Abstract: A heat protective lining for the afterburner or transition duct of a turbojet engine comprises an assembly of tiles overlapping laterally and longitudinally to form overlapping rings of tiles in which the tiles of each ring are offset laterally from those of each adjacent ring by half a tile width. The tiles are held together by eyelets projecting from the overlapped downstream portions of the tiles through apertures in the overlapping upstream portions, and locking members engaging through the eyelets. Fastening yokes for fixing the assembly to the duct casing are secured to the outside of the tiles.

Abstract: In a process for the simultaneous deposition of a protective coating, e.g. an aluminium based coating, on internal and external surfaces of heat-resistant alloy parts, the parts are placed in a box containing a donor material, preferably in the form of granules, comprising the metal to be deposited, and an activator separate from the donor and comprising at least an anhydrous powder of chromium fluoride CrF.sub.3 to provide a source of fluorine. The box is heated to a temperature above 1000.degree. C. and a controlled flow of a carrier gas, reducing or neutral, is introduced into the box so as to establish a circulation of gases in the box whereby fluorinated vapors from thermal decomposition of the CrF.sub.3 activator contact the donor to form a volatile fluoride of the metal to be deposited, and the volatile vapor is carried into contact with the external and internal surfaces of the parts to be coated to deposit the coating thereon.

Abstract: A coating for a heat engine part, particularly a turbo-machine part made of superalloy, comprises an electrophoretically deposited metallic structure of cellular form with uniformly disposed cells of predetermined size, the structure preferably being composed of M, Cr, Al, and Y, where M denotes Ni, Co, Fe and mixtures thereof. The cellular metallic structure is consolidated by a sintering treatment, which may be reactive, or metallization, preferably in the vapor phase, and the coating is completed by a ceramic material applied by plasma spraying.

Abstract: A device for locking the blade roots (3) in rotor disk alveoli (2) consists of a single split ring (9) with a Y shaped cross-section of which a radial upstream arm (9a) is inserted in the groove (7) of the downstream blade lips (6) the radial downstream arm (9b) of the ring (9) being pressed against the downstream part of the blade lips (6).

Abstract: A process for optically checking perforations in a hollow article, particularly the micro-perforations in the vicinity of the leading or trailing edge of a hollow turbine blade for a turbo-shaft engine, comprises illuminating the inner cavity of the article through an opening at one end thereof, scanning the length of the article by means of a video camera and making a record of the luminance of the reflected light received by the camera through the perforations to be checked, converting the sequence of the data thus collected into electric signals, storing the said signals in a computing and storage unit, and processing and comparing the signals with a predetermined train of reference signals derived from a standard article.

Abstract: A bladed disc of a turbomachine rotor comprising an array of blades evenly disposed around the rim of the disc and separate platforms secured to the disc between the blades, each platform comprising a plate and a mounting foot at each axial end of the plate by which the platform is secured to the rim of the disc, at least one of the feet being secured by a C-shaped clamp which rigidly connects the foot to a tooth-like element of the disc adjacent the rim and which is locked axially in position by a flange of an adjacent element of the rotor.

Abstract: In a turbojet aero-engine of the bypass type in which the compressor includes pivotally mounted blow-off valves for discharging air from the primary air flow path through the compressor to prevent surging, the compressor further includes pivoted means associated with the blow-off valves such that the pivoted means lie against the wall of the primary air flow path whenever the valves are closed or are open below a predetermined angle of opening and, when said valves are opened beyond said predetermined angle, the pivoted means are caused to project into the primary air flow path for collecting excess water carried by the air and discharging this water from the flow path.

Abstract: In a mobile blade of a gas turbine engine comprising a root, a platform, and a vane forming the aerodynamic portion of the blade, the vane is arranged so that the geometric locus of the centers of gravity of successive cross-sections of the vane between the platform and the tip of the blade vane is a curve including at least one straight line portion which is offset relative to a radial straight line contained in the axial plane of symmetry of the blade root and which is joined progressively to the origin where the radial straight line intersects the junction of the vane with the platform and root of the blade. In the case of a blade with an intermediate shoulder or fin on the vane, the locus of the centers of gravity of the vane cross-sections includes a second straight line portion offset relative to the first straight line portion and connecting assembly therewith in the region of the fin.

Abstract: A thermoplastic paste for the production of foundry mold cores comprises, per 100 parts by weight of mineral filler comprised of fused silica, zircon and cristobalite, between 0.2 and 0.5 parts by weight of a mold release agent, and an organic binder formed by at least 15 to 20 parts by weight of polyethylene glycol having an average molecular weight between 1400 and 1600. A process suitable for the production of foundry mold cores from such a past comprises a shaping stage followed by a single firing cycle in four steps, namely,(a) raising the temperature to 500.degree. C., at a rate of between 30.degree. C. and 50.degree. C. per hour.(b) raising the temperature from 500.degree. C. to a maximum temperature, at a rate of between 100.degree. C. and 200.degree. C. per hour.(c) maintaining the said maximum temperature for a period of between 4 and 5 hours, and(d) cooling rapidly using pulsed air.

Abstract: Each blade of a turbomachine rotor is secured to the drum of the rotor by upstream and downstream legs on the radially inner side of the blade platform cooperating with upstream and downstream annular beads on the periphery of the durm, and a locking plate holding the legs in position. The end of the upstream leg is received in an annular groove in the upstream bead, and the downstream leg has an aperture which receives a tongue projecting from a collar on the downstream bead. the downstream leg ends in a cylindrical bearing surface acting on a cylindrical bearing surface of the drum, and includes two hooks on its donwstream face. The locking plate is located in an annular groove of the drum at the downstream edge of the cylindrical bearing surface and has first tongues engaging with the hooks on the downstream leg and second locating tongues at each end.

Abstract: A compressor casing in a gas turbine engine includes an inner jacket formed by two half-shells connected by coupling flanges having cylindrical bellows fitted therebetween and arranged to expand and contract to control the inner diameter of the casing depending on the pressure within the bellows as provided by a supply of air taken from the downstream end of the compressor. The two half-shells are also interconnected by an additional flexible connection.

Abstract: A combined air-hydrogen turbo-rocket engine is disclosed having a simplified construction in which the hydrogen driven turbine is formed integrally with the rotor wheel of the axial air compressor stages. The rotor stages are located downstream of a stator vane structure and are driven by gaseous hydrogen passing across the turbine blades. The hydrogen is subsequently injected into an air duct surrounding the axial air compressor and defining an airflow path having an air inlet. The hydrogen-air mixture is ignited and the burned gases are expanded through a converging-diverging exhaust nozzle.

Abstract: The rotor of a turbomachine has a rotor blade stage formed by sectors which are each secured to a rotor drum by radially inwardly directed, axially spaced flanges on the blade platform of the sector cooperating with radially outwardly directed, axially spaced flanges on the drum. The cooperating downstream flanges of the drum and the blade platform have at least one pair of registering holes through which a cylindrical pin extends, the pin having a radial collar interposed between the two flanges and an annular groove positioned downstream from the collar. The assembly is held in position by scalloped segments which are inserted into an annular groove in the drum on the downstream side of the downstream flange, and which are shifted circumferentially to engage edges thereof in the grooves of the pins before being locked by tongues at opposite ends of the segments.

Abstract: In a turbomachine, such as a turboshaft aero-engine, having a compressor casing composed of upstream and downstream casing rings, and a variably settable stage of stator blades which is mounted in one of said casing rings near the junction therebetween so that, in normal operation, the blades have their leading (or trailing) edges projecting into the other casing ring, the setting of the blades being adjusted by a control ring surrounding the casing, there is provided a locking system for temporarily locking the blades in an angular setting in which the leading (or trailing) edges are retracted clear of said other casing when the casing is to be dismantled or assembled.

Abstract: Process and apparatus for measuring or checking the geometric contours of a part without contact, wherein the part is illuminated by a focussed laser beam and a reflected ray is detected by means of an array of photo diodes, the position of the part and the position of the diode which receives the maximum intensity of the reflected ray being recorded by a computer at each step as the part is moved step by step relative to the incident beam, this data enabling the computer to reconstruct the scanned contour of the part.

Abstract: An aircraft turbo-engine having an intake grille formed by radial struts disposed between inner and outer rings, each of said radial struts being in two parts, an upstream, fixed structural first part, and a downstream second part pivoted on said first part and forming an adjustable flap which constitutes an intake guide vane, all of said struts having the same cross-section as each other and at least some of the struts incorporating a pipe for the passage of oil, those oil pipe carrying struts each having its structural first part divided by a radial portion into an upstream chamber for the passage of hot air and a downstream chamber which is open along the length of its trailing edge and which receives the oil pipe.

Abstract: A method and apparatus for upsetting forged bars to form compressor vane blanks are disclosed which utilize a two-stage upsetting process. In a first stage, the rough forged bar is placed in a first die having a first enlarged cross sectional area such that the end of the bar to be upset extends into the enlarged cross sectional area of the die. The enlarged cross sectional area is shaped so as to have at least three lines of contact with the bar segment during lateral expansion of the bar. In a second upsetting stage, the expanded bar is removed from the first die and inserted into a second die, also defining an enlarged cross sectional area portion such that the expanded portion of the bar extends into the enlarged cross sectional area of the second die. The second enlarged cross sectional area has a cross sectional shape so as to accommodate the previously enlarged portion of the bar such that at least one line of contact is maintained between the bar and the die as the bar laterally expands.

Abstract: The two-dimensional adjustable nozzle according to the invention is a generally rectangularly shaped nozzle having a pair of opposite, fixed sidewalls defining the lateral boundaries of the nozzle and adjustable flap assemblies extending between the lateral walls and defining the upper and lower boundaries of the nozzle. The adjustable flap assemblies each have an interior flap and an exterior flap associated with a rocking lever which, in turn, is connected to an actuating mechanism. The actuating mechanism, which may be a jack screw, is located within the lateral sidewalls and is controlled by a rotatable cable. Rotation of the jack screw shaft which is connected to the rocking levers, causes the rocking levers to move in a direction generally transverse to the longitudinal axis of the nozzle to thereby adjust the angular positions of the interior and exterior flaps.

Abstract: The cartridge of a fan outlet for a multiple flow turbojet engine is made of composite material and includes two thick lateral strips (8a, 8b) positioned in the interior of the outer case and a narrow central band pierced with slots (10) in which guide vanes (5), provided with an in-molded cover, come to be fixed. The outer cartridge can be integral with the support of soundproofing panels (7 and 9) and support the abradable part (6) facing fan (3).

Abstract: A nacelle for mounting under the wing of an aircraft a turbojet engine unit of the rear contrafan type with a very high by-pass ratio, the engine including a gas generator driving two overlapping contra-rotating turbines integral with ducted contra-rotating propellers downstream of the gas generator. The nacelle includes generally cylindrical inner and outer cowlings defining the secondary flow path containing the propellers, and a mast for suspending the engine unit comprising a pair of arms disposed in the longitudinal vetical axial plane of the engine unit and contained in a fairing, and a horizontal carrier beam fixed to the lower ends of the arms and disposed between the inner cowling and the engine casing. The upper ends of the arms are fixed to a box structure of the wing either directly or through a conventional engine pod suspension mast.