Abstract: An air management system with a set of compressed air sources for selectively supplying pressurized air to air consumer equipment according to an aircraft operation condition. Low pressure air, high pressure air, or a combination thereof may perform such supplying of compressed air depending on the aircraft operation condition.

Abstract: An aircraft heat exchanger arranged longitudinally and including a casing with an inner chamber configured so that coolant flows longitudinally from an inlet to an outlet, a plurality of laterally spaced longitudinally extending inner chamber plates, and a plurality of channels defined between contiguous plates. Each plate includes a leading edge oriented towards the inlet and configured to divert coolant towards the channels. A plurality of the plates include an inner hollow area configured to conduct a flow of hot bleed air therethrough. Leading edges of a first group of plates are arranged in a stepped pattern. A gap defined between the first group of plates and a first casing lateral wall establishes a fluid coolant communication through the first group of plates between the casing inlet and outlet. The lateral distance between each leading edge of the first group of plates and the first lateral wall decreases longitudinally.

Abstract: An aircraft installation of a pneumatic system of an aircraft with different compressed air sources for supplying pressurized air to air consumer equipment. Either an air bleed system, electrical compressors, or a combination thereof may perform such supplying of compressed air depending on the aircraft operation condition, for instance the flight altitude or specific flight phases. Also, a turbofan engine, and a method for supplying compressed air to air consumer equipment are disclosed.

Abstract: 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.

Abstract: An air management system with a set of compressed air sources for selectively supplying pressurized air to air consumer equipment according to an aircraft operation condition. Low pressure air, high pressure air, or a combination thereof may perform such supplying of compressed air depending on the aircraft operation condition.

Abstract: 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.

Abstract: 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.

Abstract: An aircraft installation of a pneumatic system of an aircraft with different compressed air sources for supplying pressurized air to air consumer equipment. Either an air bleed system, electrical compressors, or a combination thereof may perform such supplying of compressed air depending on the aircraft operation condition, for instance the flight altitude or specific flight phases. Also, a turbofan engine, and a method for supplying compressed air to air consumer equipment are disclosed.

Abstract: 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.

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

Abstract: 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.

Abstract: 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.