Abstract: The disclosed technology can be implemented to provide a method of determining a thermal conductivity of a sample. The method includes controlling a thermal source to increase a temperature of the thermal source to an elevated temperature above a phase change temperature of a phase change material, placing the sample between and in thermal contact with the phase change material below the phase change temperature and the thermal source to allow a thermal conduction from the thermal source to the phase change material through the sample to increase an initial temperature of the phase change material to the phase change temperature to cause the phase change material to transition from a first phase to a second phase, performing a measurement on at least one of the sample or the phase change material, and determining the thermal conductivity of the sample based on the measurement.

Abstract: A method of manufacturing a target structure is provided. The method includes: obtaining a model structure of an initial material composition having a predetermined geometry and dimensions; applying a slurry mixture into the model structure; and processing the model structure with the slurry mixture inside the model structure to convert the initial material composition of the model structure into a final material composition to obtain the target structure with the final material composition and having a geometry and dimensions that are substantially similar to the predetermined geometry and dimensions of the model structure.

Abstract: Disclosed is a propeller, including a main driving device. Foldable blades and a fixed propeller are detachably connected to a projecting shaft of a driving motor. When the foldable blades are arranged, the propeller can be used as a hydrofoil board booster, and be clamped to a vertical rod of the hydrofoil board. When a fixed propeller is surrounded by a water flow culvert pipe provided with water inlet grooves, the propeller can be handheld with a handheld bracket or worn to advance and play underwater. Further, the propeller can be used as a guiding device for a diving apparatus. In combination with a gas cylinder and an airbag, the propeller can also be used as a scuba gear. Together with movable and fixed hydrofoil boards, the propeller can also be used as a gliding apparatus for diving.

Abstract: Embodiments of this application are applied to the field of terminal technologies, and provide a screen mirroring method, an apparatus, a device, and a storage medium. A mirroring suspension operation of a user is received, and to-be-encoded data is discarded in response to the mirroring suspension operation, so that when the user needs to suspend the screen mirroring service between a screen casting device and a display device, the to-be-encoded data can be discarded by simply performing the mirroring suspension operation on the screen casting device.

Abstract: Disclosed are techniques and methods for producing silicon carbide and ceramic matrix composites from hydrocarbons. In one aspect, a method includes preforming a shape using silicon carbide fibers placed into a chamber, evacuating the chamber causing a silicon and polymer slurry to enter the chamber, and pressurizing the chamber causing the silicon and polymer slurry to permeate the silicon carbide fibers. The method includes heating the chamber to cause pyrolysis of the polymer and a hydrocarbon passed into the chamber into carbon and hydrogen gas. The carbon from the pyrolyzed polymer and hydrocarbon provide a coating of carbon on the silicon in the silicon and polymer slurry. The method includes heating the chamber to a higher temperature causing the silicon to melt and react with the carbon to form silicon carbide. The formed silicon carbide and the silicon carbide fibers form the ceramic matrix composite.

Abstract: Embodiments of this application are applied to the field of terminal technologies, and provide a screen mirroring method, an apparatus, a device, and a storage medium. A mirroring suspension operation of a user is received, and to-be-encoded data is discarded in response to the mirroring suspension operation, so that when the user needs to suspend the screen mirroring service between a screen casting device and a display device, the to-be-encoded data can be discarded by simply performing the mirroring suspension operation on the screen casting device.

Abstract: This patent document relates to systems, structures, devices, and fabrication processes for ceramic matrix composites suitable for use in a nuclear reactor environment and other applications requiring materials that can withstand high temperatures and/or highly corrosive environments. In one exemplary aspect, a method of joining and sealing ceramic structures is disclosed. The method comprises forming a joint of a ceramic structure and an end plug using a sealing material, wherein the end plug has a hole that goes through a top surface and a bottom surface of the end plug; filling the ceramic structure with a desired gas composition through the hole; heating a material into a molten form using a heat source; and directing the material into the hole, wherein the material solidifies to seal the end plug.

Abstract: Disclosed are apparatuses, systems, methods, and devices for generating hydrogen pyrolysis of hydrocarbons (methane, diesel, JP8, etc.) in a reactor. The reactor includes multiple channels in parallel. A hydrocarbon flows in a channel and decomposes into hydrogen and carbon. Hydrogen gas flows out and some of the carbon will deposit on the channel wall. Once carbon deposition reaches a predetermined level, the hydrocarbon flow stops, and air or oxygen is caused to flow into the channels to oxidize carbon into carbon monoxide or carbon dioxide and supply heat to neighboring channels. Simultaneously, the hydrocarbon will flow into neighboring channels causing decomposition into hydrogen and carbon in the neighboring channels. When the carbon coating in the neighboring channels reaches a predetermined level, the gas flow is switched again to air or oxygen. In this way, each channel alternates between decomposing the hydrocarbon and oxidizing the deposited carbon.

Abstract: Disclosed are apparatuses, systems, methods, and devices for generating hydrogen pyrolysis of hydrocarbons (methane, diesel, JP8, etc.) in a reactor. The reactor includes multiple channels in parallel. A hydrocarbon flows in a channel and decomposes into hydrogen and carbon. Hydrogen gas flows out and some of the carbon will deposit on the channel wall. Once carbon deposition reaches a predetermined level, the hydrocarbon flow stops, and air or oxygen is caused to flow into the channels to oxidize carbon into carbon monoxide or carbon dioxide and supply heat to neighboring channels. Simultaneously, the hydrocarbon will flow into neighboring channels causing decomposition into hydrogen and carbon in the neighboring channels. When the carbon coating in the neighboring channels reaches a predetermined level, the gas flow is switched again to air or oxygen. In this way, each channel alternates between decomposing the hydrocarbon and oxidizing the deposited carbon.

Abstract: Fuel rod designs and techniques are provided to encapsulate nuclear fuel pellets in nuclear fuel rods. The tubular cladding in the disclosed fuel rods includes silicon carbide and a metal filler structure formed of a metal that becomes molten during a nuclear reaction of the nuclear fuel pellets and located inside the tubular cladding to include a metal tube that fills in a gap between the nuclear fuel pellets and an interior side wall of the tubular cladding and structured to include a closed metal end cap at one end of the nuclear fuel pellets to leave a space between one end of the interior of the tubular cladding and the closed metal end cap of the metal filler structure as a reservoir.

Abstract: Disclosed are techniques and methods for producing silicon carbide and ceramic matrix composites from hydrocarbons. In one aspect, a method includes preforming a shape using silicon carbide fibers placed into a chamber, evacuating the chamber causing a silicon and polymer slurry to enter the chamber, and pressurizing the chamber causing the silicon and polymer slurry to permeate the silicon carbide fibers. The method includes heating the chamber to cause pyrolysis of the polymer and a hydrocarbon passed into the chamber into carbon and hydrogen gas. The carbon from the pyrolyzed polymer and hydrocarbon provide a coating of carbon on the silicon in the silicon and polymer slurry. The method includes heating the chamber to a higher temperature causing the silicon to melt and react with the carbon to form silicon carbide. The formed silicon carbide and the silicon carbide fibers form the ceramic matrix composite.

Abstract: A polishing pad, a polyurethane polishing layer and a preparation method thereof are provided, belonging to the technical field of polishing in chemical-mechanical planarization treatment. The polyurethane polishing layer having a coefficient of thermal expansion of 100-200 ppm/° C. comprises a reaction product produced by reacting of multiple components. The multiple components include an isocyanate-terminated prepolymer, a hollow microsphere polymer and a curing agent composition. The curing agent composition includes 5-55 wt % of an aliphatic diamine composition, 0-8 wt % of a polyamine composition and 40-90 wt % of an aromatic bifunctional composition. The polyurethane polishing layer has a density of 0.6-1.1 g/cm3, a Shore hardness of 45-70D and an elongation at break of 50-450%. The polyurethane polishing layer is prepared by a simple process with low cost and energy consumption.

Abstract: This patent document relates to systems, structures, devices, and fabrication processes for ceramic matrix composites suitable for use in a nuclear reactor environment and other applications requiring materials that can withstand high temperatures and/or highly corrosive environments. In one exemplary aspect, a method of joining and sealing ceramic structures is disclosed. The method comprises forming a joint of a ceramic structure and an end plug using a sealing material, wherein the end plug has a hole that goes through a top surface and a bottom surface of the end plug; filling the ceramic structure with a desired gas composition through the hole; heating a material into a molten form using a heat source; and directing the material into the hole, wherein the material solidifies to seal the end plug.

Abstract: A gas turbine engine having a turbine blade tip clearance control system for increasing the efficiency of the engine by reducing the gap between turbine blade tips and radially outward ring segments is disclosed. The turbine blade tip clearance control system may include one or more clearance control bands positioned radially outward of inner surfaces of ring segments and bearing against at least one outer surface of the ring segments to limit radial movement of the ring segments. During operation, the clearance control band limits radial movement of the ring segments, and the turbine blade tips do not have a pinch point during start-up transient conditions. In addition, the smallest gap during turbine engine operation may be found at steady state operation of the gas turbine engine. Thus, the clearance control system can set the gap between turbine blade tips and ring segments to be zero at steady state operation.

Abstract: A polishing pad, a polyurethane polishing layer and a preparation method thereof are provided, belonging to the technical field of polishing in chemical-mechanical planarization treatment. The polyurethane polishing layer having a coefficient of thermal expansion of 100-200 ppm/° C. comprises a reaction product produced by reacting of multiple components. The multiple components include an isocyanate-terminated prepolymer, a hollow microsphere polymer and a curing agent composition. The curing agent composition includes 5-55 wt % of an aliphatic diamine composition, 0-8 wt % of a polyamine composition and 40-90 wt % of an aromatic bifunctional composition. The polyurethane polishing layer has a density of 0.6-1.1 g/cm3, a Shore hardness of 45-70D and an elongation at break of 50-450%. The polyurethane polishing layer is prepared by a simple process with low cost and energy consumption.

Abstract: Systems, structures, devices, and fabrication processes for ceramic matrix composites suitable for use in a nuclear reactor environment and other applications requiring materials that can withstand high temperatures and/or highly corrosive environments are disclosed. In one aspect, a ceramic composite structure is provided. The structure comprises a chamber including an external shell and a hollow space inside the external shell. The external shell includes an inner composite layer including a first composite structure, a middle composite layer placed outside of the inner composite layer, the middle composite layer including a second composite structure that is different from the first composite structure, and an outer monolithic layer that has a spatially uniform material property and placed outside of the middle composite layer.

Abstract: An interstage seal system (10) for adjusting the position of an interstage seal during operation of a gas turbine engine (14) to increase efficiency of the seal (12) is disclosed. The interstage seal system (10) may include a interstage seal housing (16) formed from a circumferentially extending housing having a seal (12) positioned on a radially inward surface (18) of the interstage seal housing (16). The interstage seal housing (16) may biased radially outward via one or more springs (20) to bias the radially inward surface (18) of the interstage seal housing (16) outwardly. The interstage seal housing (16) may reside in an interstage housing receiving cavity (68). The cavity (68) may be supplied with gases at a higher pressure than on the other side (24) of the seal housing (16) during turbine engine operation.

Abstract: A high-efficiency compressor section (10) for a gas turbine engine is disclosed. The compressor section includes a vane carrier (12) adapted to hold ring segment assemblies (16) that provide optimized blade tip gaps (28,29) during a variety of operating conditions. The ring segment assemblies include backing elements (30) and tip-facing elements (32) urged into a preferred orientation by biasing elements (40) that maintain contact along engagement surfaces (44,46). The backing and tip-facing elements have thermal properties sufficiently different to allow relative growth that strategically forms an interface gap (42) therebetween, resulting in blade tip gaps that are dynamically adjusted operation.

Abstract: A high-efficiency compressor section (10) for a gas turbine engine is disclosed. The compressor section includes a vane carrier (12) adapted to hold ring segment assemblies (16) that provide optimized blade tip gaps (28,29) during a variety of operating conditions. The ring segment assemblies include backing elements (30) and tip-facing, elements (32) urged into a preferred orientation by biasing elements (40) that maintain contact along engagement surfaces (44,46). The backing and tip-facing, elements have thermal properties sufficiently different to allow relative growth and geometric properties strategically selected to strategically form an interface gap therebetween (42) resulting in blade tip gaps that are dynamically adjusted operation.

Abstract: A gas turbine engine (10) having a turbine blade tip clearance control system (12) for increasing the efficiency of the engine (10) by reducing the gap (14) between turbine blade tips (16) and radially outward ring segments (18) is disclosed. The turbine blade tip clearance control system (12) may include one or more clearance control bands (20) positioned radially outward of inner surfaces (22) of ring segments (18) and bearing against at least one outer surface (24) of the ring segments (18) to limit radial movement of the ring segments (18). During operation, the clearance control band (20) limits radial movement of the ring segments (18), and the turbine blade tips (16) do not have a pinch point during start-up transient conditions. In addition, the smallest gap (14) during turbine engine operation may be found at steady state operation of the gas turbine engine (10).