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: 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.

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 invention relates to a lobed mixer (8) for arranging on the downstream end of a hood (4) separating the two co-axial streams, respectively inner and outer, the mixer (8) being shaped so as to have a least one peripheral succession of lobes (20, 21) which are generally radially oriented in relation to a longitudinal axis (LL?) of the mixer, each lobe (20, 21) forming a channel extending mainly along the longitudinal axis and comprising at least one peripheral succession of baffles (26) from the first stream to the second stream and/or from the second stream to the first stream, arranged on said lobes (20, 21).

Abstract: A fluid intake system including a fluid collector scoop designed to be fastened on an inside surface of a wall in order to collect the fluid flowing on the outside of the wall; and an extraction duct suitable for directing the fluid from an inlet orifice into the duct to at least one outlet orifice from the duct, is provided. The scoop is arranged so as to direct the collected fluid towards the inlet orifice of the extraction duct. In this system, at least one outlet orifice is of substantially elliptical section with a ratio of the major diameter of the ellipse over its minor diameter being greater than 1.5.

Abstract: 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.

Abstract: A fluid intake system (10) comprising a fluid collector scoop (12) designed to be fastened on an inside surface of a wall (16) in order to collect the fluid flowing on the outside of the wall; and an extraction duct (14) suitable for directing the fluid from an inlet orifice into said duct to at least one outlet orifice from said duct; the scoop being arranged so as to direct the collected fluid towards the inlet orifice of the extraction duct. In this system, at least one outlet orifice (25) is of substantially elliptical section with a ratio of the major diameter of the ellipse over its minor diameter being greater than 1.5.

Abstract: An annular expansion ring centered on a main axis and suitable for being mounted on a fuel injector coaxial with the ring is disclosed. The ring presents holes that are distributed around the main axis and open out into its upstream face to enable air to pass towards the zone that is downstream from the ring. The ring includes a conical annular groove that converges downstream, that is open downstream, and that has the holes opening out into the upstream portion thereof. The axis of each of the holes makes an angle relative to the main axis that is strictly greater than the angle between the generator line of the cone defining the annular groove and the main axis, such that the air exiting from the holes impacts against the inner wall of the annular groove, i.e. its wall that is closer to the main axis.

Abstract: A propulsion gas exhaust assembly in an aircraft propelled by hot gases produced along the axis of the latter by a gas generator is disclosed. The exhaust assembly includes a duct which forms a vertical elbow and a nozzle.

Abstract: A propulsion gas exhaust assembly in an aircraft propelled by hot gases produced along an axis of the aircraft by a gas generator is disclosed. The propulsion gas exhaust assembly includes a transition element emerging in two duct elements each communicating with an ejection half-nozzle, wherein each of the two duct elements forms an elbow downstream of the transition element.

Abstract: A propulsion gas exhaust assembly is presented for use in an aircraft propelled by hot gases produced along the axis of the latter by a gas generator. The assembly may include a first cylindrical duct, two second ducts, two third ducts, and two axial gas-ejection nozzles. The first cylindrical duct element receives the gases downstream of the gas generator. The gasses flow downstream from the first cylindrical duct element to two second duct elements. These two second duct elements are divergent in a first geometric plane. Each of the two second duct elements may guide the flow to their own respective third duct and nozzle. The third ducts may include elbows to assist in stealth. The nozzles may include the means to steer the aircraft.

Abstract: The invention relates to the field of fuel injector systems. More particularly, the invention relates to an annular expansion ring centered on a main axis and suitable for being mounted on a fuel injector coaxial with said ring, the ring presenting holes that are distributed around said main axis and open out into its upstream face to enable air to pass towards the zone that is downstream from the ring. The ring includes a conical annular groove that converges downstream, that is open downstream, and that has the holes opening out into the upstream portion thereof, the axis of each of the holes making an angle relative to the main axis that is strictly greater than the angle between the generator line of the cone defining the annular groove and the main axis, such that the air exiting from the holes impacts against the inner wall of the annular groove, i.e. its wall that is closer to the main axis.

Abstract: The present invention relates to a propulsion gas exhaust assembly, in an aircraft propelled by hot gases produced along the axis of the latter by a gas generator, comprising a transition element (21) emerging in two duct elements (22, 23) each communicating with an ejection half-nozzle (24, 26), wherein each of the two duct elements (22, 23) forms an elbow downstream of the transition element.

Abstract: An axially symmetric turbojet-engine exhaust nozzle which is directable as a unit. The exhaust nozzle is situated downstream of an exhaust duct (1) fitted with a spherical wall (5). A single control ring (12) driven by linear actuators (30) allows regulation of the nozzle cross section and direction. Converging flaps (7) are guided on an upstream side by the spherical wall (5) and are supported at a downstream side by a control lever (13) which hinges on the control ring (12) and rests upstream on an external surface (16) of the spherical wall (5). Diverging flaps (10) hinge on the converging flaps (7) to form an inner ring of hot flaps. The diverging flaps (10) are situated downstream in an extension of the converging flaps (7) and further hinge on an outer ring of cold flaps (11), which in turn hinge on the control ring (12).