Safran Aircraft Engines

Augustin Marc Michel Curlier

Gilles Alain Charier

Tewfik Boudebiza

Pierre-Alain Jean Philippe Reigner

Nathalie Nowakowski

Kevin Morgane Lemarchand

Laurent Soulat

Adrien Pierre Jean Pertat

Antoine Jean-Philippe Beaujard

Nicolas Maurice Herve Aussedat

Jean-Christophe Duffet

Nicolas Aussedat

Sebastien Courtois

Gwénolé Yann Le Pache

The present invention relates to a powerplant of an aircraft including at least one twin-spool gas generator of longitudinal axis (XX), at least one main fan arranged upstream of the gas generator on the longitudinal axis (XX) and driven in rotation by the gas generator, the main fan being shrouded with a main fan housing; and at least one auxiliary fan with axis (XY, XY') offset relative to the longitudinal axis (XX) and driven by the gas generator, the auxiliary fan being shrouded with an auxiliary fan housing, the gas generator including at least one low-pressure compressor and a low-pressure turbine connected by a low-pressure shaft, the low-pressure turbine driving in rotation the main fan and the auxiliary fan via at least one power transmission system including a differential gear system incorporating a bevel gear.

Aircraft propulsion assembly equipped with a main fan and with a least one offset fan

The present invention relates to an aircraft propulsion assembly comprising a turbine (), at least one fan () and a mechanism for transmitting power between the turbine and the fan, characterized in that the power transmission mechanism comprises a speed reducer () with a motion input and a motion output, the input being in the continuation of the axis () of the turbine and the output connected to the fan.

Turbine engine with fan and reduction of speed on the shaft of the power turbine

An aircraft propulsion assembly comprising at least a main turbine mounted along a longitudinal axis, at least one main fan arranged upstream of the main turbine along the longitudinal axis and driven in rotation by the said main turbine, the said main fan being ducted by a main fan casing, an auxiliary turbine mounted along the longitudinal axis, the auxiliary turbine being independent of the main turbine, an auxiliary fan of axis offset with respect to the longitudinal axis and driven by the auxiliary turbine, the auxiliary fan being ducted by an auxiliary fan casing, the main casing being separate and distinct from the auxiliary casing so as respectively to generate a main secondary flow and an auxiliary secondary flow which remain independent of one another until they are discharged into the atmosphere.

Aircraft propulsion assembly equipped with a main fan and with at least one offset fan

A non-faired propeller turbo-engine includes a gas generator and a propulsion unit that is separated from the gas generator by an intermediate housing. The turbo-engine includes a housing and a radially internal ferrule that are coaxial and are connected by hollow radial arms. The housing of the turbo-engine also defines, in part, a gas flow duct of a secondary gas flow. Each radial arm is hollow and is traversed by at least one service of the turbo-engine. Additionally, at least one arm is traversed by a ventilation gas circulation duct from the secondary gas flow and which leads to at least one component from among a power turbine and a mechanical transmission of said propulsion unit.

Turbo-engine including two separate ventilation flows

Propulsion unit for an aircraft, comprising a turbine, at least one propeller offset with respect to the turbine, and a power transmission disposed between the turbine and the propeller, the transmission comprising in series two constant velocity joints with a slide connection.

Propulsion unit for an aircraft

A turbomachine subassembly has a radially inner shell and a radially outer shell of an annular gas flow path. A radial arm extends radially between the radially inner and outer shells and delimits an isolated volume which is connected to an inner volume of a chamber partly delimited by the radially inner shell. A segment of a conduit extends radially in the isolated volume, and a ventilation air supply source is connected to supply ventilation air to the isolated volume, whereby ventilation air may be supplied to the chamber through the isolated volume. An external radial end of the radial arm supports a first connection box that closes it off. The internal volume of the radial arm communicates with the ventilation air supply source. An external cylindrical wall of the first connection box fits inside an internal cylindrical wall of the external radial end of the radial arm.

Turbomachine comprising a ventilation system

The present invention relates to an aircraft comprising a fuselage (), a propulsion unit () at the rear tip of the fuselage and at least two engines () each driving an engine shaft (), the propulsion unit including at least one propeller () driven mechanically by the engine shafts (), characterized in that the propulsion unit () includes two propellers (), each of the propellers being driven by a propeller shaft (), the two propeller shafts being driven by the engine shafts () via a first differential epicyclic gear train (). Specifically, the input of the first differential gear train () is connected to the output of a second differential epicyclic gear train (), the second differential gear train () including two inputs (), each of said two inputs being connected mechanically to one of said engine shafts ().

Aircraft comprising a propulsion assembly including a pair of propellers at the rear of the fuselage

A propulsion unit of an aircraft including a turbine (), at least one fan () with an axis offset relative to the axis of the turbine and a power transmission mechanism between the turbine and the fan. The power transmission mechanism includes a speed reducing gear () with an input and a movement output, the input being in the extension of the axis () of the turbine and the output connected to the fan.

Turbojet engine with offset fans with a differential system

A turbomachine for an aircraft, comprising a rotor shaft, a turbomachine case, a lubricated bearing chamber, at least one bearing supporting the rotor shaft and being located in the bearing chamber, a lubrication device comprising oil injection means to inject oil into the bearing chamber, and oil supply means to supply oil to said oil injection means, and an electric current generator, comprising an armature driven by the rotor shaft and a field coil fixed to the turbomachine case. The generator has an orifice, which passes longitudinally through the generator from one end to the other, and the oil injection means pass through the orifice so that oil can circulate in the axial direction through the generator.

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Boissise la Bertrand, France

Augustin Marc Michel Curlier