Abstract: A paste for a reference electrode according to an embodiment of the present disclosure includes silver chloride powder and a carbon-based conductive material. The carbon-based conductive material may include at least one compound selected from the group consisting of carbon nanotubes, graphite, graphene, and carbon black. The reference electrode formed of the paste for a reference electrode according to an exemplary embodiment may provide improved mechanical properties and electrochemical properties.

Abstract: The present disclosure discloses beamforming methods and apparatuses. According to an exemplary embodiment of the present disclosure, an antenna message generation deep neural network (DNN) and a beam characteristic generation DNN of a bipartite graph neural network (BGNN) having terminals as vertices on one side and APs as vertices on another side may be constructed.

Abstract: Disclosed herein are an airfoil, and a turbine blade and gas turbine including the same. The airfoil includes a first cooling passage allowing a first cooling fluid introduced from the bottom of a leading edge to flow into a first serpentine channel formed on a pressure side, and to be then discharged to the rear of a trailing edge, and a second cooling passage allowing a second cooling fluid introduced from the bottom of a suction side to be divided and flow into at least two second serpentine channels formed on the suction side, and allowing the divided cooling fluids introduced into the at least two second serpentine channels to be joined at the bottom thereof and to be then discharged to the rear of the trailing edge.

Abstract: The present technique presents a gas turbine blade for re-using cooling air, a turbomachine assembly having the blade, and a gas turbine having the turbomachine assembly. The blade includes a platform and an airfoil extending from the platform. The airfoil includes a pressure surface, a suction surface, a leading edge and a trailing edge. The platform includes a pressure side, a suction side, a leading-edge side and a trailing-edge side, disposed towards the pressure surface, the suction surface, the leading edge and the trailing edge of the airfoil, respectively. The suction side of the platform includes a part of the upper surface and a suction-side lateral surface of the platform. At least a part of an edge between the suction-side lateral surface and the upper surface of the platform comprises a chamfer part.

Abstract: The present technique presents a gas turbine blade for re-using cooling air, a turbomachine assembly having the blade, and a gas turbine having the turbomachine assembly. The blade includes a platform and an airfoil extending from the platform. The airfoil includes a pressure surface, a suction surface, a leading edge and a trailing edge. The platform includes a pressure side, a suction side, a leading-edge side and a trailing-edge side, disposed towards the pressure surface, the suction surface, the leading edge and the trailing edge of the airfoil, respectively. The suction side of the platform includes a part of the upper surface and a suction-side lateral surface of the platform. At least a part of an edge between the suction-side lateral surface and the upper surface of the platform comprises a chamfer part.

Abstract: A turbine blade includes a root to be mounted to a rotor; a platform having an inner side and an outer side, the inner side being coupled to the root; an airfoil extending from the outer side of the platform in a radial direction of the rotor and including an outer end on which a blade tip is formed; a protrusion formed in the blade tip; and a blade cooling passage that is formed inside the airfoil and communicates with an exit hole formed in the blade tip, the blade cooling passage to pass cooling fluid through the airfoil such that the cooling fluid exits the airfoil through the exit hole. The protrusion includes an outer side surface that is flush with an outer end surface of the airfoil and protrudes in a direction perpendicular to the radial direction to prevent hot combustion gas from invading the blade cooling passage.

Abstract: A turbine blade includes a root to be mounted to a rotor; a platform having an inner side and an outer side, the inner side being coupled to the root; an airfoil extending from the outer side of the platform in a radial direction of the rotor and including an outer end on which a blade tip is formed; a protrusion formed in the blade tip; and a blade cooling passage that is formed inside the airfoil and communicates with an exit hole formed in the blade tip, the blade cooling passage to pass cooling fluid through the airfoil such that the cooling fluid exits the airfoil through the exit hole. The protrusion includes an outer side surface that is flush with an outer end surface of the airfoil and protrudes in a direction perpendicular to the radial direction to prevent hot combustion gas from invading the blade cooling passage.

Abstract: A gas turbine blade according to an embodiment of the present invention includes a turbine blade provided in a gas turbine; and a plurality of film coolers formed in a section from a leading edge to a trailing edge of the turbine blade, in which the film cooler includes a cooling channel through which cooling air is introduced and formed in an oval shape; and an outlet through which the cooling air passing through the cooling channel is discharged and extending from an extended end of the cooling channel toward an outer side thereof and formed in an oval shape.

Abstract: A method for manufacturing a microcantilever having a cantilever and a functional probe provided on the cantilever may include steps of: providing a probe mold which accommodates a liquid probe solution in which quantum dots for the functional probe are mixed, and has a groove corresponding to the shape of the functional probe; bringing a cantilever into contact with the probe mold on which the groove is formed to correspond to the location of the functional probe; forming the functional probe on the cantilever by curing the probe solution accommodated in the groove in a state where the cantilever contacts the probe mold; and separating the cantilever from the probe mold.

Abstract: A method for manufacturing a microcantilever having a cantilever and a functional probe provided on the cantilever may include steps of: providing a probe mold which accommodates a liquid probe solution in which quantum dots for the functional probe are mixed, and has a groove corresponding to the shape of the functional probe; bringing a cantilever into contact with the probe mold on which the groove is formed to correspond to the location of the functional probe; forming the functional probe on the cantilever by curing the probe solution accommodated in the groove in a state where the cantilever contacts the probe mold; and separating the cantilever from the probe mold.

Abstract: A gas turbine blade according to an embodiment of the present invention includes a turbine blade provided in a gas turbine; and a plurality of film coolers formed in a section from a leading edge to a trailing edge of the turbine blade, in which the film cooler includes a cooling channel through which cooling air is introduced and formed in an oval shape; and an outlet through which the cooling air passing through the cooling channel is discharged and extending from an extended end of the cooling channel toward an outer side thereof and formed in an oval shape.

Abstract: There is provided a process for preparing a composite material of an oxide crystal film and a substrate by forming a Y123 type oxide crystal film from a solution phase on a substrate using a liquid phase method, wherein problems such as cracking of the oxide crystal film, separation of the oxide crystal film from the substrate, and development of a reaction layer between the substrate and the solution can be minimized. The solvent for forming the solution phase uses either a BaO—CuO—BaF2 system or a BaO—CuO—Ag—BaF2 system, and when the substrate with a seed crystal film bonded to the surface is brought in contact with the solution to form (grow) the oxide crystal film on the substrate, the temperature of the solution is controlled to a temperature of no more than 850° C.

Abstract: There is provided a process for preparing a composite material of an oxide crystal film and a substrate by forming a Y123 type oxide crystal film from a solution phase on a substrate using a liquid phase method, wherein problems such as cracking of the oxide crystal film, separation of the oxide crystal film from the substrate, and development of a reaction layer between the substrate and the solution can be minimized. The solvent for forming the solution phase uses either a BaO—CuO—BaF2 system or a BaO—CuO—Ag—BaF2 system, and when the substrate with a seed crystal film bonded to the surface is brought in contact with the solution to form (grow) the oxide crystal film on the substrate, the temperature of the solution is controlled to a temperature of no more than 850° C.