulsive assembly including a first and a second gas turbine each having a gas generator and a free power turbine, a main rotor coupled to the free power turbine of a first and a second main coupling, a first and a second reversible electric machine each coupled to the gas generator, by way of a first deactivatable coupling, and each coupled to the main rotor by way of a second deactivatable coupling, the first deactivatable coupling being activated when the electric machines are rotating in a first direction of rotation, and the second deactivatable coupling being activated when the electric machines are rotating in a second direction of rotation opposite to the first direction of rotation.

Propulsive assembly for a multi-engine hybrid aircraft

An aircraft turbomachine includes a gas generator having an output shaft and a first lubricating circuit. The turbomachine further includes equipment coupled to the output shaft and including a rotor rotationally guided by at least one rolling bearing and a second lubricating circuit that is independent of the first lubricating circuit and is configured to lubricate the rolling bearing. The equipment further includes a system for cooling the rolling bearing, the cooling system being configured to circulate oil in the region of at least one ring of the rolling bearing. The cooling system is independent of the second lubricating circuit and is connected to the first lubricating circuit.

Lubrication and cooling of equipment of an aircraft turbomachine

A device for a hybrid aircraft including a turboshaft engine having a gas generator, a free turbine, and a main rotor. The device includes a first reversible electric machine coupled to a shaft of the free turbine by way of a first free wheel, and to the main rotor. The device further includes a second reversible electric machine coupled to a shaft of the gas generator by way of a second free wheel, and coupled to the main rotor by way of a third free wheel. The second free wheel activates when the second electric machine rotates in a first direction of rotation, and the third free wheel activates when the second electric machine rotates in a second direction of rotation opposite to the first direction of rotation.

Transmission device for hybrid aircraft

A part for a centrifugal breather for an air/oil mixture of a turbomachine is configured to rotate about a longitudinal axis of symmetry. The breather forms an annular chamber for centrifugal separation of said mixture. The chamber includes mesh structure that takes up at least one space in a duct which closes communication between an axial inlet and an internal radial outlet. The mesh structure is formed by the spatial repetition of the material or of the space of a single pattern produced by the interconnection of simple shapes. The pattern is designed such that the spaces between the materials paths passing through the materials in at least three dimensions of space forming a trihedron.

Part for a turbomachine centrifugal breather having a filtering mesh

A centrifugal degasser of an air-oil mixture of a turbine engine includes a hollow shaft extending along an X axis and a pinion for rotating the hollow shaft, and an annular chamber for centrifugal separation of the mixture. The chamber is arranged around the hollow shaft and forms a fluid passage area, an inlet of which is oriented axially for feeding the chamber with the mixture, and a first outlet of which is oriented radially inwards for the outlet of the de-oiled air separated from said mixture. The chamber also includes at least one second oil outlet oriented radially outwards and configured for discharging the oil separated from said mixture to the outside of the degasser. The chamber and the pinion form a single piece.

Integral centrifugal degasser

A component for a centrifugal deaerator for removing gas from a turbomachine air/oil mixture includes a structural part configured to delimit a duct for the flow of the air/oil mixture, and includes a circumferential enclosure for the centrifugal separation of the air/oil mixture, an axial inlet for the air/oil mixture, radial oil outlets, and an outlet for oil-free air. The component includes at least one cellular structure configured to filter the oil while allowing the air to pass and occupying at least a space in the duct.

Turbomachine centrifugal breather component and method for manufacturing said component

A component for a centrifugal degasser for an air/oil mixture of a turbomachine is disclosed. The degasser rotates about an axis of symmetry, forming an annular chamber for centrifugal separation of the mixture. The chamber forms a fluid passage duct, one inlet of which is oriented axially for supplying the chamber with the mixture, and a first outlet of which is oriented radially inwards for discharging the deoiled air separated from the mixture. The chamber also includes at least one second oil outlet oriented radially outwards and intended to discharge the oil separated from the mixture to the outside of the degasser. The chamber has longitudinal walls passing radially therethrough, at least one of the surfaces of the longitudinal walls having surface structures and/or corrugations arranged to form obstacles to a flow of the mixture along the surface of the longitudinal walls.

Component for a turbomachine centrifugal degasser with adapted longitudinal walls

The invention relates to a centrifugal deaerator for an air/oil mixture of a turbomachine, comprising: an annular housing () for the centrifugal separation of said mixture, arranged around a hollow shaft (); axial inlets () for the flow of said air/oil mixture into said housing (); a pinion () for rotating said housing (); and radial oil outlets () and oil-free air outlets (), characterised in that it comprises a metal foam () housed in said housing () by partially extending along the axial direction (XX') so as to define two successive spaces, a foam-free space () and a foam-lined space (), said foam-free space opening up towards said axial inlets. A device can be advantageously added to the hollow shaft in order to reduce the free-vortex phenomenon and to thereby significantly reduce the load losses of the deaerator.

Centrifugal deaerator for a turbomachine

A centrifugal deaerator for an air/oil mixture of a turbine engine includes: an annular housing arranged around a hollow shaft and having an outer annular wall and an inner annular wall; axial mixture inlets for the inflow of the air/oil mixture into annular housing; a pinion for rotating the annular housing, the pinion including a web that is securely connected to the hollow shaft and to the inner and outer annular walls; radial oil outlets in the outer wall; and oil-free air outlets in the inner wall. The axial mixture inlets and the radial oil outlets are axially arranged on either said of the web to prevent the axial mixture inlets from reintroducing oil evacuated by radial oil outlets into the annular housing.

A torque meter includes a casing and a part is configured to move in the casing in translation in a longitudinal direction under the effect of an axial thrust representative of the torque to be measured. The torque meter further includes a bearing surface connected to the casing via at least one of the ends thereof. The bearing surface extends at least partially in a plane that is substantially perpendicular to the longitudinal direction. One longitudinal end of the movable part is configured to be brought into contact with the bearing surface so that a longitudinal displacement of the movable part leads to a deformation of the bearing surface. The torque meter also has a device configured to measure the deformation of the bearing surface.

Growing community of inventors

Moissy-Cramayel, France

Benjamin Fulleringer