Abstract: A cool air supply system includes a cool air inlet to a cabin of an aircraft fed with air cooled in a heat exchanger swept by a flow of external air from a static air inlet of the aircraft. The system further includes an ejector assembly for circulating external air in the exchanger. The ejector assembly includes a nozzle fed with air from the cabin of the aircraft via a cabin air outlet.

Abstract: In accordance with this method, air bled from the engine is compressed in a turbocompressor (4) and the air compressed in this way is cooled in an exchanger (3) through which is passed air outside the aircraft, a turbine (5) of the turbocompressor (4) is fed with the air cooled in this way, and the cool air inlet (10) of the cabin is fed with the air leaving the turbine (5). In accordance with the invention, mechanical energy is extracted from the air leaving the cabin (11) of the aircraft and that mechanical energy is injected into the turbocompressor (4). Cooling energy is also extracted from the air leaving the cabin (11) and that cooling energy is injected into the air which is fed to the turbine (5).

Abstract: The cool air inlet is fed with air cooled in a heat exchanger swept by a flow of external air from a static air inlet of the aircraft. The system further includes ejector means for circulating external air in the exchanger. The ejector means include a nozzle fed with air from a cabin of the aircraft via a cabin air outlet.

Abstract: A leading edge member of an airfoil of an aircraft has an outside wall defining a wing span and a deicing device for circulating hot air in the direction of the wing span of the airfoil. The device includes a hot air distribution duct extending inside the leading edge member in the direction of the span of the foil. The duct has a plurality of orifices distributed over at least part of its length. A hot air supply communicates with one end of the distribution duct. The hot air supply is connected by ducts located outside the leading edge member to at least one propulsion engine of the aircraft.

Abstract: A leading edge member of an airfoil of an aircraft has an outside wall and a de-icing device of the type for circulating hot air in the direction of the span of said airfoil.