Abstract: A system for securing a passenger seat to a track can include a fitting coupled with or forming a portion of the passenger seat; a shear plunger coupled with the fitting including a shear plunger body defining a shear plunger locking surface; a guide pin assembly that may include a guide pin movable along a lift axis between a retracted state and an extended state and a locking member extending laterally from the guide pin that may travel in response to a movement of the guide pin from the retracted state to the extended state and may engage the shear plunger locking surface in response to a rotation of the guide pin in the extended state; and a quick install tool operable to raise and twist the guide pin assembly such that the locking member is held in tension against the shear plunger locking surface.

Abstract: A method for manufacturing a composite panel is described. The method includes producing a first wall, a second wall, a third wall and a fourth wall from composite materials including an oxide matrix and long oxide fibres; from the first and second walls, producing a cellular core including a plurality of cells, each cell including a first end and an opposing second end, covering the first and second ends of the cells of the cellular core with the third wall and the fourth wall, respectively, so as to close the ends of said cells.

Abstract: A method for manufacturing a fibrous preform for a blade or propeller part of a turbomachine, includes at least one fixing base extended by a mounting portion of an aerodynamic profile, the method including the winding of a fibrous texture, obtained by contour weaving, on a substrate of changing section having at least a first region of extra thickness in the shape of the fixing base and a second region in the shape of the mounting portion of the aerodynamic profile.

Abstract: The invention relates to an aircraft control column, the control column comprising a first shaft and a control lever configured to rotate the first shaft about a first axis through a first angular range [?1; ?3] via a mechanical joint having a primary reduction ratio, the control column comprising a braking device configured to brake the first shaft via a first transmission device having a secondary reduction ratio, the secondary reduction ratio being maximum for an angular position, the secondary reduction ratio increasing over the range [?1; ?4] and then decreasing over the range [?4; ?3] so as to obtain an overall reduction ratio that has a limited amplitude of variation over the first angular range [?1; ?3].

Abstract: An aircraft storage bin that includes a latch system that includes a pivot plate assembly, a mounting plate assembly and a latch button assembly. The pivot plate assembly includes a pivot plate attached to the bucket, a latch arm that is pivotally connected to the pivot plate and is pivotal between latched and unlatched positions, and a latch pawl that is pivotal between latched and unlatched positions. A latch activator is secured to the latch arm, which includes a roller member. The latch pawl includes hook and roller receiver portions. In the latched position, the roller member is received in the roller receiver portion. The mounting plate assembly includes a mounting plate to which the pivot plate is pivotally connected and a striker that is received in the hook portion when the bucket is in the closed position.

Abstract: An assembly for a turbomachine with a longitudinal axis having an exhaust cone with an outer annular wall for the flow of a primary airflow and an annular box arranged radially inside the outer annular wall, an exhaust casing arranged upstream of and connected to the exhaust cone. One end of the outer annular wall or one end of the annular box may be free to move relative to and have no mechanical connection with the exhaust cone or the exhaust casing.

Abstract: A method for closing an injection mold for manufacturing a revolution part made of composite material, the mold including a mandrel supporting a fiber preform and angular sectors comprising an annular base to come into contact with the fiber texture, the annular base extending between first and second side edges along a circumferential direction. The method includes successive positioning and fixing the angular sectors on the mandrel, the annular base of each sector compacting the fiber preform portion present oppositely, the side edges of the annular base of each angular sector being in contact with the side edges of the annular base of the adjacent sectors. Before the positioning and fixing of the angular sectors on the mandrel, strip s are placed on the exposed surface of the fiber preform, each strip covering an area of the fiber preform located facing a junction area between two adjacent angular sectors.

Abstract: An assembly for a gas turbine includes a hollow central shaft which is guided in rotation by at least one bearing, the assembly further including a device for lubricating said at least one bearing, the device including a hollow lubricant delivery tube which is arranged fixedly in the central shaft and is configured to deliver lubricant to the at least one bearing, the lubricant delivery tube having a first section with a first diameter and a second section with a second diameter which is greater than the first diameter, the second section including a plurality of radial channels connecting the inside of the lubricant delivery tube and leading radially to the outside of the lubricant delivery tube towards a radially inner wall of the central shaft so as to form a lubricant film between said second section of the lubricant delivery tube and said radially inner wall of the central shaft.

Abstract: A fuel conditioning system for an aerobic hydrogen engine, including: at least one hydrogen pump configured to increase the pressure of the liquid hydrogen delivered at the outlet of a tank, one or several heat exchangers configured to increase the temperature of the pressurized hydrogen, an air supply circuit, at least one combustion device configured to ensure a partial combustion of the hydrogen with air coming from the air supply circuit in order to produce a fuel including a gas mixture including gaseous hydrogen and devoid of oxygen.

Abstract: An assembly for producing a molding, made of removable material, of a turbomachine blade, includes an injection mold for the removable material in which a first core element and a second core element are mounted in a predetermined molding position, wherein the first and second core elements extend in a first direction. The mold includes a first face for molding a pressure-side face of the blade and a second face for molding a suction-side face of the blade and arranged facing the first face in a second direction perpendicular to the first direction. Retaining members hold the cores in position in the injection mold.

Abstract: A nickel-based superalloy including in weight percentages: 5.0 to 6.5% aluminium, 0.50 to 2.5% tantalum, 1.50 to 4.0% titanium, 0 to 7.0% cobalt, 12.0 to 16.0% chromium, 0.50 to 2.5% molybdenum, 0 to 2.0% tungsten, 0.05 to 0.15% hafnium, 0 to 0.15% silicon, the remainder consisting of nickel and unavoidable impurities. A single-crystal blade including such an alloy and to a turbomachine including such a blade.

Abstract: This control device for a propulsion system, comprising means for calculating a blade-pitch setpoint of at least one propeller of the propulsion system, the calculation means using a performance predictive model of the propeller taking account of at least one flight speed for adapting a blade-pitch angle setpoint, is characterised in that the performance predictive model of the propeller is configured to use polar charts implemented in the form of a mathematical law.

Abstract: An aircraft cabin (100) is disclosed. The aircraft cabin (100) comprises a plurality of pairs of seat units (120) positioned along an aisle (101). Each aisle seat unit (122A) comprises an aisle seat (125A) and an aisle footwell (126A) and each non-aisle seat unit (123A) comprises a non-aisle seat (127A) and a non-aisle footwell (128A). The aisle seat unit (122A) and non-aisle seat unit (123A) are positioned with respect to one another such that the aisle seat (125A) faces towards a first end of the cabin (100) and has direct access to the aisle (101), the non-aisle seat (127A) faces towards a second, opposite end of the cabin (100). The aisle seat unit (122A) is oriented at an angle with respect to the non-aisle seat unit (123A) to provide the non-aisle seat unit (123A) with an aisle access path (129A) between the non-aisle seat (127A) and the aisle footwell (126A).

Abstract: An abradable coating for a turbomachine, as well as a turbomachine module and a turbomachine including such an abradable coating, the abradable coating including, with a content of greater than 50% by volume, an inorganic compound whose Mohs hardness is less than 6 and whose melting temperature is greater than 900° C.

Abstract: An assembly including a turbine engine casing, in particular for an aircraft, the turbine engine casing including an annular or cylindrical radially outer shell, provided with a radially inner surface, and an aerody-namic treatment member including a plurality of grooves distributed in a circumferential direction. The radially outer shell includes a circumferential recess in which the aerodynamic treatment member is removably mounted, the treatment member extending along at least one angular sector and having a shape that matches that of the circumferential recess, the treatment member including a circumferential opening into which the plurality of grooves open.

Abstract: A power contactor including: a fixed part; a movable part able to come into contact with the fixed part and to move between an open position and a closed position of the contactor, the movable part including at least one power contact; an auxiliary contact and a pyrotechnic actuator, the auxiliary contact and the pyrotechnic actuator being placed in parallel with the power contact, and the pyrotechnic actuator being configured to be triggered during a levitation of the contactor in such a way as to move the contactor into the open position; and a motor configured to actuate the movable part and to put it in contact with the fixed part characterized in that the power contact and the auxiliary contact are desynchronized in such a way that when the contactor is closed, the power contact comes into contact with the fixed part before the auxiliary contact.

Abstract: A method for secure pairing between a sensor and a concentrator using a mobile terminal includes generating and emitting a confirmation code by the concentrator; converting by the sensor of the confirmation code into a sequence of light signals executed by at least one light-emitting diode; converting by the mobile terminal of the sequence of light signals into a sequence code; sending the sequence code to the concentrator; comparing, by the concentrator, the sequence code and the generated confirmation code: if the sequence code does not match the generated confirmation code, generating a warning; if the sequence code matches the generated confirmation code, pairing and exchanging information between the sensor and the concentrator.

Abstract: A system for controlling the modification of the pitch of the blades of a fan of a turbine engine, in particular for an aircraft. The turbine engine comprising blades mounted radially in a drive shaft and a setting device configured to modify the pitch of the blades on the basis of an axial force applied to said setting device. The control system comprises a hydraulic actuator, a hydraulic pump, a connecting ring connected mechanically to the hydraulic pump such that the flow rate of the hydraulic pump is proportional to the relative speed between the drive shaft and the connecting ring, and a magnetic coupling device designed to control the drive speed of the connecting ring in order to control the pitch of the blades independently of the speed of the drive shaft.

Abstract: A propulsion unit for an aircraft, includes a support structure, a nacelle and a turbomachine. The support structure is configured to independently support, on the one hand, the turbomachine and, on the other hand, preferably by a cradle, an air inlet and/or a rear section of the nacelle.

Abstract: An electrical machine for use in an aircraft, including a rotor. The rotor includes a plurality of rotor poles, and a stator including a plurality of phases. Each respective phase occupies at least one elementary block and the at least one elementary block of each phase includes a set of conductors of the respective phase wound around a plurality of slots of the respective elementary block in a concentrated winding configuration. A mechanical shift angle between the respective concentrated windings of each pair of adjacent elementary blocks is greater than a rotor pole pitch. The rotor pole pitch is an angle between adjacent poles of the rotor.