Abstract: A redundant mass flow meter comprises a casing housing a main rotor and an ntermediate rotor which is freely rotatable and is disposed coaxially with a rotationally restricted turbine between the turbine and the casing, a first measuring system for measuring and controlling the position of the turbine relative to the intermediate rotor, and a second measuring system, independent of the first measuring system, for measuring and controlling the position of the intermediate rotor relative to the casing.

Abstract: A component made of superalloy is provided with a localized coating formed from three layers by a brazing heat treatment, the layers comprising an outer layer having a composition adapted to the specific surface properties sought, an inner layer having a composition which includes flux elements, and an intermediate layer obtained by the deposition of a mixture of the materials used for the other two layers.

Abstract: A turbojet engine rotor, wherein the circumference of the disk is occupied y teeth and slots in an alternating form. The teeth have a variable rigidity in the axial direction, which leads to different shapes of their cross-section. The teeth have a twisted outer surface and oblique recesses are provided on the circumference of the rotor for receiving vane roots which alternate with the teeth for separating and retaining the vanes.

Abstract: A fuel injection system is disclosed which incorporates a plurality of bowl or shroud members extending upstream of an end wall of the combustion chamber between the end wall and an air swirler in which the shroud member has an end joined with the end wall of the combustion chamber having a substantially elongated elliptical cross-sectional configuration. The end wall of the combustion chamber defines an elliptical shaped opening corresponding to the shape of the end of the shroud or bowl member to enable the fuel/air mixture to be atomized as it enters the combustion chamber. The bowl or shroud member may also define a plurality of openings to enable additional air to be mixed with atomized fuel cone.

Abstract: The rotor of a fan disposed in the annular noncombusted air flow duct of a urbojet propulsion engine of the bypass type is carried by a rotary body which includes the rotor assembly of a multi-stage turbine driven by noncombusted air supplied thereto by an axisymmetrical auxiliary duct which diverts noncombusted air from the primary duct of the engine just downstream of the compressor.

Abstract: A control system for hydraulically controlling variable engine structures is disclosed in which the control system utilizes hydraulic fluid identical to that used by the aircraft hydraulic control circuit. A high pressure hydraulic pump, driven by the aircraft engine, may be interconnected with the aircraft hydraulic control circuit, or may be associated with a separate fluid reservoir, to supply pressurized hydraulic fluid to the actuators for controlling the variable engine structures. The engine control circuit also includes a hydraulic pressure modulator to modulate the pressure of the fluid supplied to the actuator and a selector connected between the high pressure pump and, the modulator and the aircraft control circuit to selectively supply the high pressure hydraulic fluid from the pump to either the engine control circuit, or to the aircraft control circuit.

Abstract: A combustion chamber suitable for use in a gas turbine engine includes a first enclosure with a fuel injector for low-power operation and a primary-oxidizer intake, a second enclosure with a fuel injector for full-power operation and a primary-oxidizer intake, and a third enclosure from which to evacuate burnt gases and which communicates with the first and second enclosures. The wall of the first enclosure includes intake orifices for a dilution oxidizer, but the wall bounding the second enclosure lacks any orifices other than the primary-oxidizer intake orifices.

Abstract: A method and an apparatus for friction welding two elements together are disclosed in which the areas of the two elements to be welded are heated by an induction heater. The induction heater may be used to heat the areas to be welded prior to contact between the elements, during such contact, and after the friction welding has been achieved in order to provide a heat treatment of the welded zone. The induction heater is generally annular in shape and may be dimensioned so as to be located around the elements at the welding zone, or to be placed between the surfaces of the elements to be welded together.

Abstract: A system for controlling oxidizer intake diaphragms for a gas turbine engine combustion chamber is disclosed having a single, linear actuator for each pair of intake diaphragms. The movable member of each of an adjacent pair of intake diaphragms is connected to a movable piston rod of the linear actuator. A cam mechanism urges the piston rod in a first direction so as to simultaneously move the movable members of each of the pair of diaphragms. Pressurized gases from the combustion chamber act on the piston to urge it in a second, opposite direction. The forces of the pressurized gases also maintain contact between the cam member and the piston to insure accurate movement of the movable members. A plurality of such linear actuators may be disposed around the periphery of the combustion chamber, each actuator controlling a pair of adjacent intake diaphragms. The actuators may be interconnected by a flexible drive shaft to insure uniformity of movement of all of the cam elements in the system.

Abstract: A pod for a very high bypass ratio turbofan engine unit of the forward contrafan type suspended from a suspension mast under the wing of an aircraft comprises a generally cylindrical inner cowling surrounding the casing of the jet engine unit and a generally cylndrical outer cowling spaced outwardly of the inner cowling and defining therebetween the cold flow path in which the contrarotating fan propellers are located, the outer cowling being divided into three parts consisting of an openable forward casing surrounding the fan propellers and connected to the suspension mast, an intermediate casing rigidly connected to the engine casing by radial flow straightener arms disposed in the cold flow path to the rear of the fan propellers, and an openable rearward casing also connected to the suspension mast. The engine unit is attached to the suspension mast by first attachment means carried on top of the intermediate casing, and second attachment means provided on the rear part of the engine casing.

Abstract: A compensating device for the temperature in front of the high pressure turbine of a compound turboshaft aero-engine which is regulated to a designated constant temperature behind the low pressure turbine is provided with a function generator which supplies a correction value signal for the designated temperature as a function of the rotational speed of the low pressure turbine and of the actual temperature at the outlet of the said turbine. The device is activated as soon as the rotational speed of the high pressure turbine goes below 80% of its maximum rated speed and is operative to apply the correction value signal to the designated temperature for a predetermined time as soon as the rotational speed of the high pressure turbine goes above 90% of its maximum rated speed while the device is activated.

Abstract: A continuous emission radar device for determining, at short range, the relative positions of a missile and a vehicle to which the device is fitted, includes a transmitting circuit connected to a transmitting antenna for emitting a continuous signal modulated by a pseudo-random binary sequence delivered at a clock frequency fH, and three receiving circuits connected respectively to three receiving antennae which receive echos of the emitted signal from the missile, a first receiving circuit generating the clock frequency and slaving it to the missile vehicle distance, and the other two receiving circuits determining the phase shift between the echo received by the first antenna and each of the echos received by the other two antennae, these three parameters being transmitted to a device for calculating the position of the missile in relation to the vehicle.

Abstract: A blow-off device for a gas turbine bypass engine having a primary air flow path separated from an outer secondary air flow path by a partition includes a plurality of discharge passages passing through the partition from the primary air flow path to the secondary air flow path, each of the discharge passages having a first hinged flap in the outer wall of the primary air flow path, a second hinged flap in the inner wall of the secondary air flow path, and a connecting rod mechanically interlinking the first and second flaps, the connecting rod being hinged at one of its end to the first flap and at its other end to the second flap.

Abstract: Engine components of steel or superalloy subject to wear from alternating friction at medium temperatures in the region of 700.degree. C. are provided with a protective wear-resistant coating bya) electrophoretic deposition of a metal-ceramic structure comprising a mixture of from 85% to 50% of metallic powder and from 15% to 50% of ceramic powder, the metallic powder being a cobalt-based superalloy of type KC 25 NW or of M Cr Al Y wherein M represents at least one metal chosen from the group consisting of Ni, Co and Fe with the possible addition of Ta, and the ceramic powder being an oxide such as Al.sub.2 O.sub.3 or Cr.sub.2 O.sub.3, a carbide such as SiC or Cr.sub.3 C.sub.2, a nitride such as BN or TiN, or a boride such as TiB.sub.2 ;b) electrolytic pre-nickeling said deposit in an electrolysis bath at a pH between 6 and 8, andc) electrolytic nickeling said pre-nickeled deposit in an acid bath of sulphamate type.