Abstract: A slinger combustor includes; a first compressed air line connected to a compressor and configured to supply compressed air; a first fuel line connected to a fuel storage and configured to supply fuel; a rotation shaft configured to rotate and inject the fuel supplied from the first fuel line; a main combustion chamber configured to receive the fuel injected from the rotation shaft and receive the compressed air from the first compressed air line; and a sub-combustion chamber configured to selectively discharge a flame generated in an inner space of the sub-combustion chamber to the main combustion chamber.

Abstract: A fuel injection apparatus for a gas turbine includes a fuel supply pipe; a first manifold connected to the fuel supply pipe and comprising a nozzle through which fuel is sprayed; a second manifold at least partially surrounding the first manifold at a predetermined interval apart from the first manifold in a radial direction, the second manifold including: an air inlet through which a first portion of air is introduced into the second manifold; and a fuel outlet where the fuel sprayed through the nozzle collides with the air thereby forming mixed fuel; and a first swirler provided at a predetermined interval apart from the second manifold in the radial direction, the first swirler configured to swirl the air toward the air inlet and the fuel outlet.

Abstract: A core for casting a turbine blade to form at least one cooling passage in a wing portion of the turbine blade, wherein the wing portion includes a leading edge region and a trailing edge region, and has a streamlined cross-section, the core including: at least one of a first core unit having a shape corresponding to a cooling passage located at the leading edge region and a second core unit spaced apart from the first core unit and having a shape corresponding to a cooling passage located at the trailing edge region, wherein each of the first core unit and the second core unit includes: a plurality of extending portions extending in a longitudinal direction and located substantially parallel to one another; at least one curved portion connecting adjacent ends of the plurality of extending portions; and at least one through-portion located between the plurality of extending portions and having an empty space extending in a width direction of the wing portion.

Abstract: Provided herein is a swirler for a gas turbine. The swirler includes a support plate including an injection part to inject a fuel supplied from the outside, a support shaft connected to the support plate, a guide part connected to the support plate and the support shaft and configured to mix a fluid introduced via a side surface of the support plate with the fuel injected from the injection part and to guide the mixture in at least one of a first direction and a second direction, the first direction being a longitudinal direction of the support shaft and the second direction being a direction swirling the support shaft, and a cover housing spaced apart from the support plate and coupled to the guide part so as to form a transfer flow path of the fluid together with the guide part.

Abstract: An inlet guide vane assembly is provided. The inlet guide vane assembly includes a housing, a rotating shaft rotatably located in the housing, a vane portion connected to the rotating shaft, a bushing portion located between the rotating shaft and the housing, and an elastic portion located between the bushing portion and the rotating shaft.

Abstract: A fixing device for securing a thin-walled component according to an embodiment includes: a support; a pressing portion provided on the support and including: a pressure generator located at a center of the support; and a plurality of pressure transmitters arranged around the pressure generator and extending in a radial direction of the thin-walled component; and a plurality of elastic members connected to the plurality of pressure transmitters, wherein the plurality of pressure transmitters are configured to move the plurality of elastic members in the radial direction.

Abstract: An auxiliary power unit that can reduce a flow loss of gas includes: a compressor, a combustion chamber, a turbine, a turbine outlet, and a bypass duct, wherein the turbine outlet comprises an exhaust diffuser and a guide portion, wherein the bypass duct connects the compressor with the guide portion, wherein the guide portion is a channel for an air or gas and is extended radially from an outer circumferential surface of the exhaust diffuser and communicates with an inside of the exhaust diffuser via an opening, and wherein the exhaust diffuser has a first portion adjacent to a front end of the opening and a second portion adjacent to a rear end of the opening, and a radius of the second portion is larger than a radius of the first portion so that there is formed a step difference between the first portion and the second portion.

Abstract: There is provided a variable vane apparatus including: a housing portion; a plurality of vane gear portions configured to rotate and provided on the housing portion to be spaced apart from one another; a plurality of variable vane portions connected to the plurality of vane gear portions; a drive gear portion configured to transfer power to the plurality of vane gear portions; and a connection gear portion arranged between the plurality of vane gear portions and configured to transfer power amongst the plurality of vane gear portions.

Abstract: A combustor includes a combustion tube having a cylindrical shape with a combustion space where fuel is combusted and including an inlet through which the fuel is introduced, an outlet through which a gas generated when the fuel is combusted is discharged, and a protrusion protruding inward from a wall surface between the inlet and the outlet; an injection unit configured to inject fuel into the combustion tube through the inlet of the combustion tube; and an additional injection unit located on the protrusion of the combustion tube and configured to inject fuel into the combustion tube.

Abstract: A graphene synthesis chamber includes: a chamber case in which a substrate including a metal thin film is placed; a gas supply unit which supplies at least one gas comprising a carbon gas into an inner space of the chamber case; a main heating unit which emits at least one light to the inner space to heat the substrate; and at least one auxiliary heating unit which absorbs the at least one light and emits radiant heat toward the substrate.

Abstract: Provided are a graphene-based laminate, a method of preparing the same, and a transparent electrode and an electronic device each including the graphene-based laminate. The graphene-based laminate includes a substrate, a graphene layer including graphene and disposed on at least one surface of the substrate, and a metal oxide layer disposed on at least one surface of the graphene layer, wherein the metal oxide layer includes a metal oxide having a greater work function than that of the graphene, and the metal oxide layer includes the metal oxide in an amount of 1 ?g to 1 mg per unit area of 1 cm2 of the graphene layer.

Abstract: A fuel injection system of a gas turbine includes a first pilot nozzle injecting fuel in a first flow rate range, a second pilot nozzle injecting fuel in a second flow rate range that is greater than the first flow rate range, a main nozzle injecting fuel in a third flow rate range that is greater than the second flow rate range, a first valve opening or closing a first supply pipe fueling the second pilot nozzle, a second valve opening or closing a second supply pipe fueling the main nozzle, and a controller selectively opening any one of the first supply pipe and the second supply pipe or opening or closing both of the first supply pipe and the second supply pipe by reflecting a change in altitude and thus applying control signals to the first valve and the second valve.

Abstract: According to an aspect of the present invention, a turbine apparatus includes a shaft; a turbine disk provided on the shaft and having a plurality of protrusions protruding in a direction of the shaft; blades provided on the turbine disk; a support plate provided on the turbine disk and having a plurality of latching portions engaged with the plurality of protrusions; a plurality of first fixing blocks located between the plurality of latching portions; and a second fixing block located between the plurality of protrusions and fixed to the plurality of first fixing blocks, wherein a width of a space where the second fixing block is located, from among spaces between the plurality of protrusions, is less than a width of a space where the plurality of first fixing blocks are located, from among spaces between the plurality of latching portions.

Abstract: A graphene synthesis chamber includes: a chamber case in which a substrate including a metal thin film is placed; a gas supply unit which supplies at least one gas comprising a carbon gas into an inner space of the chamber case; a main heating unit which emits at least one light to the inner space to heat the substrate; and at least one auxiliary heating unit which absorbs the at least one light and emits radiant heat toward the substrate.

Abstract: A graphene synthesis chamber includes: a chamber case in which a substrate including a metal thin film is placed; a gas supply unit which supplies at least one gas comprising a carbon gas into an inner space of the chamber case; a main heating unit which emits at least one light to the inner space to heat the substrate; and at least one auxiliary heating unit which absorbs the at least one light and emits radiant heat toward the substrate.

Abstract: A compressor control system includes: a compressor; an inlet guide vane (IGV) arranged at an inlet of the compressor, and configured to adjust opening of the inlet based on a supplementary surge control signal or a performance control signal; an anti-surge valve (ASV) connected to an outlet of the compressor, and configured to prevent a surge based on a surge control signal; and a controller configured to generate the surge control signal for controlling the ASV when an operating point enters a surge control range, generate the supplementary surge control signal for controlling the IGV in an anti-surge mode when the operating point enters a supplementary surge control range set between the surge control range and a surge range, and generate the performance control signal for controlling the IGV in a performance mode until the operating point enters the surge control range.

Abstract: A graphene synthesis chamber includes: a chamber case in which a substrate including a metal thin film is placed; a gas supply unit which supplies at least one gas comprising a carbon gas into an inner space of the chamber case; a main heating unit which emits at least one light to the inner space to heat the substrate; and at least one auxiliary heating unit which absorbs the at least one light and emits radiant heat toward the substrate.

Abstract: A linear actuator having a free fall function. The linear actuator moves a piston-rod member back and forth using torque of a rotary motor. Here, the piston-rod member is disposed within a portion of a cylinder body to be movable back and forth. In the event of jamming in which the piston-rod member is stopped due to sticking between an operating nut and a screw member, the piston-rod member is caused to freely fall in a direction in which load is applied. This can consequently obtain the maximum stretched length of the piston-rod member, thereby providing safety in an emergency.

Abstract: According to an aspect of the present invention, there is provided a method of manufacturing a graphene film, the method including: preparing a catalyst metal having at least a surface on which graphene is formed; forming a support layer on the graphene; and isolating the graphene and the support layer from the catalyst metal by dipping the catalyst metal in an electrolytic solution perpendicularly to a liquid surface of the electrolytic solution when a voltage is applied to the catalyst metal.

Abstract: A diffuser for a compressor includes a body having a ring shape and including: a fluid inflow face extending along a radial direction of the diffuser; and a rim bent from the fluid inflow face; main vanes formed on the fluid inflow face and the rim to guide fluid; and at least one splitter vane disposed between adjacent main vanes of the main vanes to guide the fluid.