The invention relates to an air system for an aircraft, that includes air consumers; air sources and a network of ducts and associated control valves controlled by a control unit. The air system is characterized in that: the network of ducts and associated valves includes at least one isolation valve, arranged between an air bleed device and an air duct connecting an air conditioning pack and an auxiliary power unit; the control unit is configured to be able to determine an ideal configuration of the control valves according to the identified requirements of each consumer and a degraded configuration that makes it possible to supply air to predetermined air consumers from the available air sources when the ideal configuration is not attainable.

The invention relates to an air conditioning system for an aircraft cabin, comprising two motorized turbomachines (16a, 16b) each comprising a compressor (14a, 14b) supplying an outlet (24) common to the compressors and a turbine, one of the turbines, referred to as water extraction turbine (16a), being dedicated to a water extraction loop (28) and the other turbine, called cooling turbine (16b), helping cool the air.

The air conditioning system comprises a network of pipes and associated valves, connected to the common outlet (24) of the compressors and making it possible to supply, from the common outlet of the compressors: either the inlet (160) of the water extraction turbine (16a), or the inlet (164) of the cooling turbine (16b), bypassing the turbine (16a) and the water extraction loop, or an outlet (60) of the air conditioning system directly, bypassing the cooling turbine (16b) and the water extraction turbine (16a).

Air conditioning system of an aircraft, comprising a thermal management system supplied with air, referred to as pressurized air (12), by at least one compressor (14) of the aircraft, and supplied with non-pressurized flow air (206; 208) from at least one engine of the aircraft, and characterized in that the thermal management system comprises: at least one pressurized-air/oil heat exchanger (20) designed to provide heat exchanges between a stream of pressurized air (12) and a first oil circuit (26), allowing heat to be transferred from the pressurized air (12) to the oil of the first oil circuit (26); at least one oil/flow-air heat exchanger (22a, 22b, 22c, 22d) designed to provide heat exchanges between a second oil circuit (28) and the flow air (206; 208), allowing the heat from said second oil circuit (26) to be transferred to the flow air (206; 208); and at least one circuit (30) connecting the first oil circuit (26) and said second oil circuit (28).

Environmental control systems, airflow interleavers, and methods. The environmental control systems include an airflow interleaver and mix manifold comprising a mixing chamber. The airflow interleaver comprises a first airflow guide structure configured to guide a second airflow towards a central axis of the mixing chamber and a second airflow guide structure configured to guide a first airflow away from the central axis. The methods include channeling first and second airflows to the mix manifold, mixing the first and second airflows, which includes guiding the first airflow away from the central axis and guiding the second airflow towards the central axis. The airflow interleavers include a tubular body, and a plurality of converging airflow guides and a plurality of diverging airflow guides extending from the tubular body and collectively being configured to interleave first airflow streams flowing from the tubular body with second airflow streams flowing external to the tubular body.

Compressor valves for aircraft are described herein. An example valve for a compressor includes a first end plate, a second end plate, and a first sleeve valve disposed between the first and second end plates. The first the first sleeve valve is operable between a closed state and an open state. The example valve also includes a second sleeve valve disposed between the first and second end plates and within the first sleeve valve such that a plenum is formed between the first end plate, the second end plate, the first sleeve valve, and the second sleeve valve. The plenum is to receive outlet air from an outlet of the compressor. A passageway is formed through a center of the valve to be fluidly coupled to an inlet of the compressor. The second sleeve valve is operable between a closed state and an open state.

An environmental control system of an aircraft includes a plurality of inlets for receiving a first medium, a second medium, and a third medium and an outlet for delivering a conditioned form of the first medium to at least one load of the aircraft. A compression device is arranged in fluid communication with the plurality of inlets and the outlet. The compression device includes a plurality of turbines including a first turbine and a second turbine configured to provide energy by expanding one or more mediums of the plurality of mediums and a compressor configured to receive energy from the one or more mediums expanded across at least one of the plurality of turbines. Energy derived from the second medium and/or the third medium within the second turbine is used to compress the first medium at the compressor.

An environmental control system (ECS) for use with a gas turbine engine has an air cycle system (ACS) and a vapor cycle system (VCS). The VCS has along a vapor compression flowpath: a VCS compressor; a heat donor leg of a VCS condenser; an expansion device; and a heat receiving leg of a VCS evaporator. The ACS has along a bleed flowpath: a bleed air inlet; a primary heat exchanger; an ACS compressor; a secondary heat exchanger; a turbine coupled to the ACS compressor to drive the ACS compressor; a heat donor leg of the VCS evaporator; a water collector; and a heat receiving leg of the VCS condenser.

A method of operating an environmental control system of an aircraft includes providing a first medium to the environmental control system including a compressor and a turbine, wherein the first medium is provided to the compressor and the turbine sequentially and extracting work from a second medium provided to a power turbine operably coupled to the compressor to drive the compressor. In a first mode of operation, the first medium to be provided to a downstream load is output from the turbine, in a second mode of operation, at least a portion of the first medium to be provided to a downstream load bypasses the turbine, and in a third mode of operation, at least a portion of the first medium output from the compressor is provided to the power turbine.

A multi-engine aircraft includes a first engine drivingly engaged to a common rotatable load and a second engine drivingly engaged to the common rotatable load, the second engine having a bleed air system and a control system in communication with a compressed air switching system. The control system controls operation of the second engine and/or the compressed air switching system. The compressed air switching system includes a switching valve that is displaceable between at least a first position and a second position, the first position interconnecting a lower pressure inlet and a switch outlet, and the second position interconnecting a high pressure inlet and the switch outlet. The switch outlet is in communication with the bleed air system of the second engine. The control system actuates the switching valve to switch between the first and second positions.

A system and method include a seat assembly including a seat duct fluidly coupled to one or more air outlets. An air delivery manifold is underneath the seat assembly. The air delivery manifold includes a first outlet port. The seat duct is fluidly coupled to the first outlet port. Air is delivered to the one or more air outlets via the air delivery manifold.