Abstract: This device embodies a centrifugal compressor secured to a joint-carrier disk secured to an upstream flange of the rotor disk to be cooled. The recompressed air is ejected through channels near the roots of the blades of the disk.

Abstract: The disclosed invention relates to a sealing device for the rotor blades of a gas turbine engine which permits real time adjustment to be made of the clearances between the rotor blade tips and the sealing structure. The sealing shroud around the turbine wheel is formed of sectors, each sector being attached to a monolithic short response time ring and a monolithic long response time ring. Ventilating air from upstream of the turbine wheel is directed onto the rings such that the sectors are caused to radially expand or contract in compliance with the expansion or contraction of the tips of the rotor blades during stabilized and transient engine operational modes. A small positive clearance between the sealing sectors and the blade tips is maintained throughout the range of the engine's operation.

Abstract: Convergent flaps of a jet engine nozzle are controlled by actuating cylinders through actuating levers hinged to the fixed structure of the engine and by connecting rods. Divergent flaps are slaved to the convergent flaps by connecting rods themselves driven by the actuating levers. Cold flaps not hinged to the divergent flaps are slaved to the convergent flaps by further connecting rods connected to the first-named connecting rods.

Abstract: A turbojet engine has an outlet duct to which an annular array of actuating cylinders for nozzle flaps are hinged. The housings for the cylinders are connected together by transverse members to form a rigid structure coaxial with the outlet duct. The arrangement includes convergent flaps and slaving devices for divergent flaps, all hinged to the rigid structure and particularly to the housings.

Abstract: A nozzle comprises: a set of first flaps articulated to a rigid structure, and forming a convergent; a set of second flaps each articulated to a corresponding first flap, and forming a divergent; a set of third flaps each of which is connected at a position between two adjacent second flaps and which is, on the one hand, articulated to the rigid structure and, on the other hand, linked to each of the two adjacent second flaps by carrier linked to the aforesaid third flap by a ball joint.

Abstract: A connection device is disclosed for connecting a burner ring or flame holder made of a composite material and having a "V"-shaped cross-section, to an afterburner chamber duct of a turbojet engine. The connecting device has a cylindrical portion and a trapezoidal portion. The cylindrical portion extends through hollow projections formed from the composite ring material and extending from the ring in an upstream direction. The converging, opposite sides of the trapezoidal portion bear against inner surfaces of the converging flanges forming the "V" cross-section of the ring. The cylindrical portion is then attached to the afterburner duct via a link-bar mechanism.

Abstract: Retaining structure for a turbo-machine forming an annulus having a complex ircumferential construction comprising a cylindrical sector of a high mechanical strength material protecting a member secured on the casing of the machine. The complementary sector of the annulus is a honeycomb structure mounted between an internal and an external skin. The cylindrical sector is formed by a thickening of the internal skin. A strap of a material with a high elastic modulus serves to secure at least the complementary sector.

Abstract: A ring of an annular valve assembly is movable in the direction of its longitudinal axis and is intended for an axial compressor blow-off arrangement. The ring takes the form of an axially orientated channel-section member having a first annular skin of concave section nested in a second annular skin also of concave section. A cavity filled with a synthetic resin filler is defined by the two skins. The blow-off arrangement for an axial-flow compressor of a turbo-jet engine, which incorporates this ring, comprises an annular opening with which the ring cooperates to re-form the wall of the air flow when the blow-off arrangement is inoperative.

Abstract: The rotor of each stage of a turbine is surrounded, with a clearance by a fixed ring, formed by a metal ring supporting internally an annular thermal screen, in the form of ceramic segments. Expansions and contractions of the metal ring under the action of air which is supplied thereto in order to control the said clearance are transformed into displacements of radial faces of the ring in contact with radial flanges rigid with the turbine casing and seals serve to ensure fluidtightness of the ring.

Abstract: The invention relates to a variable area nozzle for a turbo-jet engine. This nozzle comprises a convergent portion, formed by a fixed semi-shell (2) and a semi-shell (3) pivotal about a diametral axis (4a-4b); the fluid-tightness of the convergent portion is ensured by a substantially semi-circular seal (6) and by two longitudinal seals (7a, 7b). The nozzle can be used for example with an engine comprising a partial re-heat system of moderate output.

Abstract: In a multi-spool turbo machine, a first shaft of the low pressure spool is supported for rotation with respect to a second shaft of the high pressure spool and is located with respect to the second shaft by means of a roller bearing. Rollers of the bearing are inserted between an internal ring mounted on the second shaft and an outer ring mounted by a ring support assembly carried by the first shaft. The ring support assembly includes a ring support member which comprises, at its outer periphery, a first toothed element cooperating with a second toothed element carried by retaining means. The ring support member is held axially by a channel-section member.

Abstract: A device for attaching the stator vanes of an axial compressor to an external housing is disclosed. The attachment utilizes an inner casing, having the vanes mounted on it, and an outer casing surrounding the inner casing in such a manner that differential thermal expansion between the various elements is minimized. This allows more accurate control of the clearances between the rotor and the stator.

Abstract: A vane for a convergent-divergent nozzle is constituted by a central body d a base plate. The central body comprises a reinforcement substantially in the shape of an isoceles triangle and of channel section, the reinforcement having internal and external edge flanges and a cover plate of the same shape and dimensions as the reinforcement, the reinforcement being secured to the flanges of the latter.The base plate is rectangular and has a triangular opening of a contour corresponding to that of the reinforcement. The central body is secured to the base plate by securing means constituted by a profiled member of a shape corresponding to that of the opening.The central body is of a composite carbon-carbon material; the base plate and securing means, of steel.

Abstract: A sealing device is disclosed for maintaining a small positive clearance between the sealing sectors and the turbine blade tips of a turbojet engine. The sealing segments are connected to an internal ring structure and an external ring structure located within the casing of the jet engine. The two ring structures serve to expand and contract the diameter of the ring formed by the sealing segments in conjunction with the expansion and contraction of the turbine blades for stabilized and transient engine operating modes. The device utilizes ventilating air taken from a stage of the jet engine compressor to cause the radial expansion or contraction of the internal and external rings in direct conjunction with the conditions under which the engine is operating.

Abstract: Device for the containment of fragments of a fan ring in the event of burng of the ring.The fan ring comprises two cylindrical surfaces spaced axially and located radially inside of two containment rings of high tensile strength in the circumferential direction, engaged respectively in grooves of two parts of the rotor, located on either side of the fan ring.

Abstract: A system is disclosed for attaching a cap of composite material to the exhaust housing of a turbojet. The system consists of three triangular rod assemblies arranged between the housing and the cap. The triangular rod assemblies bear at their ends eyelets pivotally connected to brackets attached to the housing. The connecting rods are connected to the brackets by means of pivot pins, and to the cap by an attachment part and pivots. The attachment part is fixed to the cap by a bolt. The housing and the cap have cooperating bearing surfaces as well as a seal device.

Abstract: A system for cooling a gas turbine by bleeding air from the compressor and channeling the air at the center of the engine towards the turbine in order to cool it. The air is bled from the plane of the disc bearing the blades of the compressor, said disc having radial ducts for the flow of the air. The invention is utilized in gas turbine engines to cool the turbine.

Abstract: A ferrule surrounding the blading of a rotor is lined externally with an assembly of elements of revolution. These elements are in the form of cylindrical rings, circular rings or of tori supported between blocking elements. The assembly is formed by alternating rings made of a composite or metallic material and a winding of fibers encased in a polymerizable resin.

Abstract: A fuel intake tube passes radially through an engine casing. It is surrounded between the casing and an injector head by a second tube attached to the casing. Guidance means and a sealing element are provided between the fuel intake tube and the second tube. The device is equipped with one or more injector heads. The guidance means consist of two elements: a cap and cylindrical projections.

Abstract: Two groups of half shells capable of being retracted from the jet flow, in a position closing the jet pipe. The thrust reverser and the silencer are concentric and their axes of rotation are upstream with respect to their position in the jet flow.