Abstract: The invention relates to an aeronautic engine (1), comprising: a housing (10), made of electrically insulating material, said housing (10) comprising at least one metallic piece (16a, 16b, 17, 18), a structural piece (2) of the engine (1), comprising metallic material (2, 3) and connected to the housing (10), and an equipment (30), fixed to the housing (10), the aeronautic engine (1) being characterized in that the equipment is connected to the structural piece (2) by means of the metallic piece (16a, 16b, 17, 18) by means of an electrically conductive connecting path (20, 22).

Abstract: The invention proposes an arrangement of a tank of lubrication liquid for an aircraft turbomachine (12), under a nacelle cowling (10) covering said turbomachine (12), with the tank being arranged in the volume located between the turbomachine (12) and the nacelle cowling (10), with the nacelle cowling (10) comprising an opening (22) for access to said volume, characterised in that the tank (18) is fastened to an internal face (20a) of a panel (20) closing off said opening (22), with the unit formed by the panel (20) and the tank being added onto the nacelle cowling (10) and able to be mounted and dismounted from the nacelle cowling (10).

Abstract: An intermediate casing for a turbojet fan compartment, including: a shroud centered along a longitudinal axis of the turbine engine; an annular cheek plate centered along the longitudinal axis of the turbine engine and mounted against a downstream face of the shroud; a suspension beam fastened to the cheek plate and extending downstream parallel to the longitudinal axis of the turbine engine; and an AGB suspended from the beam and including an upstream side face spaced apart axially from the cheek plate, a downstream side face opposite the upstream side face, and a plurality of accessories mounted against its downstream side face and distributed about the longitudinal axis of the turbine engine.

Abstract: A by-pass turbojet including a thrust reverser is disclosed. The thrust reverse includes a deflector device which deflects all or part of the primary stream gas in such a manner that the deflected primary stream gas encounters the secondary stream, thereby reducing the injection speed of the secondary stream in an aft direction, and thus generating the thrust-reversal effect. The secondary stream escapes from the aft end of the nacelle. In the thrust-reversal position, the deflector device is inscribed radially substantially within the section of the primary nozzle cowl at the aft end of the nacelle. Such a thrust reverser is particularly simple in design, inexpensive, and makes it possible to avoid having moving parts present on the outside portion of the nacelle, thus simplifying the design of the turbojet.

Abstract: An intermediate casing for a turbojet fan compartment, including: a shroud centered along a longitudinal axis of the turbine engine; an annular cheek plate centered along the longitudinal axis of the turbine engine and mounted against a downstream face of the shroud; a suspension beam fastened to the cheek plate and extending downstream parallel to the longitudinal axis of the turbine engine; and an AGB suspended from the beam and including an upstream side face spaced apart axially from the cheek plate, a downstream side face opposite the upstream side face, and a plurality of accessories mounted against its downstream side face and distributed about the longitudinal axis of the turbine engine.

Abstract: Deflection system for a gas stream 11 in an exhaust nozzle 10 of a flying craft, comprising fixed structural housings 18,20 which extend perpendicularly to the gas stream 11 and which are fed with deflection gas through one of their ends external to the nozzle 10, these housings 18,20 containing in their side walls 22,28 gas injection slits 23,30 oriented in oblique directions 24,26 relative to the gas stream 11, and controlled means for the adjustable closure of these slits 23,30.

Abstract: Exhaust nozzle 14 for an engine of a flying craft, comprising a tubular body with two outlet ducts 16, 18 and boxes 26, 28 for injecting gas into the outlet ducts for the purpose of thrust vectoring, these boxes having windows 38 aligned with slots 39 formed in the outlet ducts, and controlled means for adjusting the outflow of gas injected into the outlet ducts.

Abstract: A by-pass turbojet including a thrust reverser. The thrust reverse comprises deflector means for deflecting all or part of the primary stream gas in such a manner that the deflected primary stream gas encounters the secondary stream, thereby reducing the injection speed of the secondary stream in an aft direction, and thus generating the thrust-reversal effect. The secondary stream escapes from the aft end of the nacelle. In the thrust-reversal position, the deflector means are inscribed radially substantially within the section of the primary nozzle cowl at the aft end of the nacelle. Such a thrust reverser is particularly simple in design, inexpensive, and makes it possible to avoid having moving parts present on the outside portion of the nacelle, thus simplifying the design of the turbojet.