Abstract: A kit of parts includes a ceramic element comprising a cylindrical bore having at least one recess, and a rod comprising an outer tube comprising a jutting portion adjacent to an insert portion. An outer tube wall mates with the cylindrical ceramic bore. An outer tube bore comprises a cylindrical portion. An outer tube projecting member is insertable into a recess in the cylindrical bore. An inner mandrel insertable into the outer bore stabilizes a projecting member in a recess to couple the rod to the ceramic element.

Abstract: The present disclosure relates to the field of aircraft nacelles and concerns thrust reverser devices. More particularly, the present disclosure concerns a rear frame for a thrust reverser structure with a cascade vane of an aircraft nacelle, the nacelle comprising at least two longitudinal beams. The rear frame is intended to be attached to the two beams and to hold in place one or more cascade vanes in cooperation with a front frame. The rear frame comprises a common section having a substantially headband-like shape.

Abstract: A kit of parts includes a ceramic element comprising a cylindrical bore having at least one recess, and a rod comprising an outer tube comprising a jutting portion adjacent to an insert portion. An outer tube wall mates with the cylindrical ceramic bore. An outer tube bore comprises a cylindrical portion. An outer tube projecting member is insertable into a recess in the cylindrical bore. An inner mandrel insertable into the outer bore stabilizes a projecting member in a recess to couple the rod to the ceramic element.

Abstract: An integral metal end cap for use in a conveyor roll assembly is suitable for use in an environment subject to significant temperature variation. The metal end cap comprises a first end connectable to rotary means, and a second end comprising an integral body adapted to fit over the end of a ceramic spool. The integral body contains a torque transmission portion having a plurality of deformable strips enabling transmission of torque during temperature variations. A conveyor roll assembly comprises a ceramic spool having a longitudinal axis and, at least at one end of the ceramic spool, a metal end cap as described.

Abstract: A conveyor roll assembly for use at high temperature comprises (a) a ceramic spool having a flexural strength of at least 15 MPa and an external diameter D and (b) a torque transmitter and support of a general cylindrical shape and having a longitudinal axis, comprising a body and (b1) a supporting portion comprising at least one cylindrical supporting surface and (b2) a connecting portion that is mechanically and resiliently deformed, comprising at least two distinct connecting surfaces, frictionally connecting the torque transmitter and support to the ceramic spool. At least one end of the ceramic spool has an axial, centered bore of a diameter 10 mm?d?¾ D, and a depth Dd?1.5 d. The torque transmitter and support is housed at least partially in the bore of the ceramic spool.

Abstract: An integral metal end cap for use in a conveyor roll assembly is suitable for use in an environment subject to significant temperature variation. The metal end cap comprises a first end connectable to rotary means, and a second end comprising an integral body adapted to fit over the end of a ceramic spool. The integral body contains a torque transmission portion having a plurality of deformable strips enabling transmission of torque during temperature variations. A conveyor roll assembly comprises a ceramic spool having a longitudinal axis and, at least at one end of the ceramic spool, a metal end cap as described.

Abstract: A conveyor roll assembly for use at high temperature comprises (a) a ceramic spool having a flexural strength of at least 15 MPa and an external diameter D and (b) a torque transmitter and support of a general cylindrical shape and having a longitudinal axis, comprising a body and (b1) a supporting portion comprising at least one cylindrical supporting surface and (b2) a connecting portion that is mechanically and resiliently deformed, comprising at least two distinct connecting surfaces, frictionally connecting the torque transmitter and support to the ceramic spool. At least one end of the ceramic spool has an axial, centered bore of a diameter 10 mm?d?¾ D, and a depth Dd?1.5 d. The torque transmitter and support is housed at least partially in the bore of the ceramic spool.

Abstract: The present disclosure relates to the field of aircraft nacelles and concerns thrust reverser devices. More particularly, the present disclosure concerns a rear frame for a thrust reverser structure with a cascade vane of an aircraft nacelle, the nacelle comprising at least two longitudinal beams. The rear frame is intended to be attached to the two beams and to hold in place one or more cascade vanes in cooperation with a front frame. The rear frame comprises a common section having a substantially headband-like shape.

Abstract: An aircraft nacelle includes: a thrust reverse device having movable cowls, and a supporting structure to support the thrust reverser device. The supporting structure includes: a base body extending along a longitudinal direction of the nacelle and made from a composite material, and a wall of the base body forming an unclosed cross section having an open portion to provide access to an inner surface of the supporting structure from outside, and a plurality of reinforcements which is made from a composite material, and attached on the inner surface along the longitudinal direction. In particular, the reinforcements are integrated in the inner surface of the supporting structure.

Abstract: The present disclosure relates to a beam, in particular for a cascade thrust reverser, including a skin made of a composite material and defining a closed section, wherein said beam is filled with a core material.

Abstract: Methods for case management in a production environment. An update to an existing case management solution running in a production environment is received. A collection of existing case instances created before the update was made to the existing case management solution is retrieved. Each case instance in the received collection of existing case instances is processed to add missing tasks to the case instance and to update a case instance structure for each case instance. Each processed case instance is saved.

Abstract: Methods and apparatus, including computer program products, implementing and using techniques for case management in a production environment. An update to an existing case management solution running in a production environment is received. A collection of existing case instances created before the update was made to the existing case management solution is retrieved. Each case instance in the received collection of existing case instances is processed to add missing tasks to the case instance and to update a case instance structure for each case instance. Each processed case instance is saved.

Abstract: A method for manufacturing a T-shaped composite part by resin transfer molding, includes the following steps: making a preform with a planar stack of plies and with two L-shaped stacks of plies; placing the preform so that the L-shaped stacks meet between two cores of a resin transfer molding tool; inserting and removing fibers through the planar stack in a direction perpendicular or quasi-perpendicular to the planar stack and so that loops are formed inside a portion of the L-shaped stacks which are substantially perpendicular to the planar stack; closing the resin transfer molding tool; injecting a resin into the resin transfer molding tool; and heating the resin transfer molding tool to cure the resin.

Abstract: A supporting half-structure for an aircraft engine nacelle is provided that includes at least one longitudinal beam and a front half-frame, the beam and the half-frame being formed of composite materials. The half frame has an open section, and the half-structure defines a structure selected from the group consisting of: the beam and the front half-frame form a one-piece part; the beam has an extension with an open section, the shape of which matches that of the front half-frame, the extension being attached to the half frame; and the front half-frame has an extension with an open shape, the shape of which matches the beam, wherein the extension is attached to the beam.

Abstract: A stub frame for a cascade vane thrust reverser structure of an aircraft nacelle is attached to one or more cascade vanes. The stub frame includes an integral primary structure with a C-shaped longitudinal section, a secondary structure acting as a cascade edge and attached to the primary structure at one end, and transverse stiffeners connecting the two ends of the primary structure.

Abstract: The invention concerns compounds of general formula (I), wherein n, X1, X2, X3, X4, Y and W are as defined herein. The invention also concerns a method for preparing said compounds and their therapeutic use.

Abstract: The invention relates to compounds of the general formula (I): Wherein X, Y, Z, Z1, Z2, Z3, Z4 and n are as defined herein. The invention also relates to a method for making the same and to the use thereof in therapy.

Abstract: The invention relates to compounds of the general formula (I): Wherein X, Y, Z, Z1, Z2, Z3, Z4 and n are as defined herein. The invention also relates to a method for making the same and to the use thereof in therapy.

Abstract: The disclosure relates to compounds of formula (I): wherein X1, X2, X3, X4, Y, n, A, and W are as defined in the disclosure, or a salt thereof, or a hydrate or solvate thereof, and to processes for the preparation of these compounds and the therapeutic use thereof.

Abstract: The invention concerns compounds of general formula (I): Wherein n, X1, X2, X3, X4, Y, Z, Z1, Z2, Z3 and Z4 are as defined herein. The invention also concerns a process for the preparation of compounds of formula (I) and their therapeutic use.