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: In accordance with at least one aspect of this disclosure, an emergency power unit system for an aircraft includes a fuel cell system configured to generate power using a fuel and an oxidant, and an oxidant supply system fluidly connected to the fuel cell system to supply the oxidant to the fuel cell system via an oxidant supply line. The oxidant supply system is fluidly connected to an environmental control system of an aircraft.

Abstract: An oscillating heat pipe device can include a body formed to be at least partially flexible, one or more channels within the body and defined by the body, an evaporator portion within the body at a first end of the one or more channels and in fluid communication with the one or more channels, and a condenser portion within the body at a second end of the one or more channels and in fluid communication with the one or more channels. The body can be configured to flex between the evaporator portion and the condenser portion. The device can include a heat transfer fluid trapped within the channels to transfer heat between the evaporator portion and the condenser portion.

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 component for use in an environmental control system includes an inlet portion having a longitudinal axis, an inlet formed at the inlet portion, and an outlet portion including a front side and a back side. The front side is arranged closer to the inlet portion than the back side. An outlet is formed at the outlet portion and is arranged at a non-parallel angle relative to the inlet. An intermediate portion extends between and fluidly couples the inlet portion and the outlet portion. The intermediate portion includes a reservoir spaced laterally from the back side of the outlet portion and offset from the longitudinal axis of the inlet portion.

Abstract: An air data probe includes an air data probe body and an additively manufactured heater on the air data probe body.

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 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 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: 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 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 ram air fan inlet assembly for cabin air compressor (CAC) motor cooling flow enhancement includes a gas path defined by a ram air duct and a fan section, a CAC motor cooling return duct having an outlet provided through a wall of the ram air duct, and a centerbody body disposed in the ram air duct. The fan section is disposed immediately downstream and abutting the ram air duct. The ram air duct and fan section share a common axis. The centerbody is disposed about the common axis and configured to reduce of volume of the gas flow path in the ram air duct. The centerbody and the outlet axially overlap.

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 exhaust moisture removal system for an electric generation system including: a sorbent wheel; an interchanger; a hydrogen evaporator including an exhaust portion; and an exhaust outflow stream passageway configured to convey an exhaust from a hydrogen fuel cell of the electric generation system through a first pass and then through a second pass, the second pass being located downstream of the first pass, wherein the first pass of the exhaust outflow stream passageway passes through the sorbent wheel, then through the interchanger, and then through the hydrogen evaporator, and wherein the second pass of the exhaust outflow stream passageway passes through the hydrogen evaporator, then through the interchanger, and then through the sorbent wheel.

Abstract: Aircraft fuel system including a fuel vessel containing a non-mixture fuel. A protective vessel is arranged about the fuel vessel such that the fuel vessel is contained within the protective vessel and a protective space is defined between an outer surface of a vessel wall of the fuel vessel and an inner surface of a vessel wall of the protective vessel. At least one mounting structure fixedly positions the fuel vessel within the protective vessel. A fuel consumption device configured to consume the non-mixture fuel. A fuel output fluidly connects an interior of the fuel vessel to the fuel consumption device, the fuel output being fluidly isolated from the protective space. A relief output fluidly connects the protective space to a relief flow path, the relief output and relief flow path configured to vent gas from the protective space and remove any non-mixture fuel from the protective space.

Abstract: A system for cooling a power component includes a first metal layer. A cooling layer having a first surface is in contact with a surface of the first metal layer. A second metal layer is included having a surface in contact with a second surface of the cooling layer opposite the first metal layer. The cooling layer is of a material different from that of the first metal layer and that of the second metal layer. A plurality of cooling features are embedded in the material of the cooling layer. The cooling channels are spaced apart from both the first metal layer and the second metal layer by the material of the cooling layer. An electrically conductive path connects the first metal plate to the second metal plate.