A duct is provided and includes a tubular member having an inlet portion, an outlet portion and a central portion interposed between the inlet and outlet portions and a tributary tubular member fluidly coupled to the tubular member at the central portion. The tributary tubular member includes first and second torus sectors defining first and second apertures, respectively, through which an upstream end of the central portion extends. The second torus sector is disposed within the first torus sector to define a sectioned toroidal annulus about the first and second apertures and between an exterior surface of the second torus sector and an interior surface of the first torus sector.

A duct is provided and includes a tubular member having an inlet portion, an outlet portion and a central portion interposed between the inlet and outlet portions and a tributary tubular member fluidly coupled to the tubular member at the central portion. The tributary tubular member includes first and second torus sectors defining first and second apertures, respectively, through which an upstream end of the central portion extends. The second torus sector is disposed within the first torus sector to define a sectioned toroidal annulus about the first and second apertures and between an exterior surface of the second torus sector and an interior surface of the first torus sector.

The invention relates to a module (23) for recovery of energy of an aircraft cabin (5) comprising at least one air outlet (16) from the cabin and at least one fresh air inlet (15) into the cabin, the said module comprising: a turbine engine (30) comprising a compressor (31) and a turbine (32) mechanically coupled to one another; a cabin-air recovery duct (42) designed to be able to link the air outlet (16) from the cabin and the said turbine (32); a cabin-air injection duct (41) designed to be able to link the compressor (31) and fresh air inlet (15) into the cabin; an emergency duct (43) designed to be able to link a high-pressure air source and the said turbine (32); a control unit (25) configured to be able, according to predetermined operational conditions, to activate either a routine mode, in which the said turbine (32) is exclusively supplied by the air evacuated from the cabin (5), or an emergency mode, in which the said turbine (32) is exclusively supplied by the air provided by the high-pressure air source.

The invention relates to a module (23) for recovery of energy of an aircraft cabin (5) comprising at least one air outlet (16) from the cabin and at least one fresh air inlet (15) into the cabin, the said module comprising: a turbine engine (30) comprising a compressor (31) and a turbine (32) mechanically coupled to one another; a cabin-air recovery duct (42) designed to be able to link the air outlet (16) from the cabin and the said turbine (32); a cabin-air injection duct (41) designed to be able to link the compressor (31) and fresh air inlet (15) into the cabin; an emergency duct (43) designed to be able to link a high-pressure air source and the said turbine (32); a control unit (25) configured to be able, according to predetermined operational conditions, to activate either a routine mode, in which the said turbine (32) is exclusively supplied by the air evacuated from the cabin (5), or an emergency mode, in which the said turbine (32) is exclusively supplied by the air provided by the high-pressure air source.

A method for managing the offtake of power produced by an auxiliary power unit of an aircraft. The method comprises a step of calculating a maximum capacity for offtake of mechanical power that the auxiliary power unit can provide to the aircraft, a step of determining an actual offtake of mechanical power taken off by a first mechanical power offtake system of the auxiliary power unit, a step of comparing the maximum capacity for offtake of mechanical power and the actual offtake of mechanical power, a step of optimizing the offtake of mechanical power which step, based on the comparison of the maximum capacity for offtake of mechanical power and the actual offtake of mechanical power, determines at least one corrective action. A device for managing the offtake of power produced by an auxiliary power unit of an aircraft and an aircraft including such a device are provided.

A method and system for controlling fresh air flow into a controlled environment are disclosed herein. The method comprises: measuring, using a sensor, a predetermined property in the controlled environment; estimating, by a controller, a number of people inside the controlled environment based on the measured property, and setting, by the controller, a rate of fresh air flow to the controlled environment based at least in part on the estimated number of people inside the controlled environment.

A method and system for controlling fresh air flow into a controlled environment are disclosed herein. The method comprises: measuring, using a sensor, a predetermined property in the controlled environment; estimating, by a controller, a number of people inside the controlled environment based on the measured property, and setting, by the controller, a rate of fresh air flow to the controlled environment based at least in part on the estimated number of people inside the controlled environment.

An air handling system for distributing airflow in a vehicle is disclosed and includes a passenger compartment configured to contain one or more occupants, a cargo compartment, and a flow regulating valve configured to actuate into a commanded position to apportion airflow between the passenger and cargo compartments. The air handling system also includes one or more processors in electronic communication with the flow regulating valve and a memory coupled to the one or more processors. The memory stores data comprising a database and program code that, when executed by the one or more processors, causes the air handling system to receive one or more signals indicating a total available airflow rate available to the vehicle and a system configuration. The one or more processors instruct the flow regulating valve to actuate into a commanded position. The commanded position is calculated based on at least a target cargo airflow rate.

An air handling system for distributing airflow in a vehicle is disclosed and includes a passenger compartment configured to contain one or more occupants, a cargo compartment, and a flow regulating valve configured to actuate into a commanded position to apportion airflow between the passenger and cargo compartments. The air handling system also includes one or more processors in electronic communication with the flow regulating valve and a memory coupled to the one or more processors. The memory stores data comprising a database and program code that, when executed by the one or more processors, causes the air handling system to receive one or more signals indicating a total available airflow rate available to the vehicle and a system configuration. The one or more processors instruct the flow regulating valve to actuate into a commanded position. The commanded position is calculated based on at least a target cargo airflow rate.

An air intake system comprising an air duct suitable for providing airflow to the inside of an aircraft, preferably to an auxiliary power unit; an inlet arranged at one end of the air duct; a skin surrounding the inlet; a plurality of slots arranged on the skin; a driving arrangement, a flap door connected to the driving arrangement, and a plurality of fins connected to the driving means. The driving arrangement is configured for moving the flap door between at least two positions, the positions being a closed position wherein the flap door closes the inlet, and an opened position wherein the flap door is driven away from the closed position. The driving arrangement is also configured for moving the plurality of fins such that the plurality of fins protrudes through the slots.