Abstract: A closed loop cooling system and method for an oil-free electric motor of an aircraft cabin air compressor. A closed-loop fan, which may be coupled to a motor rotor opposite a compressor impeller, circulates the required cooling air in a closed loop through a motor stator and bearings, a motor cooler, and a ducting used to complete the flow circuit via a ram air cooled heat exchanger. The cooling air may be pressurized to cabin pressure. The system and method of the present invention eliminates the possibility of contaminating trace amounts of oil in cabin supply air.

Abstract: A flow diverter comprises a heat sink array in fluid communication with a turbine outlet and an inlet face of a heat exchanger, the heat sink array comprising a plurality of heat sink elements, the heat sink array being separated from the inlet face by a distance, and the heat sink array being positioned between the turbine outlet and the inlet face such that at least a portion of a fluid flowing from the turbine outlet contacts the heat sink array before the portion of the fluid contacts the heat exchanger inlet face.

Abstract: A closed loop cooling system and method for an oil-free electric motor of an aircraft cabin air compressor. A closed-loop fan, which may be coupled to a motor rotor opposite a compressor impeller, circulates the required cooling air in a closed loop through a motor stator and bearings, a motor cooler, and a ducting used to complete the flow circuit via a ram air cooled heat exchanger. The cooling air may be pressurized to cabin pressure. The system and method of the present invention eliminates the possibility of contaminating trace amounts of oil in cabin supply air.

Abstract: An aircraft environmental control system (ECS) provides fresh air for the cabin of an aircraft by using electric motor driven compressors in place of traditional engine bleed air. Conventional aircraft ECS use an engine bleed to provide the pressurized fresh air flow for an aircraft cabin. However, such a system suffers from the disadvantage of requiring additional fuel consumption in order to provide an adequate engine bleed source. The present invention, using a zero bleed, electric powered architecture, does not suffer from this drawback of the conventional ECS.

Abstract: A ram air turbine includes a reaction turbine and an electrical generator that is driven by shaft power of the reaction turbine. A scoop directs a flow of ram air to an inlet of the reaction turbine and creates a pressure head for the reaction turbine. The reaction turbine and the scoop are contained entirely within a pod. The ram air turbine further includes a turbocompressor, including a turbine stage and a compressor stage, which provides a stream of cooled air to equipment inside the pod. The turbocompressor also reacts loads shed by the electrical generator.

Abstract: A two spool environmental control system includes a low pressure spool subsystem having a low pressure turbine. A high pressure spool subsystem is in air flow communication with the low pressure spool subsystem, while the high pressure spool subsystem is capable of conditioning compressed air prior to the low pressure spool subsystem conditioning the compressed air. The high pressure spool subsystem includes a high pressure turbine which is mechanically operable independently of the low pressure turbine.

Abstract: A floating speed electrically driven suction system for sucking boundary layer air flow off the external surface of an aircraft. A variable speed electrical generator drives a variable speed electrical motor which in turn drives a variable speed pneumatic compressor. Inlet guide vanes are automatically adjustable to compensate for variations in pressure. A surge control valve is operable to port in additional inlet flow as needed to avoid low volumetric surge in the suction compressor.

Abstract: A solid state controller is mounted directly to a permanent magnet, brushless DC motor. The controller operates the motor at constant torque and variable speed. Speed is determined in accordance with density of the through flow. The motor and controller can be employed to circulate fluid in a circulation loop having variable pressure.

Abstract: A variable speed turbo vacuum pump system (10) utilizes a motor driven compressor (12) to evacuate a gaseous medium from an enclosed space (22). The compressor (12) is a rotational type having at least one compressor wheel (40), the rotational speed of which is increased in inverse proportion to the decreasing inlet density of the gaseous medium from within the enclosed space (22).

Abstract: A cryocooler system including a reversed Brayton cycle turbo-refrigerator system having a surge control valve in the bypass line between the compression section inlet and outlet. The compression section includes at least one compressor and an aftercooler which rejects the heat of compression to a heat sink. The cooling section includes at least one regenerator and a turbo-alternator for expansive cooling of the working fluid.