Abstract: An abradable coating for a turbomachine part, includes a matrix made of a first metal material and particles made of a second metal material that are dispersed in the matrix, the first metal material having a melting temperature greater than 900° C., the second metal material having a melting temperature at least 50° C. lower than the melting temperature of the first metal material.

Abstract: The present invention relates to para-amino-benzyl linker compounds useful for linking drug moieties to antibodies, to linker-drug compounds in which said para-amino-benzyl linker compounds are covalently linked to drug moieties, and to antibody-drug conjugates in which said para-amino-benzyl linker compounds are covalently linked to drug wherein said drug is enzymatically cleaved from the conjugate at a particular cell or tissue type targeted by said antibody.

Abstract: The invention relates to an aerial transport device by means of connections with supply lines and cables for the transport of electricity, liquids and goods, at the limit of the atmospheres of the planets, in areas with low gravitational attraction, so that the flight can take place in the formation. The aerial transport device by means of flight devices (A, A1n, B, Bn, A4) that are in motion and connected between them, characterized in that the system can supply (P1) and simultaneously transport physical objects, liquids, and energy (P) to and from the outer space of dense atmospheres (D) and to reach the maximum limit of the environment density suitable for space flight devices (A3) with aerodynamic load as well as for horizontal air transport (A4, A2, P, An, A3). The invention is technical device for transporting in space with flying devices and move in formation flight of at least three forming connections.

Abstract: The invention relates to a bent connecting rod (31) for linking a first assembly to a second assembly which are movable relative to each other and through which a flow in the space defined thereby passes. The rod has at least one first and one second pivot point (35, 38) that are designed so as to enable the pivotal movement of the connecting rod (31) relative to said first and second assemblies, respectively, the bent connecting rod (31) being suitably positionable such that the bend (40) is located upstream from said flow relative to said second pivot point (38), said second pivot point (38) being suitably built into the second movable assembly, characterized in that the bent connecting rod (31) includes at least two portions (33, 37) linked together by at least one self-aligning means (39a, 39b).

Abstract: An assembly to hold an interface of a stationary outer structure of a nacelle and a casing of a jet engine includes first and second raised elements and two half rings. The first raised element belongs to an upstream end of the stationary outer structure, and the second raised element belongs to a downstream end of the casing. The first and second raised elements are formed so as to be placed in contact with each other, and the two half-rings are formed by a wall and an abutment. The wall defines a housing to receive the first and second raised elements when the casing and the stationary outer structure are mounted edge to edge, and the abutment is formed so as to keep the first and second raised elements in the housing.

Abstract: A nacelle for a turbojet engine of an aircraft is provided that includes a fan case, an internal structure positioned upstream from the fan case, and a thrust reverser positioned downstream from the fan case. The thrust reverser includes a cowl delimiting an external line (LE) and including two removable half cowls. A device for absorbing circumferential stresses are shaped so as to lock the half cowls in the closed position when it occupies a locking configuration on the one hand and for allowing the opening of the half cowls when it occupies an unlocking configuration on the other hand. The stress absorbing device is positioned under an upstream portion of a pylon and is exclusively attached to the half cowls in order to allow the opening of the two half cowls independently of the opening/closing of an external fan cowl.

Abstract: The invention relates to an assembly for holding the interface of a stationary outer structure (15) of a nacelle (3) and housing (27) of a jet engine (5), said assembly including: a first raised element belonging to the upstream end of the stationary outer structure (15); a second raised element belonging to the downstream end of the housing (27), said first and second raised elements being formed so as to be placed in contact with each other; two half-rings (109) formed by a wall defining a recess that is formed so as to receive the first and second raised elements when the housing (27) and the stationary outer structure (15) are mounted edge to edge; and an abutment means formed so as to keep the first and second raised elements in the recess.

Abstract: The invention relates to a bent connecting rod (31) for linking a first assembly to a second assembly which are movable relative to each other and through which a flow in the space defined thereby passes. The rod has at least one first and one second pivot point (35, 38) that are designed so as to enable the pivotal movement of the connecting rod (31) relative to said first and second assemblies, respectively, the bent connecting rod (31) being suitably positionable such that the bend (40) is located upstream from said flow relative to said second pivot point (38), said second pivot point (38) being suitably built into the second movable assembly, characterized in that the bent connecting rod (31) includes at least two portions (33, 37) linked together by at least one self-aligning means (39a, 39b).

Abstract: The present invention relates to a locking system (20) for a movable lateral cowl (8) of a turbine engine nacelle intended to be connected to a pylon (4) of an aircraft, comprising, on the one hand, a clevis (21) intended to be connected to the pylon, and, on the other hand, a rod (22) intended to be mounted on the movable cowl and capable of engaging with the clevis when the movable cowl is in the closed position, characterized in that the rod is mounted so that it can move translationally along a substantially longitudinal axis of the movable cowl so as to form a slider which can shift between a locked position, in which it is engaged with the clevis and provides a structural connection between the pylon and the movable cowl, and an unlocked position, in which it is disengaged from the clevis and allows the movable cowl to be opened.

Abstract: The present invention relates to a locking system (20) for a movable lateral cowl (8) of a turbine engine nacelle intended to be connected to a pylon (4) of an aircraft, comprising, on the one hand, a clevis (21) intended to be connected to the pylon, and, on the other hand, a rod (22) intended to be mounted on the movable cowl and capable of engaging with the clevis when the movable cowl is in the closed position, characterized in that the rod is mounted so that it can move translationally along a substantially longitudinal axis of the movable cowl so as to form a slider which can shift between a locked position, in which it is engaged with the clevis and provides a structural connection between the pylon and the movable cowl, and an unlocked position, in which it is disengaged from the clevis and allows the movable cowl to be opened.

Abstract: The present invention relates to a nacelle (1) of a turbojet engine (4), which nacelle is intended to be attached to a structure (2) of an aeroplane by a connecting pylori (3) and comprises at least one moving part (9?, 9?) above to be opened in order to provide access to the interior of the nacelle, characterized in that the said moving part is mounted to pivot about a pivot axis (25) directed along a line more or less perpendicular to the plane of the structure of the aeroplane to which the nacelle is attached.

Abstract: A threaded hole with damaged threads and a repair apparatus including an elongated, flexible strip material, a portion of the strip material inserted between the threads of the threaded hole and the fastener. The strip material characterized as flowable under compressive stress between the threads of the threaded fastener and the threaded hole, and having substantial rigidity as to engage the fastener within the threaded hole.

Abstract: This invention provides an improved apparatus and method for encapsulating the solder ball interconnections of an integrated circuit assembly which accommodates the use of high viscosity encapsulating materials and enables flush molding to be accomplished without substantially altering the exposed surface of the integrated circuit chip. In accordance with the preferred embodiment of this invention, an integrated circuit chip assembly including an integrated circuit chip mounted on a chip carrier or directly on a circuit board in a standoff relationship by solder ball connections is provided. A mold is placed over the integrated circuit chip. The mold of one embodiment has a compliant material disposed on the molding surface of the mold cavity. The mold also has at least one inlet hole for dispensing encapsulant into the mold, at least one opening for applying a vacuum to the mold and at least one vent.

Abstract: A shaft bushing provides a internal circumferential or annular surface and an adjacent internal radial surface both of which receive lubricant directly from an aperture in the bushing, in such a manner that outfacing surfaces, radial surfaces and in-facing surfaces of elements which are either a part of the shaft itself, or are mounted on the shaft, receive lubricant directly from the aperture. The aperture is formed as a straight hole and directed at an angle through the bushing wall so that its interface with the interior surfaces of the bushing are elliptical. Lubricant is directed through this hole to the interior of the bushing and thence to surfaces in contact therewith. The placing of the hole at an angle allows the lubricant to move in a straight line with no turns which might contribute to clogging, and results in a smooth transfer of lubricant from the hole to the interior surfaces in two orthogonal planes.

Abstract: An apparatus is provided for indicating if the temperature of a fluid within a machine has surpassed a critical temperature. An integrally formed support of a rigid material able to withstand the critical temperature includes a head and a cavity formed within the head. The head provides a hexagonal nut such that a standard socket wrench or other wrench may be used to engage and rotationally drive the head of the device. An engagement shaft extends from the head and provides an external machine screw thread that enables engagement of the shaft within a complimentary threaded hole in the machine. The shaft further includes an axial bore that extends from a distal end of the shaft, through the shaft, and terminates adjacent to the cavity within the head. A temperature indicator is made of a material having a melting temperature equal to the critical temperature and is bonded within the cavity such that the support means and the indicator means are in good thermal contact.