Safran Aircraft Engines

Snecma

Nathalie Nowakowski

Michel Gilbert Roland Brault

Arnaud Nicolas Negri

Romain Guillaume Cuvillier

Guillaume Patrice Kubiak

Nils Edouard Romain Bordoni

Kevin Morgane Lemarchand

Gilles Alain Charier

Gilles Alain Marie Charier

Tewfik Boudebiza

Nicolas Jérôme Jean Tantot

Jeremy Dievart

Jonathan Evert Vlastuin

Thomas Alain Christian Vincent

Laurent Soulat

Yanis Benslama

Augustin Marc Michel Curlier

Pierre-Alain Jean Philippe Reigner

Henri Yesilcimen

Adrien Pierre Jean Pertat

Roland Gilbert Michel Brault

Thomas Alain Vincent

Bruno Albert Beutin

Caroline Marie Frantz

Antoine Jean-Philippe Beaujard

Augustin Curlier

Emmanuel Pierre Dimitri Patsouris

Nicolas Joseph Sirvin

Sebastien Christophe Chalaud

Nicolas Alain Bader

Philippe Gerard Chanez

Christian Sylvain Vessot

Sebastien Emile Philippe Tajan

Sébastien Christophe Chalaud

Matthieu Pierre Michel Dubosc

Dominique Gerhardt Mayhew

Nicolas Maurice Herve Aussedat

Jérémy Dievart

Kévin Lemarchand

Lionel Jean Leon Lefranc

Caroline Marie Franz

Kévin Morgane Lemarchand

Michel Gilbert Rolland Brault

Jean-Philippe Antoine Beaujard

Mathieu Lallia

Ludovic Michael Laurent Toupet

Nicolas Jerôme Jean Tantot

A turbofan includes a fan, a casing positioned downstream of the fan and separating a primary flowpath from a secondary flowpath, a compressor, a combustion chamber and a turbine being arranged in the primary flowpath, the turbofan having a differential transmission coupled to the turbine, and a power supply device configured to provide additional power to the one provided by the turbine to drive the compressor.

Turbofan comprising a power supply device to drive the compressor

Turbojet engine includes a fan, a compressor, a combustion chamber, and a turbine configured to rotatably drive the fan via a first reduction gear and the compressor via a second reduction gear, in which an outlet of the first reduction gear is rotatably coupled to an inlet of the second reduction gear by a reduction shaft, the reduction shaft being supported by a bearing arranged between the first reduction gear and the second reduction gear.

Turbojet with step-down mechanism

A turbofan having a dilution rate of at least 10 and including a fan having a disc provided with blades at the periphery thereof, a distance between the head of the blades and the housing of the fan being less than or equal to ten millimeters; a primary flow space and secondary flow space that are concentric; a turbine, housed in the primary flow space and in fluid communication with the fan; and a reduction mechanism coupling the turbine and the fan.

Gas turbine engine with minimal tolerance between the fan and the fan casing

A turbomachine comprising a ducted fan, a low-pressure turbine shaft and a reduction gearbox housed in a casing between the fan and the low-pressure turbine shaft, the fan rotor supplying airflow to a primary stream and a secondary stream and comprising a hub of diameter D, wherein&#x2014;the diameter Dof the fan rotor is greater than 82 inches (2.08 metres), &#x2014;the pressure ratio of the fan is between 1.10 and 1.35, the turbomachine comprises a low-pressure compressor separate from the fan, the reduction gearbox being interposed between the fan rotor and a turbine shaft of the low-pressure compressor, and wherein the reduction gearbox casing has an outside diameter Dgreater than the diameter Dof the hub, the pitch diameter Dof the reduction gearbox ring being between 0.15 and 0.35 times the fan rotor diameter.

Turbomachine with fan rotor and reduction gearbox driving a low-pressure decompressor shaft

Aircraft turbine engine, including at least one first compressor, an annular combustion chamber and at least one first turbine, which define a first flow duct for a primary flow. Between the combustion chamber and the first turbine is a device for discharging at least part of the primary flow.

Aircraft turbine engine comprising a discharge device

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 including a fuselage, a lateral support wing () and a propulsion assembly () mounted under the wing. The wing includes at least two structural spars () extending from the fuselage toward the tip of the wing, one of these () being upstream and the other () downstream. The propulsion assembly includes a gas generator () and at least two offset fans () arranged on either side of the axis of the gas generator. The offset fans () are attached directly to one of the spars () and the gas generator () is attached directly to the two spars. The leading edge of the wing forms a given sweep of angle (&#x3b1;) with the axis of the fuselage. The two offset fans () are axially offset from one another.

Aircraft with multiple fan propulsion assembly fixed under the wing

A multi-flow turbojet engine generally includes an upstream ducted fan driven by a gas generator, the gas generator having a first and a second compressor, which are coaxial, an inlet case forming a support for the rotors of the upstream ducted fan and of the first compressor, an inter-compressor case downstream of the inlet casing and forming a support for the rotors of the second compressor, attachment means for thrust take-up rods, which attachment means are arranged on the inter-compressor case. The turbojet engine includes at least one axial stress transmission rod for connecting the inlet case to the inter-compressor case.

Turbojet engine with thrust take-up means on the inter-compressors case

A turbofan engine including: a turbine shaft; a fan shaft; and a reduction mechanism coupling the turbine shaft and the fan shaft, is provided. The turbofan engine has a bypass ratio greater than or equal to 10, and the turbine shaft is supported by four bearings such that the flexural deformation modes of the turbine shaft are positioned in transient phase or outside the operating range of the turbofan engine.

Turbofan comprising a low-supercritical-pressure shaft

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 turbofan including a low-pressure shaft; a high-pressure shaft; a fan shaft; a reducing mechanism that couples the low-pressure shaft to the fan shaft; and a maximum of six chambers that accommodate the bearings of the low-pressure shaft, the bearings of the high-pressure shaft and the bearings of the fan as well as the reducing mechanism.

Turbojet engine comprising a simplified bearing lubrication unit

A turbomachine module includes a rotor supporting variable pitch blades, and an inner annular shaft, a blade pitch control device, a device for feathering at least one blade comprising at least one gas generator placed between a body and a movable member. The control device and the feathering device are situated radially between the shaft and the blades, the movable member is coupled with the at least one blade and capable, under the action of the gas generated and/or released by the generator, of being moved into a reference position wherein it entails a feathered position to the at least one blade.

Turbomachine module comprising a rotor supporting pitchable blades

An aircraft turbine engine includes a fan and a reduction gear including a plurality of rotary elements and driving the fan. The turbine engine further includes a gearbox and a mechanical power takeoff box driving the gearbox. The turbine engine includes a first toothed wheel and a second toothed wheel forming part of the mechanical power takeoff box and meshing with the first toothed wheel.

Aircraft turbine engine with improved mechanical power takeoff

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

A bypass turbojet engine including a low pressure shaft supported by at least two low pressure bearings, a high pressure shaft supported by at least two high pressure bearings, a fan shaft supported by at least two fan bearings, a reduction system coupling the low pressure shaft, with the fan shaft, enclosures housing the low pressure bearings, the high pressure bearings, the fan bearings and the reduction system, and a lubrication assembly including a closed oil circuit configured to supply oil to the enclosures in order to cool the bearings and the reduction system and at most five recovery pumps configured to recover oil from the enclosures.

Turbofan comprising a simplified bearing lubrication assembly

Growing community of inventors

Moissy-Cramayel, France

Nathalie Nowakowski