Abstract: An aircraft propulsion assembly comprising at least a main turbine mounted along a longitudinal axis, at least one main fan arranged upstream of the main turbine along the longitudinal axis and driven in rotation by the said main turbine, the said main fan being ducted by a main fan casing, an auxiliary turbine mounted along the longitudinal axis, the auxiliary turbine being independent of the main turbine, an auxiliary fan of axis offset with respect to the longitudinal axis and driven by the auxiliary turbine, the auxiliary fan being ducted by an auxiliary fan casing, the main casing being separate and distinct from the auxiliary casing so as respectively to generate a main secondary flow and an auxiliary secondary flow which remain independent of one another until they are discharged into the atmosphere.

Abstract: Systems and methods of improved network analytics are disclosed. A system may determine feature propagation in a network of nodes of a graph database. The system may compute, at scale, datasets having complex relationships using graph analysis to determine network effects of entities in a network of entities stored in a graph database. The system may identify entities of interest, which may be associated with a quantitative feature value. The system may compute paths from an entity to the entities of interest, centrality metrics for entities in each of the paths, and path lengths to determine network effects of the entity of interests on the entity. The system may use the computed network effects, taking into account types of relationships between entities in the paths, to determine scaled quantitative feature values for the entity that is subject to the network effects of the entities of interest.

Abstract: A non-faired propeller turbo-engine includes a gas generator and a propulsion unit that is separated from the gas generator by an intermediate housing. The turbo-engine includes a housing and a radially internal ferrule that are coaxial and are connected by hollow radial arms. The housing of the turbo-engine also defines, in part, a gas flow duct of a secondary gas flow. Each radial arm is hollow and is traversed by at least one service of the turbo-engine. Additionally, at least one arm is traversed by a ventilation gas circulation duct from the secondary gas flow and which leads to at least one component from among a power turbine and a mechanical transmission of said propulsion unit.

Abstract: An apparatus and method are provided for supporting vehicle-to-vehicle communication utilizing a base station. Included is a vehicular network interface configured to receive, from a first subset of a set of vehicles, first messages. The vehicular network interface is further configured to receive composite messages that are generated by a base station based on second messages transmitted by a second subset of the set of vehicles. Also included is circuitry in communication with the vehicular network interface. The circuitry is configured to re-create at least a portion of the second messages based on at least a portion of the first messages and at least a portion of the composite messages.

Abstract: Propulsion unit for an aircraft, comprising a turbine, at least one propeller offset with respect to the turbine, and a power transmission disposed between the turbine and the propeller, the transmission comprising in series two constant velocity joints with a slide connection.

Abstract: A turbomachine subassembly has a radially inner shell and a radially outer shell of an annular gas flow path. A radial arm extends radially between the radially inner and outer shells and delimits an isolated volume which is connected to an inner volume of a chamber partly delimited by the radially inner shell. A segment of a conduit extends radially in the isolated volume, and a ventilation air supply source is connected to supply ventilation air to the isolated volume, whereby ventilation air may be supplied to the chamber through the isolated volume. An external radial end of the radial arm supports a first connection box that closes it off. The internal volume of the radial arm communicates with the ventilation air supply source. An external cylindrical wall of the first connection box fits inside an internal cylindrical wall of the external radial end of the radial arm.

Abstract: The present invention relates to an aircraft comprising a fuselage (1), a propulsion unit (7) at the rear tip of the fuselage and at least two engines (3, 5) each driving an engine shaft (32, 52), the propulsion unit including at least one propeller (71, 73) driven mechanically by the engine shafts (32, 52), characterized in that the propulsion unit (7) includes two propellers (71, 73), each of the propellers being driven by a propeller shaft (72, 74), the two propeller shafts being driven by the engine shafts (32, 52) via a first differential epicyclic gear train (40). Specifically, the input of the first differential gear train (40) is connected to the output of a second differential epicyclic gear train (60), the second differential gear train (60) including two inputs (61c2, 62c2), each of said two inputs being connected mechanically to one of said engine shafts (32, 52).

Abstract: A compressed air supply installation for the operation of a pneumatic system includes a compressed air feed, a compressed air connection to a pneumatic unit, a venting connection, a main pneumatic line disposed between the compressed air feed and the compressed air connection, and a first venting line disposed between the compressed air connection and the venting connection, the first venting line including a venting valve including a first venting valve connection, a second venting valve connection, and a control connection pneumatically connected to a control valve by a pneumatic control relay line. The venting valve is closed between the first venting valve connection and the second venting valve connection to the venting connection in a first switching state of the venting valve and is opened between the first venting valve connection and the second venting valve connection to the venting connection in a second switching state.

Abstract: A propulsion unit of an aircraft including a turbine (15), at least one fan (10) with an axis offset relative to the axis of the turbine and a power transmission mechanism between the turbine and the fan. The power transmission mechanism includes a speed reducing gear (20) with an input and a movement output, the input being in the extension of the axis (16) of the turbine and the output connected to the fan.

Abstract: A compressed air supply installation for the operation of a pneumatic system includes a compressed air feed, a compressed air connection to a pneumatic unit, a venting connection, a main pneumatic line disposed between the compressed air feed and the compressed air connection, and a first venting line disposed between the compressed air connection and the venting connection, the first venting line including a venting valve including a first venting valve connection, a second venting valve connection, and a control connection pneumatically connected to a control valve by a pneumatic control relay line. The venting valve is closed between the first venting valve connection and the second venting valve connection to the venting connection in a first switching state of the venting valve and is opened between the first venting valve connection and the second venting valve connection to the venting connection in a second switching state.

Abstract: A turbomachine for an aircraft, comprising a rotor shaft, a turbomachine case, a lubricated bearing chamber, at least one bearing supporting the rotor shaft and being located in the bearing chamber, a lubrication device comprising oil injection means to inject oil into the bearing chamber, and oil supply means to supply oil to said oil injection means, and an electric current generator, comprising an armature driven by the rotor shaft and a field coil fixed to the turbomachine case. The generator has an orifice, which passes longitudinally through the generator from one end to the other, and the oil injection means pass through the orifice so that oil can circulate in the axial direction through the generator.

Abstract: The present invention relates to an aircraft propulsion assembly comprising a turbine (15), at least one fan (10) and a mechanism for transmitting power between the turbine and the fan, characterized in that the power transmission mechanism comprises a speed reducer (20) with a motion input and a motion output, the input being in the continuation of the axis (16) of the turbine and the output connected to the fan.

Abstract: The present invention relates to an aircraft comprising a fuselage (1), a propulsion unit (7) at the rear tip of the fuselage and at least two engines (3, 5) each driving an engine shaft (32, 52), the propulsion unit including at least one propeller (71, 73) driven mechanically by the engine shafts (32, 52), characterised in that the propulsion unit (7) includes two propellers (71, 73), each of the propellers being driven by a propeller shaft (72, 74), the two propeller shafts being driven by the engine shafts (32, 52) via a first differential epicyclic gear train (40). Specifically, the input of the first differential gear train (40) is connected to the output of a second differential epicyclic gear train (60), the second differential gear train (60) including two inputs (61c2, 62c2), each of said two inputs being connected mechanically to one of said engine shafts (32, 52).

Abstract: An aircraft propulsion assembly comprising at least a main turbine mounted along a longitudinal axis, at least one main fan arranged upstream of the main turbine along the longitudinal axis and driven in rotation by the said main turbine, the said main fan being ducted by a main fan casing, an auxiliary turbine mounted along the longitudinal axis, the auxiliary turbine being independent of the main turbine, an auxiliary fan of axis offset with respect to the longitudinal axis and driven by the auxiliary turbine, the auxiliary fan being ducted by an auxiliary fan casing, the main casing being separate and distinct from the auxiliary casing so as respectively to generate a main secondary flow and an auxiliary secondary flow which remain independent of one another until they are discharged into the atmosphere.

Abstract: The present invention relates to a powerplant of an aircraft including at least one twin-spool gas generator of longitudinal axis (XX), at least one main fan arranged upstream of the gas generator on the longitudinal axis (XX) and driven in rotation by the gas generator, the main fan being shrouded with a main fan housing; and at least one auxiliary fan with axis (XY, XY?) offset relative to the longitudinal axis (XX) and driven by the gas generator, the auxiliary fan being shrouded with an auxiliary fan housing, the gas generator including at least one low-pressure compressor and a low-pressure turbine connected by a low-pressure shaft, the low-pressure turbine driving in rotation the main fan and the auxiliary fan via at least one power transmission system including a differential gear system incorporating a bevel gear.

Abstract: The invention proposes a casing (30) of an aircraft turbine (16), intended to support a set of ring sectors (28) which partly delimits a channel for the passage of a gas stream through the turbine (16), where the casing (30) includes means for dynamic adjustment of the radial position of the ring sectors (28) by controlled injection of an air stream on to portions (36) of an annular wall (34) of the casing (30), where the casing (30) includes an upstream radial tab (38) which connects an upstream end of each ring sector (28), in the flow direction of the gas stream, to the casing (30), and a downstream radial tab (40) which connects a downstream end of each ring sector (28) to the casing (30), where both upstream and downstream radial tabs (38, 40) are made from a single piece with the casing (30), characterized in that each radial tab (38, 40) is made as two portions (42, 44) from different materials.

Abstract: A first aspect of the invention relates to an electrocatalytically active nanocomposite material, comprising electrically conductive carbon material decorated with platinum nanoparticles or nanoclusters anchored thereon. The decorated electrically conductive carbon material is overcoated with catecholamine-based polymer. Another aspect of the invention relates to a method for producing electrocatalytically active nanocomposite material.

Abstract: An apparatus and method are provided for supporting vehicle-to-vehicle communication utilizing a base station. Included is a vehicular network interface configured to receive, from a first subset of a set of vehicles, first messages. The vehicular network interface is further configured to receive composite messages that are generated by a base station based on second messages transmitted by a second subset of the set of vehicles. Also included is circuitry in communication with the vehicular network interface. The circuitry is configured to re-create at least a portion of the second messages based on at least a portion of the first messages and at least a portion of the composite messages.

Abstract: The invention relates to a propulsion unit of an aircraft comprising a turbine (15), at least one fan (10) with an axis offset relative to the axis of the turbine and a power transmission mechanism between the turbine and the fan, characterized in that the power transmission mechanism comprises a speed reducing gear (20) with an input and a movement output, the input being in the extension of the axis (16) of the turbine and the output connected to the fan.

Abstract: Propulsion unit for an aircraft, comprising a turbine, at least one propeller offset with respect to the turbine, and a power transmission disposed between the turbine and the propeller, the transmission comprising in series two constant velocity joints with a slide connection.