Safran Aircraft Engines

Snecma Société Anonyme

Pierre-Alain Francis Claude Sebrecht

Damien Joseph Cellier

Sébastien Claude Cochon

Arnaud Langlois

Axel Theux

Nishanth Thomas Rajaratnam

Cédric Michel Claude Chretien

Sébastien Cochon

A mechanism for driving a first member for adjusting the orientation of the blades of a first stage of a turbine engine diffuser and a second member for adjusting the orientation of the blades of a second stage of the turbine engine diffuser, including a single drive wheel which simultaneously drives the first adjustment member and the second adjustment member and a set of gears which is arranged between the drive wheel and the two adjustment members, wherein the set of gears includes a first gearwheel which is directly coupled with the drive wheel and with the first adjustment member and which is coupled with the second adjustment member with a secondary gearwheel which is directly coupled with the second adjustment member.

Mechanism for driving blade orientation adjustment bodies

A sealing flange sector for a turbomachine rotor disc includes a radially outer part which is configured to bear at least partly against blades of the turbomachine rotor disc to ensure sealing between the blades and a radially inner part configured to bear on an annular strip mounted on a face of the turbomachine rotor disc, the radially inner part having a first groove disposed radially outwardly of a second groove. The first groove includes at least one foolproofing element.

Rotor disc sealing flange sector

A stage of variable-pitch vanes for a turbine engine includes a plurality of vanes. Each vane has a blade with a first radially internal frusto-conical surface. The cone angle of the first frusto-conical surface is radially flared inwards and is configured to interact with an internal frusto-conical surface of a first frusto-conical bushing. The vane further includes a second radially external frusto-conical surface with cone angle that is radially flared outwards and is configured to interact with an internal frusto-conical surface of a second substantially frusto-conical bushing.

Stage of variable-pitch blades for a turbine engine, turbine engine and associated installation method

A turbine-engine compressor, in particular for an aircraft turboprop engine or turbojet engine, comprising an annular casing and at least one annular row of variable-pitch blades, each blade comprising a radially external end comprising a pivot mounted in an orifice in the casing and connected by a link to a control ring able to pivot axially about its axis with respect to the casing. Each link comprises a first end fixed to the pivot of the blade and a second end mounted so as to be able to pivot on the control ring. The pivot axes of first and second links on the control ring are offset from each other along the axis of the compressor, the second end of the second link being mounted on the ring by a connecting member, allowing a connection of the sliding or annular linear pivot type.

Turbine engine compressor, in particular for an aircraft turboprop engine or turbojet engine

A turbine engine compressor includes a stator featuring an annular casing and at least one annular row of variable-pitch vanes, wherein each vane comprises a radially external end having a pivot mounted in an orifice in the casing and connected by a linking member to an control ring capable of pivoting axially in relation to the casing, where the linking member comprises a first end fixed to the pivot of the vane and a second end having a pin inserted in a hole in the control ring, where at least one of the holes in the control ring serves for insertion of the pins of the linking members, is oblong in shape and extends in the circumferential direction in order to allow movement of the pin in the oblong hole, during rotation of the control ring.

Turbine engine compressor, in particular of an aeroplane turboprop or turbofan

A drive mechanism () for driving a first adjustment member () for adjusting the orientation of the blades () of a first turbomachine rectifier stage () and a second adjustment member () for adjusting the orientation of the blades () of a second turbomachine rectifier stage (), which comprises a mechanism for simultaneously moving the two adjustment members () in the turbomachine, characterised in that it comprises a single drive wheel () that simultaneously drives the first adjustment member () and the second adjustment member () and comprises two gear stages () that are arranged between the drive wheel () and one or the other of the first adjustment member () and the second adjustment member () and that have different transmission ratios.

Mechanism for driving members for adjusting the orientation of blades

A drive mechanism is provided for driving at least two adjusting members used to adjust the orientation of the blades of a turbomachine rectifier vane associated therewith, where the drive mechanism simultaneously drives the displacement of at least two adjusting members in the turbomachine. A single threaded rod drives several levers, each lever being associated with an adjusting member. A first part of each lever engages with the threaded rod and one end of an arm of the lever is connected to the adjusting member associated therewith so that the rotation of the threaded rod causes a simultaneous rotation of the levers associated with the adjusting members.

Growing community of inventors

Paris, France

Pierre-Alain Francis Claude Sebrecht