Abstract: A heat exchanger includes a body, a plurality of first flow channels defined in the body; and a plurality of second flow channels defined in the body. The second flow channels are fluidly isolated from the first flow channels. The first flow channels and second flow channels are arranged in a checkerboard pattern.

Abstract: A turbine rotor includes a base and a plurality of blades. A central nose is radially inward of the blades and defines an axis of rotation. A plurality of cooling manifolds is disposed within the turbine rotor and includes impingement cooling jets extending through a rear surface of the turbine rotor. An internal cooling manifold extends radially inward of the impingement cooling jets and extends between the base and the rear surface of the turbine rotor. A central nose cooling manifold extends into the central nose and is fluidically connected to the internal cooling manifold. A base cooling manifold is fluidically connected to the central nose manifold and extends radially outward from the central nose cooling manifold. A blade cooling manifold is fluidically connected to the base cooling manifold and extends within the blade. Trailing edge jets extend from the blade cooling manifold and through the trailing edge of blades.

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: A cold plate apparatus is disclosed. A cold plate includes a first set of sinusoidal conduits and a second set of sinusoidal conduits formed therein. The first set of sinusoidal conduits is arranged in a first direction, and the second set of sinusoidal conduits is arranged in a second direction. Crests of the first set of sinusoidal conduits overlap troughs of the second set of sinusoidal conduits. Crests of the second set of sinusoidal conduits overlap troughs of the first set of sinusoidal conduits. A first set of header plates is fluidically coupled to the first set of sinusoidal conduits, and a second set of header plates is fluidically coupled to the second set of sinusoidal conduits.

Abstract: Aircraft systems including a pressurized fuel tank containing a pressurized fuel, a turbo expander configured to receive the pressurized fuel from the fuel tank, the turbo expander configured to decrease a pressure of the pressurized fuel to generate low pressure fuel having pressure less than the pressurized fuel, a fuel-to-air heat exchanger configured to receive the low pressure fuel from the turbo expander as a first working fluid and air as a second working fluid, the heat exchanger configured to cool the air and warm the fuel, an aircraft cabin configured to receive the cooled air, and a fuel consumption system configured to consume the fuel to generate power.

Abstract: A stator of an electric motor includes a stator core including a rim and a plurality of stator teeth extending from the rim. The plurality of stator teeth define a plurality of tooth gaps between circumferentially adjacent stator teeth. A plurality of stator windings are wrapped along the plurality of stator teeth. The plurality of stator windings include a plurality of core segments extending along the plurality of tooth gaps, and a plurality of end turn segments connecting adjacent core segments. A plurality of non-electrically conductive cooling channels are located in the stator core. The plurality of cooling channels are configured to direct a cooling fluid flow therethrough to cool the plurality of stator windings.

Abstract: A method of manufacturing a heat exchanger core from glass ceramic matrix composite includes placing one or more reinforcing fibers around one or more mandrels into a mold cavity. A glass matrix material infiltrates the one or more reinforcing fibers to produce an infiltrated core and the one or more mandrels is removed to create one or more passages passing through the infiltrated core.

Abstract: A turbine rotor includes a base and a plurality of blades. A central nose is radially inward of the blades and defines an axis of rotation. A plurality of cooling manifolds is disposed within the turbine rotor and includes impingement cooling jets extending through a rear surface of the turbine rotor. An internal cooling manifold extends radially inward of the impingement cooling jets and extends between the base and the rear surface of the turbine rotor. A central nose cooling manifold extends into the central nose and is fluidically connected to the internal cooling manifold. A base cooling manifold is fluidically connected to the central nose manifold and extends radially outward from the central nose cooling manifold. A blade cooling manifold is fluidically connected to the base cooling manifold and extends within the blade. Trailing edge jets extend from the blade cooling manifold and through the trailing edge of blades.

Abstract: A heat sink with a primary flow volume, an inlet, an outlet, a bottom plate, a top plate, distribution, heat transfer and collector sections, and flow paths between pillars. The inlet cross-section defines the primary flow volume cross-section and the length of the primary flow volume extends into the heat sink at a right angle to the inlet cross-section. The distribution section is proximate to the flow inlet and has distribution pillars extending from the bottom or top plate. The heat transfer section is proximate to the distribution section and has heat transfer pillars extending from the bottom or top plate. The collector section is proximate to the heat transfer section and has collector pillars extending from the bottom or top plate. The distribution cross-section is greater than the heat transfer cross-section which is smaller than the collector cross-section. The flow paths extend outside of the primary flow volume.

Abstract: A gas turbine engine includes a core engine that includes a core flow path that connects a compressor section, combustor section and a turbine section. The gas turbine engine further includes a bottoming cycle system that includes a supercritical CO2 (sCO2) working fluid flow. A first recuperator is disposed in the core flow path downstream of the turbine section, the first recuperator is configured to transfer thermal energy from a core flow aft of the turbine section to the sCO2 working fluid flow. A second recuperator is disposed in the compressor section, the second recuperator is configured to transfer thermal energy from the sCO2 working fluid flow to a location forward of the combustor section.

Abstract: A heat sink with a primary flow volume, an inlet, an outlet, a bottom plate, a top plate, distribution, heat transfer and collector sections, and flow paths between pillars. The inlet cross-section defines the primary flow volume cross-section and the length of the primary flow volume extends into the heat sink at a right angle to the inlet cross-section. The distribution section is proximate to the flow inlet and has distribution pillars extending from the bottom or top plate. The heat transfer section is proximate to the distribution section and has heat transfer pillars extending from the bottom or top plate. The collector section is proximate to the heat transfer section and has collector pillars extending from the bottom or top plate. The distribution cross-section is greater than the heat transfer cross-section which is smaller than the collector cross-section. The outlet and the flow paths extend outside of the primary flow volume.

Abstract: A heat exchanger includes a heat exchanger body having a first end and a second end opposed to the first end along a flow axis. A plurality of flow channels is defined in the heat exchanger body extending axially with respect to the flow axis. A first set of the flow channels forms a first flow circuit and a second set of the flow channels forms a second flow circuit that is in fluid isolation from the first flow circuit. Each flow channel is fluidly isolated from the other flow channels. The flow channels all conform to a curvilinear profile.

Abstract: An aircraft system includes a turbine engine having a compressor, a combustor having an inlet and an outlet, and a turbine having an inlet portion and an outlet portion. An auxiliary power unit (APU) is operatively connected to the turbine engine. The APU includes a compressor portion, a generator, and a turbine portion. The compressor portion is operatively connected to the turbine portion through the generator. A source of cryogenic fluid is operatively connected to the turbine engine and the APU. A heat exchange member includes an inlet section operatively connected to the source of cryogenic fluid, a first outlet section operatively connected to the turbine engine and a second outlet section operatively connected to the compressor portion.

Abstract: A turbine rotor includes a base and a plurality of blades. A central nose is radially inward of the blades and defines an axis of rotation. A plurality of cooling manifolds is disposed within the turbine rotor and includes impingement cooling jets extending through a rear surface of the turbine rotor. An internal cooling manifold extends radially inward of the impingement cooling jets and extends between the base and the rear surface of the turbine rotor. A central nose cooling manifold extends into the central nose and is fluidically connected to the internal cooling manifold. A base cooling manifold is fluidically connected to the central nose manifold and extends radially outward from the central nose cooling manifold. A blade cooling manifold is fluidically connected to the base cooling manifold and extends within the blade. Trailing edge jets extend from the blade cooling manifold and through the trailing edge of blades.

Abstract: A turbine rotor includes a base and a plurality of blades. A central nose is radially inward of the blades and defines an axis of rotation. A plurality of cooling manifolds is disposed within the turbine rotor and includes impingement cooling jets extending through a rear surface of the turbine rotor. An internal cooling manifold extends radially inward of the impingement cooling jets and extends between the base and the rear surface of the turbine rotor. A central nose cooling manifold extends into the central nose and is fluidically connected to the internal cooling manifold. A base cooling manifold is fluidically connected to the central nose manifold and extends radially outward from the central nose cooling manifold. A blade cooling manifold is fluidically connected to the base cooling manifold and extends within the blade. Trailing edge jets extend from the blade cooling manifold and through the trailing edge of blades.

Abstract: A cold plate apparatus is disclosed. A cold plate includes a first set of sinusoidal conduits and a second set of sinusoidal conduits formed therein. The first set of sinusoidal conduits is arranged in a first direction, and the second set of sinusoidal conduits is arranged in a second direction. Crests of the first set of sinusoidal conduits overlap troughs of the second set of sinusoidal conduits. Crests of the second set of sinusoidal conduits overlap troughs of the first set of sinusoidal conduits. A first set of header plates is fluidically coupled to the first set of sinusoidal conduits, and a second set of header plates is fluidically coupled to the second set of sinusoidal conduits.

Abstract: Power generation systems are described. The systems include a shaft, a compressor operably coupled to a first end of the shaft, a turbine operably coupled to a second end of the shaft, a generator operably coupled to the shaft between the compressor and the turbine, and a working fluid arranged in a closed-loop flow path that flows through each of the compressor and the turbine to drive rotation of the shaft. The shaft includes an internal fluid conduit configured to receive a portion of the working fluid at one of the first end and the second end and convey the portion of the working fluid through the generator to the other of the first end and the second end, wherein the portion of the working fluid is rejoined with a primary flow path of the working fluid.

Abstract: A header for a high-pressure heat exchanger includes a first high-pressure transition section with inlets for multiple first high-pressure flow channels that are spaced from one another in a radial direction and collectively arranged in a substantially circular shape. The inlets for the multiple first high-pressure flow channels on a radially outer edge of the first high-pressure transition section are spaced further apart in a circumferential direction from adjacent inlets of the multiple first high-pressure flow channels than radially inward inlets are spaced from adjacent radially inward inlets of the multiple first high-pressure flow channels. The header also includes multiple first high-pressure flow channels extending from the first high-pressure transition section to a second-high pressure transition section that is configured to divide each of the multiple first high-pressure flow channels into at least two first high-pressure sub-flow channels.

Abstract: An environmental control system (ECS) for an aircraft includes a primary heat exchanger, a compressor including an inlet fluidically connected to the primary heat exchanger, a turbine operatively connected to the compressor, and a cryogenic fluid heat exchanger fluidically connected to the primary heat exchanger.