Safran Aircraft Engines

Snecma

Christian Sylvain Vessot

Bruno Albert Beutin

Matthieu Leyko

Philippe Gérard Chanez

Philippe Gerard Chanez

Sébastien Christophe Chalaud

Mathieu Patrick Jean-Louis Lallia

Gilles Alain Charier

Nathalie Nowakowski

Marc Patrick Tesniere

Kevin Morgane Lemarchand

Nicolas Joseph Sirvin

Nicolas Alain Bader

Romain Jean-Claude Ferrier

Bastien Pierre Verdier

Hervé Jean Albert Mouton

Gabriela Philippart

Nicolas Maurice Herve Aussedat

Guillaume Rodolphe Jacques Gérard Pouyau

Lauren Davis

Sébastien Chalaud

Mathieu Lallia

Lionel Jean Leon Lefranc

Ludovic Michael Laurent Toupet

Propulsion assembly comprising a duct for feeding the gas generator in an inter-duct casing

The outlet of a heat exchange circuit extending under a wall, such as a nacelle cowling of an aircraft engine, is divided into openings in the form of parallel slots which are elongated in the longitudinal direction and successively arranged in the transverse direction to divide the hot gas into streams while facilitating the circulation of fresh gas streams, originating from an external flow, on the intermediate laminates. The hot gas cannot fall back easily onto the outer face of the wall and risk damaging the wall, and the gas mixes more effectively with the fresh outdoor air. The openings are provided with nozzles flaring in the transverse direction and the downstream longitudinal direction to facilitate the mixing of the hot and cold gas streams.

Outlet of a hot-gas pipe of an aircraft engine passing through an engine wall

A turbomachine including at least one stator vane sector () and a fluid distribution circuit (), the stator vane sector comprising at least one vane (), a fluid inlet (), a fluid outlet (), and a channel () providing fluid flow connection between the fluid inlet and the fluid outlet while extending at least in part in the vane (), the vane and the channel being adapted, to enable heat to be exchanged between a hot fluid passing through the channel and a stream of cold air passing through the vane sector, the fluid distribution circuit () presenting a feed pipe () and a recovery pipe (), the fluid inlet () being in fluid flow connection with a branch tapping () of the feed pipe () while the fluid outlet () is in fluid flow connection with a branch tapping () of the recovery pipe ().

Turbomachine provided with a vane sector and a cooling circuit

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

An aircraft propulsion assembly, comprising a gas generator and two fans rotated by the gas generator and offset on either side of a vertical plane passing through the axis of said gas generator. The propulsion assembly comprises an air inlet sleeve comprising an inlet pipe oriented along a first axis that is substantially parallel and offset with respect to a longitudinal axis of the gas generator, the inlet pipe dividing into a supply pipe that is connected to an inlet opening of the gas generator and a discharge pipe configured such that particles ingested by the inlet pipe are discharged without entering the gas generator.

Propulsion assembly for an aircraft, comprising a gas generator, two offset fans and an air inlet sleeve

The invention relates to an aircraft propulsion assembly (), comprising a single gas generator () and two fans () drive in rotation by the gas generator () and offset on either side of a vertical plane passing through a longitudinal axis (X) of the gas generator, the rotational axes of the fans lying substantially in the same fan plane. According to the invention, the propulsion assembly () comprises an air inlet fairing formed upstream of a nacelle () connecting the fans, said fairing () having, between the fans (), an air inlet opening (') lying substantially perpendicular to the fan plane and on either side of this plane, the propulsion assembly further comprising an air supply device configured so as to supply the gas generator () with a part of the incoming air and to take off, from the remaining part of the incoming air, a cooling airflow intended to cool elements of the propulsion assembly and/or a wing supporting the propulsion assembly.

Propulsion assembly for an aircraft, comprising a gas generator and two offset fans

A forward fan rotor is disclosed with a hub of axis of rotation (X) and a cone mounted on the hub of the fan. The cone comprises an air bleed orifice which opens into an air duct of which a forward end portion passes through the fan rotor, said forward end portion comprising mechanical air entrainment means. The air bleed orifice has an annular shape and in that the cone is divided by said orifice into a front vertex portion and a rear frustoconical portion. A turbomachine forward axial spool equipped with such a fan rotor is also disclosed.

Fan rotor for a turbo machine such as a multiple flow turbojet engine driven by a reduction gear

A device for circulation of air for a turbomachine, the device including an inlet provided to receive incident airflow, air circulation ducts connected to the inlet, a central part including side walls, peripheral walls arranged at a distance from the central part, so as to form the air circulation ducts, each duct being arranged between one of the side walls of the central part and one of the peripheral walls, each peripheral wall including an upstream end portion delimiting with one of the side walls an inlet orifice of one of the ducts and a downstream end portion delimiting with one of the side walls an outlet orifice of one of the ducts, at least one member mobile in translation relative to the peripheral walls, the at least one mobile member being formed in the central part and arranged so that its displacement varies a section of each of the inlet orifices and a section of at least one of the outlet orifices.

Air circulation device for turbomachine

Growing community of inventors

Moissy-Cramayel, France

Christian Sylvain Vessot