Abstract: Provided are a compound represented by Formula 24, an organic electric element comprising a first electrode, a second electrode, and an organic material layer formed between the first electrode and the second electrode and comprising the compound of Formula 24, and an electronic device thereof, the element and device having improved driving voltage, luminous efficiency and lifetime from the employment of the compound.

Abstract: Disclosed are an apparatus and a method for compensating for a phase delay of a resolver signal. The apparatus includes an input/output interface, and a processor connected to the input/output interface, wherein the processor receives a command signal and the resolver signal through the input/output interface, calculates a delay time of the resolver signal with respect to the command signal based on the command signal and the resolver signal, calculates a compensation time based on the delay time, and compensates the command signal based on the compensation time.

Abstract: A multiple and broadband stealth structure comprises a radar absorption unit that absorbs broadband microwave, a low-frequency transmission filter unit that is stacked on an upper portion of the radar absorption unit, and an infrared radiation unit that is combined with the low-frequency transmission filter unit to selectively emit infrared ray, thereby selectively controlling the infrared emissivity of the surface to emit infrared radiation only through an atmospheric absorption window with a low infrared transmittance and to avoid the infrared detection system.

Abstract: Proposed is an airfoil wing-shaped aircraft including a body having a wing-shaped longitudinal cross-section and having an upper surface on which a shape of a concave curvature-surface portion is formed along a center axis in a streamwise direction, a fluid inlet being formed in each of the opposite lateral sides of a leading portion of the body, and a fluid output being formed in each of the opposite lateral sides of a tail portion of the body, wherein a duct connects the fluid inlet and the fluid outlet to each other.

Abstract: The present invention relates to a gas turbine blade having a shelf squealer tip, the gas turbine blade including an airfoil-shaped blade housing, and a squealer tip extending from an edge portion of a tip surface that is an end surface of the blade housing, in which the squealer tip is formed only on a part of the edge portion of the tip surface. According to the present invention, it is possible to maximize film-cooling performance on the tip surface and additionally reduce an aerodynamic loss by suppressing high-temperature main flow reattachment and swirl flow generation on the tip surface.

Abstract: Provided is a gas turbine vane and blade assembly in which lattice structures are installed between an impingement plate and an effusion plate. The gas turbine vane and blade assembly is capable of enhancing cooling efficiency in an impingement/effusion cooling technique. In addition, the gas turbine vane and blade assembly can be manufactured using an additive manufacturing technique, and the lattice structures are capable of replacing supports that are used during an additive manufacturing process, and improving not only structural rigidity and stability but also cooling performance.

Abstract: Proposed is a 3-dimensional resonant structure-based infrared selective emitter capable of maximizing the infrared selective radiation function by broadening the emissivity in the non-detection bands with resonance phenomena between multiple resonator units at the same time as securing infrared camouflage and energy dissipation-resultant surface thermal stability by reducing the emissivity significantly in the infrared detection band and selectively dissipating energy to the non-detection bands.

Abstract: A turbine blade having cooling holes formed therein and a turbine including the same are provided. The turbine blade includes an airfoil having a leading edge and a trailing edge formed thereon and a cooling passage defined for flow of a cooling fluid therethrough, and a cooling hole configured to communicate between the cooling passage and outside in the airfoil and having an inlet and an outlet, wherein the cooling hole includes an expanded portion and a grooved portion formed in the outlet, the grooved portion being recessed from the expanded portion toward the trailing edge.

Abstract: The present invention provides an infrared selective emitter that can selectively emit infrared energy in a desired wavelength band, can be easily applied to a curved surface due to its flexible properties, and can protect the formed surface structure of the infrared selective emitter from external stimuli such as friction, thereby improving wear resistance and maximizing the function of infrared selective emission.

Abstract: The present invention provides an infrared selective emitter in which since infrared energy can be emitted in a desired wavelength band by adjusting a metamaterial having a repeating structure on a plane, infrared camouflage is possible by attaching to the surface of the shape of an object to be camouflaged, and at the same time, the infrared selective emitter has flexible characteristics that can be applied to curved surfaces without limitations on the shape of an object.

Abstract: A cooling structure for a trailing edge of a turbine blade is provided. The cooling structure for the trailing edge of the turbine blade comprising an airfoil shaped blade part including a leading edge, a trailing edge, a pressure surface and a suction surface connecting the leading edge and the trailing edge, and a cavity channel formed in the blade part and through which a cooling fluid flows, the cooling structure including slots and lands arranged alternately on the trailing edge along a span direction of the pressure surface by cutting a portion of the pressure surface, the slots communicating with the cavity channel and defined by adjacent lands where the pressure surface remains, wherein a pin-fin structure is disposed in the cavity channel on an upstream side of the slot, and wherein the cooling fluid is introduced through a micro-channel formed inside the pin-fin structure and is discharged through film cooling holes formed in the pressure surface.

Abstract: An impingement cooling structure is provided. The impingement cooling structure includes a flow channel formed between a first wall and a second wall facing the first wall, a plurality of impingement cooling holes disposed in the first wall such that the plurality of impingement cooling holes are spaced apart from each other along the flow channel, and a flow diverter convexly protruding from a surface of the second wall in each space between injection axes of the plurality of impingement cooling holes.

Abstract: Provided is a gas turbine vane and blade assembly in which lattice structures are installed between an impingement plate and an effusion plate. The gas turbine vane and blade assembly is capable of enhancing cooling efficiency in an impingement/effusion cooling technique. In addition, the gas turbine vane and blade assembly can be manufactured using an additive manufacturing technique, and the lattice structures are capable of replacing supports that are used during an additive manufacturing process, and improving not only structural rigidity and stability but also cooling performance.

Abstract: A turbine blade having cooling holes formed therein and a turbine including the same are provided. The turbine blade includes an airfoil having a leading edge and a trailing edge formed thereon and a cooling passage defined for flow of a cooling fluid therethrough, and a cooling hole configured to communicate between the cooling passage and outside in the airfoil and having an inlet and an outlet, wherein the cooling hole includes an expanded portion and a grooved portion formed in the outlet, the grooved portion being recessed from the expanded portion toward the trailing edge.

Abstract: An airfoil having a leading edge and a trailing edge is provided. The airfoil includes a rear cooling path connected to the trailing edge to discharge air to the trailing edge, a plurality of cooling fins formed in the rear cooling path, and a flow guide rod connecting the cooling fins to support the cooling fins, wherein each of the plurality of cooling fins includes an upper fin portion protruding upward from an upper portion of the flow guide rod, a lower fin portion protruding downward from a lower portion of the flow guide rod, and an intermediate fin portion inserted through the flow guide rod.

Abstract: An airfoil having a leading edge and a trailing edge is provided. The airfoil includes a rear cooling path connected to the trailing edge to discharge air to the trailing edge, a plurality of cooling fins formed in the rear cooling path, and a flow guide rod connecting the cooling fins to support the cooling fins, wherein each of the plurality of cooling fins includes an upper fin portion protruding upward from an upper portion of the flow guide rod, a lower fin portion protruding downward from a lower portion of the flow guide rod, and an intermediate fin portion inserted through the flow guide rod.

Abstract: A cooling structure for a trailing edge of a turbine blade is provided. The cooling structure for the trailing edge of the turbine blade comprising an airfoil shaped blade part including a leading edge, a trailing edge, a pressure surface and a suction surface connecting the leading edge and the trailing edge, and a cavity channel formed in the blade part and through which a cooling fluid flows, the cooling structure including slots and lands arranged alternately on the trailing edge along a span direction of the pressure surface by cutting a portion of the pressure surface, the slots communicating with the cavity channel and defined by adjacent lands where the pressure surface remains, wherein a pin-fin structure is disposed in the cavity channel on an upstream side of the slot, and wherein the cooling fluid is introduced through a micro-channel formed inside the pin-fin structure and is discharged through film cooling holes formed in the pressure surface.

Abstract: An impingement cooling structure is provided. The impingement cooling structure includes a flow channel formed between a first wall and a second wall facing the first wall, a plurality of impingement cooling holes disposed in the first wall such that the plurality of impingement cooling holes are spaced apart from each other along the flow channel, and a flow diverter convexly protruding from a surface of the second wall in each space between injection axes of the plurality of impingement cooling holes.

Abstract: Proposed is an airfoil wing-shaped aircraft including a body having a wing-shaped longitudinal cross-section and having an upper surface on which a shape of a concave curvature-surface portion is formed along a center axis in a streamwise direction, a fluid inlet being formed in each of the opposite lateral sides of a leading portion of the body, and a fluid output being formed in each of the opposite lateral sides of a tail portion of the body, wherein a duct connects the fluid inlet and the fluid outlet to each other.

Abstract: A technique of adjusting absorptivity of radar waves and emissivity of infrared waves by controlling the waves of the radar and infrared regions using a structure formed of a meta-material. A composite structure for controlling absorptivity and emissivity includes: a first anti-detection unit; and a second anti-detection unit stacked on the first anti-detection unit, wherein the first anti-detection unit is an absorber for absorbing electromagnetic waves of a first range input from an outside of the first anti-detection unit, and the second anti-detection unit is a selective emitter for selectively blocking emission of electromagnetic waves of a second range and selectively allowing emission of electromagnetic waves of a third range among electromagnetic waves that can be emitted to an outside of the second anti-detection unit.