Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: An air inlet duct for 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.

Abstract: 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.

Abstract: 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.

Abstract: An aircraft including a fuselage, a lateral support wing (1) and a propulsion assembly (100) mounted under the wing. The wing includes at least two structural spars (11ba, 11bf) extending from the fuselage toward the tip of the wing, one of these (11ba) being upstream and the other (11bf) downstream. The propulsion assembly includes a gas generator (106) and at least two offset fans (102, 104) arranged on either side of the axis of the gas generator. The offset fans (102, 104) are attached directly to one of the spars (11ba, 11bf) and the gas generator (106) is attached directly to the two spars. The leading edge of the wing forms a given sweep of angle (?) with the axis of the fuselage. The two offset fans (102, 104) are axially offset from one another.

Abstract: A turbomachine of the «open rotor» 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.

Abstract: The invention relates to a turbomachine (24) of the «open rotor» type or a turboprop engine comprising a nacelle (26) defining an air inlet (28), a central hub (30) and an annular air intake section (32) surrounding the central hub (30) and opening into a air supply main section (34), with the central hub (30) comprising a central trap (36) having an aperture (38) for trapping the foreign objects in an air flow entering the turbomachine (24), and an air recovery channel (48) having a discharge end (48a), through which said air recovery channel (48) opens into the main section (34), provided on the central hub (30).

Abstract: The present invention relates to an aircraft comprising a fuselage, a lateral support wing (1) and propulsion assembly (100) mounted under the wing, the wing comprising at least two structural spars (11ba, 11bf) extending from the fuselage toward the tip of the wing, one of these (11ba) being upstream and the other (11bf) downstream, and the propulsion assembly comprising a gas generator (106) and at least two offset fans (102, 104) arranged on either side of the axis of the gas generator. The aircraft is characterized in that the offset fans (102, 104) are attached directly to one of the said spars (11ba, 11bf) and the gas generator (106) is attached directly to the two spars. In particular, with the leading edge of the wing forming a given sweep of angle (?) with the axis of the fuselage, the two offset fans (102, 104) are axially offset from one another.

Abstract: 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.

Abstract: 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.

Abstract: Air intake sleeve (32) for an aircraft turboprop engine, comprising an air bleed duct (54) that is oriented substantially along a first axis (A) and a duct (56) for supplying air to a compressor, which duct is oriented substantially along a second axis (B), at a distance from the first axis and substantially in parallel with the first axis, said air bleed duct and said supply duct being interconnected by an intermediate duct (60) having a general S shape, when viewed from the side, characterised in that said intermediate duct comprises, on at least one of the walls thereof, means for sucking air into the flow path of the intermediate duct, said suction means (64, 66) being positioned and/or designed to suck a boundary layer of said flow path.