Abstract: A turbomachine roller bearing that supports a shaft constituted by a trunnion of a shaft line of a high-pressure spool of a turbomachine to rotate relative to a stationary support that is connected to a casing of the turbomachine, said bearing comprising rollers inserted between an outer ring disposed adjacent to the stationary support and an inner ring disposed adjacent to the high-pressure trunnion, the inner ring extending along the axis beyond a downstream end of the high-pressure trunnion to which it is secured by clamping means, and being provided with anti-rotation means for preventing said inner ring from rotating relative to the high-pressure trunnion.

Abstract: A device for axially holding a ring spacer sector of a high-pressure turbine of a turbomachine, said spacer sector comprising an upstream radial wall provided with an outer upstream tongue for being engaged in a corresponding upstream groove of a casing of the turbine, and with an inner upstream tongue for being engaged in a corresponding upstream groove of a ring sector, said device comprising a piece of longitudinally-extending sheet metal that constitutes a heat shield disposed upstream from the upstream radial wall of the spacer sector against an inner surface of the casing, the piece of longitudinally-extending sheet metal bearing axially against the upstream radial wall of the spacer sector and being secured to the casing so as to hold the spacer sector axially.

Abstract: This invention pertains to an absorber in elastomer material for a connecting component, such as a connection rod, the said component having a head with two faces parallel to each other and traversed by a bore forming a housing for a ball-joint with its cage. The absorber is characterised in that it has two elements in the form of discs, parallel to each other, each with a central opening sufficiently wide so as not to cover the portions of the ball-joint protruding in relation to the head and connected at their periphery by means of connection. The present invention is applied in particular to suspension connecting rods installation of the accessories gearbox of a turbojet.

Abstract: This object is achieved by the bleed-off means comprising means for tapping air from the primary duct which are arranged upstream of the intermediate casing and means for evacuating the air tapped into the secondary duct downstream of the support arms, these means comprising conduits arranged around the intermediate casing under the platforms.

Abstract: A turbine blade including a head at its peripherally outer end, and on the outside face thereof at least one wiper is formed having a first end portion and a second end portion, with a wiper tip extending between the two end portions. The first portion situated on the suction side of the blade is taller than the second end portion to form a sawtooth effect between the wipers of two adjacent blades mounted on a turbine rotor. The tip of each wiper presents a convex surface between the first portion and the second portion.

Abstract: The balancing device is applicable to a rotor (10) disk (14) provided with a rim (18). It comprises housings (36, 38) formed in the rim (18), balancing masses (40, 30) housed in the housings (36, 38), the housings (36, 38) being closed off by a spring retaining ring (44, 442, 444). Application to a rotor (10) with integrally bladed disks (14).

Abstract: A nozzle comprising an inner barrel, a centerbody disposed inside the inner barrel so as to define a first channel for a primary flow, and an outer barrel surrounding the inner barrel so as to define a second annular channel for a secondary flow, the free end of the inner barrel presenting a surface having a first series of undulations made up of negative undulations alternating with positive undulations, the centerbody presenting a second series of undulations made up of negative undulations alternating with positive undulations, the negative and positive undulations of the series of undulations being of radial height that varies angularly and being disposed in such a manner that the negative undulations of the first series are disposed facing negative undulations of the second series, and vice versa, so as to generate turbulence and radial shear between the primary and secondary flows while conserving a constant flow section around the entire circumference of the nozzle.

Abstract: A method of measuring the adhesion of a coating to a substrate, wherein the measurement is done in air and wherein an ultrasound transducer is applied to the substrate by means of a thin film of gel, and a quality factor is calculated, given by the ratio between the amplitudes of the echoes associated with the first two reflections on the substrate/coating interface after passing through the substrate or on the coating/air interface after passing through the substrate and the coating.

Abstract: The turbojet according to the invention is designed to be fixed onto the upper part of the aft section of the fuselage of an aircraft using at least one coat hanger, the turbojet comprising a fan, a forward casing, an aft casing, accessories arranged around the periphery of the forward casing, the forward casing comprising attachment points, for the coat hanger. The attachment points are arranged so that the turbojet can be installed indifferently on either side of the aircraft fuselage, accessories being arranged on the casing so that they are accessible from the outside of the fuselage regardless of which side the installation is done.

Abstract: The present invention pertains to a turbo-jet engine comprising a fixed structure, a fan rotor integral with a drive shaft supported by a first bearing and a second bearing. It is characterized in that it comprises means forming axial retaining means for the fan rotor and/or forming an emergency bearing, cooperating with means of the fixed structure and mounted integral with the drive shaft. In particular it comprises a structural flange on which the second bearing is fixed, and the means forming axial retaining means for the fan and/or forming an emergency bearing comprise a retaining disk mounted on the drive shaft and cooperating with a stop disk of flange for axially retaining fan and with a longitudinal sleeve of flange to form an emergency bearing.

Abstract: A turbojet diffuser disposed between a compressor and a combustion chamber, and secured to an outer upstream annular flange of an outer casing of the combustion chamber by suspension means which comprise a first frustoconical wall extending from the outer longitudinal wall of the diffuser towards the combustion chamber, and a second frustoconical wall extending towards the compressor between the first frustoconical wall and the outer casing of the combustion chamber.

Abstract: The system retains a plate against a disk presenting in its radial face an annular recess defined by a plurality of walls, one of which is formed by a face of a flange, said plate presenting an annular base pressing against the radially outer wall of the recess and a root which extends from the base into the recess, said system including a split annular retaining ring disposed in the recess. In characteristic manner, said flange presents a top end of crenellated outline provided with at least one notch, said root is provided with a front rim of crenellated outline, having at least one mortise, and a rear rim between which rims there is formed an annular groove for receiving the ring which presents an axial tenon suitable for penetrating into said notch and into said mortise.

Abstract: A turbojet comprises at least a fan, a compressor, a combustion chamber, a turbine, and a rigid substantially-cylindrical jacket fastened at its upstream end to an intermediate casing and at its downstream end to an exhaust casing, the jacket serving to transmit forces between the intermediate casing and the exhaust casing.

Abstract: A control lever for the pitch angle of a blade in a turbomachine, said lever having a first end intended to be mounted on a blade pivot so as to rotate it and a second end comprising a cylindrical peg for mounting on a control annulus, this peg being fixed by crimping of one of its ends in an orifice of the second end of the lever and comprising an annular flange to which is applied the second end of the lever, wherein stress distribution means are interposed between the second end of the lever and the crimped end of the peg.

Abstract: A system for controlling a leakage zone under platforms of blades of a turbomachine blade-wheel by liners having edges that flare radially inwards, and that are disposed in inter-blade cavities defined by the platforms, by upstream and downstream radial walls of the blades and by the periphery of the wheel disk. One of the flared edges, upstream or downstream, presents an elastic zone bearing on an inclined surface of the adjacent radial wall relative to a radial plane, such that the liner tends to move axially towards the radial wall facing, under action of centrifugal forces, to improve sealing in the zone, and so that when the wheel stops, the elastic zone moves radially inwards, the liner pivoting around an axis distant from the elastic zone.

Abstract: The invention relates to a turbojet having two counter-rotatable fans (3, 5) at the front of an intermediate casing (2), said fans being secured to a counter-rotatable low-pressure compressor (7). The blades (14) of the rear fan (5) extend into the by-pass air flow (F2) from a wheel (15) that surrounds the outer rotor (20) of the low-pressure compressor (7). The distance (L) between the blades (10) of the front fan (3) and the blades (14) of the rear fan (5) is not less than twice the length (l) of the projection onto the axis of the cord-line of the blades (10) of the front fan (3).

Abstract: The invention relates to a turbomachine of axis X and comprising, from upstream to downstream, a high pressure compressor whose rotor presents a downstream cone (4), a diffuser (3) extending downstream beside the axis X by an inner casing (5) disposed radially outside said downstream compressor cone, a combustion chamber disposed radially outside said inner diffuser casing, and a high pressure turbine whose rotor is connected to the downstream cone of the compressor by a connection drum, the inner diffuser casing and the downstream compressor cone defining between them an under-chamber cavity that is situated downstream from a discharge labyrinth (13) in which cooling air flows downstream, the turbomachine being characterized in that it also comprises a stator shroud (20) that is installed under the inner diffuser casing (5) downstream from the discharge labyrinth (13).

Abstract: A variable cycle propulsion system for a supersonic airplane, the system comprising at least one engine having at least one compressor and capable of generating thrust for supersonic flight speeds, and at least one auxiliary propulsion assembly separate from said engine, and capable of generating additional thrust for takeoff, landing, and subsonic cruising speeds, at least one pipe connecting the engine to the auxiliary propulsion assembly to convey thereto compressed air produced by the compressor so as to enable the auxiliary propulsion assembly to generate additional thrust for takeoff, landing, and subsonic cruising flight, there being at least one valve enabling the pipe to be closed off for supersonic cruising flight.

Abstract: This invention refers to a labyrinth seal for a gas turbine engine incorporating from upstream to downstream ends, a high pressure compressor with a rotor, a diffuser and a fixed wall element forming at least one part of the internal envelope of the combustion chamber said seal comprising a stator part mounted on the wall element by virtue of an attaching part with flanges and supporting an annular wearing part said wearing part working jointly with a rotor element provided with at least one circumferential tooth integral with rotor of the compressor to form the labyrinth seal. It is characterized by the fact that at least one of the flanges of said attaching means is heavy enough to harmonize the rate of dilatation of the stator part with respect to the dilatation rate of the rotor element during engine accelerations. In conformity with another characteristic, ventilation orifices are arranged in the wall element.

Abstract: A connection device between a nozzle and a feed enclosure for feeding cooling fluid to at least one injector in a turbomachine, the device comprises at least one bushing having open axial ends engaged in orifices in a wall of the nozzle and in a wall of the feed enclosure, together with retaining means for retaining the bushing axially, the retaining means being formed to project from an outer cylindrical surface of the bushing between the axial ends of the bushing and at a distance from said ends.