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).

A system includes a primary heat exchanger with a first passage connected to a hot fluid source, a second passage connected to the first passage, and a third passage connected to the second passage and an outlet line. A compressor inlet is connected to the outlet line. A secondary heat exchanger is connected to a compressor outlet. First and second turbines are connected to an outlet of the secondary heat exchanger. A first load heat exchanger is connected to the first turbine. A second load heat exchanger is between the second turbine and a system outlet. A first valve connects the hot fluid source to the second and third passages. A second valve connects the first and second passages with the outlet line. A third valve is between the secondary heat exchanger and the second turbine. A fourth valve is between the first load heat exchanger and the system outlet.

An environmental control system includes a first inlet for providing a first medium from a first source, a second inlet for providing a second medium from a second source, distinct from the first source, an outlet for receiving a conditioned form of at least one of the first medium and the second medium, and a compression device including a compressor connected to an electric motor by a first shaft. The compressor is arranged in fluid communication with the first inlet and is only driven by the electric motor. An expansion device including a turbine is rotatable about a second shaft distinct from the first shaft. The turbine is arranged in fluid communication with the second inlet.

Disclosed is a cabin air compressor (CAC) of an aircraft environmental control system, the CAC having: a CAC case defining a forward end and an aft end axially spaced apart axially from the forward end, wherein the forward end defines a compressor inlet; and a supplemental cooling passage defined by the CAC case, wherein the supplemental cooling passage is configured to direct a supplemental cooling medium through it.

A ram air module for use in a ram air system, the ram air module includes a diffuser having a diffuser body including an inlet end and an outlet end, a flow diverter assembly connected to the inlet end of the diffuser body, and a valve connected to the outlet end of the diffuser body.

An environmental control system of an aircraft includes a ram air circuit including a ram air shell having a plurality of heat exchangers positioned therein, the plurality of heat exchangers including a first heat exchanger, a second heat exchanger, and a third heat exchanger. The ram air circuit is configured and arranged so that a first medium received at the first heat exchanger passes through the first heat exchanger and then through the third heat exchanger and so that a second medium received at the second heat exchanger passes through the second heat exchanger. A compressing device is arranged in fluid communication with the ram air circuit.

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.

An aircraft air conditioning system includes a lower cooling zone and an upper cooling zone. The lower cooling zone includes a lower recirculation heat exchanger configured to receive cabin air from a cabin and convert the cabin air into lower cooled recirculated cabin air. The upper cooling zone includes an upper recirculation heat exchange configured to receive the cabin air from the cabin and convert the cabin air into upper cooled recirculated cabin air. A power system selectively delivers power to the lower cooling zone and the upper cooling zone. A controller is in signal communication with the power system. The controller determines a target temperature of the cabin and invokes a recirculation ground maintenance mode that commands the power system to deliver power to one or both of the lower cooling zone and the upper cooling zone so that a temperature of the cabin reaches the target temperature.

The system can include an on-board thermal management subsystem. The system 100 can optionally include an off-board (extravehicular) infrastructure subsystem. The on-board thermal management subsystem can include: a battery pack, one or more fluid loops, and an air manifold. The system 100 can additionally or alternatively include any other suitable components.

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.