Abstract: An airplane provided with dual-flow turbojet engines having nacelles at least partially encased in the fuselage, wherein the air intake of each engine is connected to the fuselage by two boundary layer guiding walls, the walls extending towards the upstream side of the air intake and being spaced apart towards the upstream side.

Abstract: The present invention relates to a helical ring (100) comprising a polygonal body (110) and a plurality of cylindrical radial housings (150) arranged in said body, each housing (150) having a surface adapted to receive support means of a blade of a helix, characterised in that the surface of each housing (150) is arranged on a radially internal surface (201) of a corresponding hub (200), each hub (200) being a separate piece attached to the body (110) of the ring, intended to be received in a radial housing (21) of the latter, and in that it also comprises two projecting pins (32) relative to its external surface to be fastened to the edges of a housing of the annular body, the two projecting pins forming a centring axis. The invention also relates to a manufacturing process of such a ring, a helix and a turbomachine fitted with such a ring.

Abstract: A fan rotor including a disk carrying blades including roots engaged in slots in the disk, a frustoconical cap mounted on the disk upstream from the blades, and a retaining mechanism axially retaining the blades on the disk and including a ring mounted in an annular groove of the disk and forming an abutment for the roots of the blades, the ring being festooned or crenellated and co-operating with a festooned radial annular bead of the annular groove of the disk, and a mechanism preventing the ring from moving in rotation, which includes an annulus carrying at least one axial tooth inserted in hollow portions of the bead of the disk and of the ring, the annulus being fastened by bolts on an upstream radial face of the disk.

Abstract: The invention relates to a method for managing services on a network, comprising: at least two interconnected computer sites, each of which is capable of implementing at least one service that can be accessed from the network; at least one service implemented on a network site; a means for transferring a service from an initial site to a separate destination site. Each is associated with security attributes and the method includes transferring at least one service from an initial site to a destination site of the network following a predetermined transfer sequence which depends on the security attributes.

Abstract: A method for mineralizing siloxane derivatives from a liquid organic phase by adding a base in the form of an alkaline hydroxide.

Abstract: A breathing assembly for aircraft comprising a storage unit, a breathing mask and a releasable securing device. The storage unit has a guiding surface extending perpendicularly to an elevation direction and a maintaining element. The breathing mask comprises a rigid support having a sliding surface adapted to slide in contact with the guiding surface of the storage unit, along a sliding direction between a storage position and an exit position. The support further has a maintaining element. In the storage position, the sliding surface of the support is prevented from moving away from the guiding surface of the storage unit along the elevation direction at the distal end by engagement of the maintaining element of the support with the maintaining element of the storage unit.

Abstract: The present invention is directed to a pneumatic tire comprising at least one component, the at least one component comprising a rubber composition, the rubber composition comprising: at least one diene based elastomer; from 20 to 40 parts by weight, per 100 parts by weight of elastomer (phr), of silica; and from 10 to 25 weight percent of aluminum hydroxide; wherein the composition is self-extinguishing at a temperature of 1000° C., and the composition is exclusive of halogenated paraffins and antimony trioxide.

Abstract: Controllable pitch blade non-ducted propeller for a jet engine, comprising a rotor member comprising radial housing for mounting blade support plates, each plate being attached in a ring centered and guided in rotation in a housing of the rotor member and comprising external toothing engaged and locked in internal toothing of the ring, to withstand the centrifugal forces to which the propeller blades are subjected in operation.

Abstract: An assembly in a turbine engine for controlling plural toothed pivotally-mounted blades arranged in azimuth around the axis of the turbine engine and including an actuator ring controlling a position of the blades. Racks mounted on the ring present corresponding sets of teeth meshing with the set of teeth of a respective one of the blades to place it in a selected angular position, and they are held in the radial direction by radial positioning mechanism fastened to the blade. Each rack is mounted on the ring by plural guides spaced apart circumferentially around the ring, that connect together movements of the rack and of the ring in the circumferential direction, and that are configured to slide relative to the ring, for each guide in its own radial direction, and relative to the rack in a direction of movement that is substantially radial and specific to the rack.

Abstract: A variable pitch blade propeller hub for a turbomachine with a longitudinal axis includes a polygonal ring supporting the blades, concentric with the longitudinal axis and including two spaced parallel annular end flanges between which are diametrically fastened, by root areas arising from the annular flanges, collars with cylindrical radial housings to receive the blades. The collars are equi-angularly distributed at the lateral periphery of the polygonal ring and separated from each other by intermediate areas with through-openings. The also includes connectors connecting the polygonal ring to a turbine rotor element of the turbomachine. The intermediate areas defined between two concentric collars and the annular end flanges include elements for reinforcing the collars that are arranged radially and/or tangentially and fastened at least to the lateral walls of two consecutive collars.

Abstract: An assembly including a gas turbine engine and a nacelle in which the engine is housed, the nacelle including an air intake fairing that forms an air inlet and includes: a member for deflecting foreign objects, which together with the fairing, forms an air intake duct; and, downstream from the deflecting member, a secondary deflecting channel, and a main channel for supplying air to the engine. The air intake duct is configured to deflect at least some of the foreign objects sucked in through the air inlet towards the secondary deflecting channel. The secondary deflecting channel is shaped such that the flow velocity of the air flowing therethrough increases from upstream to downstream, the secondary channel having an outlet with an opening leading into the outer wall of the nacelle.

Abstract: A hub for a propeller having variable pitch blades for a turbine engine, for example for a propfan turbine engine. The propeller hub includes: a polygonal ring having substantially radial cylindrical housings distributed about a central axis of the ring for receiving the blades; a rotor element for the turbine of the turbine engine; a supporting flange attached to the ring so as to connect the ring to the rotor element; and a plurality of backup retaining members linked to the rotor element, and each of which includes at least one bearing surface opposite an outer surface of the ring with a radial spacing.

Abstract: A prestressing device extending about an axis between a first plane that is substantially perpendicular to the axis and a second plane that is substantially parallel to the first plane and axially offset relative to the latter. The device includes a first annular body extending in the first plane, and a first series of at least three tabs, each of which is connected to the first body and extending in an essentially radial direction, each of the tabs of the first series including a planar surface extending in the second plane. This arrangement ensures surface contact between the parts of the elements to be subjected to prestressing. The device can be used for example for a rotor, and for example for a rotor of an unducted propeller for a turbine engine.

Abstract: A prestressing device extending about an axis between a first plane and a second plane, the first plane being located at a predetermined distance from the second plane, each plane being perpendicular to the axis. The device includes at least three deformation areas. The deformation areas extend in the first plane. The device further includes, between each deformation area, a planar contact surface extending in the second plane.

Abstract: A hub of a propeller with variable-pitch blades for a turbine engine, for example for a propfan engine. The hub of the propeller includes a polygonal ring with substantially radial cylindrical recesses distributed about a central axis of the ring for receiving the blades, a turbine rotor element of the turbine engine, and a securing flange that is attached to the ring so as to connect the ring to the rotor element. The hub further includes a plurality of back-up hooks inserted with clearance in openings, the back-up hooks being connected either to the ring or to the rotor element, and the openings being connected to the other one of the two.

Abstract: A turbine stage in a turbomachine is disclosed. The stage includes a wheel mounted in a ring carried by a turbine casing, and a nozzle situated upstream from the wheel and including an annular fastener rim for fastening to the turbine casing, sealing being provided between the outer rim of the nozzle and the upstream end of the ring by a radial annular sheet bearing axially at its inner and outer peripheries against a downstream face of the outer rim of the nozzle, with its middle annular portion being axially spaced apart from the outer rim of the nozzle and bearing axially against the upstream end of the ring.

Abstract: An airplane provided with dual-flow turbojet engines having nacelles at least partially encased in the fuselage, wherein the air intake of each engine is connected to the fuselage by two boundary layer guiding walls, the walls extending towards the upstream side of the air intake and being spaced apart towards the upstream side.

Abstract: A closure 10 for a container, comprises a substantially circular base 20, a skirt 30 extending from the periphery thereof, a bore seal 50 in the form of an annulus and a rib 70 lying on the surface of the base 20 in a substantially radial direction and in contact with the radially inner surface of the bore seal 50 at one end for transferring any movement of the center of the base 20, relative to the skirt 30, to the bore seal 50 such that the bore seal 50 is pulled radially inward to allow venting of excess pressure within the container, wherein the end of the rib 70 in contact with the radially inner surface of the bore seal 50 is substantially thinner, in a plane parallel to the base 20, than the other end of the rib 70.

Abstract: A plastic closure for a container is provided. The closure includes a top plate with a side skirt depending from the periphery thereof. A sealing strip depends from the top plate and is adapted to sealingly engage a container neck finish. The closure also comprises an abutment member including a guide surface for guiding the sealing strip towards the neck finish as the closure is applied, to increase the strength of the seal. The guide surface includes a guide member that projects from the abutment member, thereby minimizing friction between the strip and the abutment member. The sealing strip is inclined radially towards the neck finish to improve the sealing effect.

Abstract: A turbofan exhaust system includes at least one exhaust nozzle with a trailing edge having an upper edge, a lower edge, an inner lateral edge-and an outer lateral edge. The upper edge is upstream with respect to the lower edge. The outer lateral edge of the exhaust nozzle is also upstream of the inner lateral edge. This arrangement makes it possible to reduce the noise perceived in the cabin of the aircraft at the same time as the noise perceived on the ground.