Snecma

Safran Aircraft Engines

Philippe Gerard Chanez

Christian Sylvain Vessot

Gilles Alain Charier

Bruno Albert Beutin

Nathalie Nowakowski

Marc Versaevel

Jacky Novi Mardjono

Kevin Morgane Lemarchand

Nicolas Joseph Sirvin

Didier Jean-Louis Yvon

Thomas Alain Christian Vincent

Nicolas Alain Bader

Jean-Loic Herve Lecordix

Pierre Philippe Marie Loheac

Henri Yesilcimen

Mathieu Patrick Jean-Louis Lallia

Pascal Moise Michel Bigot

Maxime Koenig

Claude Sensiau

Nicolas Maurice Herve Aussedat

Franck Zaganelli

Kamel Zeggai

Stephane Jacques Francois Thomas

Gaetan Jean Mabboux

Jeremy Paul Gonzalez

Philippe Gilles Minot

Mathieu Lallia

Lionel Jean Leon Lefranc

Ludovic Michael Laurent Toupet

Pascal Moise Bigot

Pierre Philippe Loheac

Jeremy Gonzalez

Jacky Mardjono

Lamine M'BENGUE

Jérémy Gonzalez

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 double flow turbojet includes a fan including a disk centered on an axis of the fan which is provided with fan blades on its periphery, the blades having a leading edge, and an air inlet sleeve extending upstream of the fan and configured to delimit a gas flow designed to enter into the fan the air inlet sleeve having a collecting surface, the turbojet having an aspect ratio included in the interval where L/D is the form factor of the air inlet sleeve.

Low fan noise turbojet

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 device for reducing the jet noise of a turbine engine includes an outer cover having an inside wall defining the outside of an annular passage for passing a bypass stream from the engine, the wall of the outer cover including a plurality of microjet circuits, each including intakes for taking a gas stream from the bypass stream flow passage and leading to a single feed duct, which in turn opens out into the trailing edge of the outer cover via at least one ejection grating suitable for splitting the intake gas stream into a plurality of gas streams of right sections of dimensions less than a right section of the feed duct.

Device with gratings for ejecting microjets in order to reduce the jet noise of a turbine engine

An assembly including a gas turbine engine and a nacelle in which the engine is housed, the nacelle including an air intake fairing that forms an air inlet and includes: a member for deflecting foreign objects, which together with the fairing, forms an air intake duct; and, downstream from the deflecting member, a secondary deflecting channel, and a main channel for supplying air to the engine. The air intake duct is configured to deflect at least some of the foreign objects sucked in through the air inlet towards the secondary deflecting channel. The secondary deflecting channel is shaped such that the flow velocity of the air flowing therethrough increases from upstream to downstream, the secondary channel having an outlet with an opening leading into the outer wall of the nacelle.

Gas turbine engine air intake in a nacelle

An airplane provided with dual-flow turbojet engines having nacelles at least partially encased in the fuselage, wherein the air intake of each engine is connected to the fuselage by two boundary layer guiding walls, the walls extending towards the upstream side of the air intake and being spaced apart towards the upstream side.

Airplane having engines partially encased in the fuselage

A turbofan exhaust system includes at least one exhaust nozzle with a trailing edge having an upper edge, a lower edge, an inner lateral edge-and an outer lateral edge. The upper edge is upstream with respect to the lower edge. The outer lateral edge of the exhaust nozzle is also upstream of the inner lateral edge. This arrangement makes it possible to reduce the noise perceived in the cabin of the aircraft at the same time as the noise perceived on the ground.

Turbofan exhaust system

The present invention relates to an air inlet for a nacelle of a jet engine with a front fan, comprising an upper part (S), a lower part (I), an inner lateral part () and an outer lateral part (ext), defining a leading edge () between an external wall () of the nacelle and an internal wall () forming the air supply channel of the jet engine. According to the invention, the air inlet is characterized in that the leading edge of the outer lateral part () is to the rear with respect to the leading edge of the inner lateral part (int). Preferably, the leading edge of the upper part (S) is likewise to the rear with respect to the leading edge of the lower part (I).

Air inlet for a turbofan engine

The invention relates to an exhaust nozzle for a bypass turbomachine, the nozzle comprising a central body, a primary cowl surrounding the central body to define a primary channel, and a secondary cowl surrounding the primary cowl to define a secondary annular channel, the secondary cowl comprising a stationary portion and a movable portion disposed to extend the stationary portion and capable of moving longitudinally upstream and downstream relative to the stationary portion and relative to the primary cowl so as to vary the exhaust section and/or the throat section of the nozzle, the stationary portion of the secondary cowl presenting a plurality of spaced-apart repetitive patterns disposed extending its trailing edge, and the movable portion of the secondary cowl including in its outside surface a plurality of indentations of shapes complementary to the patterns of the stationary portion.

Gas exhaust nozzle for a bypass turbomachine having an exhaust or throat section that can be varied by moving the secondary cowl

Growing community of inventors

Paris, France

Philippe Gerard Chanez