Snecma

Safran Aircraft Engines

Alexandre Nicolas Dervaux

Sabine Bermond

Thibaud Mangin

Franck Dubreucq

Jean-Michel Guimbard

Thierry Kohn

Renaud James Martet

Patrick Joseph Marie Girard

Eric Roger Schwartz

Philippe Jean-Pierre Pabion

Gael Loro

Jean-Luc Bacha

Olivier Jean Daniel Baumas

Guillaume Jean-Claude Robert Renon

Yves Roland Crochemore

Stephanie Dominique Roger

Damien Cesar

Stephane Baucher

Pascal Bertrand Yves Claude Papot

Damien Gilbert Andre Redon

Philippe Hazevis

Philippe Gérard Marie Hazevis

Olivier Jean Baumas

Renaud Martet

Stephanie Roger

Eric Schwartz

Stéphanie Dominique Roger

A method for transporting a turbine engine held by a transport kit by a carriage. The transport kit connected to a connection member hoists the engine to connect to an aircraft fuselage. The transport kit is a structure which includes a hoisting interface () arranged on a rigid hoisting arm () which extends over the turbine engine and is connected to a rigid transport arm () which extends over a lateral side of the turbine engine. The transport arm is connected to at least two engine mounts () solid with the turbine engine. The transport arm (), or one of the engine mounts connected to the transport arm, includes a transport interface () that can be supported by a bearing element () of a truck () used for transporting the turbine engine.

Transport and hoisting structure for a turbomachine

The invention relates to an assembly for the removal, transportation and maintenance of an aircraft turbine engine () on a maintenance trolley (), comprising a turbine engine () comprising an upper means () for attaching the housing () of the turbine engine () to the aircraft and a first lower means () dedicated to transportation for attaching the housing () of the turbine engine (), a maintenance trolley (), and a member () comprising a means for attaching said member () to the housing () and at least one means for support and articulation of said member () and of the turbine engine () on the trolley (), allowing the turbine engine () to pivot to the vertical; characterised in that the member comprises a first attachment means designed to engage with the upper means (), a second attachment means designed to engage with the first lower means (), and a pivot means forming the support and articulation means engaging with a complementary receiving means () of the trolley ().

Assembly for the removal, transportation, and maintenance of a turbine engine

A device for cooling a turbine casing in a turbomachine including a turbine is disclosed. The turbine includes several stages, at least one of the stages includes a nozzle assembly formed of an annular row of fixed vanes and an impeller mounted to rotate in a cylindrical shroud formed of ring sectors fixed to the casing, a cooling circuit including ducts carrying cooling air into cavities formed in the vanes of the nozzle assembly, and an air-carrying arrangement which carries air to casing upstream hooks for suspending the ring sectors.

Device for cooling a turbomachine turbine casing

An assembly includes a vane and a cooling liner for cooling the vane, the vane having a central cavity with at least one first opening into which the liner extends, the liner having a flange fixed to the rim of the opening. This assembly includes, near the flange, a peripheral insert inserted between the wall of the liner and the wall of the opening.

Assembly comprised of a vane and of a cooling liner, turbomachine nozzle guide vanes assembly comprising this assembly, turbomachine and method of fitting and of repairing this assembly

A bladed stator sector for a turbo-engine reduces the occurrence of thermally-induced stress cracks in stator blades by increasing the flexibility of the sectors by using one or more cutouts. The stator sector includes at least one stator blade between inner and outer platforms and at least one flange on one or more of the platforms. Each flange has a first end portion fixed to one of the platforms and a second end portion that is not fixed to either of the platforms. The one or more cutouts may be located on the flange and may be non-opening.

Bladed stator for a turbo-engine

A layout for cooling a blade having a cavity surrounded by an internal wall including cooling fins which are spaced apart from each other by a pitch (p) and each have a thickness (e). The blade has, inside the cavity, a jacket passed through by emission holes each having a diameter (d). When the jacket is in place in the cavity of the blade, and in respect of the critical operating point of the turbine engine, each emission hole of the jacket is opposite a place on the internal wall of the blade which is located between cooling fins.

Cooling layout for a turbine blade, turbine blade included therein, turbine and aircraft engine equipped therewith

A link device between an enclosure for passing cooling air and a stator nozzle in a turbomachine, the device comprising metal tubes having their ends mounted in leaktight manner in orifices in a casing and in orifices in the stator nozzle, each tube including a bellows between its ends and accommodating relative displacements and changes of alignment between the orifices in the casing and the orifices in the nozzle.

Link device between an enclosure for passing cooling air and a stator nozzle in a turbomachine

A link device between an enclosure for passing cooling air and a stator nozzle in a turbomachine, the device comprising metal tubes having their ends mounted in leaktight manner in orifices in a casing and in orifices in the stator nozzle, one end of each tube being engaged in a ring having an outer collar movable in sliding between two surfaces carried by the nozzle, the guide surface situated beside the casing being held stationary relative to the nozzle, while the other guide surface is movable axially relative to the nozzle and is associated with return means urging it towards the casing.

Growing community of inventors

Paris, France

Alexandre Nicolas Dervaux