An air conditioning system that is designed to be retroactively added to, and removed from, an existing aircraft, vehicle, boat or similar confined space. The air conditioning system includes a cooler module that is carried into a first compartment to circulate and cool the air. The cooler module contains a condenser, an evaporator and a compressor. A heat exchanger module is mounted into a vented second compartment. The heat exchanger is capable of exchanging heat with the ambient air. The heat exchanger module is connected to the cooler module with tubes that contain a heat exchanger fluid. In order for the tubes to pass through a compartment barrier, fluid couplings are mounted through the barrier. The tubes connect to the fluid couplings on either side of the barrier. A control unit is provided within the pressurized cabin and/or cockpit for controlling the operations of the cooler module.

A pressurized air supply unit (1; 1′) for an aircraft, comprising: a load compressor (30; 30′) configured to supply pressurized air (3), the load compressor (30; 30′) having a compressor shaft (23; 23′); and a drive portion (10) configured to supply power via an output shaft (20); the pressurized air supply unit (1; 1) being characterized in that it comprises: a gearbox (50); an electric motor (40), the electric motor (40) being coupled to said compressor shaft (23; 23′) via the gearbox (50); and a coupling system (25) configured to enable the output shaft (20) to drive the compressor shaft (23; 23′) and to prevent the compressor shaft (23; 23′) from driving the output shaft (20), and in that the output shaft (20) and the compressor shaft (23) lie on the same axis.

Systems to produce cabin supply air for aircraft and related methods are described herein. An example system includes an air conditioning pack including a heat exchanger including a first flow path and a second flow path isolated from the first flow path. The second flow path is to receive cabin exhaust air from a cabin of an aircraft. The cabin exhaust air is to reduce a temperature of the cabin supply air flowing through the first flow path of the heat exchanger. The system also includes a turbine to receive the cabin supply air from the heat exchanger. The turbine is to reduce a temperature and pressure of the cabin supply air. A turbine outlet of the turbine is fluidly coupled to the cabin to provide the cabin supply air to the cabin. The system further includes a fan to direct the cabin exhaust air from the heat exchanger.

Disclosed is an air cycle machine (ACM) having: a turbine; a compressor; a compressor shaft connected to the compressor and configured to receive rotational energy from a gearbox; and a turbine shaft connected to the turbine and configured to provide rotational energy to the gearbox; wherein the turbine shaft and the compressor shaft operate at different rotational speeds.

A dual entry turbine of a compression device includes a housing having a first inlet and a second inlet, and a first outlet and a second outlet. A turbine impeller is arranged within the housing. The turbine impeller has a first gas path and a second gas path. A first flow path extends from the first inlet to the first outlet via the first gas path and a second flow path extends from the second inlet to the second outlet via the second gas path. The first flow path and the second flow path being fluidly separate from one another.

Disclosed is a cabin air compressor (CAC) of an aircraft environmental control system, the CAC having: a CAC case defining a forward end, an aft end axially spaced apart from the forward end, wherein the forward end defines a compressor inlet; and a supplemental cooling jacket, positioned around at least a portion of the CAC case and at least partially conforming the CAC case, and wherein the supplemental cooling jacket is configured to direct a cooling medium through it.

An aircraft air conditioning system, powered solely using electrical energy, to draw bleed air from outside the aircraft and deliver conditioned air to the aircraft's interior, includes at most three motorized rotary machines, which include: independent first and second motorized turbocompressors, each turbocompressor includes a turbine compressor and an electric motor; and a motor compressor interconnected between the turbocompressors via an interconnection pipe. The motor compressor: generates a primary air flow, which drives a secondary air flow, allowing a breathing air flow to be cooled in a first operation phase, corresponding to a ground operation or at relatively low altitude and relatively low aircraft speed; be at shutdown or at low idle in a second phase of operation at relatively low altitude and relatively high aircraft speed; and, provide a top up breathing air flow in a third phase of operation at relatively high altitude and relatively high aircraft speed.

An air conditioning system for an aircraft is provided. The air conditioning system includes a first rotating component and a second rotating component. The first rotating component includes a compressor and a turbine. The compressor pressurizes a first medium. The first turbine receives a mixture of a second medium and a pressurized form of the first medium. The second rotating component includes a fan.

An air cycle machine for an environmental control system for an aircraft is provided. The air cycle machine includes a compressor configured to compress a first medium, a turbine configured to receive second medium, a mixing point downstream of the compressor and downstream of the turbine; and a shaft mechanically coupling the compressor and the turbine.

An airplane is provided. The airplane includes a compressing device. The compressing device includes a turbine with a first inlet and a second inlet. The turbine provides energy by expanding mediums. The first inlet is configured to receive a first medium of the mediums. The second inlet is configured to receive a second medium of the mediums. The compressing device includes a compressor and a motor. The compressor receives a first energy derived from the first and second mediums being expanded across the turbine during a first mode of the compressing device, receives a second energy derived from the first medium being expanded across the turbine during a second mode of the compressing device, and compresses the second medium in accordance with the first mode or the second mode. The motor provides a supplementary energy to the compressor