Abstract: A turbojet having an air intake case including radial arms between an outer annular structure and an inner central structure, and a deicing unit configured to deice the radial arms by microwaves and located in the central structure. The deicing unit has a microwave generator and a transmitting element configured to transmit energy and including an inside annular waveguide located inside of the central structure. An energy distributing element configured to eliminate ice is coupled with the transmitting element by a coupling element. The radial arms are made from a dielectric composite material.

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 separate inter-blade platform for a turbomachine rotor comprises a structural rectilinear longitudinal member formed by a foam core, plies of a carbon/epoxy type material in bidirectional layers of crossed fibres oriented at 45.degree. laid around the core and around an insert at each end of the longitudinal member, each insert being made of juxtaposed radial plies of a carbon/epoxy type material in bidirectional layers of fibres crossed at .+-.45 degrees, and further plies of a carbon/epoxy type material in unidirectional layers oriented in the direction of the major axis of the longitudinal member covering the upper and lower faces of the member, the platform further comprising lateral packing cores made of a foam material, plies of a glass/epoxy type material covering the lateral faces of the longitudinal member and connecting it to the lateral foam cores, and peripheral plies of a glass/epoxy type material covering the assembly formed by the longitudinal member and the lateral cores connected thereto.

Abstract: An integral, one-piece afterburner structure for a turbojet engine is disclosed which is formed of composite material. The afterburner structure has an outer casing formed as a body of revolution about a central axis, an inner casing also formed as a body of revolution about the central axis, which casings are integrally joined by a plurality of connecting arms extending between the inner and outer casing. The connecting arms are also formed of a composite material and are integrally molded with both the inner and outer casings. The afterburner structure also has a plurality of secondary support arms formed of composite material which extend either from the outer, or the inner casing in a generally radial direction relative to the central axis. Integrally formed with the plurality of secondary support arms is at least one annular flameholder ring which extends around the central axis and is supported by the secondary support arms.

Abstract: An afterburner assembly is disclosed in which the flameholder ring is for by plurality of flameholder ring segments, each segment being integrally formed with a generally radially extending arm. The flameholder ring segments extend beyond each opposite sides of the arm. The arm and flameholder ring segments are attached to the casing of the afterburner by a support element which is pivotally attached to the arm and fixedly attached to the afterburner casing. The distal end of the arm slidably contacts the casing defining the opposite side of the afterburner duct to enable the arm to slide relative to the casing to allow for differential thermal expansion of the respective elements. When each of the arm/flameholder ring segments are attached to the afterburner casing, the flameholder ring segments form a generally annular flameholder ring.

Abstract: A variable geometry flame trap device for use in an after-burner device of a gas turbine, which is not exposed to deformation forces during its use in the after-burner mode. This is achieved with a plurality of flame trap plate pairs (21), positioned downstream of the turbine at the outlet of a primary air flow duct (9) and mounted so as to pivot on a plurality of diffuser arms (19) located at the outlet of a secondary air flow duct (7), characterized in that the plates (21) of each pair are made from a composite material and in that they have a cam projecting from their facing faces (42), said two cams (43) bearing on one another.

Abstract: A gas turbine engine impeller having a plurality of blades attached to a rotor disk and an integral, annular collar defining openings through which the blades extend which acts as a platform extending between the adjacent blades. The annular collar is formed as an integral, annular structure and may be formed from a composite material, or other material which is resistant to high temperatures and high centrifugal forces. The annular collar defines a plurality of openings to accommodate the blade portion of the plurality of blades and to enable the blades to extend radially outwardly from the collar. The openings may be formed in the annular collar when the collar itself is formed, or may be machined therein after the collar has been fabricated.

Abstract: A separate inter-blade platform for a bladed rotor disk of a turbo-machine comprises a first part in the form of a four-sided frame of generally trapezoidal shape and made of a laminated material, the frame having smaller and larger ends for location on the upstream and downstream sides respectively of the rotor disk, and two lateral sides interconnecting said ends for location between successive blades of the rotor, and a second part made of a relatively flexible and self-adhesive material of the polyurethane type attached to the first part, the second part defining a plate capping the frame over the greater part of its two lateral sides and leaving the smaller and larger end portions free, a portion enclosing the two lateral sides of the frame in line with the plate, and a plurality of evenly spaced, transverse reinforcing ribs which are integral with said enclosing portion and the underside of the plate.

Abstract: Molding apparatus, for example for molding components of polymerized resin without drawing, comprises a mold defined by a mold wall having a first thermal expansion coefficient, and a die including a die wall having a second thermal expansion coefficient greater than the said first coefficient, a molding operation being carried out by inserting the die into the mold at a first temperature, heating the die and the mold to a second temperature higher than the first temperature, and subsequently cooling the die and the mold after a component has been molded. In accordance with the invention, the die wall includes a plurality of separate sectors which are pivotally mounted on a common support member and which are arranged and dimensioned such that, at the second temperature, the radially outer faces of the sectors adjoin one another contiguously to define the molding face of the die wall.

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: 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: 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: Two coaxial bodies of revolution made of materials having distinctly different expansion coefficients are joined together to form an assembly by fixing means comprising at least three resilient brackets of trapezoidal shape, the larger end of each bracket having a flanged edge secured at at least two points by hollow rivets to a metal ring and by bolts extending through the rivets to the body with the higher expansion coefficient, and the smaller end of each bracket being secured by at least one bolt to the body with the lower expansion coefficient in a manner which imposes a cold prestress on the bracket.

Abstract: The system according to the invention has an annular array of converging flaps, diverging flaps and cold flaps attached to the downstream edge of the turbojet engine exhaust duct by several pairs of longitudinally extending support beams. The pairs of beams are interconnected and the flap actuators are located between such interconnected pairs of support beams. The control system has a plurality of generally straight control shafts extending around the circumference of the converging and diverging flaps. The control shafts are interconnected with the actuators, the support beams, the diverging flaps and the cold flaps to ensure that the flaps are synchronously adjusted to their desired positions. Triangularly shaped link members are attached to each end of the control shafts and serve to interconnect adjacent shafts. A base of each of the link members is pivotally attached to an end of the control shaft, while a universal-type ball joint interconnects the adjacent apexes of the triangular link members.

Abstract: A device for automatically controlling the rate of flow of turbine ventilation air in a turbo-machine comprises two superimposed ceramic rings which are split and are each fixed at a single point to a metal support so that differential expansion of the support and the two rings in response to the operating conditions of the turbo-machine causes the registry of peripherally disposed slots in the ceramic rings to vary and thereby control the rate of ventilation air flow therethrough in accordance with the turbo-machine operating conditions.

Abstract: An adjustable two-dimensional nozzle is disclosed in which simplified control means are located away from the flow of gasses through the nozzle. The nozzle includes a movable frame located outside of fixed sidewalls and has pivotally attached thereto a pair of upstream or converging nozzle flaps. Upstream edges of the upstream flaps are attached to the movable frame such that the flaps pivot about axes extending substantially perpendicular to the longitudinal axis of the nozzle. Downstream or diverging flaps are attached to the downstream edges of the upstream flaps such that these flaps also pivot about axes extending substantially perpendicular to the longitudinal axis of the nozzle. A cam member extends between each of the movable frames and each downstream flap to control the angular variations of the flaps during movement of the frame.

Abstract: Disclosed is a method of manufacturing a composite material burner ring made wholly of a composite material. The burner ring is manufactured by winding a carbon or ceramic type refractory material about a toroidal form until a specific material thickness is obtained. The burner ring elements, such as radial arms, fastening clips or fuel feed tubes are then fastened onto the winding. Each of the elements may be formed in mirror-image halves and may be assembled onto the burner ring body in adjacent pairs, each one of the pairs facing in an opposite direction. The winding of the composite material is continued until a final thickness is obtained, thereby integrally attaching the burner ring elements to the burner ring body. The assembly is then subjected to a carbonization or ceramization head treating process.