AIRCRAFT PROPULSION SYSTEM COMPRISING A DOUBLE FLOW TURBOREACTOR AND A REDUCED SIZE AIR SAMPLING SYSTEM

摘要

The invention relates to a propulsion system (120) for an aircraft comprising an air system (206), said propulsion system (120) comprising: - a fairing (112) having a perforated grid (114), - a turbojet engine double flow (110) with a compression stage (202) and a secondary vein (204), and - an air bleed system (200) having a heat exchanger (208), a hot pipe (250) connected between compression stage (202) and the air system (206), and passing through the heat exchanger (208), and a cold pipe (252) connected between the secondary vein (204) and the perforated grid (114), and passing through the heat exchanger (208). The air sampling system (200) comprises a flap (210) which is arranged at the perforated grid (114) and is moved by a motor (212) between an open position in which the flap (210) n not closing the holes of the perforated grid (114) and a closed position in which the flap (210) closes the holes of the perforated grid (114). The integration of the evacuation and regulation function at the perforated grid (114) saves space, which facilitates the integration of the air sampling system (200) into the propulsion system (120). ).