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.

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.

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 cycle machine for extracting bleed air from a gas turbine engine of an aircraft is provided. The air cycle machine extracts a stream of low pressure bleed air and a stream of high pressure bleed air from a compressor section of the gas turbine engine. The air cycle machine includes a compressor that receives the stream of low pressure bleed air and a turbine that receives the stream of high pressure bleed air. The stream of high pressure bleed air is expanded as it drives the turbine, and the stream of low pressure bleed air is compressed by the compressor. The resulting streams of bleed air are substantially the same pressure, such that they may be merged using a junction into a combined bleed air stream having a temperature and pressure suitable for use by a variety of aircraft accessory systems, such as an environmental control system. The air cycle machine may further power or be powered from an electrical storage device or generator on the fan.

The invention relates to an air conditioning system for a cabin (10) of an aircraft (80) comprising: a bleed air source (12); a ram-air circulation channel (13); a network of pipes and control valves; an air cycle turbine engine comprising at least one compressor (3) and a power turbine (4) which are mechanically connected to one another; and at least one primary cooling exchanger (PHX) which is accommodated in said channel (13), characterized in that said pipe network comprises a thermal power pipe (53) which is suitable for being able to fluidically connect, upon control of at least one control valve (25, 21), said air outlet (4b) of said power turbine (4) and said ram-air circulation channel (13) upstream of said primary exchanger (PHX) so that said bleed air expanded by said power turbine (4) can form a thermal energy source for said ram air being supplied to said primary circuit of said primary exchanger (PHX).

A pressure actuated switching valve includes a first valve chamber including a first chamber portion. The first chamber portion has a first inner diameter, a second chamber portion having a second inner diameter that is greater than the first inner diameter, a third chamber portion having a third inner diameter that is greater than the first inner diameter, a fourth chamber portion having a fourth inner diameter that is greater than first inner diameter, and a valve member. The valve member includes a first section having a first outer diameter that is greater than the first inner diameter. A second section of the valve member has a second outer diameter that is closely matched to the third inner diameter. A third section of the valve member is arranged has a third outer diameter that is greater than the first outer diameter.

A system for cooling a motor operating within an aircraft system includes an enclosure receiving ram air from a first ram air duct and discharging ram air to a second ram air duct to form a cooling path. The second ram air duct is discrete and independent from the second ram air duct. The system can discharge ram air between a heat exchanger and a fan within the second ram air duct that define a reduced or negative pressure region within the second ram air duct.

A gas turbine engine includes a turbomachine, the turbomachine defining a core flow therethrough during operation. A first heat exchange assembly is in fluid communication with the turbomachine for receiving a first bleed flow from the turbomachine. A second heat exchange assembly is in fluid communication with the turbomachine for receiving a second bleed flow from the turbomachine. A first flow outlet is provided for receiving the first bleed flow from the first heat exchange assembly and providing the first bleed flow to a first aircraft flow assembly. A second flow outlet is provided for receiving the second bleed flow and providing the second bleed flow from the second heat exchange assembly to a second aircraft flow assembly.