Abstract: The invention relates to an intermediate case (25) for a twin spool turbomachine for an aircraft, comprising a hub (26), an outer shell (23) and outlet guide vanes (24) installed at their ends on the hub and on the outer shell, and each of at least some of the outlet guide vanes (24) performing a heat exchanger function and comprising a lubricant passage (50a, 50b) designed to be cooled by the fan flow (58) following an outer surface of the outlet guide vane. According to the invention, the case also comprises at least one lubricant duct (55) passing along a circumferential direction of the hub (26) and at least part of which is made from a single casting with the hub, the lubricant duct (55) having at least one lateral opening communicating with the lubricant passage (50a, 50b) of at least one of the vanes (24).

Abstract: The present invention relates to a system for coupling an accessory box (16) of the engine (14) of an aircraft to an accessory box (12) of the aircraft, the engine accessory box being connected to a first shaft (20) inside which is slidably mounted a slide (28) carrying first coupling means (28d) capable of cooperating with second coupling means (38) carried by a second shaft (22) connected to the aircraft accessory box (12) so as to couple the first (20) and the second (22) rotating shaft, wherein it further comprises electrical means for moving the slide (28) along the axis (30) of the first shaft (20) between a first uncoupling position with the second shaft and a second first coupling position with the second shaft.

Abstract: A part for an aircraft turbojet engine nacelle is made of a composite material and includes at least one outer face (S1), a fibrous preform including fiber locks and having a surface(s) delimiting depressions between fiber locks, a covering material which at least partially covers the surface(s) of the fibrous preform and in particular the depressions, and a matrix which binds entirely the covering material and the fibrous preform. The covering material is a fibrous mat and the outer face (S1) is smooth. A method for manufacturing such a part includes manufacturing the fibrous preform, providing a fibrous mat, depositing the fibrous preform and fibrous mat in a mold, dispersing the matrix between the fibers of the preform and mat and consolidating the fibrous preform and mat.

Abstract: A method for controlling an inverter configured to power electrically a motor including a stator and a rotor capable of being rotated relative to the stator when the motor is electrically powered, the inverter including a plurality of switches suitable for being controlled to open/close in order to regulate the power supply of the motor, each switch having a predetermined transition time from a closed state to an open state, and a predetermined transition time from the open state to the closed state, wherein the method includes the step of not generating the command to open and close the switches when this violates the predetermined transition times from a closed state to an open state, and the predetermined transition times from the open state to the closed state.

Abstract: A device for fabricating a three-dimensional part by selectively melting a powder bed, the device including a first tank for containing a first powder and provided with a first powder dispenser valve, a second tank for containing a second different powder and provided with a second powder dispenser valve, a first and a second monitoring device for monitoring the quantity of first powder delivered by the first valve and the quantity of second powder delivered by the second valve, a mixer chamber in communication with the first and second valves and including a third powder dispenser valve, and a mixer for mixing the powder particles in the chamber, a support for receiving the powder delivered by the third valve and on which the parts is to be fabricated, a powder spreader for spreading powder on the support, and a heater member for locally melting the powder spread on the support.

Abstract: An aircraft undercarriage comprising a shock absorber further comprising first and second portions that are mounted to slide telescopically relative to each other and that can come into internal abutment in the event of the shock absorber being compressed, the undercarriage being fitted with a detector device for detecting the shock absorber coming into internal abutment, which comprises firstly a punch secured to the first portion of the shock absorber or to a portion of the undercarriage that does not slide relative to the first portion of the shock absorber, and secondly a sacrificial piece secured to the second portion of the shock absorber or to a portion of the undercarriage that does not slide relative to the second portion of the shock absorber, the punch and the sacrificial piece being arranged in such a manner that, in the event of the two portions of the shock absorber coming into internal abutment, the punch strikes the sacrificial piece so as to form an indentation therein.

Abstract: A heat exchange and noise reduction panel the panel for an aircraft comprising: an external surface intended to be swept by an airflow and from which fins extend along a first and a second main predetermined direction; cavities forming Helmholtz resonators, linked to the first ends of channels for the passage of air, the second ends of which communicate with said airflow, such that said channels form necks, referred to as Helmholtz resonators, extending substantially along the first direction; and at least one oil flow chamber extending between said external surface and said at least one cavity, and intended to discharge the thermal energy carried by the oil, wherein said channels are formed, at least in part, inside said fins.

Abstract: The invention relates to an inter-turbine casing (1) comprising: an inner shell (10), an outer shell (20), and an assembly of arms (2) extending radially between the timer (10) and outer (20) shells; and an assembly of splitter blades (30) positioned between the arms (2), each splitter blade (30) comprising an inner platform (33) and an outer platform (36). The inner shell (10) comprises at least one inner groove (11) for slidably receiving one or more inter platforms (33). The outer shell (20) comprises at least one outer groove (21) for slidably receiving one or more outer platforms (36). The inter-turbine casing further comprises locking means (4, 5) for locking the splitter blades (30) in the inner (11) and outer (21) grooves. The splitter blades are arranged using multiple tenons (39) that extend in corresponding ribs (12, 22).

Abstract: An aircraft undercarriage having a leg for mounting to move on an aircraft structure between a deployed position and a retracted position is provided. The undercarriage generally includes a brace member arranged between the structure of the aircraft and the leg in order to stabilize the leg in the deployed position, and a drive actuator for moving the leg from the deployed position to the retracted position. The brace member includes a strut arm having a proximal end that is designed to be hinged on the structure of the aircraft. The arm presents a longitudinal slot extending until the slot reaches a distal end in order to terminate in a bend and having slidably engaged therein a finger that is secured to the leg, the drive actuator being coupled to the strut arm.

Abstract: A method for manufacturing a panel includes disposing one or several supports in a respective cavity(ies) in a honeycomb structure having a first skin and a second skin clasping the honeycomb structure. The supports are made of a fugitive material such as a thermoplastic and are auxetic so that, under the effect of an increase in temperature, their dimension between the first and the second skins remains below a predetermined value.

Abstract: A labyrinth seal lip (5) comprises, standing on one of its lateral faces (7), a deflector (13) which channels the flow of gas tangent to the lip (5) towards the facing seal (4) so as to disturb the leakage flow (22) through the gap and decrease the flow rate.

Abstract: The invention relates to an electrical transformer (T, T?) comprising: a primary central winding (11a) extending around an axis (X) and configured to generate a central magnetic flux when a current is passed through it circulating in a first direction around the axis (X), two peripheral primary windings (12a, 13a) extending around the axis (X), between which the central primary winding (11a) is located, and configured to generate peripheral magnetic fluxes when currents are passed through same respectively circulating in a second direction around the axis (X) which is opposite to the first direction, the peripheral magnetic fluxes superimposing on the central magnetic flux, wherein the windings are further configured in such a way that the peripheral magnetic fluxes compensate the central magnetic flux in the regions located beyond the peripheral windings.

Abstract: The invention relates to a planet-carrier (230) cage (234) for a turbomachine speed reducer (110) with a planetary gear set, said cage being designed such that it can contain a central sun wheel (151) with an axis of rotation X and an annular row of planets (150) arranged around the axis X and engaged with said sun wheel, the cage comprising axial receiving elements (280) on the periphery thereof, for receiving axial arms (282) secured to a barrel (242) of said reducer, a substantially radial finger (288) passing through each receiving element and being used to guide the rotation of a ball joint (286) carried by one of said arms, characterised in that each finger comprises means (294, 295) for lubricating said ball joint.

Abstract: An electrical control device including at least one power module which further includes at least one controlled power switch, at least one control card attached to the power module, and electrical connection which connect the control card to the control module. The electrical connection includes at least one pin which is electrically connected and extends from the power module, or, respectively, the control card, and at least one receptacle which is electrically connected and mounted on the control card, or, respectively, the power module, the pin being inserted, at least partially, into the receptacle. The pin and the receptacle is designed to provide an electrical connection between them whilst allowing the pin to be removed from the receptacle.

Abstract: A method for controlling a system for generating electric power for a power distribution network of an aircraft, the system for generating electric power comprising a generator, a rectifier, an inverter which produces a voltage according to several fixed-frequency phases, a DC voltage bus which connects the rectifier to the inverter, the control method comprising: —a correction step to determine at least one correction quantity GC, —a step of determining a signal SO for controlling the inverter from the determined correction quantity GC, —a step of determining a signal SG for controlling the generator from the determined correction quantity GC and —a step of transmitting the control signals SO, SG to the inverter and to the generator, respectively.

Abstract: A system and a method for inspecting components of a turbojet engine using RFID tags and an associated interrogator device. The inspection system includes at least one RFID tag associated with a component of the turbojet engine and an interrogator device arranged so as to be able to communicate with the RFID tag, the interrogator device being equipped with an RFID antenna arranged so as to be able to be inserted into a nacelle compartment of the turbojet engine through an inspection opening intended for the passage of an endoscope probe.

Abstract: A device for regulating the fuel supply flow rate for a turbine engine, comprising at least a pump, an upstream line leading to the pump, a downstream line downstream of the pump, a recirculation duct branched off the downstream line, allowing to collect the fluid in the downstream line and channel it towards the upstream line, a means for regulating the flow rate disposed on the recirculation duct, a phase measurer disposed in the upstream line, a computing unit connected to the phase measurer and to the flow rate regulating means, said computing unit controlling the flow rate regulating means such as to control the degree of opening of said flow rate regulating means, according to the gas content value in the upstream line.

Abstract: Described are examples of a seating arrangement for an aircraft with a first seat in a first accommodation space and a second seat in a second accommodation space, wherein the first and second accommodation spaces are configured to share a common floor space at a floor level of the aircraft. One seating arrangement includes a divider screen located between the first and second accommodation spaces, moveable, by sliding in a direction along the common floor space, between a stowed position permitting passenger egress between the first and second accommodation spaces across the common floor space, and a deployed position preventing passenger egress between the first and second accommodation spaces across the common floor space.

Abstract: An aircraft propulsion assembly, including a turbine engine comprising at least one gas generator configured to generate a main flow, which is supplied by a central jet to at least one power turbine, the central jet being surrounded by an outer fairing, and the power turbine driving, on the periphery thereof, at least one fan rotor. The aircraft propulsion assembly comprises first movable means which are arranged so as to divert at least some of the main flow from the central jet to the outside of the outer fairing and preferably upstream of the turbine engine so as to generate thrust reversal. An aircraft which uses the propulsion assembly, particularly on the rear tip of the fuselage of the aircraft.

Abstract: A mechanical reduction gear for a turbomachine, in particular for an aircraft, this reduction gear including a sun gear having an axis of rotation, a ring gear that extends around the sun gear, planet gears which are meshed with the sun gear and the ring gear, and a lubricating oil distributor which is configured to supply oil to the internal cavities of tubular supports of the planet gears, wherein each of the tubular supports includes a first angular sector including oil conveying pipes and a first outer peripheral surface for forming an oil film, and a second angular sector including a second outer peripheral surface in which a breaking tub of the oil film and recovering of the oil is formed.