Snecma

Ge Aviation Systems Limited

Hispano Suiza

Safran Aircraft Engines

Denis Louis Bocquet

Gilles Alain Charier

Didier Rene Andre Escure

Didier René André Escure

Gilles Le Gouellec

Sebastien Emile Philippe Tajan

Christopher Roy Carrington

Pascal Marly

Caroline Frantz

Aleksander Krzysztof Szymandera

Jan Sikorski

Antoine Jean Baptiste Stutz

Cedric Montarou

Marek Malitka

Aleksander Szymandera

Didier Rene Escure

The present invention relates to a propulsion unit comprising a pair of contra-rotating coaxial propellers, that are referred to as upstream () and downstream (), the downstream propeller, forming a rotating reference frame, being mounted for rotation about a central member forming a stationary reference frame, and being provided with a device for changing the pitch of the blades, characterized in that the downstream propeller is supported by bearings arranged externally on the cylindrical central support, an upstream bearing () of which is arranged downstream of a device for changing the pitch of the blades of the upstream propeller, and in that said device for changing the pitch of the downstream propeller comprises a linear actuator () in the stationary reference frame with an element () that is able to move axially along the axis of the downstream propeller, the upstream bearing comprising an inner ring that is rigidly connected to the linear actuator and an outer ring that is rigidly connected to a rotating casing () of the downstream propeller, and a movement-transmission mechanism () connecting said movable element of the linear actuator to the blades, comprising a load-transfer bearing arranged to transmit the axial forces from the linear actuator to the rotating reference frame of the downstream propeller.

Propulsion unit with a pair of propellers for an aircraft

A turbo engine includes a system for changing a pitch of blades of a propeller, the system including an annular fluid cylinder with a linear drive and a link mechanism linking the cylinder to the blades of the propeller to change an orientation of the propeller. The annular cylinder of the system can be rigidly mounted on a fixed housing supporting the propeller and internal to the propeller, unlike the blades mounted in an external rotating hub of the propeller, and the link mechanism includes a displacement transfer bearing fixed, on one side, to the mobile part of the cylinder and cooperating, on the other side, with a mechanism linking to the blades of the rotating hub of the propeller.

Turbo engine with propeller(s) for an aircraft with a system for changing the pitch of the propeller

Turbomachine blade incidence control system including a fluidic cylinder with a first and a second chamber and having a pressurized fluid network adapted to selectively supply pressurized fluid to the first and/or the second chamber, the fluid network having one fluid routing device having a first normal position and a second protection position. The fluidic cylinder includes a fluid inlet positioned to be in fluid communication with the first chamber when the fluidic cylinder is in the blocked position, the routing device being adapted to set up a fluid communication between the inlet and the second chamber when it is in the protection position and to inhibit the fluid supply to the inlet when it is in the normal position.

Turbomachine blade incidence control system and turbomachine

A turbomachine control system comprising an auxiliary hydraulic circuit with an auxiliary hydraulic pump, at least one hydraulic actuator, and at least one servo-valve, the auxiliary pump powering the actuator via the servo-valve. The auxiliary hydraulic circuit is connected in parallel with the main fuel or lubricating oil circuit of the turbomachine. Said auxiliary pump is driven by an electric motor.

Turbomachine control system

Growing community of inventors

Bois-le-Roi, France

Denis Louis Bocquet