Abstract: According to some embodiments, system and methods are provided, comprising receiving one or more mission objectives for an aircraft mission, and condition data at a mission execution module; generating, via the mission execution module, a mission plan executable to address at least one of the one or more mission objectives via manipulation of a power-thermal management system (PTMS); receiving the generated mission plan at the PTMS directly from the mission execution module; and automatically executing the generated mission plan to operate an aircraft. Numerous other aspects are provided.

Abstract: According to some embodiments, system and methods are provided, comprising receiving one or more mission objectives for an aircraft mission, and condition data at a mission execution module; generating, via the mission execution module, a mission plan executable to address at least one of the one or more mission objectives via manipulation of a power-thermal management system (PTMS); receiving the generated mission plan at the PTMS directly from the mission execution module; and automatically executing the generated mission plan to operate an aircraft. Numerous other aspects are provided.

Abstract: A gas compression system that includes an electric motor that drives a compressor, a gas treatment device, and a gas cooling device. The electric motor may be cooled by a circulating flow of gas that is cooled by the gas cooling device and had been treated by the gas treatment device. The gas compression system may further include a gas feed that provides a supply of raw gas and a valve connected to the gas feed that controls a flow of raw gas from the gas feed to the gas treatment device. The valve may control the flow of raw gas from the gas feed to the gas treatment device such that any of the circulating flow of gas that is lost due to leakage is replaced. The gas treatment device may remove corrosive or abrasive impurities from the supply of raw gas.

Abstract: A method for assembling a turbine engine to facilitate preventing ice accumulation on the turbine engine during engine operation. The method includes coupling a manifold to the gas turbine engine such that the manifold is coupled in thermal communication with a heat source, coupling a first heat pipe to the manifold such that the first heat pipe partially circumscribes the gas turbine engine in a clockwise orientation, and coupling a second heat pipe to the manifold such that the second heat pipe partially circumscribes the gas turbine engine in a counter-clockwise orientation.

Abstract: An electrical machine to facilitate transporting fluids through a pipeline is provided. The machine includes a stator, a rotor magnetically coupled to the stator, and a housing enclosing the rotor and the stator. The housing includes a wall that facilitates channeling a first fluid at a first pressure through a portion of the housing. The machine also includes a stator enclosure defined by at least one wall that facilitates maintaining a second fluid within the stator enclosure. The stator enclosure is positioned within the electric machine housing. The stator enclosure has at least one wall that substantially isolates the second fluid from the first fluid such that only the second fluid is in flow communication with the stator. The stator enclosure has at least one wall that facilitates heat transfer from the second fluid to the first fluid. At least a portion of at least one of the stator enclosure walls is configured to facilitate equalizing the first pressure and the second pressure.

Abstract: A synchronous reluctance machine that has a stator and a rotor shaft operationally disposed within the confines of the stator. Laminations are axially stacked to form boat shaped segments. A plurality of selected boat shaped segments form a selected number of rotor poles about the rotor shaft and a plurality of support bars disposed intermittently between the boat shaped segments. Each segment of lamination is boat shaped with angular acuity facing towards the stator.

Abstract: A thermal management system and method for cooling Magnetic Resonance Imaging gradient coils. The system includes least one first header tube positioned adjacent to said gradient coils and configured to transport a coolant fluid; at least one set of cooling tubes connected to said header tube at inlet ends and configured to transport said coolant fluid, wherein said cooling tubes are parallel to each other and at least one second header tube positioned adjacent to said gradient coils, connected to said at least one set of cooling tubes at outlet ends of said at least one set of cooling tubes and configured to transport said coolant fluid.

Abstract: A turbomachinery system for cooling a high power density device includes a turbomachine configured to deliver a high flux cooling medium toward the high power density device, a housing containing a motor, a compressor, or both, of the turbomachine, a heat exchanger in fluid communication with the turbomachine and arranged for being thermally coupled to the high power density device, and a transition duct arranged intermediate the heat exchanger and turbomachine.

Abstract: A semiconductor device die (10, 116) is disposed on a heat-sinking support structure (30, 100). Nanotube regions (52, 120) contain nanotubes (54, 126) are arranged on a surface of or in the heatsinking support structure (30, 100). The nanotube regions (52, 120) are arranged to contribute to heat transfer from the semiconductor device die (10, 116) to the heat-sinking support structure (30, 100). In one embodiment, the semiconductor device die (10) includes die electrodes (20, 22), and the support structure (30) includes contact pads (40, 42) defined by at least some of the nanotube regions (52). The contact pads (40, 42) electrically and mechanically contact the die electrodes (20, 22). In another embodiment, the heat-sinking support structure (100) includes microchannels (120) arranged laterally in the support structure (100). At least some of the nanotube regions are disposed inside the microchannels (100).

Abstract: A turbomachinery system for cooling a high power density device includes a turbomachine configured to deliver a high flux cooling medium toward the high power density device, a housing containing a motor, a compressor, or both, of the turbomachine, a heat exchanger in fluid communication with the turbomachine and arranged for being thermally coupled to the high power density device, and a transition duct arranged intermediate the heat exchanger and turbomachine.

Abstract: A turbomachinery system for cooling a high power density device includes a turbomachine configured to deliver a high flux cooling medium and a high power density device arranged in fluid communication with the turbomachine, the turbomachine having a motor and a compressor driven by the motor.