Abstract: A process for manufacturing a part provided with a lubricating surface coating (10), in which: a composition is prepared that includes at least one precursor having at least one organic group, the composition is deposited on the part, a heat treatment is carried out, wherein the heat treatment of the coating is carried out at a temperature above 220° C., so as to form a lubricating surface coating (10) formed of an at least partially inorganic solid network incorporating solid carbon in at least one lubricating allotropic form in the dispersed state and trapped within the solid network. A part, such as a foil of a foil bearing (1) obtained by the process, a turbomachine, such as a turbomachine for a fuel cell, including such a part, and an aircraft cabin air-conditioning system including at least one such turbomachine are also described.

Abstract: A method for producing a corrugated foil bearing stiffener involves starting with an austenitic nickel superalloy sheet (15) having an elasticity limit higher than 500 MPa, and subjecting the sheet (15) to at least one step of press bending plastic deformation of the entire thickness of same with a deformation energy higher than 10 kJ in a time shorter than 10?5 s in such a way as to create corrugations.

Abstract: The manufacturing method notably includes a step (110) for sintering steel powder (10), the chemical composition of which includes, in mass percent, 2.3% of carbon, 4.2% of chromium, 7% of molybdenum, 6.5% of tungsten, 10.5% of cobalt and 6.5% of vanadium, so as to obtain a sintered steel (12) and shaping of the sintered steel (12), for forming a bearing ring (18).

Abstract: A bent heat exchange device includes a heat-conducting outer plate, an inner plate, a partition separating an upstream area (23) and a downstream area (24), a fluid inlet, a fluid outlet, a flow guide (27) in the upstream area, a flow guide in the downstream area, the partition being mechanically secured to the inner plate and to the outer plate and including, between the upstream area (23) and the downstream area (24), a sealed partition (29) and a slatted partition (30) having openings for the flow of a heat transfer fluid.

Abstract: An aircraft air conditioning system, powered solely using electrical energy, to draw bleed air from outside the aircraft and deliver conditioned air to the aircraft's interior, includes at most three motorized rotary machines, which include: independent first and second motorized turbocompressors, each turbocompressor includes a turbine compressor and an electric motor; and a motor compressor interconnected between the turbocompressors via an interconnection pipe. The motor compressor: generates a primary air flow, which drives a secondary air flow, allowing a breathing air flow to be cooled in a first operation phase, corresponding to a ground operation or at relatively low altitude and relatively low aircraft speed; be at shutdown or at low idle in a second phase of operation at relatively low altitude and relatively high aircraft speed; and, provide a top up breathing air flow in a third phase of operation at relatively high altitude and relatively high aircraft speed.

Abstract: This rotor assembly for a turbine engine includes: a solid permanent magnet (6) press-fitted inside a band (4) made of a non-magnetic material, a first shaft (2) having at least one bearing (12) intended for engaging with a support bearing so as to form a gas bearing and ensure rotational guidance of the first shaft (2), the band (4) forming an integral assembly with the first shaft (2) in the extension thereof, and a second shaft (8) having at least one bearing (14) intended for engaging with a support bearing so as to form a gas bearing and ensure rotational guidance of the second shaft (8) extending from the band (4) opposite the first shaft (2), coaxially with the first shaft (2) such that the first shaft (2), the band (4), and the second shaft (8) form an integral assembly. Turbine engine with such rotor assembly.

Abstract: An aircraft air conditioning system, powered solely using electrical energy, to draw bleed air from outside the aircraft and deliver conditioned air to the aircraft's interior, includes at most three motorized rotary machines, which include: independent first and second motorized turbocompressors, each turbocompressor includes a turbine compressor and an electric motor; and a motor compressor interconnected between the turbocompressors via an interconnection pipe. The motor compressor: generates a primary air flow, which drives a secondary air flow, allowing a breathing air flow to be cooled in a first operation phase, corresponding to a ground operation or at relatively low altitude and relatively low aircraft speed; be at shutdown or at low idle in a second phase of operation at relatively low altitude and relatively high aircraft speed; and, provide a top up breathing air flow in a third phase of operation at relatively high altitude and relatively high aircraft speed.

Abstract: A compression device includes at least: two interleaved scrolls each of which is made of an aluminum alloy, one of the scrolls, being a fixed scroll (3), and is fixed and the other scroll, which is an orbiting scroll and moves eccentrically without rotating. Also included are anti-rotation means made of an aluminum alloy and configured to allow anti-rotation of the orbiting scroll. The compression device also includes one flat thrust bearing configured to axially contain the orbiting scroll and is made of aluminum alloys or grades of cast iron. The compression device also includes coatings for promoting friction between the fixed scroll, the orbiting scroll, the anti-rotation means and the flat thrust bearing.

Abstract: This aerodynamic foil bearing has a sleeve (4) inside which are arranged: a foil referred to as the top foil (16), and a bump foil (14) arranged between the top foil (16) and the sleeve (4), a foil (12) of viscoelastic material arranged between an inner face of the sleeve (4) and the bump foil (14).

Abstract: High temperature use of a self lubricating coating material in a foil bearing and part coated with such a material. A material according to the disclosure includes between 50 and 90 wt % of alumina (Al2O3), as well as an oxide selected from the group consisting of titanium oxide (TiO2), chromium oxide (Cr2O3), and a mixture of these. Application to a rotor and/or a thrust disc at least partially covered with such a material.

Abstract: This aerodynamic foil bearing has a sleeve (4) inside which are arranged: a foil referred to as the top foil (16), and a bump foil (14) arranged between the top foil (16) and the sleeve (4), a foil (12) of viscoelastic material arranged between an inner face of the sleeve (4) and the bump foil (14).

Abstract: A mixing pump (2) according to the invention comprises: an air duct, referred to as a cool air duct; an air intake (10), referred to as a hot air intake, leading to the cool air duct; as well as means for injecting air from the hot air intake (10) into the cool air duct. The hot air intake (10) leads to a chamber (16) arranged at least partially in the cool air duct. The injection means have at least one opening (30) for connecting the interior of the chamber (16) to the interior of the cool air duct, and means (12) for modifying the flow area through the at least one opening connecting the interior of the chamber (16) to the interior of the cool air duct.

Abstract: A body panel (1) for a transport vehicle—in particular for an aircraft—includes a supporting plate (2) and a heat-exchange device (6), the supporting plate forming (2) on the outer face (4) thereof facing the exchanger (6) an indentation (10) extending in the body of the supporting plate (2) holding the heat-exchange device (6) such that the heat-exchange device (6) does not extend beyond the general profile of the body of the transport vehicle.

Abstract: The aerodynamic foil bearing in the form of a radial or axial thrust bearing, includes a rotor and a stator including a support designed to support, facing the rotor, a lift device including: a plurality of evenly distributed elastic foils fixed by a fixing edge to a surface of the lift device facing the rotor; rows of ventilation orifices passing through the lift device and opening between a free edge of each elastic foil and the fixing edge of the next foil, wherein the support includes a cavity having grooves extending under the rows of ventilation orifices and at least one circular groove intersecting the grooves and supplied with a stream of pressurized cooling gas to distribute same so as to cool the underside of each foil and provide a supply of fresh gas above the next foil to compensate for gas losses at the ends of the bearing.

Abstract: A method for producing a corrugated foil bearing stiffener involves starting with an austenitic nickel superalloy sheet (15) having an elasticity limit higher than 500 MPa, and subjecting the sheet (15) to at least one step of press bending plastic deformation of the entire thickness of same with a deformation energy higher than 10 kJ in a time shorter than 10?5 s in such a way as to create corrugations.

Abstract: A body panel (1) for a transport vehicle—in particular for an aircraft—includes a supporting plate (2) and a heat-exchange device (6), the supporting plate forming (2) on the outer face (4) thereof facing the exchanger (6) an indentation (10) extending in the body of the supporting plate (2) holding the heat-exchange device (6) such that the heat-exchange device (6) does not extend beyond the general profile of the body of the transport vehicle.

Abstract: Energy management on board an aircraft includes: a plurality of thermal and electrical energy sources, a plurality of loads which are capable of being supplied with power by the various energy sources, among which at least one load is capable of being supplied with power by an electrical energy source and by a thermal energy source, and real-time management means for energy transfers from the various energy sources to the various loads as a function of the present and future energy requirement of the various loads and the present and future availability of the various sources, with the management means providing a permanent and standardized correlation between thermal and electrical energies.

Abstract: The invention relates to a device having a polyphase electrical machine, wherein a plurality of inverters (36, 37, 38), which are controlled by an interlaced control modulated by pulse width to an identical cutoff frequency, provide, on the phase outputs thereof, an alternating voltage signal having an identical fundamental frequency, amplitude and phase to an electrical machine (2) that comprises at least two separate so-called star windings (33, 34, 35), each star winding being supplied by a related inverter, each phase output of which is connected to a phase circuit that includes the phase winding of the star winding, the device being characterized in that each phase circuit for a star winding has a negative mutual inductance with the homologous phase circuit of another star winding.

Abstract: Energy management on board an aircraft includes: a plurality of thermal and electrical energy sources, a plurality of loads which are capable of being supplied with power by the various energy sources, among which at least one load is capable of being supplied with power by an electrical energy source and by a thermal energy source, and real-time management means for energy transfers from the various energy sources to the various loads as a function of the present and future energy requirement of the various loads and the present and future availability of the various sources, with the management means providing a permanent and standardized correlation between thermal and electrical energies.

Abstract: Described is an anti-condensation method for an aircraft (13), wherein part of a stream of cold air is withdrawn, the part of a stream of cold air is heated, and the part of the stream of hot air is introduced into the crown (19) of the aircraft (13) through an air introduction duct (8). Also described is an anti-condensation device called “Air Dryer System”.