Abstract: A variable pitch rectifier for a compressor includes a plurality of radial vanes having respectively, at outer and inner ends of same, outer and inner pivots, the inner pivots being received between two upstream and downstream inner rings, which are assembled by a link device. The link device includes only a set of angular sectors of elastically deformable stirrups, arranged to grip together the inner peripheral edges of the upstream and downstream rings by clamping one against the other.

Abstract: A gas turbine engine for propulsion of an aircraft, the engine extending axially from upstream to downstream and including a composite part, a metal part, and a device for flexible fixing of the parts, the fixing device including: a flexible connecting element including a first fixing portion connected to the metal part by an axial connection and a second fixing portion connected to the composite part by an axial connection, the connecting element including an axially extending free end; and a rigid locking element including a fixing portion connected to the metal part by an axial connection and an axially extending free end, the free end of the locking element being aligned radially with the free end of the connecting element to limit deformation of the connecting element while the engine is in operation.

Abstract: A device for discharging oil from an oil chamber located in a downstream part of a gas turbine engine, the device including: a mechanism discharging at least part of the oil contained in the chamber to exterior of the engine; and a drive mechanism for driving the oil, which allows passage of an air flow that assists in driving the discharge of the oil to the exterior of the engine. The drive mechanism includes: a ventilation port in the downstream part of the engine, such that the oil passes through the ventilation port; and a guide element arranged such that, after the oil has passed through the ventilation port, the oil is directed towards a downstream bleed area of the low-pressure turbine. A turbomachine can include such an oil discharge device.

Abstract: A turbomachine separator including a device for de-icing the turbomachine separator, and a distribution element, wherein the separator is formed by an inner ferrule and an outer ferrule, wherein the inner ferrule is fitted with a first mounting flange and a second mounting flange, the de-icing device including an internal air supply duct, able to inject air into the separator, wherein the internal supply duct is connected to an air inlet, wherein the air inlet forms a projection external to the de-icing device, allowing a flexible connection with a tube of the distribution element for conveying hot air, a first fastener constructed and arranged to be attached to the first mounting flange; and a second fastener constructed and arranged to be attached to the second mounting flange.

Abstract: A device for locking a root of a rotor blade in a groove in a rotor disk of a turbomachine including: a circular ring sector configured to be mounted, transversely to the axis of the turbomachine, in a groove in the rotor disk; at least one locking wedge, which is rigidly secured and perpendicular to the ring sector, and extends parallel to the axis of the ring sector so as to hold the root of the blade radially in the groove; and at least one locking tooth extending from the ring sector radially with respect to the axis of the ring sector, so as to prevent the root of the blade from moving axially in the groove.

Abstract: A rotor of a turbomachine including a spinner which is attached removably to the upstream end of the rotor by an attachment system is provided. The attachment includes a dog clutch and a rotation-proofing system preventing the spinner from rotating with respect to the rotor.

Abstract: A gas turbine engine for propulsion of an aircraft, the engine extending axially from upstream to downstream and including a composite part, a metal part, and a device for flexible fixing of the parts, the fixing device including: a flexible connecting element including a first fixing portion connected to the metal part by an axial connection and a second fixing portion connected to the composite part by an axial connection, the connecting element including an axially extending free end; and a rigid locking element including a fixing portion connected to the metal part by an axial connection and an axially extending free end, the free end of the locking element being aligned radially with the free end of the connecting element to limit deformation of the connecting element while the engine is in operation.

Abstract: A variable pitch rectifier for a compressor includes a plurality of radial vanes having respectively, at outer and inner ends of same, outer and inner pivots, the inner pivots being received between two upstream and downstream inner rings, which are assembled by a link device. The link device includes only a set of angular sectors of elastically deformable stirrups, arranged to grip together the inner peripheral edges of the upstream and downstream rings by clamping one against the other.

Abstract: A double-body gas turbine engine, including a low-pressure body LP and a high-pressure body HP, rotatably mounted about a single shaft in a stationary casing, the low-pressure body LP including a compressor and a turbine connected by a low-pressure shaft LP. The low-pressure shaft LP is supported by an upstream LP bearing, a first downstream LP bearing, and an additional downstream LP bearing by the stationary casing, the high-pressure body being supported by an upstream HP bearing and a downstream HP bearing which is an inter-shaft bearing including an inner track rigidly connected to the HP turbine rotor and an outer track rigidly connected to the LP shaft.

Abstract: The invention relates to an assembly between a compressor shaft trunnion and a bevel gear for driving an accessory gearbox of a turbomachine. The assembly comprises a bevel gear, a compressor shaft trunnion arranged coaxially inside the bevel gear, torque transmission means between the compressor shaft trunnion and the bevel gear, a lock nut for preventing the bevel gear from moving axially on the compressor shaft trunnion, the lock nut being suitable for being screwed onto the bevel gear and including a shoulder projecting radially outwards and suitable for coming into axial abutment firstly upstream against a stop nut screwed onto an upstream end of the compressor shaft trunnion, and secondly downstream against a bearing surface of the compressor shaft trunnion, and an anti-rotation pin for preventing the lock nut from rotating.

Abstract: A turbomachine separator including a device for de-icing the turbomachine separator, and a distribution element, wherein the separator is formed by an inner ferrule and an outer ferrule, wherein the inner ferrule is fitted with a first mounting flange and a second mounting flange, the de-icing device including an internal air supply duct, able to inject air into the separator, wherein the internal supply duct is connected to an air inlet, wherein the air inlet forms a projection external to the de-icing device, allowing a flexible connection with a tube of the distribution element for conveying hot air, a first fastener constructed and arranged to be attached to the first mounting flange; and a second fastener constructed and arranged to be attached to the second mounting flange.

Abstract: A device for discharging oil from an oil chamber located in a downstream part of a gas turbine engine, the device including: a mechanism discharging at least part of the oil contained in the chamber to exterior of the engine; and a drive mechanism for driving the oil, which allows passage of an air flow that assists in driving the discharge of the oil to the exterior of the engine. The drive mechanism includes: a ventilation port in the downstream part of the engine, such that the oil passes through the ventilation port; and a guide element arranged such that, after the oil has passed through the ventilation port, the oil is directed towards a downstream bleed area of the low-pressure turbine. A turbomachine can include such an oil discharge device.

Abstract: A device for locking a root of a rotor blade in a groove in a rotor disk of a turbomachine including: a circular ring sector configured to be mounted, transversely to the axis of the turbomachine, in a groove in the rotor disk; at least one locking wedge, which is rigidly secured and perpendicular to the ring sector, and extends parallel to the axis of the ring sector so as to hold the root of the blade radially in the groove; and at least one locking tooth extending from the ring sector radially with respect to the axis of the ring sector, so as to prevent the root of the blade from moving axially in the groove.

Abstract: An oil recovery device is disclosed. The oil recovery device includes two bearing supports mounted on an inter-turbine casing, a first bearing and a second bearing mounted on the bearing supports, a low-pressure turbine journal mounted rotating with respect to the inter-turbine casing, a fixed ferrule, and an oil passage provided in the low-pressure turbine journal making it possible to discharge the oil inside the fixed ferrule. The ferrule is preferentially widened from the end at which the oil is discharged.

Abstract: A coupling device for coupling a turbine upstream guide vane which is coupled to a supporting part which itself attached to a stabilizing part is disclosed. The coupling device includes a interlocking device for interlocking a supporting end of the supporting part with a stabilizing end of the stabilizing part, and a retaining part to keep the supporting end and the stabilizing end interlocked. The coupling device may be used to couple an upstream guide vane of a turbojet turbine.

Abstract: A device for detecting breakage of a turbomachine shaft is disclosed. The device includes 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 device for, in a gas turbine engine, braking a turbine including a rotor driving a shaft capable of rotating with respect to a stator in the event of said shaft breaking is disclosed. The device includes a first braking member provided with at least one abrasive element and a second braking member including a ring-shaped element (120A) made of a material capable of being eroded by the abrasive element. One of the two braking members being secured to the rotor and the other of the two braking members being secured to the stator. The braking members come into contact with one another through axial displacement of the rotor once the shaft has broken. The abrasive element of the first braking member eroding the ring-shaped element of the second braking member.

Abstract: A device for supplying ventilation air to a turbine rotor of a gas turbine engine including a first turbine disk, a second turbine disk, and a downstream shell ring together forming a one-piece drum is disclosed. The second turbine disk includes cavities machined in the rim to house the turbine blades, where the blades are axially retained by axial retaining segments. The downstream shell ring has at least one aperture drilled therethrough, downstream of the rim, which places an internal volume of the drum in fluid communication with at least one of the cavities via a passage formed in the segments.

Abstract: A device for, in a gas turbine engine, braking a turbine including a rotor, having at least one disk with a rim driving a shaft and capable of rotating with respect to a stator, is disclosed. The device is for the event of the shaft breaking and includes a first braking member, secured to the rim and provided with at least one cutting element, and a second braking member secured to the stator downstream of the rim and including a ring-shaped element made of a material that can be cut by the cutting element. The two braking members coming into contact with one another through axial displacement of the rotor once the shaft has broken. The cutting element of the first braking member cuts the ring-shaped element of the second braking member.

Abstract: A double-body gas turbine engine, including a low-pressure body LP and a high-pressure body HP, rotatably mounted about a single shaft in a stationary casing, the low-pressure body LP including a compressor and a turbine connected by a low-pressure shaft LP. The low-pressure shaft LP is supported by an upstream LP bearing, a first downstream LP bearing, and an additional downstream LP bearing by the stationary casing, the high-pressure body being supported by an upstream HP bearing and a downstream HP bearing which is an inter-shaft bearing including an inner track rigidly connected to the HP turbine rotor and an outer track rigidly connected to the LP shaft.