Abstract: A cooling system includes a liquid loop, a vapor compression loop, and a heat exchanger in fluid communication with each of the liquid loop and the vapor compression cycle loop. The liquid loop includes a cold sink for cooling a heat load. The vapor compression cycle loop is fluidly coupled to the liquid loop by a separator, which is configured to separate a two-phase form of a working fluid received from the cold sink into a vapor form of the working fluid and a liquid form of the working fluid.

Abstract: A thermal management system for an aircraft includes a liquid loop, a vapor compression cycle loop, and an air loop. The liquid loop includes a pump to deliver a working fluid a cold sink for cooling a heat load with the working fluid. The vapor compression cycle loop is fluidly coupled to the liquid loop by a separator. The separator is configured to separate a two-phase form of the working fluid into a vapor form of the working fluid for delivery to a compressor of the vapor compression cycle loop and a liquid form of the working fluid for delivery to the liquid loop. The air loop in thermal communication with the working fluid and configured to provide cooling or heating air for an aircraft cabin.

Abstract: A fuel delivery system for an aircraft turbine engine assembly includes a storage tank that is configured for storage of a cryogenic fuel in a liquid phase, at least one thermal compression tank where liquid fuel from the fuel storage tank is pressurized by exposure to thermal energy to elevate a pressure of the liquid fuel, a heat communication device that is in thermal communication with the thermal compression tank for communicating thermal energy to the liquid fuel within the thermal compression tank, a valve system for controlling the flow of pressurized liquid fuel into and out of the thermal compression tank, and a controller that is programmed to operate the valve system to release pressurized liquid fuel from the thermal compression tank into a conduit for communication to a combustor.

Abstract: A heat exchanger includes an outer shell enclosing an interior space. An inlet extends through the outer shell and is in fluidic communication with the interior space. An outlet extends through the outer shell and is in fluidic communication with the interior space. At least one phase change element is inside the interior space and includes a core comprising a phase change material.

Abstract: Thermal management systems include a vapor cycle and a liquid cycle sharing a common working fluid. The vapor cycle includes, along a vapor cycle flow path, a compressor and a condenser. The liquid cycle includes, along a liquid cycle flow path, a fluid driver, a load, a regulator valve, and a phase change material heat exchanger. A cold sink is thermally coupled to a heat load. A separator is configured to separate liquid and vapor portions of the working fluid and direct the liquid into the liquid cycle and the vapor into the vapor cycle. The separator is part of both the vapor cycle and the liquid cycle. The regulator valve controls a temperature of the working fluid within the liquid cycle at a location upstream of the phase change material heat exchanger to control a mode of operation of the phase change material heat exchanger.

Abstract: A cooling system includes a liquid loop, a vapor compression loop, and a heat exchanger in fluid communication with each of the liquid loop and the vapor compression cycle loop. The liquid loop includes a cold sink for cooling a heat load. The vapor compression cycle loop is fluidly coupled to the liquid loop by a separator, which is configured to separate a two-phase form of a working fluid received from the cold sink into a vapor form of the working fluid and a liquid form of the working fluid.

Abstract: A thermal management system for an aircraft includes a liquid loop, a vapor compression cycle loop, and an air loop. The liquid loop includes a pump to deliver a working fluid a cold sink for cooling a heat load with the working fluid. The vapor compression cycle loop is fluidly coupled to the liquid loop by a separator. The separator is configured to separate a two-phase form of the working fluid into a vapor form of the working fluid for delivery to a compressor of the vapor compression cycle loop and a liquid form of the working fluid for delivery to the liquid loop. The air loop in thermal communication with the working fluid and configured to provide a cooling or heating air for an aircraft cabin.

Abstract: Cooling systems include a cold sink having a number of heat load cooling paths and a heat load associated with each cooling path. An inlet is configured to supply a cooling fluid into the cold sink and an outlet is configured to receive the cooling fluid after passing through the plurality of heat load cooling paths of the cold sink. A pressure regulating element is arranged along each cooling path, each pressure regulating element arranged between the inlet and the heat load along each cooling path and configured to cause a pressure drop in the cooling fluid prior to passing the cooling fluid to each heat load. The pressure drop caused by each pressure regulating element is the same and is a pressure drop greater than a maximum pressure drop across each heat load of a system without such pressure regulating elements.

Abstract: Cooling systems include a cold sink thermally coupled to a heat load, a separator configured to separate liquid and vapor portions of a working fluid, and a cooling cycle having a vapor loop and a liquid loop, the cooling cycle having the working fluid configured to pass through both the vapor loop and the liquid loop. The vapor loop includes the separator, a compressor, a condenser, and a valve. A vapor form of the working fluid flows from the separator into the compressor, and the working fluid then flows to the condenser, and then through the valve, and returned to the separator. The liquid loop includes the cold sink, the separator, and a pump. A liquid form of the working fluid flows from the separator into the pump and the working fluid is increased in pressure and supplied to the cold sink and then returned to the separator.

Abstract: Cooling systems include a cold sink having a number of heat load cooling paths and a heat load associated with each cooling path. An inlet is configured to supply a cooling fluid into the cold sink and an outlet is configured to receive the cooling fluid after passing through the plurality of heat load cooling paths of the cold sink. A pressure regulating element is arranged along each cooling path, each pressure regulating element arranged between the inlet and the heat load along each cooling path and configured to cause a pressure drop in the cooling fluid prior to passing the cooling fluid to each heat load. The pressure drop caused by each pressure regulating element is the same and is a pressure drop greater than a maximum pressure drop across each heat load of a system without such pressure regulating elements.

Abstract: Cooling systems include a cold sink thermally coupled to a heat load, a separator configured to separate liquid and vapor portions of a working fluid, and a cooling cycle having a vapor loop and a liquid loop, the cooling cycle having the working fluid configured to pass through both the vapor loop and the liquid loop. The vapor loop includes the separator, a compressor, a condenser, and a valve. A vapor form of the working fluid flows from the separator into the compressor, and the working fluid then flows to the condenser, and then through the valve, and returned to the separator. The liquid loop includes the cold sink, the separator, and a pump. A liquid form of the working fluid flows from the separator into the pump and the working fluid is increased in pressure and supplied to the cold sink and then returned to the separator.