Abstract: Embodiments of the present disclosure provide a blade-stator system and the vertical take-off and landing flight apparatus comprising the blade-stator system, the blade-stator system including a duct disposed inside a flight body, upper and lower sides of the duct being open, and an inside of the duct being hollow; a blade assembly installed rotatably inside the duct and including a blade body of which an angle is changeable; a stator assembly connected to the blade assembly and the duct, supporting the blade assembly, and rotatable by a predetermined angle; a controller electrically connected to the blade assembly and the stator assembly and configured to control driving of the blade body and the stator assembly, wherein the angle of the stator assembly is changed in response to receiving an electrical signal from the controller so as to be interlocked with a change of the angle of the blade body.

Abstract: A solenoid valve having an explosion-proof structure, a fuel feeding system, and a method of manufacturing the solenoid valve having an explosion-proof structure are provided. The solenoid valve having an explosion-proof structure includes: a body including a channel through which a fluid flows; a housing connected to the body and having one surface opened; a solenoid assembly arranged inside the housing and electrically connected to a controller; an armature, at least a portion of which is arranged in the channel and which opens or closes the channel by moving relative to the solenoid assembly by a magnetic field generated by the solenoid assembly; and a cover plate arranged on the one surface of the housing to face the armature.

Abstract: A fuel supply device includes: an outer tubular member; an inner tubular member inside the outer tubular member; and a flow distribution portion on an inner surface of the outer tubular member or an outer surface of the inner tubular member, wherein the flow distribution portion includes first and second distribution wall portions arranged apart from one another in an axial direction of the inner tubular member, the first distribution wall portion includes first individual wall portions spaced apart from one another along a first circumference of the inner tubular member, the second distribution wall portion includes second individual wall portions spaced apart from one another along a second circumference of the inner tubular member, at least some of the first individual wall portions are arranged to face spaces between at least some of the second individual wall portions, respectively, in the axial direction of the inner tubular member.

Abstract: An exhaust duct assembly includes: a case having an inner space; a duct inserted into an inner space of the case, the duct including an inlet through which an exhaust gas is introduced, and an exhaust port through which the exhaust gas is exhausted; a stiffener configured to attach the duct to the case; and a connector disposed on the exhaust port, wherein the duct, the stiffener and the connector are welded to one another such that at least a portion of each of the duct, the stiffener and the connector overlaps one another in a first direction.

Abstract: A fuel supply device includes: an outer tubular member; an inner tubular member inside the outer tubular member; and a flow distribution portion on an inner surface of the outer tubular member or an outer surface of the inner tubular member, wherein the flow distribution portion includes first and second distribution wall portions arranged apart from one another in an axial direction of the inner tubular member, the first distribution wall portion includes first individual wall portions spaced apart from one another along a first circumference of the inner tubular member, the second distribution wall portion includes second individual wall portions spaced apart from one another along a second circumference of the inner tubular member, at least some of the first individual wall portions are arranged to face spaces between at least some of the second individual wall portions, respectively, in the axial direction of the inner tubular member.

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: Provided are an exhaust duct, an exhaust duct assembly, and an aircraft using the exhaust duct. The exhaust duct has a structure that enables combustion gas to be diverged and discharged from an inlet end to a first outlet end and a second outlet end at respective sides of the exhaust duct. The exhaust duct includes a first housing including a first body forming an outer wall of the inlet end, and further includes second bodies respectively extending on respective sides from the first body and respectively forming the first outlet end and the second outlet end; a second housing spaced apart from the first body, forming an inner wall of the inlet end, and extending curvedly toward the second bodies; and a connection housing connecting the first housing to the second housing and including at least one recess portion recessed toward the inlet end.

Abstract: Provided are an exhaust duct, an exhaust duct assembly, and an aircraft using the exhaust duct. The exhaust duct has a structure that enables combustion gas to be diverged and discharged from an inlet end to a first outlet end and a second outlet end at respective sides of the exhaust duct. The exhaust duct includes a first housing including a first body forming an outer wall of the inlet end, and further includes second bodies respectively extending on respective sides from the first body and respectively forming the first outlet end and the second outlet end; a second housing spaced apart from the first body, forming an inner wall of the inlet end, and extending curvedly toward the second bodies; and a connection housing connecting the first housing to the second housing and including at least one recess portion recessed toward the inlet end.

Abstract: Provided is a method of inspecting a growth quality of a graphene layer of a graphene-grown copper foil obtained by growing the graphene layer on a copper foil layer by chemical vapor deposition (CVD), the method including reacting oxygen or water molecules with the copper foil layer via a defect portion of the graphene layer, partitioning an entire region of the graphene-grown copper foil into partial regions, sequentially obtaining images of the partial regions, detecting, with respect to each of the images of the partial regions, an oxidized region where the copper foil layer is oxidized, and setting the oxidized region as a graphene defect region, and obtaining a ratio of an area of the graphene defect region to an entire area of each of the images of the partial regions.

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.

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: 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.