Safran Aircraft Engines

Safran

Safran Electrical & Power

Pierre-Alain Jean Philippe Reigner

Tewfik Boudebiza

Augustin Marc Michel Curlier

Gilles Alain Charier

Nathalie Nowakowski

Kevin Morgane Lemarchand

Laurent Soulat

Adrien Pierre Jean Pertat

Olivier Belmonte

Michel Gilbert Roland Brault

Gilles Alain Marie Charier

Julien Fabien Patrick Becoulet

Antoine Jean-Philippe Beaujard

Paul Ghislain Albert Levisse

Emmanuel Pierre Dimitri Patsouris

Didier René André Escure

Claire Marie Figeureu

Emmanuel Fabrice Marie Baret

Philippe Delbosc

Jean-Claude Christian Taillant

Philippe Naneix

Romain Truco

Jean-François Endy Bersot

Yann Fefermann

The present invention relates to a system for converting and transporting electrical energy in a turbomachine-propelled aircraft, said system including:

System for converting and transporting electrical energy for the internal hybridisation of an aircraft turbomachine

A turbomachine for an aircraft comprising a stator, a turbine shaft and an electric machine arranged to the rear of the turbine shaft, and comprising an electric machine stator and an electric machine rotor, a rotationally fixed coupling carriage capable of moving in axial translation relative to the electric machine rotor between coupled and uncoupled positions, coupling members which are designed to engage with one another after the coupling carriage has moved from the uncoupled position to the coupled position and to transmit a torque from the turbine shaft to the electric machine rotor when they are engaged, and an elastic return member designed to elastically return the coupling carriage in axial translation to the coupled position.

Aircraft turbomachine comprising an electric machine

A fan module for an aircraft turbomachine includes a fan with a disc carrying fan blades and a rotor of an electric machine. The rotor has an annular shape and is mounted coaxially downstream of the fan. The module further includes an annular support for the rotor with a downstream end fixed to the rotor and with an upstream end fixed to the fan disc. The support is fixed to the disc by shear bolts configured to break when a torque transmitted by the disc to the support exceeds a predetermined threshold.

Turbomachine module equipped with an electric machine rotor

A device for controlling pitch of fan blades of a turbine engine including an un-ducted fan, the device including: at least one set of fan blades of adjustable pitch, the set being constrained to rotate with a rotary ring centered on a longitudinal axis and mechanically connected to a turbine rotor, each blade of the set being mounted on a blade root support that is pivotally mounted on the rotary ring; and at least one radial control shaft adjusting pitch of at least two adjacent blades of the set, the control shaft being constrained to rotate with the rotary ring and being configured to pivot about an axis of the shaft, being coupled to the blade root supports of the at least two blades of the set to adjust their pitch via a transmission system including eccentrics connected together by at least one connecting rod.

Radial shaft device for controlling the pitch of fan blades of a turbine engine having an un-ducted fan

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

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

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

Growing community of inventors

Moissy-Cramayel, France

Pierre-Alain Jean Philippe Reigner