United States of America As Represented by the Secretary of the Air Force

Abdeel J Roman

A bladder control system for a two-phase pump loop (TPPL) includes an air compressor, an air line connected to the air compressor, first and second solenoid valves located along the air line, a refrigerant tank having a port operatively connected to the TPPL for selective flow of refrigerant between the refrigerant tank and the TPPL, an expandable bladder located within the refrigerant tank and having a port connected to the air line between the first and second solenoid valves for selective flow of air between the expandable bladder and the air line, and a controller. The controller selectively expands and contracts the expandable bladder to control flow of refrigerant out of the refrigerant tank to the TPPL and into the refrigerant tank from the TPPL for maintaining the system refrigerant pressure within a desired tight range. This is particularly useful for obtaining tight temperature control at the thermal load.

Two-phase refrigerant pump bladder control system

A unique cooling system for an aircraft is designed to provide extremely low temperature cooling airflow. The system includes an air source, a first system compressor and a second system compressor positioned in series for compressing and heating the air. A least one heat exchanger can be used to cool the air at predefined locations. A condenser for condensing water out of the air is positioned downstream of the second compressor. The water can be removed with a water separator and at least a portion of any remaining water in the form of liquid or vapor is removed from the air in a membrane dehydration device. The air is expanded in at least one system turbine to bring the air temperature to a subfreezing temperature. The subfreezing air is then used to cool electronic components and mechanical components within the aircraft.

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Dayton, OH, United States of America

Abdeel J Roman