Abstract: In order to compensate for the increase in a leakage rate of ventilation air originating in a circuit via a labyrinth seal that gradually wears at the bottom of a ventilation chamber, and the reduction of a purge rate via an opening upstream from the chamber, a second injection opening is added to a main injection opening. The second injection opening communicates with the chamber via a second labyrinth seal that wears at the same time as the first, and thus gradually increases the air flow rate passing through the injector in order to compensate for the additional leakage rate through the first injector and maintain the ventilation at its initial level.

Abstract: Described is a articulating arm assembly for a passenger seat that includes a mounting bracket attached to a passenger seat, a pivot attached to the mounting bracket, an arm body rotatably attached to the pivot such that the arm body is configured to move between a stowed position and a deployed position, and a closeout that includes a flexible portion, a first end attached to a first attachment point internal to the pivot, and a second end attached to a second attachment point internal to the pivot. The flexible portion is configured to change shape depending on a location of the arm body.

Abstract: An acoustic attenuation panel for a propulsion unit including a nacelle and a turbojet engine includes a cellular core disposed between an inner skin and an outer skin, called acoustic skin, the acoustic skin including a plurality of acoustic apertures, the acoustic apertures being inclined, at a non-zero inclination angle (?) relative to the direction normal to the acoustic skin, upstream with respect to the flow direction of the air or gas flow to which the panel is intended to be subjected under normal operating conditions, that is to say upstream of the propulsion unit when the panel is mounted in such a unit.

Abstract: A DC/AC electrical power converter device having inlet terminals for electrically connecting to a DC electricity power supply network, outlet terminals for electrically connecting to an electric motor, a chopper electrical converter coupled to the inlet terminals, and an electrical inverter coupled between the chopper electrical converter and the outlet terminals. The converter device further includes a control unit for controlling the electrical inverter and that is configured to operate using pre-calculated pulse width modulation with pre-calculated unchanging switching instants for the controlled switches of the electrical inverter regardless of the frequency of rotation of the motor and of the voltage of the electricity network for connection to the device.

Abstract: The invention provides a method of assembling together a first core (12) and a second core (14) in order to make a non-permanent model configured for use in lost wax molding to form a part having a first cavity and a second cavity corresponding respectively to the first core and to the second core. The invention is characterized by the fact that the first and second cores (12, 14) are assembled together with a first spacer (20), the first spacer (20) being arranged between the first and second cores.

Abstract: A fitting assembly includes a fitting with at least one a pocket. The pocket includes a web extending inward from a perimeter of the pocket, and the web has cutout that defines an inner edge. A stiffener is mounted within the pocket. The stiffener includes a lattice and a coupler that is configured to engage at least a portion of the web to mount the lattice to the fitting.

Abstract: A method of fabricating a multi-perforated part out of composite material includes positioning a sand-blasting mask on a preform including a fiber texture impregnated with a polymerized ceramic-precursor resin, the mask having a plurality of openings corresponding to the perforations to be made in the preform; projecting abrasive particles at high speed against the surface of the mask so as to perforate the preform exposed in the openings of the mask; and pyrolyzing the multi-perforated preform so as to form a ceramic matrix in the multi-perforated fiber texture.

Abstract: A nozzle of a turbomachine is provided with chevrons with a non-axisymmetric inner face. A cover for the nozzle of longitudinal axis L-L includes an internal wall having a section with a predetermined abscissa on the L-L axis defining, on the wall, a neck line. The cover has, downstream from the abscissa, indentations in the trailing edge of the cover delimiting chevrons distributed in the circumferential direction, in which, on the cover, from the abscissa the internal wall moves away radially towards the outside of the upstream tangent, to the top of an indentation, the outer wall of the cover moves towards the upstream tangent to the top of an indentation, and the internal wall moves away radially towards the inside of the upstream tangent, to the tip of a chevron.

Abstract: A turbine engine rotor blade including an airfoil defined by plane airfoil sections stacked in a radial direction, each airfoil section being positioned radially at a height H, where height H is expressed as a percentage of the total height of the airfoil, and being identified by its sweep angle ? and its dihedral angle ?, wherein the sweep angle ? varies as a function of height H in such a manner that the sweep angle ? reaches a maximum at a height H?M, the value H?M lying in the range 5% to 40%, and the sweep angle ? increases from 0% to H?M, and wherein the dihedral angle ? varies as a function of H, the dihedral angle ? being a decreasing function of height H for heights H lying in the range 0% to H?1, H?1 lying in the range 10% to 40%.

Abstract: A turbine engine part includes at least a substrate, and present on the substrate, a ceramic coating for protection against calcium and magnesium aluminosilicates, the ceramic coating including Al2O3 at a molar content lying in the range 33% to 49%, Y3Al5O12 at a molar content lying in the range 21% to 53%, and yttria-stabilized zirconia at a molar content lying in the range 13% to 31%.

Abstract: The invention relates to an assembly comprising a structure (2) and a tubular element (6), which is mounted isostatically in the structure (2), said tubular element (6) comprising a first end (7) connected to said structure by at least four connecting rods 10a-10b-10c-10d, thus setting four first degrees of freedom, and a second end (8) connected to said structure (2) by an attachment means (20) that sets two second degrees of freedom, said connecting rods comprising a means for adjusting the length thereof. In particular, it relates to an exhaust suitable for an auxiliary power unit in the compartment thereof and to the mounting method for aligning them.

Abstract: A reduction gear having an epicyclic gear train for a turbine engine, in particular of an aircraft, comprising: a planetary shaft having an axis of rotation A; a ring gear having an axis A extending around said planetary shaft; planet gears distributed around said axis A, which mesh with said ring gear and the planetary shaft; and a planet carrier including members for supporting bearings of the planet gears, having axes of rotation B, which are evenly distributed around the axis A, as well as a part holding each supporting member substantially by the middle thereof along the axis B thereof, wherein said supporting members are made as a single part having means for supplying lubricating oil to said bearings. A method for assembling said reduction gear is also provided.

Abstract: A method and configuration to optimize an entire traction system available on a helicopter including an auxiliary engine by allowing the engine to provide non-propulsive and/or propulsive power during flight. The auxiliary engine is coupled to participate directly in providing mechanical or electrical propulsive power and electrical non-propulsive power to the aircraft. An architecture configuration includes an on-board power supply network, two main engines, and a system for converting mechanical energy into electrical energy between a main gearbox to the propulsion members and a mechanism receiving electrical energy including the on-board network and power electronics in conjunction with starters of the main engines. An auxiliary power engine provides electrical energy to the mechanism for receiving electrical energy via the energy conversion system and a mechanism for mechanical coupling between the auxiliary engine and at least one propulsion member.

Abstract: A turbine comprising an intermediate casing axially inserted between an upstream high pressure turbine casing and a downstream low pressure turbine casing and comprising an outer annular shroud from which an annular flange radially extends, characterized in that the downstream end of the high pressure turbine casing and the upstream end of the low pressure turbine casing are attached on the radial annular flange of the intermediate casing.

Abstract: Described are commercial aircraft cabin arrangement comprising a plurality of seat units (14), each seat unit including a primary seat (16) and a secondary seat (18) arranged facing one another. The primary seat (16) and the secondary seat (18) are configured to combine into a single bed position for the seat unit. The plurality of seat units (14) are arranged in two columns separated by a wide central aisle (72).

Abstract: A coupon suitable for peeling tests, derived from a vane and including: (i) a portion of blade that comprises an intrados surface, an extrados surface and a leading edge and/or trailing edge and (ii) a vane reinforcement that covers and is glued to at least a part of the intrados surface, a part of the extrados surface and which extends beyond the leading and/or trailing edge. The reinforcement is split over the entire length of the leading edge and/or trailing edge such that the reinforcement is separated into two plates separate from one another and facing each other on either side of the slit beyond the leading and/or trailing edge. Furthermore, at least one of the plates furthermore comprises, beyond the leading and/or trailing edge, notches configured to provide a hold to this same plate.

Abstract: A system for measuring an oil retention volume of a first member of an engine lubricating system, the injected oil flowing inside the first member mixed with a first air volume, the mixture forming a first fluid, the measuring system including an oil injector at the inlet of the lubricating system; a first flowmeter to measure a first oil flow rate at the inlet of the lubricating system; a second flowmeter at the outlet of the first member to measure a second flow rate of the first fluid at the outlet of the first member; a measuring device to calculate a first value representing a quantity of oil in a volume of the first fluid flowing inside the first member; a calculator to calculate a third oil flow rate at the outlet from the second flow rate of the first fluid measured and the first value calculated and the instantaneous oil retention volume in the first member from the comparison of the first oil flow rate with the third oil flow rate.

Abstract: A device for retaining drained fluids for a propulsive assembly includes a cavity for storing the drained fluids and two walls mounted at the opening of said cavity. The cavity has a fluid storage volume V1 when the device is in a substantially vertical position, and each wall is configured such as to define a fluid storage volume (V2 and V3 respectively) in the cavity when the device is in a substantially horizontal position, each of the volumes V2 and V3 being at least equal to the volume V1.

Abstract: The invention relates to a support providing a complete connection between a degassing pipe (3) and a turbine shaft (2), said support including a plurality of outer contact spans (41a) intended to bear on the inner walls of the turbine shaft to secure the degassing pipe with respect thereto, characterized in that the different spans are each bordered by at least one elastomer insert (41g) which contributes to the protection of the turbine shaft during insertion of the support therein.

Abstract: The present invention relates to a device for transmission by power-line communication (1) between two items of equipment (10, 20) on board an aircraft (1), comprising a transmission cable (3) configured to simultaneously transmit a power supply current and a data signal. This cable (3) comprises two twisted pairs of conductors (34, 34a, 34b). The device comprises a data sender (100) comprising a COFDM coupler (44) configured to modulate a signal by carrier modulation according to a COFDM mode, and a data receiver (200) comprising a COFDM coupler (44) configured to demodulate a signal modulated by carrier modulation according to a COFDM mode. The data sender (100) is configured to send a test signal by carrier modulation according to a COFDM mode, while the data receiver (200) is configured to detect signals corresponding to the test signals sent, and to analyze the carriers of the detected signal in regard to the signal sent and deduce therefrom the state of the transmission cable (3).