Abstract: A carbon dioxide capture system includes a first heat exchanger configured to exchange heat between an exhaust stream and a lean carbon dioxide effluent stream. The carbon dioxide capture system also includes a first turboexpander including a first compressor driven by a first turbine. The first compressor is coupled in flow communication with the first heat exchanger. The first turbine is coupled in flow communication with the first heat exchanger and configured to expand the lean carbon dioxide effluent stream. The carbon dioxide capture system further includes a carbon dioxide membrane unit coupled in flow communication with the first compressor. The carbon dioxide membrane unit is configured to separate the exhaust stream into the lean carbon dioxide effluent stream and a rich carbon dioxide effluent stream. The carbon dioxide membrane unit is further configured to channel the lean carbon dioxide effluent stream to the first heat exchanger.

Abstract: A counter-flow heat exchanger including a core region and a plenum region. The core region including a first set of heat exchanging passageways and a second set of heat exchanging passageways disposed at least partially therein. A plenum region is disposed adjacent opposed distal ends of the core region. Each of the plenum regions including a fluid inlet plenum, a fluid outlet plenum and a tube plate disposed therebetween. The first set of heat exchanging passageways is truncated and defines a first tube-side fluid flow path in a first direction. The second set of heat exchanging passageways defines a second tube-side fluid flow path in a second opposing direction. Each of the heat exchanging passageways extending from a fluid inlet plenum to a fluid outlet plenum. The tube plates and the core region include one of a cast metal formed thereabout each of the heat exchanging passageways or a braze bond formed between each of the heat exchanging passageways.

Abstract: Methods and systems of electrochemically machining a component are provided. The method may include applying two or more potentials to a tool electrode comprising an array of two or more individual electrodes to generate two or more electric fields in between the tool electrode and a workpiece opposite of the tool electrode, wherein each of the two or more electric fields is generated by one of the array of two or more individual electrodes.

Abstract: A customizable power conversion system (1000) is configured to operate with multiple alternating current (AC) and direct current (DC) power sources (1001,1003) and supplies multiple AC and DC loads (1018,1020,1022,1024). The customizable power conversion system is also configured to be assembled from a plurality of customizable power converters (1004,1006,1008,1010,1012), each of which is configured to function as a building block of the customizable power conversion system. More particularly, each customizable power converter may be configured as any DC/DC, DC/AC, AC/DC, or AC/AC converter, such as any of i) an inverter, ii) a DC/DC converter for use with a photovoltaic (PV) array (or string of PV arrays), and iii) a DC/DC converter for use with an energy storage element (e.g., a battery or battery string).

Abstract: A hypersonic aircraft includes one or more leading edge assemblies that are designed to manage thermal loads experienced at the leading edges during high speed or hypersonic operation. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. The outer wall may define a vapor chamber and a capillary structure within the vapor chamber for circulating a working fluid in either liquid or vapor form to cool the leading edge. In addition, a dual-modal cooling structure can enhance heat transfer from the outer wall at the leading edge to the outer wall within the condenser section of the vapor chamber.

Abstract: An energy storage system is disclosed. The energy storage system includes an insulated housing defining an interior chamber, a battery disposed within the interior chamber of the insulated housing, a cooling system configured to manage a temperature of the interior chamber of the insulated housing, and a temperature controller communicatively coupled to the cooling system and comprising at least one processor in communication with at least one memory device. The at least one processor is configured to determine a reference current level at the battery, compute, based on the reference current level, a target temperature for the interior chamber of the insulated housing, and instruct the cooling system to maintain the temperature in the interior chamber of the insulated housing at the target temperature.

Abstract: A hypersonic aircraft includes one or more leading edge assemblies that are designed to manage thermal loads experienced at the leading edges during high speed or hypersonic operation. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. The outer wall may define a vapor chamber and a capillary structure within the vapor chamber for circulating a working fluid in either liquid or vapor form to cool the leading edge. In addition, a dual-modal cooling structure can enhance heat transfer from the outer wall at the leading edge to the outer wall within the condenser section of the vapor chamber.

Abstract: A hypersonic aircraft includes one or more leading edge assemblies that are designed to manage thermal loads experienced at the leading edges during high speed or hypersonic operation. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. The outer wall may define a vapor chamber and a capillary structure within the vapor chamber for circulating a working fluid in either liquid or vapor form to cool the leading edge. In addition, a dual-modal cooling structure can enhance heat transfer from the outer wall at the leading edge to the outer wall within the condenser section of the vapor chamber.

Abstract: A hypersonic aircraft includes one or more leading edge assemblies that are designed to manage thermal loads experienced at the leading edges during high speed or hypersonic operation. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. The outer wall may define a vapor chamber and a capillary structure within the vapor chamber for circulating a working fluid in either liquid or vapor form to cool the leading edge. In addition, a dual-modal cooling structure can enhance heat transfer from the outer wall at the leading edge to the outer wall within the condenser section of the vapor chamber.

Abstract: A power supply system is provided. A power supply system includes a direct current (DC) bus, a first alternating current (AC) bus, at least one modular power conversion unit, and a battery string. The at least one modular power conversion unit includes a high-frequency direct current to alternating current (DC/AC) transformer electrically coupled between the DC bus and the first AC bus, and a direct current to direct current (DC/DC) converter electrically coupled to the high-frequency DC/AC transformer and the DC bus. The DC/DC converter is electrically coupled between the DC bus and the battery string.

Abstract: A customizable power conversion system (1000) is configured to operate with multiple alternating current (AC) and direct current (DC) power sources (1001,1003) and supplies multiple AC and DC loads (1018,1020,1022,1024). The customizable power conversion system is also configured to be assembled from a plurality of customizable power converters (1004,1006,1008,1010,1012), each of which is configured to function as a building block of the customizable power conversion system. More particularly, each customizable power converter may be configured as any DC/DC, DC/AC, AC/DC, or AC/AC converter, such as any of i) an inverter, ii) a DC/DC converter for use with a photovoltaic (PV) array (or string of PV arrays), and iii) a DC/DC converter for use with an energy storage element (e.g., a battery or battery string).

Abstract: A hypersonic aircraft includes one or more leading edge assemblies that are designed to cool the leading edge of certain portions of the hypersonic aircraft that are exposed to high thermal loads, such as extremely high temperatures and/or thermal gradients. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. A coolant supply may be in fluid communication with at least one fluid passageway that passes through the outer wall to deliver a flow of cooling fluid, such as liquid metal, to the stagnation point. The liquid metal vaporizes when the leading edge experiences a high heat load, thereby transpiration cooling the leading edge and/or facilitating a magnetohydrodynamic process for generating thrust or electricity.

Abstract: A hypersonic aircraft includes one or more leading edge assemblies that are designed to cool the leading edge of certain portions of the hypersonic aircraft that are exposed to high thermal loads, such as extremely high temperatures and/or thermal gradients. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. A coolant supply provides a flow of cooling fluid to a porous tip that is joined to the forward end of the outer wall and defines variable porosity and/or internal barriers to direct a flow of cooling fluid to the regions of the leading edge experiencing the highest thermal loading.

Abstract: A hypersonic aircraft includes one or more leading edge assemblies that are designed to cool the leading edge of certain portions of the hypersonic aircraft that are exposed to high thermal loads, such as extremely high temperatures and/or thermal gradients. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. A coolant supply provides a flow of cooling fluid to a porous tip that is joined to the forward end of the outer wall and defines variable porosity and/or internal barriers to direct a flow of cooling fluid to the regions of the leading edge experiencing the highest thermal loading.

Abstract: A hypersonic aircraft includes one or more leading edge assemblies that are designed to cool the leading edge of certain portions of the hypersonic aircraft that are exposed to high thermal loads, such as extremely high temperatures and/or thermal gradients. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. A coolant supply may be in fluid communication with at least one fluid passageway that passes through the outer wall to deliver a flow of cooling fluid, such as liquid metal, to the stagnation point. The liquid metal vaporizes when the leading edge experiences a high heat load, thereby transpiration cooling the leading edge and/or facilitating a magnetohydrodynamic process for generating thrust or electricity.

Abstract: Heat engines employing fluid bearing assemblies hermetically sealed with a closed flowpath for a working fluid are generally disclosed. For example, the heat engine includes a rotating drivetrain and a fluid bearing assembly. The rotating drivetrain includes a compressor section, an expander section, and a heat exchanger. The compressor section and expander section together define at least in part a closed flowpath for the flow of a working fluid. The heat exchanger is thermally coupled to the closed flowpath for adding heat to the working fluid. The fluid bearing assembly is configured to utilize the working fluid to support the rotating drivetrain. Further, the fluid bearing assembly is hermetically sealed with the closed flowpath.

Abstract: A carbon dioxide capture system includes a first heat exchanger configured to exchange heat between an exhaust stream and a lean carbon dioxide effluent stream. The carbon dioxide capture system also includes a first turboexpander including a first compressor driven by a first turbine. The first compressor is coupled in flow communication with the first heat exchanger. The first turbine is coupled in flow communication with the first heat exchanger and configured to expand the lean carbon dioxide effluent stream. The carbon dioxide capture system further includes a carbon dioxide membrane unit coupled in flow communication with the first compressor. The carbon dioxide membrane unit is configured to separate the exhaust stream into the lean carbon dioxide effluent stream and a rich carbon dioxide effluent stream. The carbon dioxide membrane unit is further configured to channel the lean carbon dioxide effluent stream to the first heat exchanger.

Abstract: An axial load management system for a turbomachine including a rotating drivetrain, a thrust bearing assembly, a sensor, and a valve supply line. The rotating drivetrain includes a compressor section and an expander section fluidly coupled together by a closed flowpath. The thrust bearing assembly includes a thrust runner, a thrust bearing housing, and a gas thrust bearing extending between the thrust runner and the thrust bearing housing. Further, the gas thrust bearing supports the rotating drivetrain. The sensor is attached to at least one of the thrust bearing housing or the gas thrust bearing. The valve supply line is fluidly coupled to the closed flowpath. A valve positioned within the valve supply line selectively allows a working fluid to flow between the closed flowpath and a thrust chamber defined by a rotating surface and a fixed surface to modify an axial load on the rotating drivetrain.

Abstract: A carbon dioxide capture system includes a first heat exchanger that exchanges heat between an exhaust stream and a lean carbon dioxide effluent stream. The carbon dioxide capture system also includes a second heat exchanger in flow communication with the first heat exchanger. The second heat exchanger is configured to cool the exhaust stream such that a condensate is formed, and the second heat exchanger is configured to channel a condensate stream for injection into the lean carbon dioxide effluent stream. A first turboexpander including a first compressor is driven by a first turbine. The first compressor is coupled in flow communication with the first heat exchanger. The first turbine is coupled in flow communication with the first heat exchanger and configured to expand the lean carbon dioxide effluent stream. The carbon dioxide capture system further includes a carbon dioxide membrane unit coupled in flow communication with the first compressor.

Abstract: At least one thermal module in fluidic communication with the one or more electronic components. The thermal module including a hydraulic motor operable to rotate a motor output shaft. The module further including a fan coupled to the motor output shaft, at least one heat exchanger in fluidic communication with the fan to provide passage therethrough of an air stream in response to rotational movement of the fan, and a conduit carrying a pressurized liquid stream through the hydraulic motor and each of the at least one heat exchanger. The pressurized liquid stream causing the motor output shaft to rotate and wherein heat in one of the air stream or the pressurized liquid stream is passed through each of the at least one heat exchanger and rejected into the other of the air stream or the pressurized liquid stream. A thermal management system including the at least one thermal module is disclosed.