Airbus Operations (s.a.s.)

Airbus (sas)

Airbus Operations Sl

Airbus Operations Gmbh

Thomas Stevens

Adeline Soulie

Julien Cayssials

Didier Poirier

Juan Tomas Prieto Padilla

Diego Barron Vega

Bruno Medda

Pierre-Alain Pinault

Esteban Martino-Gonzalez

Alain Porte

Esteban Martino González

Cyril Bonnaud

Matthieu Fargues

Olivier Barbara

Stéphane Dostes

Frédéric Roche

An aircraft propulsion system, including a turbojet and a heat exchanger system including a main heat exchanger, a hot air supply pipe and regulating valve, a high pressure pipe bleeding high pressure stage hot air through a first valve, an intermediate pressure pipe bleeding intermediate pressure stage hot air through a second valve, a pipe transferring hot air to an air management system, a main supply pipe supplying fan duct cold air including a main regulating valve, an evacuation pipe expelling air to the outside, a sub heat exchanger, wherein the supply pipe from the regulating valve goes through the sub heat exchanger, a sub supply pipe supplying cold air from the main supply pipe, a sub evacuation pipe expelling air to the fan duct, a temperature sensor measuring hot air temperature exiting the main heat exchanger, and a controller controlling the valves according to the measured temperature.

Aircraft propulsion system including a heat exchanger system

An aircraft propulsion system including a turbojet and heat exchanger system including a heat exchanger. A supply connection and evacuation connection are forward, and aft are a transfer connection and a scoop connection, a supply pipe connected to the supply connection, and which bleeds hot air from the compression stages. A transfer pipe connected to the transfer connection transfers hot air to an air management system. A scoop connected to a scoop connection bleeds cold air from a fan duct and an evacuation pipe, including an inlet connected to the evacuation connection and an outlet, which emerges on the outside, where hot air through the heat exchanger from the supply pipe to the transfer pipe passes along a first transfer direction and cold air passes through the heat exchanger from each scoop to the inlet along a second transfer direction parallel to the first transfer direction in the opposite direction.

An aircraft propulsion system, including a turbojet and a heat exchanger system which includes a main heat exchanger, a hot air supply pipe, a transfer pipe transferring hot air to an air management system, a main supply pipe supplying cold air from the fan duct, an evacuation pipe expelling air to the outside, a sub heat exchanger with a high pressure pipe going therethrough, a sub supply pipe supplying cold air and including a sub regulating valve, a sub evacuation pipe expelling air, a temperature sensor, and a controller controlling the system according to the temperature measured The sub regulating valve comprises a door articulated between closed and open positions, a return spring constraining the door in the open position, and a realizing system, controlled by the controller, mobile between a blocking position and a realizing position in which the door is released to move to the open position.

An aircraft nacelle includes an outside wall (), at least one air system with at least one air intake (), whereby the nacelle is connected by connecting element to a mast that is itself connected to the aircraft, with the connecting element allowing a relative movement between the nacelle and the mast in the longitudinal direction of the nacelle, whereby at the front of the junction zone with the nacelle, the mast includes an aerodynamic surface that is called a fairing () that covers and exposes a zone of the outside wall called an overlapping zone () based on the position of the nacelle () relative to the mast, characterized in that an air intake () for an air system is arranged at the overlapping zone ().

Nacelle comprising an air entrance in a cap

An aircraft with an outer surface from which flows an aerodynamic stream of cold air and includes at least one hot gas outlet, characterized in that it includes at least one device () for generating aerodynamic disturbances so as to mix hot gas and cold air, whereby the at least one device is connected to an outer surface () for protection against the heat and/or close to a hot gas outlet ().

Device for generating aerodynamic disturbances so as to protect the outer surface of an aircraft against elevated temperatures

Growing community of inventors

Tournefeuille, France

Thomas Stevens