Safran Aircraft Engines

Snecma

Tewfik Boudebiza

Gilles Alain Charier

Pierre-Alain Jean Philippe Reigner

Gilles Alain Marie Charier

Antoine Jean-Philippe Beaujard

Nathalie Nowakowski

Kevin Morgane Lemarchand

Augustin Curlier

Augustin Marc Michel Curlier

Catherine Pikovsky

Laurent Soulat

Serge Benyamin

Julien Michel Patrick Christian Austruy

Jean-Christophe Duffet

Adrien Pierre Jean Pertat

Olivier Belmonte

Julien Fabien Patrick Becoulet

Cedrik Djelassi

Caroline Marie Frantz

Vincent François Georges Millier

Marc Patrick Tesniere

Emmanuel Pierre Dimitri Patsouris

Loïc Paul Yves Guillotel

Didier Rene Andre Escure

Didier René André Escure

Emmanuel Fabrice Marie Baret

Bastien Pierre Verdier

Thomas Julien Nguyen Van

Jean-Claude Christian Taillant

Frederic Paul Eichstadt

Michel Henri Ziegler

Guillaume Marcillaud

Jean-François Endy Bersot

Jean Philippe Pierre-Alain Reigner

Julien Michel Austruy

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

The invention describes a system for controlling the cyclic setting of blades () of a turbine engine propeller, the blades () being arranged in a plane normal to the axis of rotation (r) of the propeller, the system comprising: &#x2014;a plate assembly () that can be tilted relative to the normal plane (P), &#x2014;an articulation system () articulating the plate assembly () relative to the blades () such that tilting the plate assembly () modifies the setting of the blades (), &#x2014;a force sensor () designed to measure a force applied in the normal plane (P) by an air flow at the inlet of the propeller blades (), &#x2014;a cylinder () suitable for tilting the plate assembly () in response to a force measured by the force sensor ().

System for controlling the cyclic setting of blades

A fan module for an aircraft turbine engine, this module comprising a fan and an electrical machine, such that the electrical machine is coaxially mounted downstream of the fan and comprises a rotor coupled to rotate with the fan and an annular member with generally C-shaped axial cross-section, the opening of which is axially orientated and receives the rotor, this member comprising a radially outer portion forming a stator, and a radially inner portion forming a support for bearings guiding the rotor.

Fan module equipped with an electrical machine for an aircraft turbine engine

Double flow turbojet including an intermediate flow path dedicated to supplying with air via radial arms an exhaust casing of this turbojet

A mechanical decoupler () at the inlet to a turbomachine is positioned on the outside of an intake casing, where radiating arms () meet an external casing () so as to partially unload a low-pressure shaft when a significant out-of-balance appears. Because it is positioned a long way from the bearing, the decoupler () can be designed with a greater degree of freedom at a location where there is more space available and where layout constraints are less of an issue. More specifically, it is housed in a cavity () of the external casing () which opens onto the flow path ().

Aircraft engine intake arrangement comprising a mechanical decoupler

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

A turbojet includes an inlet casing, a low pressure compressor, a high pressure spool, a low pressure turbine, and an exhaust casing. The inlet casing and the low pressure compressor define an air inlet channel that divides downstream into a primary flow channel and a secondary flow channel. A low pressure shaft is supported by a first roller bearing, borne by the inlet casing, a second bearing borne by the intermediate casing, a third bearing borne by the exhaust casing, and an additional ball bearing borne by the intermediate casing and arranged between the first bearing and the second bearing. Such a configuration of bearings makes it possible to withstand an increased level of load and to be compatible with an increase in the rate of dilution.

Turbojet with bearing architecture optimised for the support of a low pressure shaft

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

An aircraft includes a wing having a first upstream spar and a second downstream spar extending in the direction of the span of said wing, and at least one propulsion unit supported by the wing. The propulsion unit includes a turboprop engine and a propeller. The propeller includes an external annular casing fixed to a suction surface of the wing, and at least to the first upstream spar via at least one first and second fastener.

Aircraft with a propulsion unit with offset fan

Engine comprising a propeller unit with a pair of contrarotating propellers (), a gas generator () supplying a power turbine (), the pair of propellers being rotationally driven by the shaft (A) of the power turbine via a speed reduction gearbox, the axis of rotation (XX) of the pair of propellers not being coaxial with that (YY) of the power turbine, the speed reduction gearbox comprising a differential gearset () and a first stage () comprising a simple gearset connecting the turbine shaft (A) and the differential gearset (), the engine air intake comprising an air intake duct (), the air intake duct () being in the shape of a lobe adjacent to the assembly formed by the simple gearset and the differential gearset ().

Turbine engine with a pair of contrarotating propellers placed upstream of the gas generator

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

An epicyclic gear device for driving rotation of a first blade set of a turbine engine, the device: including a sunwheel centered on a longitudinal axis of the turbine engine and connected to a rotor of the engine in order to be driven in rotation; at least one planet meshing with the sunwheel; a planet carrier rotatably carrying the planet and connected to a first blade set in order to drive it in rotation; and a ring meshing with the planet; the sunwheel being connected to the rotor via a first constant velocity ball transmission joint.

Epicyclic reduction device for the rotational drive of blade sets of a reduction turbomachine

A device for lubricating a turbomachine rolling bearing includes a rolling bearing mounted between an internal component and an external component. The bearing has rolling elements mounted between an outer ring secured to the external component and an inner ring secured to the internal component. The internal component includes at least one first duct for the passage of oil for supplying the internal ring of the bearing with oil, wherein the internal component is a stator component and at least one first duct is connected to an oil supply source configured to deliver the oil at a pressure high enough that this oil can be conveyed as far as the rolling elements of the bearing.

Device and method for lubricating a turbomachine rolling bearing

An aircraft propulsion engine including a fan case, and a cowl forming part of the nacelle of the engine and being designed to at least partially surround the case leaving a space between the cowl and the case, in which space at least one piece of equipment is mounted and extends along the axis of the engine, is provided. The cowl includes a wall and wall stiffeners fixed to the internal face of the wall. At least a part of the stiffeners of the cowl is arranged to form air guide ducts, the air guide ducts being assembled into an air distribution circuit to ventilate the equipment.

Growing community of inventors

Moissy-Cramayel, France

Tewfik Boudebiza