The present invention relates to an assembly (20) for an aircraft turbine engine comprising a fan casing (14) having an inner surface (14b), at least one acoustic panel (26) fastened using fastening elements (48, 54) to the inner surface of the fan casing, and at least one circumferential stiffener (40) of the fan casing (14). According to the invention, the fastening elements (48, 54) connect the fan casing (14) to the stiffener (40) incorporated with the acoustic panel (26).

A high efficiency hydrogen fuel system for an aircraft at high altitude which utilizes compressors to compress air to a sufficiently high pressure for the fuel cell. Liquid hydrogen is compressed and then utilized in heat exchangers to cool the compressed air, maintaining the air at a temperature low enough for the fuel cell. The hydrogen is also used to cool the fuel cell as it is also depressurized prior to its entry in the fuel cell cycle. A water condensation system allows for water removal from the airstream to reduce impacts to the atmosphere. The hydrogen fuel system may be used with VTOL aircraft, which may allow them to fly at higher elevations. The hydrogen fuel system may be used with other subsonic and supersonic aircraft, such as with asymmetric wing aircraft.

A process for using an air input of a turboreactor nacelle of an aircraft, comprising an air input lip which comprises at least one fixed portion and at least one portion which can be moved between a first position, in which the air input lip has an aerodynamic profile so as to guide the internal air flow over the internal wall in order to promote a thrust phase, and a second position, in which the portion is displaced in relation to the fixed portion so that the air input lip has a second radial thickness in the second position which is less than the first radial thickness in the first position so as to promote a reverse thrust phase.

The present invention relates to an assembly (20) for an aircraft turbine engine comprising a fan casing (14) having an inner surface (14b), at least one acoustic panel (26) fastened using fastening elements (48, 54) to the inner surface of the fan casing, and at least one circumferential stiffener (40) of the fan casing (14). According to the invention, the fastening elements (48, 54) connect the fan casing (14) to the stiffener (40) incorporated with the acoustic panel (26).

An environmental control system includes an ambient air conduit and a bleed air conduit, an electric compressor connected to the ambient air conduit and a mechanical compressor connected to the electric compressor. The electric compressor is supported for rotation independent of the mechanical compressor. A turbine is operatively connected to the mechanical compressor, the turbine connected to both the ambient air conduit and the bleed air conduit to provide conditioned air to a conditioned air conduit. Computer program products and methods of providing conditioned air to conditioned air loads are also described.

An aircraft provided with a turboshaft engine comprising a gas generator, the gas generator comprising a compression assembly supplying air to a combustion chamber and a turbine assembly supplied with gas by the combustion chamber, the aircraft having a plenum supplying air to the compression assembly. The aircraft comprises a heating system, the heating system comprising a heat exchanger arranged in the plenum, the heating system comprising a fluid supply connection and a fluid discharge connection connected to the heat exchanger, the fluid supply connection conveying hot air from the turboshaft engine into the heat exchanger.

A thrust unit for an aircraft with a hydrogen fuel system. The aircraft may utilize compressors to compress air to a sufficiently high pressure for the fuel cell. Liquid hydrogen is compressed and then utilized in heat exchangers to cool the compressed air, maintaining the air at a temperature low enough for the fuel cell. The thrust unit may be an electrically powered fan unit with a fan within a fan tube. The fan tube may include air inlets for the fuel cell system, as well as outlets for exhaust from the fuel cell system. The fan tube may contain heat exchangers which are part of the fuel cell thermodynamic system.

A hydrogen fuel cell powered electric vertical take-off and landing (eVTOL) aircraft with a high efficiency hydrogen fuel system. The eVTOL aircraft may utilized tilt-up rotors for hover flight, which then transition to a forward facing forward flight configuration. The fuel cell system may use one or more compressors to compress air to a sufficiently high pressure for the fuel cell. Liquid hydrogen may be compressed and then utilized in heat exchangers to cool the compressed air, maintaining the air at a temperature low enough for the fuel cell. The hydrogen may also be used to cool the fuel cell as it is also depressurized prior to its entry in the fuel cell cycle.