Abstract: Devices for intaking gases from the boundary layer through ducts hollowed out in blades. These devices are suitable for variable setting blades, installed on the stator using pivots. The seal is maintained despite the variation in the relative position between the moving pivots through which ducts pass, and the fixed intake header pipe.

Abstract: A process for manufacturing an integrally bladed disk for a turbomachine rotor by friction welding is disclosed. The manufacturing process includes arranging a plurality of blades in the form of a ring in a mold having symmetry of revolution; casting a degradable material, preheated to a temperature above its melting point, onto the ring of blades in the mold; extracting the molded ring which is obtained after the degradable material has solidified; welding the molded ring onto a disk; and eliminating the degradable material.

Abstract: A device for ventilating turbine components in a gas turbine engine which includes first and second turbine rotors mechanically independent of each other, the first turbine rotor includes an HP turbine disk and the second turbine rotor includes an LP turbine disk and with a first circuit for ventilating the LP turbine is disclosed. The device includes an air compression wheel arranged downstream of the HP turbine disk between the HP turbine disk and LP turbine disk in order to assist the circulation of the air in the first circuit.

Abstract: A jet engine with a system for recovering oil around the lubricating chamber of the rear rolling bearing of the shaft of the jet engine. The shaft is supported by a rolling bearing situated in a lubricating chamber surrounded by a single recovery chamber having a seal situated downstream from the rotor of the turbine driving the shaft.

Abstract: A turbomachine comprising at least one Stirling cycle thermal engine which is mounted at the end of a radial arm of the exhaust casing and comprises a working chamber located outside the primary and secondary flows, a displacing piston associated with a moving element of an energy generation system, and two exchangers, heating and cooling, formed in parts of the radial arm respectively intercepting the primary flow and the secondary flow, these two exchangers communicating with each other and with the working chamber for the circulation of a working fluid.

Abstract: The invention relates to a bypass turbojet engine comprising an outer fan duct and an inner fan duct (IFD), between which the secondary flow passes, and a high pressure compressor having an outer casing. In characteristic manner, the IFD is fastened on the outer casing. The invention is applicable to a turbojet engine having a high pressure compressor of the axial-centrifugal type.

Abstract: A turbomachine such as an aircraft turbojet including an electrical generator/starter that can be mounted and dismounted by axial translation in an upstream enclosure of the turbomachine between the low-pressure compressor and the high-pressure compressor, and couple to electrical cables which extend inside the structural arms of the intermediate casing of the turbomachine.

Abstract: The present invention relates to a device for supplying ventilation air to a turbine rotor of a gas turbine engine comprising a first and a second turbine disk (11, 12) and a downstream shell ring (14) together forming a one-piece drum, the second turbine disk (12) comprising cavities machined in the rim (12J) to house the turbine blades (6), the blades being axially retained by axial retaining segments (18, 18?). The device is one wherein at least one drilling (12P) is made in the shell ring (14) downstream of the rim (12J) placing the inside of the drum in communication with at least some of said cavities, a passage (18P; 18?P) being formed in the segments (18; 18?).

Abstract: Guide shaft bearing comprising an internal ring mounted on a cylindrical contact surface of a shaft and means for the axial locking of the ring comprising a ring mounted sliding on the cylindrical contact surface and an annular rib made of shape memory material mounted in two annular grooves of the cylindrical contact surface and of the ring, the annular rib being able to expand radially by shape memory effect when it is subjected to a temperature greater than a transition temperature of its material to pass to a locking position of the ring on the cylindrical contact surface.

Abstract: A device for centering a tube inside a hollow shaft, the device comprising deformable means interposed between the tube and the hollow shaft and including bearing members for bearing against the inside surface of the shaft and suitable for being spaced away from the inside surface of the shaft in order to enable them to be moved inside the shaft, the deformable means being made of a shape-memory material suitable for deforming to press the bearing members against the inside surface of the shaft or to space them away therefrom on being subjected to a predetermined temperature.

Abstract: Turbomachine such as an aircraft turbojet comprising an electrical generator/starter (26) that can be mounted and dismounted by axial translation in an upstream enclosure (18) of the turbomachine between the low-pressure compressor and the high-pressure compressor, and couple to electrical cables (34) which extend inside the structural arms (12) of the intermediate casing (10) of the turbomachine.

Abstract: A turbomachine front portion includes an internal support shroud for the fan outlet guide vanes, and a flow splitter fairing from which a primary duct and a secondary duct originate. The front portion includes at least one deflector system configured to prevent/limit the ingress of hailstones inside the primary duct, the system including at least one deflecting surface together with an actuator for moving the surface from a retracted position to a deployed position for deflecting the hailstones, the system being mounted on the shroud such that, in the deployed position, a downstream end of the surface is situated upstream of the splitter fairing.

Abstract: An aeroengine includes a primary air circuit; a high-pressure compressor fed by the primary air; and a secondary air circuit. The engine further includes at least one heat exchanger mounted in the primary air circuit upstream from the high-pressure compressor, the heat exchanger including a cold secondary circuit and a hot primary circuit, the hot primary circuit being fed with air from the primary air circuit and the cold secondary circuit being fed with air from the secondary air circuit. The cold circuit of the heat exchanger is fed by pipes that open out into the secondary air circuit.

Abstract: The invention relates to a deoiling device. It comprises a tube (46), a first bearing (16) and a second bearing (18), the first and second bearings being placed in an oil chamber (20) in which an oil fog is maintained by rotation of the bearings. A deoiler (30) is provided in one wall of the oil chamber. The deoiler centrifuges oil in suspension in air and allows a deoiled air flow to pass inside the tube. The tube (46) comprises a closing cap (48) fitted with one or several outlet orifices (50) in its upper part designed to evacuate air, and an oil drain orifice (52) in its lower part.

Abstract: A support for a bearing that guides a shaft in a turbomachine, comprising an annular part made of a shape memory material which retains an initial shape when the load applied to it remains below a threshold value and which deforms, absorbing energy when the applied load becomes at least equal to the threshold value, this annular part being capable of reverting at least approximately to its initial shape when the applied load drops back below the threshold value.

Abstract: A device for varying the section of the throat of a turbine nozzle, the nozzle being formed by a plurality of stationary vanes extending radially between outer and inner annular platforms and spaced apart from one another in order to define a throat presenting a minimum flow section. The device comprises an annular element having a coefficient of expansion that is less than that of the platforms of the nozzle, the annular element being secured to the outer platform and being capable of taking up two positions: one position corresponding to no expansion of the platforms, in which the element provides continuity for the profile of the flow passage; and another position corresponding to the platforms having expanded, in which position the element projects into the flow passage so as to reduce its section.

Abstract: The present invention relates to a device for, in a gas turbine engine, braking a turbine comprising a rotor driving a shaft capable of rotating with respect to a stator in the event of said shaft breaking. The device is one which comprises a first braking member (110) provided with at least one abrasive element (110A) and a second braking member (120) comprising a ring-shaped element (120A) made of a material capable of being eroded by the abrasive element (110A), the two braking members being secured one of them to the rotor and the other to the stator and coming into contact with one another through axial displacement of the rotor once the shaft has broken, the abrasive element (110A) of the first braking member (110) eroding the ring-shaped element (120A) of the second braking member (120).

Abstract: The present invention relates to detecting breakage of a shaft of a turbomachine, in particular of the aviation type. The invention relates in particular to a device designed to perform such detection. According to the invention, the device for detecting breakage of a turbomachine shaft comprises: a shaft having an upstream end and a downstream end; a rod having an upstream end and a downstream end, and placed coaxially inside the shaft, the downstream end of the rod being securely fastened to the downstream end of the shaft and the upstream end of the rod being free to rotate relative to the upstream and of the shaft; and a sensor suitable for detecting a difference in speed of rotation between the upstream end of the rod and the upstream end of the shaft.

Abstract: A turbomachine comprising at least one Stirling cycle thermal engine which is mounted at the end of a radial arm (36) of the exhaust casing (24) and comprises a working chamber (40) located outside the primary (B) and secondary (A) flows, a displacing piston (42) associated with a moving element (44) of an energy generation system, and two exchangers, heating (58) and cooling (62), formed in parts of the radial arm respectively intercepting the primary flow (B) and the secondary flow (A), these two exchangers (58, 62) communicating with each other and with the working chamber (40) for the circulation of a working fluid.

Abstract: A dual-flow turbomachine (10), essentially comprising a fan (14), a compressor (20), a combustion chamber (21), a turbine (22) and an exhaust casing (24), which comprises an auxiliary air compressor (48) driven by a Stirling engine (53) mounted downstream of the combustion chamber (21) and having a hot chamber in thermal contact with the flow (B) of hot gases leaving the turbine and a cold chamber in thermal contact with a flow (A) of cold gases generated by the fan (14) and flowing around the turbine (22) and the exhaust casing (24).