Abstract: An environmental control system includes an environmental control system pack having a trim outlet and a primary outlet. A trim medium is output from the trim outlet and a first medium is output from the primary outlet. An inlet of a mixing manifold is connected to the primary outlet of the at least one environmental control system pack. A trim heat exchanger is connected to the trim outlet and the at least one inlet of the environmental control system pack. Within the trim heat exchanger, the trim medium is arranged in a heat exchange relationship with a second medium. From the trim heat exchanger, the second medium is provided to an inlet of the least one environmental control system pack and the trim medium is mixed with a flow output from an outlet of the mixing manifold.

Abstract: An environmental control system of an aircraft including a compression device including a compressor having a compressor inlet and a compressor outlet, a primary inlet for supplying a first medium to the compressor inlet, and a secondary inlet for supplying a second medium to the compressor inlet.

Abstract: An air cycle machine is provided. The air cycle machine can be included an environmental control system of an aircraft. The air cycle machine can include a turbine comprising a plurality of inlet gas flow paths, a compressor driven by the turbine from a shaft, and a fan driven by the turbine from the shaft.

Abstract: An airplane is provided. The airplane includes a pressurized medium, a turbine, and a valve. The turbine includes at least one nozzle. The valve is located upstream of the turbine. The valve provides the pressurized medium to the at least one nozzle of the turbine according to an operational mode.

Abstract: An environmental control system of a vehicle includes a first compression device including a compressor, a first turbine, and a power turbine operably coupled by a shaft. The first turbine is configured to receive a first medium, the compressor is configured to receive a second medium, and the power turbine is configured to receive a third medium. A second compression device, separate from the first compression device, includes a second turbine. The environmental control system is operable in a first mode and a second mode. In the first mode, the second medium is provided to the compressor and the second turbine sequentially. In the second mode, the second medium bypasses the second turbine. In in both the first mode and the second mode, only the second medium is provided to an outlet of the environmental control system.

Abstract: An environmental control system includes a compression device including a compressor, a turbine, and an electric motor operably coupled by a shaft. The electric motor and the turbine are arranged in series relative to a flow of a first medium.

Abstract: A system is provided. The system includes an inlet providing a first medium; an inlet providing a second medium; a compressing device including a compressor and a turbine; and at least one heat exchanger located downstream of the compressor. The compressing device is in communication with the inlet providing the first medium. The turbine is downstream of the compressor. An outlet of the at least one heat exchanger is in fluid communication with an inlet of the compressor and an inlet of the turbine.

Abstract: 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.

Abstract: A system of an aircraft includes an inlet arranged in fluid communication with a bleed air source such that the inlet is configured to receive a flow of bleed air. A compressing device includes a compressor having a compressor inlet fluidly connected to the inlet. A heat exchanger is fluidly coupled to an outlet of the compressor. The heat exchanger includes a first pass and a second pass, both of which are located downstream from the compressor. An outlet of the first pass is directly connected to an inlet of the second pass via a first conduit. The outlet of the first pass is also fluidly connected to an inlet of the compressor via a second conduit such that a portion of the bleed air output from the first pass is returned to the compressor inlet via the second conduit.

Abstract: An aircraft is provided. The aircraft includes a pressurized volume and an air conditioning system. The air conditioning system operates in a first mode when the aircraft is performing high altitude operations and a second mode when the aircraft is performing low altitude operations. The first mode includes when a first medium, a second medium, and a third medium are mixed by the air conditioning system to produce a chamber ready medium. The second mode comprises when only the first medium and the second medium are mixed by the air conditioning system to produce the chamber ready medium. The air conditioning system provides the chamber ready medium to the pressurized volume.

Abstract: 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 and extracting work from a second medium provided to a second turbine operably coupled to the compressor to drive the compressor. The first medium is provided to the compressor and the turbine sequentially. In a first mode of operation, the first medium to be provided to a downstream load is output from the turbine and in a second mode of operation, at least a portion of the first medium to be provided to the downstream load bypasses the turbine.

Abstract: An environmental control system includes a plurality of inlets for receiving a plurality of mediums including a first medium and a second medium and an outlet for delivering a conditioned flow of the second medium to one or more loads of the aircraft. A ram air circuit includes a ram air shell having at least one heat exchanger positioned therein and a compressing device is arranged in fluid communication with the ram air circuit and the outlet. The compressing device includes a compressor and at least one turbine operably coupled via a shaft. The environmental control system is operable in a first mode and a second mode. In the second mode, a pressure of the second medium output from the compressor is equal to the pressure of the second medium provided to the outlet.

Abstract: An environmental control system of an aircraft includes a compressing device including a compressor and a turbine configured to receive a flow of first medium sequentially and a second turbine arranged in fluid communication with an outlet of the compressor. The second turbine is configured to receive a flow of second medium distinct from the first medium. A dehumidification system is arranged in fluid communication with the turbine, a first bypass valve is configured to divert at least a portion of the flow of the first medium output from the compressor around the turbine, and a second bypass valve configured to divert at least a portion of the flow of first medium output from the compressor to the second turbine.

Abstract: 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.

Abstract: 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.

Abstract: An environmental control system of an aircraft includes a compressing device including a compressor and a turbine configured to receive a flow of first medium sequentially. The compressing device additionally includes a second turbine configured to receive a flow of second medium distinct from the first medium. A dehumidification system is arranged in fluid communication with the turbine and a bypass valve is configured to divert the flow of the first medium output from the compressor around the turbine.

Abstract: An airplane is provided. The airplane includes a pack. The pack includes a shaft, a compressor, and a turbine coupled to the compressor via the shaft. The turbine receives and expands a first medium to provide power to the compressor via the shaft. The compressor receives and compresses a second medium in accordance with the power provided by the turbine via the shaft. The turbine is fluidly coupled to a heat exchanger of an air conditioning system.

Abstract: An environmental control system of an aircraft includes a ram air circuit including a ram air shell having at least one heat exchanger positioned therein and a divider arranged within the ram air shell to separate the ram air shell into a first region and a second region. The at least one heat exchanger is arranged within both the first region and the second region. A first medium is configured to flow through the first region and a second, distinct medium is configured to flow through the second region. The environmental control system additionally includes a dehumidification system arranged in fluid communication with the ram air circuit and a compression device arranged in fluid communication with the ram air circuit and the dehumidification system.

Abstract: An environmental control system of an aircraft includes a plurality of inlets for receiving a plurality of mediums including a first medium and a second medium and an outlet for delivering a conditioned flow of the second medium to one or more loads of the aircraft. A ram air circuit includes a ram air shell having at least one heat exchanger positioned therein. A compressing device is arranged in fluid communication with the ram air circuit and the outlet. The compressing device including a first compressor, a second compressor, and at least one turbine operably coupled via a shaft. The first compressor and the second compressor are arranged in parallel with respect to a flow of the second medium and the first medium is used as a heat sink by another component within the environmental control system.

Abstract: An environmental control system of an aircraft including a plurality of inlets for receiving a plurality of mediums including a first medium, a second medium, and a third medium and an outlet for delivering a conditioned flow of the second medium to one or more loads of the aircraft. The environmental control system additionally includes a first compressing device and a second compressing device. The second compressing device is arranged in fluid communication with the first compressing device and the outlet. An inlet of the second compressing device is directly connected to an outlet of the first compressing device, and the first compressing device is driven by energy extracted from the first medium. The first medium is a flow of bleed air.