Yonsei University

Doosan Enerbility Co., Ltd.

Other

Hyung Hee Cho

Seungyeong Choi

Hee Seung Park

Taehyun Kim

Beom Seok Kim

Chang Yong Lee

Juyeong Nam

Ho Seop Song

Hwanseong Lee

Joon-Soo Lim

Tae Hyun Kim

Yong Jin Kim

Taeil Kim

Jun Su Park

Kyung Min Kim

Jung Shin Park

Seon Ho Kim

Ki Don Lee

Su Won Kim

Ye Jee Kim

Ki Hoon Yang

Namkyu Lee

Joon-soo Lim

Minho Bang

Taedoo Yoon

Ju Yeong Nam

Maroosol Yun

Injoong Chang

Nam Kyu Lee

Hyung Mo Bae

Jihyuk Kim

In Joong Chang

Heeseung Park

Jeong Ju Kim

Minjoo Hyun

JeongJu Kim

Ho Kyu Moon

Min Ho Bang

Seok Min Choi

Dong Il Shim

Hoanju Yoo

Donghwi Lee

Geehong Choi

Hokyu Moon

Ji-Yeul Bae

Taehwan Kim

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.

Flexible infrared selective emitter and manufacturing method thereof

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.

Infrared selective emitter with improved wear resistance

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.

Airfoil wing-shaped aircraft

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.

Gas turbine vane and assembly in lattice-structure cooling type

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.

Turbine blade and turbine including the same

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.

Cooling structure for trailing edge of turbine blade

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.

Impingement jet cooling structure with wavy channel

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.

Turbine airfoil and turbine including same

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.

Composite structure for controlling absorptivity of radar and emissivity of infrared regions

Provided are a carrier for a dry adsorbent for carbon dioxide, including spherical silica whose surface is engraved in the form of nanowires, and a method for preparing the same. Although the carrier for a dry adsorbent for carbon dioxide including spherical silica that has nanowires on the surface thereof has a very non-uniform shape, it serves better as a host structure adsorbing carbon dioxide as compared to the conventional carrier for a carbon dioxide adsorbent, and thus may be used for a host-guest adsorbent applicable to a fluidized bed process. In addition, the method for preparing a carrier for a carbon dioxide adsorbent provides nanowire-coated silicon spheres having an increased surface roughness and an increased surface area, thereby providing increased carbon dioxide capturing efficiency. Further, since the method for forming nanowires is simple, it is easy to carry out mass production without any separate process, thereby providing excellent cost efficiency.

Carrier for dry adsorbent for carbon dioxide including spherical silica whose surface is engraved in the form of nanowires and method for preparing the same

The present invention relates to a gas turbine device using a supercritical fluid as a cooling fluid, the gas turbine device having a compressor for compressing air, a combustor for burning the air emitted from the compressor and fuel, and a turbine driven by the burned gas emitted from the combustor, wherein the gas turbine device includes cooling passages formed in the combustor and the turbine, along which the supercritical fluid as a cooling fluid flows to allow the combustor and the turbine to be cooled.

Gas turbine device using supercritical fluid as cooling fluid

Growing community of inventors

Seoul, South Korea

Hyung Hee Cho