Abstract: A device for deicing a separator nose of an aviation turbine engine, and including a separator nose for positioning downstream from a fan of the engine to separate annular channels for passing a primary stream and a secondary stream coming from the engine, and a casing fastened to the separator nose so as to extend it downstream, the casing having an inner shroud defining the outside of the primary stream flow passage, and including at least one air duct incorporated in the inner shroud so as to be formed integrally therewith, the air duct opening out downstream to an air feed and opening out upstream into the inside of the separator nose.

Abstract: A turbine engine in which an air flow circulates from upstream to downstream, or for an aircraft, including a rotary shaft extending axially and a de-oiling tube mounted to be rigidly connected to and on the inside of the shaft by an upstream fixing mechanism including: a first inner dog clutch extending on an inside from the shaft, a second dog clutch extending on an outside from the de-oiling tube, which is longitudinally aligned with the first dog clutch and positioned downstream of the first dog clutch, and an anti-rotation longitudinal locking latch extending between the rotary shaft and the de-oiling tube to prohibit rotation of the second dog clutch of the de-oiling tube relative to the first dog clutch of the rotary shaft.

Abstract: A turbomachine including an intermediate casing including, fastened to the end thereof, an outer casing of a high pressure compressor, and an air bleed mechanism bleeding air downstream from the stream through the compressor and including an outlet connected to an air reinjection mechanism reinjecting air upstream from the compressor via an annular manifold surrounding the inner wall of the intermediate casing and situated radially between the inner wall and an outer wall defining a secondary flow stream of the turbomachine.

Abstract: A turbojet engine including an intermediate casing including radial arms and a driveshaft for a gearbox for auxiliary machines of the turbojet engine, the driveshaft mounted in a radial arm, the radial arm including an intermediate bearing supporting the driveshaft, the intermediate bearing including plural rolling bearings supporting the driveshaft, the driveshaft including a first shaft element connected at one end to a mechanism providing mechanical transmission to an engine shaft of the turbojet engine, and a second shaft element connected at one end to a mechanism providing mechanical transmission to the box. The first shaft element and the second shaft element are linked by a connection including plural splines. A single plane transversely passes through the plural splines and the plural rolling bearings.

Abstract: A rotary assembly for a turbomachine fan includes a disk rotatable about an axis; a plurality of blades fastened by their roots to the disk and extending radially outwards from the disk; and a plurality of inter-blade platforms, each extending between two adjacent blades and defining the inner profile for the flow section of the fluid passing through the fan. On their facing side faces, these adjacent blades present slides between which the platform can slide, these slides limiting outward radial movement of the platform.

Abstract: A venting pipe used to guide a gas stream in a turbojet including at least one hollow rotary shaft inside which the pipe is mounted, the pipe extending generally along an axis. The pipe includes at least two pipe segments configured to be aligned longitudinally and assembled to one another while retaining a degree of freedom in relative translation thereof, at least one of the segments including a deformable mechanism configured to deform radially as the pipe segments are tightened against one another in the shaft of the turbojet, to bear on the shaft. The pipe structure facilitates mounting of the pipe.

Abstract: Reinjecting air to the inlet of a compressor in order to improve its pumping margin. The inlet stator of the compressor includes injection holes passing through at least some of the vanes in the vicinity of their pivots.

Abstract: The invention relates to the field of free turbines mounted on a gas turbine engine. It provides a fastener device for fastening a free turbine stator on a gas generator casing that shares a common axis with the turbine stator, the fastener device comprising a flange carrying a plurality of assembly parts providing a first releasable connection between the turbine stator and the gas generator casing, the flange providing first centering of the turbine stator on the casing. The fastener device further comprises a second releasable connection between the turbine stator and the gas generator casing that is axially offset from the flange towards the gas generator and that provides second centering of the turbine stator on the casing.

Abstract: A turbomachine including an intermediate casing including, fastened to the end thereof, an outer casing of a high pressure compressor, and an air bleed mechanism bleeding air downstream from the stream through the compressor and including an outlet connected to an air reinjection mechanism reinjecting air upstream from the compressor via an annular manifold surrounding the inner wall of the intermediate casing and situated radially between the inner wall and an outer wall defining a secondary flow stream of the turbomachine.

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: A device for balancing a turbomachine rotor includes at least one counterweight fitted to the rotor, wherein the counterweight includes two radial bearing surfaces oriented in two opposite radial directions, the said surfaces interacting with two radial bearing surfaces made on the rotor, the counterweight being held against the rotor by an axial retention device. In particular, the axial retention device can be a bolt with a nut, the bolt holding the counterweight against a coupling flange fixed ly attached to the rotor, including an axial bearing surface and the radial bearing surfaces.

Abstract: Reinjecting air to the inlet of a compressor in order to improve its pumping margin. The inlet stator of the compressor includes injection holes passing through at least some of the vanes in the vicinity of their pivots.

Abstract: A rotary assembly for a turbomachine fan comprises: a disk rotatable about an axis; a plurality of blades fastened by their roots to said disk and extending radially outwards from said disk; and a plurality of inter-blade platforms, each extending between two adjacent blades and defining the inner profile for the flow section of the fluid passing through the fan. On their facing side faces, these adjacent blades present slides between which said platform can slide, these slides limiting outward radial movement of said platform.

Abstract: The invention relates to an aeroengine comprising: a primary air circuit; a high-pressure compressor fed by said primary air; and a secondary air circuit. The engine further comprising at least one heat exchanger mounted in the primary air circuit upstream from said high-pressure compressor, said heat exchanger comprising a cold secondary circuit and a hot primary circuit, said hot primary circuit being fed with air from said primary air circuit and said 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 the field of free turbines mounted on a gas turbine engine. It provides a fastener device for fastening a free turbine stator on a gas generator casing that shares a common axis with the turbine stator, the fastener device comprising a flange carrying a plurality of assembly parts providing a first releasable connection between the turbine stator and the gas generator casing, the flange providing first centering of the turbine stator on the casing. The fastener device further comprises a second releasable connection between the turbine stator and the gas generator casing that is axially offset from the flange towards the gas generator and that provides second centering of the turbine stator on the casing.

Abstract: A turbine module for a gas turbine engine includes at least one turbine disk and a disk-shaped component mounted on the turbine disk upstream relative to the gas flow. The module can be assembled to the compressor of the engine, wherein the component is preassembled to the turbine disk, before the module is assembled to the compressor, by bolting to an attachment flange fixedly attached to the turbine disk.

Abstract: The invention relates to a turbomachine comprising a rotor with a drive shaft centered on the axis of the turbomachine by a first bearing and a second bearing which bearings are supported respectively by a first-bearing-support piece and a second-bearing-support piece which are secured to one another and connected to the turbomachine fixed structure by a decoupling device. This turbomachine comprises means designed to collaborate with at least one element of the turbomachine fixed structure in order to perform a dual function, that of preventing the bearing supports, from rotating and that of radially retaining the drive shaft in the event of the bearings becoming decoupled.

Abstract: In a succession of rotor disks, only the end disks are connected to a main structure by bolted extensions and the intermediate disks are suspended from rigid spacer pieces by centering and anti-rotation connections. The end disks are interconnected to clamp the assembly in the axial direction. There is no bolted connection between the successive disks. Assembly is very easy. The disks and the spacer pieces are stacked together in alternately, and the assembly is torsionally very rigid because of the use of a high number of claw-coupling teeth formed by protruding ends of the blade roots forming teeth that engage in spacer piece end rims.

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: In a succession of rotor disks, only the end disks are connected to a main structure by bolted extensions and the intermediate disks are suspended from rigid spacer pieces by centering and anti-rotation connections. The end disks are interconnected to clamp the assembly in the axial direction. There is no bolted connection between the successive disks. Assembly is very easy. The disks and the spacer pieces are stacked together in alternately, and the assembly is torsionally very rigid because of the use of a high number of claw-coupling teeth formed by protruding ends of the blade roots forming teeth that engage in spacer piece end rims.