Abstract: A vane for a turbojet engine, is disclosed having an airfoil-shaped body with a leading edge, a trailing edge, a generally concave sidewall and a generally convex sidewall defining a hollow vane interior. A cooling air supply duct extends substantially over the entire length of the vane and communicates with a turbulence chamber in the vicinity of the leading edge which is separated from the supply duct by a partition having air cooling orifices to allow the air to pass from the cooling air supply duct into the turbulence chamber. The air from the turbulence chamber is evacuated through evacuation orifices defined by the generally convex sidewall in the vicinity of the leading edge. A plurality of heat exchange members are located in the interior of the vane such that they are spaced apart, extend substantially parallel to each other and substantially perpendicular to a longitudinal axis of the vane.

Abstract: A transition pipe for location between an afterburner pipe and a jet nozzle in a jet pipe assembly for a turbojet engine comprises a funnel shaped inner casing tapering downstream from a circular section at its upstream end to a quadrangular section at its downstream end, a horn shaped outer casing surrounding the inner casing and flared downstream from a circular upstream end section to a downstream end section formed of four joined segments of generally parabolic shape, and a plurality of peripherally spaced, longitudinally extending stiffeners interconnecting the inner and outer casings in the space therebetween.

Abstract: Disclosed is an improved device to control and regulate the opening and closing of a cross section of a turbojet propulsive nozzle having at least one hydraulic cylinder acting on at least one movable flap element. The invention includes a first system to supply the cylinder with hydraulic fluid under pressure for normal operation and a second supply system to be used in an emergency. The elements for changing from the normal operation to an emergency operation are combined with the elements to generate in the hydraulic cylinder a differential pressure, such that the cross section of the nozzle assumes an intermediate position assuring sufficient thrust for the engine, while avoiding the danger of overloading the compressor. The system is effected automatically when the pilot actuates the emergency supply system.