Safran Aircraft Engines

Snecma

Institut Superieur De L'aeronautique Et De L'espace

Nicolas Joseph Sirvin

Daniel-Ciprian Mincu

Frédéric Dautreppe

Guillaume Pouyau

Jagoda Alina Worotynska

Anthony Binder

Eva Julie Lebeault

Jackie Raymond Julien Prouteau

Romain Jean-Claude Ferrier

Mathieu Patrick Jean-Louis Lallia

Alexandre Couilleaux

Gilles Alain Charier

Bruno Albert Beutin

Caroline Marie Frantz

Nathalie Nowakowski

Kevin Morgane Lemarchand

Antoine Elie Hellegouarch

Nicolas Jérôme Jean Tantot

Philippe Gerard Chanez

Philippe Gérard Chanez

Nicolas Alain Bader

Laurent Louis Robert Baudoin

Quentin Matthias Emmanuel Garnaud

Christian Sylvain Vessot

Jean-Loïc Hervé Lecordix

Romeo Brogna

Nicolas Maurice Herve Aussedat

Alexandre Gérard François Couilleaux

Romain Ferrier

Ludovic Michael Laurent Toupet

Lionel Jean Leon Lefranc

Mathieu Lallia

Xavier Carbonneau

Nicolas Garcia Rosa

Alejandro Martin Pleguezuelo

A process for using an air input of a turboreactor nacelle of an aircraft, comprising an air input lip which comprises at least one fixed portion and at least one portion which can be moved between a first position, in which the air input lip has an aerodynamic profile so as to guide the internal air flow over the internal wall in order to promote a thrust phase, and a second position, in which the portion is displaced in relation to the fixed portion so that the air input lip has a second radial thickness in the second position which is less than the first radial thickness in the first position so as to promote a reverse thrust phase.

Process for using an air input of a turboreactor nacelle comprising an air input lip which comprises a portion which can be moved to promote a thrust inversion phase

An air inlet duct or a nacelle of an aircraft propulsion assembly includes an annular body and an annular air inlet lip with two coaxial annular walls, inner and outer, respectively. The inner wall defining a portion of an inner annular surface of the air inlet duct and the outer wall defining a portion of an outer annular surface of the air inlet duct. A control system translates the lip from a first position, in which the lip is attached to the body, to a second position, in which the lip is axially separated from the body. An annular row of grilles is translatably secured to the lip. The grilles are housed inside the body in the first position and extended from the body in order for an air flow entering the air inlet duct to pass therethrough in the second position.

Air inlet duct for a nacelle of an aircraft propulsion assembly

An aircraft turbojet engine extending along an X axis and comprising a blower configured to provide a reverse thrust and a nacelle comprising an air intake which comprises at least one deflection member movably mounted between a deployed position in which the deflection member projects from the inner wall or from the lip of the air intake in a radially inward direction of deployment facing the X axis or in a longitudinal direction of deployment with respect to the X axis, in order to allow a release of the reverse air flow from the inner wall to support the reverse thrust phase, and a retracted position in which the air intake has an aerodynamic profile so as to guide the internal air flow along the inner wall in order to support the thrust phase.

Turbojet engine comprising a nacelle with an air intake to promote a reversed thrust phase

The invention relates to an assembly for a turbomachine, comprising: —a nacelle comprising an inlet lip which defines an air inlet, and—a device for modifying the geometry of the air inlet, comprising: —a first spout, and—a second spout, the first spout and the second spout being translatably movable in relation the nacelle between: —a first configuration, in which the first spout forms the inlet lip and the second spout extends inside the nacelle, and—a second configuration, in which the first spout extends away from the inlet lip, and the second spout forms the inlet lip so as to define an air flow channel between a downstream surface of the first spout and an upstream surface of the second spout.

Assembly for a turbomachine

An aircraft turbojet engine comprising a fan configured to provide a reverse thrust and a nacelle comprising an air intake, the air intake comprising at least one circulation duct in the annular cavity opening, on the one hand, at the air intake lip and, on the other hand, at the inner wall and/or the outer wall so as to promote a reverse thrust phase, the air intake comprising at least one cover member mounted to move between a covered position, in which the cover member closes the circulation duct at the air intake lip and an uncovered position, in which the cover member opens the circulation duct at the air intake lip.

Turbojet comprising a nacelle with an air intake for promoting a reverse thrust phase

Method for using an air intake of a turbojet engine nacelle comprising at least one elastically deformable portion, at least one connecting member mounted in an annular cavity integrally with the elastically deformable portion, and at least one controllable displacement member, in which method: during a thrust phase of the turbojet engine, the controllable displacement member moves the connecting member into a first position in which the elastically deformable portion of the air intake lip has an aerodynamic profile, and during a thrust reversal phase of the turbojet engine the controllable displacement member moves the connecting member into a second position in which the elastically deformable portion of the air intake lip has an irregular profile so as to allow a release of the reverse air flow from the elastically deformable portion.

Method for operating an air intake of a turbojet engine nacelle during a thrust phase and during a reverse thrust phase

The invention relates to an arrangement, in a pod of an aircraft propulsion assembly, for drawing in air and trapping foreign bodies. Said arrangement includes a main air inlet duct () separating into, on one hand, a channel () for leading air to a compressor and, on the other hand, a bypass channel () capable of trapping foreign bodies () that enter said main duct (). Said arrangement comprises a heat exchanger () that extends along a section of the bypass channel (). Said heat exchanger () carries out surface heat exchange along said section and is coupled with an external oil system in order to cool the oil thereof by heat exchange with the air () flowing in the bypass channel (). Said bypass channel () has an air outlet () acting as a means for discharging the foreign bodies ().

Arrangements for drawing in air and trapping foreign bodies in an aircraft propulsion assembly

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 turbomachine of the &#xab;open rotor&#xbb; type or a turboprop engine comprises a nacelle defining an air inlet, a central hub and an annular air intake section surrounding the central hub and opening into a air supply main section, with the central hub comprising a central trap having an aperture for trapping the foreign objects in an air flow entering the turbomachine, and an air recovery channel having a discharge end, through which said air recovery channel opens into the main section, is provided on the central hub.

Turbomachine comprising a trap for foreign objects circulating in an air flow

A turbine engine nozzle having confluent streams, the nozzle including a core cowl arranged around an annular central body and co-operating therewith to define a core annular channel for passing a flow of a core stream, the core stream on entry into the nozzle possessing an azimuth component driving residual gyratory movement of the core stream in two opposite gyratory flow directions corresponding to two operating speeds of the engine, the core cowl having an annular upstream portion that is extended downstream by an annular terminal portion having longitudinal cuts forming a plurality of flaps that overlap radially in pairs via their respective side edges in such a manner that, for each flap, one of the two side edges of the flap is positioned internally relative to the corresponding side edge of one of the adjacent flaps, while the other side edge of the flap is positioned externally relative to the corresponding side edge of the other adjacent flap.

Turbine engine nozzle having confluent streams and including a core cowl with overlapping flaps

An air guidance device for a turbomachine includes an air supply channel of a turbomachine engine. The supply channel has an upstream section and a downstream section connected together by a diverting section, the upstream section and the diverting section being connected together via an internal elbow and an external elbow. At the internal elbow, the internal surface has a groove extending longitudinally in the longitudinal direction of the supply channel and the longitudinal edges of which are widened in the direction of the downstream end of the upstream section of the supply channel.

Air guidance device for a turbomachine with grooves to maintain boundary layer

An exhaust centerbody for a turbine engine is provided. The centerbody includes a truncated downstream part, which is connected to an upstream part by an annular ridge marking a discontinuity between the outer surfaces of the upstream and downstream parts. The outer surface of the downstream part has a substantially conical general shape, of which the tip is oriented downstream and is positioned in the region of the axis A, the axial half-section of this outer surface defining a line of which the upstream end part is substantially tangential to a straight line passing through the ridge and forming a non-zero angle &#x3b1; with a tangent to the outer surface of the upstream part, in the region of the ridge, and of which the downstream end part is substantially tangential to a straight line passing through the tip and forming a non-zero angle &#x3b2; with the axis A.

Exhaust centerbody for a turbine engine

A method of mixing in a discharge conduit, in a turbine engine with two or more flows, of a primary flow and a secondary flow, the two flows emerging in the discharge conduit by two coaxial ducts, separated by an internal housing which has an end downstream relative to the flow direction of the flows, the two coaxial ducts each being defined between an internal wall and an external wall, upstream of the downstream end of the internal housing, and the secondary flow surrounding the primary flow, is provided. The method includes disposing a divergent radial deflection device in the primary duct, spaced apart from the walls of the primary duct. A turbine engine including the deflection device is also provided.

Growing community of inventors

Moissy-Cramayel, France

Nicolas Joseph Sirvin