Abstract: A turbo generator rotor assembly is provided and includes a generator, first and second bearings on a compressor-side and a turbine-side of the generator and a combination seal configuration in which leakage from the compressor cools the first bearing, the generator and the second bearing. The combination seal configuration leads to minimal leakage past the turbine with the generator and the first and second bearings being cooled with leakage flow from the compressor.

Abstract: A heat exchanger includes a heat exchanger core. The heat exchanger core includes a first fin and a second fin. The second fin is spaced apart from the first fin. The heat exchanger core also includes a primary passage defined between the first fin and the second fin and extending through the heat exchanger core. The heat exchanger core also includes a plurality of airfoils extending through the first fin, the primary passage, and the second fin. At least one airfoil of the plurality of airfoils includes a secondary passage. The secondary passage extends through the heat exchanger core within the at least one airfoil transverse to the primary passage.

Abstract: A turbo generator rotor assembly is provided and includes a generator, first and second bearings on a compressor-side and a turbine-side of the generator and a combination seal configuration in which leakage from the compressor cools the first bearing, the generator and the second bearing. The combination seal configuration leads to minimal leakage past the turbine with the generator and the first and second bearings being cooled with leakage flow from the compressor.

Abstract: Power and cooling systems including a drive system, a power generation unit, and a cooled fluid generation unit. A primary working fluid that is expanded within a turbine of the drive system and compressed within compressors in a closed-loop cycle. The power generation unit includes a generator and a heat source configured to heat the primary working fluid prior to injection into the turbine. T cooled fluid generation unit includes an ejector downstream of the compressors and a separator arranged downstream of the ejector and configured to separate liquid and gaseous portions of the primary working fluid. The gaseous portion is directed to the compressors and the liquid portion is directed to an evaporator heat exchanger to generate cooled fluid.

Abstract: A battery thermal management system for an air vehicle includes a first heat exchange circuit, a battery in thermal communication with the first heat exchange circuit, and a heat exchanger positioned on the first heat exchange circuit. The heat exchanger is operatively connected to a second heat exchange circuit. The system includes a controller operatively connected to the second heat exchange circuit. The controller is configured to variably select whether heat will be rejected to the second heat exchange circuit. A method for controlling a thermal management system for an air vehicle includes determining an expected fluid temperature of fluid in a fluid heat exchange circuit. The method includes commanding a flow restrictor at least partially closed or commanding the flow restrictor at least partially open.

Abstract: A turbo generator rotor assembly is provided and includes a generator, first and second bearings on a compressor-side and a turbine-side of the generator and a combination seal configuration in which leakage from the compressor cools the first bearing, the generator and the second bearing. The combination seal configuration leads to minimal leakage past the turbine with the generator and the first and second bearings being cooled with leakage flow from the compressor.

Abstract: A battery thermal management system for an air vehicle includes a liquid heat exchange circuit. The system includes at least one battery in thermal communication with the liquid heat exchange circuit. The system includes a controller operatively connected to the liquid heat exchange circuit. The controller is configured and adapted to variably select whether heat will be rejected to the liquid heat exchange circuit. The system includes at least one heat exchanger positioned on the liquid heat exchange circuit. The at least one heat exchanger is a liquid-air heat exchanger or a liquid-liquid heat exchanger. A method for controlling a thermal management system for an air vehicle includes determining an expected temperature of at least one battery, and cooling the at least one battery with a cooling device if the expected temperature exceeds a pre-determined expected temperature threshold.

Abstract: A heat exchanger system for a propulsion system inlet duct includes a heat exchanger assembly that is disposed within an inlet duct assembly. The heat exchanger includes a heat exchanger with a front facing area that is greater than an area of the inlet duct that is transverse to a longitudinal length of the inlet duct.

Abstract: A heat exchanger system for a propulsion system inlet duct includes a heat exchanger assembly that is disposed within an inlet duct assembly. The heat exchanger includes a heat exchanger with a front facing area that is greater than an area of the inlet duct that is transverse to a longitudinal length of the inlet duct.

Abstract: A heat exchanger includes a heat exchanger core. The heat exchanger core includes a first fin and a second fin. The second fin is spaced apart from the first fin. The heat exchanger core also includes a primary passage defined between the first fin and the second fin and extending through the heat exchanger core. The heat exchanger core also includes a plurality of airfoils extending through the first fin, the primary passage, and the second fin. At least one airfoil of the plurality of airfoils includes a secondary passage. The secondary passage extends through the heat exchanger core within the at least one airfoil transverse to the primary passage.

Abstract: Power and cooling systems including a drive system, a power generation unit, and a cooled fluid generation unit. A primary working fluid that is expanded within a turbine of the drive system and compressed within compressors in a closed-loop cycle. The power generation unit includes a generator and a heat source configured to heat the primary working fluid prior to injection into the turbine. T cooled fluid generation unit includes an ejector downstream of the compressors and a separator arranged downstream of the ejector and configured to separate liquid and gaseous portions of the primary working fluid. The gaseous portion is directed to the compressors and the liquid portion is directed to an evaporator heat exchanger to generate cooled fluid.

Abstract: A turbo-expanding cracking assembly includes a plurality of stages each including a rotating blade coupled to an output shaft and a fixed stator, at least one heat exchanger configured to transfer heat to an ammonia containing fuel flow, and a catalyst that is configured to decompose an ammonia containing fuel flow into a flow containing hydrogen (H2).

Abstract: A hybrid powerplant can include a fuel cell cycle system configured to generate a first power using a fuel and an oxidizer. The powerplant can also include a supercritical carbon dioxide (sCO2) cycle system operatively connected to the fuel cell cycle to receive heat from the fuel cell cycle to cause the sCO2 cycle system to generate a second power.

Abstract: A combined cycle power generation system for an aircraft includes fuel cell and supercritical CO2 cycles. The fuel cell cycle includes a compressor and turbine disposed on a first shaft, a fuel cell in fluid communication with the compressor and a fuel source, and a combustor in fluid communication with the fuel cell and the turbine. The combustor is configured to combust partially spent fuel from the fuel cell and produce combustion exhaust gas for delivery to the turbine. The supercritical CO2 cycle includes a compressor and turbine disposed on a second shaft, a supercritical CO2 fluid circuit in thermal communication with the combustor and configured to deliver CO2 to the turbine and compressor, and a heat exchanger in thermal communication with the supercritical CO2 fluid circuit and a source of cooling fluid. A mechanical linkage is configured to transfer power from the second shaft to the first shaft.

Abstract: A turbo-expanding cracking assembly includes a plurality of stages each including a rotating blade coupled to an output shaft and a fixed stator, at least one heat exchanger configured to transfer heat to an ammonia containing fuel flow, and a catalyst that is configured to decompose an ammonia containing fuel flow into a flow containing hydrogen (H2).

Abstract: A turbo generator rotor assembly is provided and includes a generator, first and second bearings on a compressor-side and a turbine-side of the generator and a combination seal configuration in which leakage from the compressor cools the first bearing, the generator and the second bearing. The combination seal configuration leads to minimal leakage past the turbine with the generator and the first and second bearings being cooled with leakage flow from the compressor.

Abstract: A system includes a power cycle and a cooling cycle. The power cycle includes a first compressor, a recuperative heat exchanger, a waste-heat heat exchanger, and a turbine. The turbine includes a drive shaft coupled to the first compressor. The working fluid from the waste-heat heat exchanger drives the turbine, the drive shaft, and the first compressor. The recuperative heat exchanger cools the working fluid from the turbine, and at least one ram-air heat exchanger further cools the working fluid from the recuperative heat exchanger. The first compressor is configured to pressurize the working fluid from the at least one ram-air heat exchanger. The cooling cycle includes a pump, an isenthalpic valve, an ambient air heat exchanger, and a second compressor. The cooling cycle cools the working fluid and ambient air and is connected to the power cycle in the at least one ram-air heat exchanger.

Abstract: A hybrid powerplant can include a fuel cell cycle system configured to generate a first power using a fuel and an oxidizer. The powerplant can also include a supercritical carbon dioxide (sCO2) cycle system operatively connected to the fuel cell cycle to receive heat from the fuel cell cycle to cause the sCO2 cycle system to generate a second power.

Abstract: A combined cycle power generation system for an aircraft includes fuel cell and supercritical CO2 cycles. The fuel cell cycle includes a compressor and turbine disposed on a first shaft, a fuel cell in fluid communication with the compressor and a fuel source, and a combustor in fluid communication with the fuel cell and the turbine. The combustor is configured to combust partially spent fuel from the fuel cell and produce combustion exhaust gas for delivery to the turbine. The supercritical CO2 cycle includes a compressor and turbine disposed on a second shaft, a supercritical CO2 fluid circuit in thermal communication with the combustor and configured to deliver CO2 to the turbine and compressor, and a heat exchanger in thermal communication with the supercritical CO2 fluid circuit and a source of cooling fluid. A mechanical linkage is configured to transfer power from the second shaft to the first shaft.

Abstract: A turbo-generator is provided including a housing, a plurality of turbine impellers arranged within the housing, a shaft extending between and coupling the plurality of turbine impellers; and a generator mounted within the housing between the plurality of turbine impellers. The generator includes a stator having a stator core including a plurality of windings and a rotor. The rotor is rotationally coupled to the shaft. A cooling system includes at least one cooling passage integrated into the stator core of the generator.