Abstract: A combustor for use in a gas turbine engine including a heat shield panel having a first surface and a second surface opposite the first surface of the heat shield panel and a combustor shell having an inner surface and an outer surface opposite the inner surface. The inner surface of the combustor shell and the second surface of the heat shield panel being in a facing spaced relationship defining an impingement cavity therebetween. The combustor shell further includes an impingement aperture that has a nonaxisymmetric shape. The impingement aperture extending from the outer surface to the inner surface through the combustor shell.

Abstract: A cryocooler device including a cryocooler including an input and an output, the input forming a cooling path, and a first stage that cools a working fluid in the cooling path. At least one thermal energy storage device selectively connectable to the cooling path and the cooling loop, wherein in a first operational mode of the cryocooler device where the at least one thermal energy storage device is connected to the cooling loop where the heat to be removed at the input exceeds a cooling capacity of the cryocooler device, and a second operational mode where the at least one thermal energy storage device is connected to the cooling path where the heat to be removed is less than the cooling capacity of the cryocooler and the heat is removed from the at least one thermal energy storage device.

Abstract: A header for an electric machine that include a stator core and one or more windings that include coolant passages formed therein. The header includes an inlet to receive a coolant, an outlet though which the coolant exits the header, an inlet plenum fluidly connected to the inlet, and an outlet plenum fluidly separated from the inlet plenum and fluidly connected to the outlet. The inlet and outlet plenums each have a varying cross section that varies from a top of the header as compared to a bottom of the header.

Abstract: A stator includes a stator hub, a plurality of stator teeth extending from stator hub that define a stator slot and at least one winding disposed in the stator slot, the winding including a cooling passage formed therein through. The cooling passage is connected to an inlet plenum and an outlet plenum. The stator can also include coil separators tint include cooling passages.

Abstract: Direct pin-fin cooling assemblies are disclosed for a high-power printed circuit boards (PCBs). The disclosure can solve the classical coldplate problem associated with liquid cooling of high-power PCBs namely: (1) Inhomogeneous cooling due to the calorimetric heating up of the coolant, (2) thermal interface material (TIM) related quality issues such as dry-out effects, (3) high cost due to complicated metal coldplate structure, and (4) low thermal conductivity due to multi-layer structure. This includes incorporating pin-fin direct cooling into high-power PCB structures without additional coldplate structure or TIM. In this approach, a TIM and a top plate of coldplate can be removed. Thus, the cooling performance can be improved because the thermal conductivity between a liquid coolant and a power device is increased.

Abstract: Disclosed is a heat exchanger having: an inlet manifold configured to receive a cooling fluid; a reservoir; first and second condenser arms connected between and that respectively fluidly couple the inlet manifold to the reservoir, so that fluid received at the inlet manifold travels from the inlet manifold into the reservoir; and an outlet pump having a pump inlet port coupled to the reservoir and having a pump outlet port, wherein the inlet manifold, the reservoir, the first and second condensers, in combination, form a continuous shape.

Abstract: A propulsion system for an aircraft includes a core engine that includes a core flow path where air is compressed in a compressor section, communicated to a combustor section, mixed with a hydrogen based fuel and ignited to generate a core gas flow that is expanded through a turbine section. The propulsion system includes a hydrogen fuel system that is configured to supply hydrogen fuel to the combustor through a fuel flow path, a condenser that is arranged along the core flow path and configured to condense water within the core gas flow, and a separator that includes an inlet, a primary water outlet and an exit that includes a plurality of exit guide vanes for straightening the core gas flow that proceeds through the exit. The exit guide vanes include a secondary water outlet for removing condensed water in the core gas flow that proceeds through the exit.

Abstract: A propulsion system for an aircraft includes a hydrogen fuel system suppling hydrogen fuel to the combustor through a fuel flow path. A condenser extracts water from a high energy gas flow. The condenser includes a plurality of rotating passages that are disposed within a collector. The passages are configured to rotate about a condenser axis to generate a transverse pressure gradient to direct water out of the high energy gas flow toward the collector.

Abstract: An annular water removal system (AWRS) for an air cycle environmental control system (ECS) includes a line replaceable unit (LRU) configured to output air flow, and a water collector coupled to the LRU. The water collector includes an upper portion and a lower portion. The upper portion includes a coalescing unit having a collector inlet to receive the air flow and configured to coalesce moisture from the air flow output from the LRU. The lower portion includes a collection unit in fluid communication with the coalescing unit. The collection unit is configured to collect the moisture coalesced by the coalescing unit.

Abstract: Electric motors and stators thereof are described. The stators of the electric motors include a first header, a second header fluidly connected to the first header, a plurality of windings fluidly connected to the first header and the second header to receive a cooling fluid passing from the first header to the second header along one or more flow channels, and one or more phase-change material elements arranged to thermally interact with at least one of the first header, the second header, the one or more flow channels, and the plurality of windings.

Abstract: Aircraft electric motors include a motor unit having a rotor and a stator. The stator includes a plurality of windings and cooling channels arranged to provide cooling thereto. A drive unit is configured to drive operation of the motor unit. A cooling system includes a working fluid arranged within a cooling fluid flow path, wherein the cooling fluid flow path includes a liquid cooling path configured to direct flow of the working fluid through, at least, the cooling channels of the motor unit and a vapor cooling path configured to direct flow of the working fluid through the drive unit and a separator arranged upstream of each of the liquid cooling path and the vapor cooling path and configured to direct a liquid portion of the working fluid into the liquid cooling path and configured to direct a vapor portion of the working fluid into the vapor cooling path.

Abstract: An electric machine includes a rotor located at and rotatable about a central axis and a stator positioned proximate to the rotor and defining a radial machine gap between the rotor and the stator. A cold plate is positioned proximate to the rotor. The cold plate is rotationally stationary relative to the central axis and is spaced apart from the rotor to define a cold plate gap between the cold plate and the rotor. The cold plate includes one or more coolant pathways therein such that thermal energy from the rotor is transferred to a flow of coolant circulated through the one or more coolant pathways.

Abstract: An oscillating heat pipe that can maintain efficient heat transfer even in a high gravity force equivalent environment is provided. The heat pipe can comprise a condenser region having a first plurality of bends, an evaporator region having a second plurality of bends, and a plurality of intermediate portions. The plurality of intermediate portions can extend between the first plurality of bends and the second plurality of bends. The plurality of intermediate portions can include a first intermediate portion and a second intermediate portion. A cross-sectional area of the first intermediate portion can be larger than a cross-sectional area of the second intermediate portion in a plane at a first distance from the evaporator region. The cross-sectional area of at least one of the first or second intermediate portions can increase from the condenser region towards the evaporator region.

Abstract: The present disclosure relates to heat exchangers and heat exchange systems such heat exchangers. The heat exchangers include a shell having an inlet and an outlet and heat exchange tube bundles arranged therein. The shell includes a first region communicating with the inlet configured to accommodate the heat exchange tube bundles and a refrigerant input from the inlet. The refrigerant performs heat exchange with a fluid in the heat exchange tube bundles. A second region is arranged between the first region and the outlet and communicates with the first region and the outlet. A heating device is disposed in the second region. Embodiments may optimize spatial layout of the heat exchanger tube bundles, effectively improving the utilization of shell space of the heat exchanger the heat transfer efficiency of the heat exchanger at the same material cost, and enhance the overall performance, safety and reliability of the system.

Abstract: An annular water removal system (AWRS) for an air cycle environmental control system (ECS) includes a line replaceable unit (LRU) configured to output air flow, and a water collector coupled to the LRU. The water collector includes an upper portion and a lower portion. The upper portion includes a coalescing unit having a collector inlet to receive the air flow and configured to coalesce moisture from the air flow output from the LRU. The lower portion includes a collection unit in fluid communication with the coalescing unit. The collection unit is configured to collect the moisture coalesced by the coalescing unit.

Abstract: A propulsion system for an aircraft includes a hydrogen fuel system suppling hydrogen fuel to the combustor through a fuel flow path. A condenser extracts water from a high energy gas flow. The condenser includes a plurality of rotating passages that are disposed within a collector. The passages are configured to rotate about a condenser axis to generate a transverse pressure gradient to direct water out of the high energy gas flow toward the collector.

Abstract: A propulsion system for an aircraft includes a hydrogen fuel system supplying hydrogen fuel to the combustor through a fuel flow path. A condenser extracts water from an exhaust gas flow and includes a plurality of spiral passages disposed within a collector. The spiraling passages generate a transverse pressure gradient to direct water out of the exhaust gas flow toward the collector.

Abstract: Aircraft electric motors are described. The aircraft electric motors include a motor unit having a rotor and a stator, wherein the stator includes a plurality of windings and cooling channels arranged to provide cooling to the plurality of windings, a drive unit configured to drive operation of the motor unit, and a cooling system having at least one directional feature forming a portion of at least one cooling channel, the at least one directional feature configured to prevent backflow of a cooling fluid that passes through the at least one cooling channel.

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 method of making a heat exchanger with a net shape moldable highly thermally conductive polymer composite includes mixing a polymer and a thermally conductive filler material and molding the polymer composite into heat exchanger components. The heat exchanger can be tailored to varying heating and cooling needs with moldable geometries.