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 fuel metering unit including a movable element including at least one fuel passage section opening upstream towards a fuel supply conduit and opening downstream towards a conduit of use through a metering slot with a flared profile having a narrow passage section flaring as far as a wide passage section, the movable element being able to be moved with respect to a fixed element between a low flow rate position in which the metering slot is for a large part obstructed and a high flow rate position in which the metering slot is for a large part exposed, the metering slot being made in the fixed element or in the movable element and its obstruction being obtained by covering the slot with a wall of the movable element or of the fixed element.

Abstract: The invention relates to an aircraft turboprop engine having two unducted propellers, coaxial about a rotation axis (LL), respectively upstream (12) and downstream (14?), each propeller comprising an annular row of blades, the blades of the downstream propeller (14?) each having a truncated head and each comprising a leading edge (20?) and a trailing edge (22?), the radially external ends (A2, B1) of which are distant from each other and are connected by a terminal edge (21?), characterised in that the terminal edge (21?) of each blade of the downstream propeller (14?) has, at at least two points, tangents in a meridian plane having different slopes, the upstream end (A) of the terminal edge defining a maximum radial dimension (R2) of the blade and its downstream end (B1) defining a minimum radial dimension (R3) of the terminal edge.

Abstract: A vane intended to be mounted in a supply fluid pattern, includes a blade delimited in a lateral direction by an outer surface, the blade housing a data routing channel and having a groove leading to the outer surface and which communicates with the data routing channel, and data collecting means for collecting data on one of the outer surface of the blade and the vicinity thereof, the data collecting means being connected, through the groove, to the data routing channel, or extending there through. The data collecting means include one of an inserted tube and a cable, and the groove is formed in one of the outer surface opposite that whereto the inserted tube and the cable leads, and the blade that includes an orifice passing therethrough the outer surface.

Abstract: A data processor system for monitoring a complex system, the processor system configured to receive a plurality of pieces of state information and to merge at least the pieces of state information into a piece of failure information, at least one of the pieces of state information being associated with a confidence flag, and the piece of failure information also being associated with a confidence flag. The system performs the merging by implementing a fuzzy logic technique to produce the piece of failure information while taking account of the respective confidence flag of the pieces of state information and to produce the confidence flag associated with the failure information.

Abstract: A set of turbomachine guide vanes including plural vanes arranged around an annulus, each vane having a leading edge extending between root and tip ends, the leading edge offset between these two ends being greater than 10% of the blade height. A tangential stacking of the guide vanes towards the suction face side, the curve of tangential stacking, of the position, in the direction tangential to the annulus, of centers of gravity of successive vane cross sections along the vane height, is a curve that increases constantly towards the suction face side. The curve, near the vane tip end, has an accentuated gradient towards the suction face side compared with the rest of the curve, and has a mean gradient near the vane tip end that is greater than at least 1.2 times the mean gradient of the curve over the portion between 30% and 90% of the vane height.

Abstract: The invention relates to a turbine engine exhaust casing (1), characterized in that it comprises: a hub (2), an outer ring (3); a plurality of structural arms (10) arranged circumferentially between the hub (2) and the outer ring (3); a stiffener (11) extending along at least a portion of the inner circumference of the hub (2), the hub (2) comprising at least one discharge hole (15), and the stiffener (11) comprising at least one discharge slot (16), so as to enable the discharge of a fluid from the casing (1). The invention also relates to a turbine engine comprising such an exhaust casing.

Abstract: A method of making a fiber preform, and the preform, for fabricating a turbine engine blade out of composite material, the method including: making a single-piece fiber blank by three-dimensional weaving with layers of longitudinal yarns interlinked by yarns of layers of transverse yarns; and shaping the fiber blank to obtain a single-piece fiber preform including a portion forming an airfoil preform and at least one portion forming a platform preform. During weaving, yarns of a first group of longitudinal yarns are extracted from the fiber blank beside one of side faces of the blank to form a portion corresponding to a blade platform preform, and yarns of a second group of longitudinal yarns are inserted into the fiber blank with mutual crossing of the yarns of the first group and the yarns of the second group.

Abstract: A reaction propulsion device in which a first feed circuit for feeding a main thruster with a first propellant includes a branch connection downstream from a pump of a first turbopump, which branch connection passes through a first regenerative heat exchanger and a turbine of a first turbopump, and in which a second feed circuit for feeding the main thruster with a second propellant includes, downstream from a pump of a second turbopump, a branch-off passing through a second regenerative heat exchanger and a turbine of the second turbopump. At least one secondary thruster is connected downstream from the turbines of the first and second turbopumps.

Abstract: A vaned wheel device traversed by a radial drive shaft includes radial arms, one of which contains the shaft, and stationary vanes manufactured separately from the casing and a ferrule and assembled thereto. A sleeve encompassing the shaft traverses the casing and serves to support a bearing for supporting the shaft with positional accuracy, and maintaining tightness by forming a single cavity with the radial arm cavities traversing the shaft.

Abstract: A characterization method for characterizing an article made of composite material having woven, braided, or sewn fiber reinforcement, the method including a determination step of using X-ray tomography to determine gray levels of at least a portion of the article, followed by an exploitation step of exploiting the gray levels to obtain information concerning the weaving by distinguishing between at least the free matrix and the threads of fibers mixed with the matrix, the threads being considered as being a material that is homogeneous.

Abstract: The main aim of the invention is a propeller (32) for a turboengine (1) comprising a plurality of blades (48) and a blade support ring (47) provided with housings (50), each receiving a pivot (52) bearing the foot (58) of one of said blades (48), characterized in that at least one of the pivots (52) is equipped with at least one counterweight system (90, 91) provided with at least one inner channel (93, 96) for airflow ventilation discharge (F1, F3) for capturing and guiding said airflow directly in contact with the blade foot (58) borne by said at least one of the pivots (52).

Abstract: A device for surfacing a metal alloy part by laser welding, the part including a recess to be surfaced and located at a planar area of the part, the device including first and second protective elements arranged on either side of the recess, the first and second protective elements each having an irradiation surface which is to be at least partially covered with a layer of powder to enable welding by passing a laser beam over the powder, the laser beam passing over the irradiation surface of the first protective element during welding and then the irradiation surface of the second protective element, the second protective element having a shape for containing a layer of powder having a height that is greater at the end, in the direction of propagation of the laser beam during welding, of the second protective element than at the start of the second protective element.

Abstract: The invention relates to a turbine engine blade, particularly made of composite material, including: on the one hand, an airfoil (10) which exhibits: a leading edge (12), a trailing edge (14) opposite to the leading edge (12), intrados (16) and extrados (18) lateral walls which connect the leading edge (12) to the trailing edge (14), et on the other hand, a structural reinforcement (20) including a base (24) extending into two fins (26, 28) and designed to be applied to the leading edge (12) and the lateral walls (16, 18) of the airfoil (10), characterized in that the fins (26, 28) of the structural reinforcement (20) and/or the lateral walls (16, 18) of the airfoil (10) are shaped to maintain an assembly space (30) with nonzero thickness between at least one of the fins (26, 28) and the airfoil (10) when the structural reinforcement (20) is in place on the airfoil (10), said assembly space (30) extending from a free end (27, 29) of said fin (26, 28) toward the base (24) of the structural reinforcement

Abstract: A device for localizing a position on a part includes a support to receive the part, a bushing movably mounted with respect to the support, a removable localization member to be inserted into the bushing, and a blocking device to fix the bushing with respect to the support and to maintain it in position.

Abstract: A journal configured to be driven in rotation in a housing of a turbine engine, or for an aircraft, the journal including: a circumferential main body including plural ventilation openings configured to allow plural axial airflows to circulate from upstream to downstream in the turbine engine, two consecutive ventilation openings being connected by a connecting segment, and a circumferential ring for recovering a flow of lubrication oil, which ring is rigidly connected to the main body and is radially inside the ventilation openings, the circumferential ring including plural radial discharge openings for allowing plural radial flows of oil to be discharged towards the outside, each discharge opening being radially aligned with a connecting segment of the main body to allow each flow of oil to be discharged radially between the airflows.

Abstract: An assembly for an aircraft turbine engine including an integral element including a disk and a plurality of blades is provided. Each blade has a connection zone connecting the blade to the disk, the connection zone including a first part arranged at the external flowpath delimitation surface provided on the disk, and at least one second end part arranged at a recess formed in the disk along the axial extension of the external surface, the average fillet radius defined by the second end part being larger than the fillet radius defined by the first part. The assembly further includes a flowpath reconstruction part formed in the aerodynamic continuity of the external surface, so as to cover the recess.

Abstract: In a fiber structure woven as a single piece by three-dimensional weaving, first warp yarns interlink layers of weft yarns in a first portion of the fiber structure adjacent to a non-interlinked zone and also weft yarns of a second portion of the fiber structure beyond the non-interlinked zone, and second warp yarns interlink layers of weft yarns of the second portion of the fiber structure adjacent to the non-interlinked zone and also layers of weft yarns of the first portion of the fiber structure beyond the non-interlinked zone, such that the paths of the first and second warp yarns cross in at least one transition zone extending within the fiber structure from the end of the non-interlinked zone, the transition zone extending in the warp direction over a distance greater than the pitch between adjacent warp columns.

Abstract: A device for guiding variable pitch stator vanes of a turbine engine is provided. The device includes a plurality of inner ring angular sectors arranged end-to-end in order to form an inner ring, each inner ring sector having chimneys passing radially through the inner ring sector, a plurality of cylindrical bushings, each being put into place in a chimney of the inner ring from the inside and each serving to receive a guide pivot of a stator vane, a plurality of reconstitution ring angular sectors arranged end-to-end in order to form a reconstitution ring and put into place radially from the inside against the inner ring, and a plurality of blocking elements passing axially through the inner and reconstitution rings in order to assemble the rings together.

Abstract: A turbine engine has at least two successive annular rows of stationary vanes, e.g. formed by the vanes of a nozzle and by an annular row of casing arms arranged downstream from the nozzle Each casing arm extends substantially in a radial plane passing between the trailing edges of two adjacent stationary vanes of the nozzle, and the pitch between these two stationary vanes is greater than the pitch between the other stationary vanes of the nozzle, in such a manner that the wakes formed at the trailing edges of these two stationary vanes pass respectively on either side of the corresponding casing arm.