Abstract: A turbomachine blade or vane is made of composite material including fiber reinforcement obtained by three-dimensional weaving of yarns and densified by a matrix. The blade or vane includes a first portion constituting at least an airfoil exhibiting two faces each connecting a leading edge to a trailing edge, the first portion forming a single part with at least one second portion present only on one of the faces of the airfoil, the second portion constituting a portion of at least one of the following elements: a flowpath delimiting outer portion of an inner platform, an inner portion of an inner platform, a flowpath delimiting inner portion of an outer platform, and an outer portion of an outer platform, the portions of the fiber reinforcement corresponding to the first and the second portions of the blade being at least partially mutually imbricated, with yarns of the first portion of the fiber reinforcement penetrating into the second portion of the fiber reinforcement.

Abstract: An aircraft failure diagnostic method and system includes a group of at least one smart mobile device, mobile in relation to the on-board equipment of an aircraft. The smart mobile device transmits a request for measurement data to an on-board equipment, following a tree structure of measurement data to be acquired. A piece of measurement data received from the on-board equipment by a smart mobile device causes passage to a later step in the tree structure of measurement data requests or interactive maintenance document. The interactive maintenance document is generated by automatically extracting inferences, data to be measured, measurements achievable on the on-board equipment, and measurements requiring a tool not included in the on-board equipment from an aircraft technical documentation.

Abstract: An adapting part is designed to be held on a casing of a turbo-engine, partially covering the casing. The adapting part includes, in the extension of one of its axial ends, a first connector to engage with a first complementary connector associated with the casing to form a sliding connection. The adapting part also includes, at its other axial end, a second connector to be secured to a second complementary connector associated with the casing to form a rigid connection.

Abstract: A gas turbine engine including at least a first composite part configured for mounting in a second metal part of the engine, the first composite part including an interface surface configured to be in surface contact with the second metal part, the engine including a metal protection removably mounted on the first composite part and configured to cover the interface surface.

Abstract: A turbine nozzle or a compressor diffuser includes sectors made of CMC material, each having an inner platform, an outer platform, and airfoils. An abradable material support ring is made up of sectors, each presenting upstream and downstream attachment tabs. Each inner platform presents on the inside an upstream hook and a downstream hook, and the abradable material support ring is supported by the nozzle or the diffuser by mutually engaging without fastening together firstly the end portions of the upstream attachment tabs and the upstream hooks and secondly the end portions of the downstream attachment tabs and the downstream hooks.

Abstract: A turbine nozzle comprises a plurality of composite material vanes, each vane comprising an inner platform, an outer platform with attachment tabs on the outside, and at least one airfoil extending between the inner and outer platforms and secured thereto. The attachment tabs of the vanes are engaged on a metal assembly ring supporting all of the vanes, extending continuously along the outer platforms of adjacent vanes, and forming a distinct assembly part between the vanes and a turbine casing.

Abstract: A method for fabricating turbine engine blade or vane made of composite material includes: performing three-dimensional weaving to make a single-piece fiber blank; shaping the fiber blank to obtain a single-piece fiber preform having a first portion forming a preform for at least a blade/vane airfoil, at least one second portion forming a preform for an inner part of a blade/vane inner platform or for an outer part of a blade/vane outer platform, and at least one third portion forming a preform for an outer part of a blade/vane inner platform or for an inner part of a blade/vane outer platform; and densifying the fiber preform with a matrix to obtain a composite material blade, and forming a single piece with an inner and/or outer platform(s) incorporated therein.

Abstract: A turbomachine blade made of composite material including a fiber reinforcement obtained by three-dimensional weaving of yarns and densified by a matrix, comprises a first portion constituting an airfoil and a blade root. The first portion constitutes a single part with at least one second portion constituting a blade inner platform, said blade then lacking a blade anti-tilting wall, or a blade anti-tilting wall, said blade then lacking a blade inner platform. The first portion also constitutes a single part with at least one third portion constituting a blade outer platform spoiler plate, said blade then lacking a blade outer platform wiper plate, or a blade outer platform wiper plate, said blade then lacking a blade outer platform spoiler plate.

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 turbomachine blade or vane of composite material comprising fiber reinforcement densified by a matrix is fabricated by a method comprising: making a one-piece fiber blank by three-dimensional weaving; shaping the fiber blank to obtain a one-piece fiber preform having a first portion forming a blade airfoil and root preform and at least one second portion forming a blade platform preform; and densifying the preform with a matrix to obtain a composite material blade or vane having fiber reinforcement constituted by the preform and densified by the matrix, forming a single part with at least one incorporated platform.

Abstract: A turbomachine blade is made of composite material. The blade includes a first portion constituting at least an airfoil exhibiting two faces each connecting a leading edge to a trailing edge, the first portion forming a single part with at least one second portion present only on one of the faces of the airfoil. The second portion constitutes a portion of at least one of the following elements: a flowpath delimiting outer portion of an inner platform, an inner portion of an inner platform, a flowpath delimiting inner portion of an outer platform, and an outer portion of an outer platform. Portions of fiber reinforcements corresponding to the first and the second portions of the blade are at least partially mutually imbricated. Yarns of the first portion of the fiber reinforcement penetrate into the second portion of the fiber reinforcement.

Abstract: Composite material turbine nozzle blade including an airfoil (10) adapted to have a cooling fluid flow through it and extending between a shroud (11) and a root (12), said shroud being shaped to be attached to one or more turbine casings (6, 7) of a turbomachine and said root being shaped to provide a junction with a turbine internal casing (5), wherein its root (12) is produced with a loosened texture and includes an external upstream side loosened texture lug (122) and an external downstream side loosened texture lug (124), the ends of the two external side lugs extending axially relative to the rotation axis of the turbomachine to form means for supporting and centering said internal casing.

Abstract: Composite material turbine nozzle blade including an airfoil (10) adapted to have a cooling fluid flow through it and extending between a shroud (11) and a root (12), said shroud being shaped to be attached to one or more turbine casings (6, 7) of a turbomachine and said root being shaped to provide a junction with a turbine internal casing (5), wherein its root (12) is produced with a loosened texture and includes an external upstream side loosened texture lug (122) and an external downstream side loosened texture lug (124), the ends of the two external side lugs extending radially relative to the rotation axis of the turbomachine to form means for supporting and centering said internal casing.

Abstract: The present invention relates to a control system for aircraft airbrakes, which comprises control means of a continuous operating mode or of an incremental operating mode in nominal operation of the airbrakes and control means of an incremental operating mode in the event of breakdown.

Abstract: This invention relates to a two stage push button control device, in which the push button (9) has at least one of its inputs (A, C) connected to the output of a processing organ (15) and its two outputs (B, D) connected to two inputs (E1, E2) of this processing organ (15).

Abstract: This invention relates to a two stage push button control device, in which the push button (9) has at least one of its inputs (A, C) connected to the output of a processing organ (15) and its two outputs (B, D) connected to two inputs (E1, E2) of this processing organ (15).

Abstract: The present invention relates to a control system for aircraft airbrakes, which comprises control means of a continuous operating mode or of an incremental operating mode in nominal operation of the airbrakes and control means of an incremental operating mode in the event of breakdown.

Abstract: A process and device for identifying faults in a complex system containing a plurality of elements connected together are disclosed. The device has a centralized processing station monitoring a system of complex elements which issue fault cues, within a predetermined time, to the central processing station. The fault cues are composed of an identification indicator and an origin indicator that allow the fault cues to be grouped together on the basis of their respective indicators for making a determination as to the origin of the fault. The system aide in the diagnosis and correction of a fault in a complex system, which are involved in locating and repairing such faults.