Safran Aircraft Engines

Snecma

Aircelle Limited

Safran Nacelles

François Gallet

Wouter Balk

Bertrand Desjoyeaux

Gilles Alain Charier

Olivier Kerbler

Jean-Pierre Serey

Nicolas Dezeustre

Nicolas Jérôme Jean Tantot

Hervé Hurlin

Mathieu Ange Poisson

Stéphane Rousselin

Alexandre Tan-Kim

Patrick Morel

Julien Michel Patrick Christian Austruy

Ivan Guy Rouesne

Patrick Joyez

Boris Briantais

Michel Brault

François Robert Bellabal

Mathieu Ange Alexis Poisson

Mario Lambey

An aircraft comprising a fuselage and propelled by a turbine engine having two coaxial and contrarotating fans, the turbine engine comprising a power turbine having two contrarotating rotors, one of which drives a fan upstream from the turbine, the other a fan downstream from the turbine, each fan comprising a ring of blades, and the assembly of the fans and the power turbine being incorporated at the rear of the fuselage, in the extension of same. The aircraft comprises, for at least one of the fans, a device for blocking the rotation of the fan and a device configured to modify the pitch of the blades of the fan in such a way as to make it operate as a flow straightener with respect to the other fan.

Aircraft comprising a turbine engine incorporated into the rear fuselage comprising a system for blocking the fans

An aircraft propelled by a turbojet having contrarotating fans, the turbojet being incorporated at the rear of a fuselage of the aircraft and in line therewith and including two gas generators that feed a working turbine having two contrarotating turbine rotors for driving two fans arranged downstream from the gas generators, and distinct air intakes for feeding each gas generator, the air intakes being connected to the fuselage of the aircraft so as to take in at least a portion of the boundary layer formed around the fuselage of the aircraft.

Aircraft propelled by a turbojet engine with contrarotating fans

A system for supplying pressurized air installed in an aircraft turbine engine, configured to supply pressurization air to a portion of the aircraft for using compressed air from pressurization air collected from a portion for collecting compressed air, characterized in that it comprises a collection port formed on a casing of the compressed air collection portion, a collection member coupled to the collection port, a through port of the collection member formed on a casing of a compartment of the turbine engine, said casing being subjected to small movements relative to the casing of the compressed air portion, the collection member crossing the through port with a freedom of movement relative to the latter during said small movements, a high-pressure space crossed by the collection member, located between the casing of the compressed air collection portion and the casing of the compartment.

System for supplying pressured air installed in an aircraft turbine engine including sealing means

The invention provides a suspension structure for suspending a turboprop () having two unducted propellers on a structural element of an aircraft, the suspension structure comprising a cradle () for fastening to a structural element of the aircraft and having two lateral beams () connected to a main beam () extending parallel to a longitudinal axis () of the turboprop so as to form a V-shaped cradle structure, the cradle being fastened to the turboprop via two angle members () connecting each free end of the lateral beams of the cradle to the turboprop, via an axial link () connecting one end of the main beam of the cradle of the turboprop, and via at least one transverse link () situated in a plane extending transversely relative to the longitudinal axis of the turboprop and connecting the cradle to the turboprop.

Structure for suspending a turboprop having two unducted propellers on a structural element of an airplane

A turboprop provided with a blade-positioning device including a stationary nacelle, a rotary nacelle including a plurality of blade roots, a turbine, the stationary and rotary nacelles and the turbine being coaxial along a longitudinal axis, a blade positioning device including for each blade a device configured to transform movement suitable for transforming a translation movement into a rotation movement, each one of the device for transforming movement being secured to the rotary nacelle and being suitable for pivoting a blade. The positioning device is placed between the inner surface of the stationary nacelle and the outer surface of the turbine, the positioning device including a member including a body secured to the stationary nacelle and a rod for sliding along an axis substantially parallel to the longitudinal axis.

Turboprop provided with a blade-positioning device

A nacelle for a turbojet engine is provided that includes an air intake upstream from the turbojet engine, a middle section intended to surround a fan of the turbojet engine and its case, and a downstream section. The middle section is made from at least one aerostructure capable of ensuring external aerodynamic continuity of the nacelle, and the aerostructure is rigidly bound, so as to be able to be taken apart, to at least one surrounding fixed structure.

Turbojet engine nacelle

A device adapted to be fitted with propeller blades includes a first retention ring including over a periphery thereof a plurality of radial bores; and a second retention ring including over a periphery thereof a plurality of radial bores, the first and second retention rings being mounted one on top of the other in the radial direction, each bore in the first retention ring being positioned opposite a bore in the second retention ring, a bore in the first retention ring arranged opposite a bore in the second retention ring forming a bore pair adapted to receive a foot of a blade.

Device adapted to be fitted with propeller blades

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Paris, France

François Gallet