Abstract: A plasma electrode module, an underwater plasma discharge device including the plasma electrode module, and a water treatment system are provided. The plasma electrode module includes a conductive substrate including a plurality of holes, a ceramic layer surrounding a portion of the outer surface of the conductive substrate, and a plasma electrode disposed in each of the plurality of holes, wherein the plasma electrode has a multilayer structure in which a cylindrical ground portion, a fixed portion, and a discharge portion are sequentially stacked, the ground portion is in contact with the conductive substrate and plasma is generated on the discharge portion, and each of the plurality of holes has a diameter in a range of 1 mm to 10 mm.

Abstract: An airfoil cooling structure, an airfoil having the airfoil cooling structure, and a turbine blade/vane element including the airfoil are disclosed. The airfoil cooling structure includes a cooling path formed inside the airfoil and having a first surface and a second surface opposite to the first surface, and an additive manufactured (AM) feature disposed in the cooling path, manufactured by additive manufacturing, and including a plurality of column parts intersecting with each other so as to abut against the first surface and the second surface.

Abstract: A combined power plant is provided. The combined power plant includes a gas turbine configured to combust fuel to generate a rotating force, a boiler configured to heat water to generate steam, an ammonia decomposition apparatus configured to receive a combustion gas generated in the gas turbine to thermally decompose ammonia to generate a decomposed gas containing hydrogen, nitrogen, and a residual ammonia, a steam turbine configured to generate a rotating force using the steam generated in the boiler, and a decomposed gas supply line configured to supply the decomposed gas generated in the ammonia decomposition apparatus to a combustor of the gas turbine.

Abstract: A micro-mixer includes a plurality of fuel tubes through which air and fuel flow, a casing accommodating the plurality of fuel tubes therein, and a plurality of injection parts each formed as a pyramidal protrusion on one side of the casing and connected to a front end of the fuel tube to inject the air and the fuel, wherein each of the plurality of injection parts has an inclined injection hole formed obliquely with respect to an extension direction of the plurality of fuel tubes on at least one side of the pyramidal protrusion.

Abstract: A swirler with a fuel manifold, and a combustor and gas turbine including the same are provided. The swirler may include a swirler body disposed between an inner surface of a fuel nozzle and an outer surface of a center body, a fuel injection hole disposed on the swirler body, a fuel manifold formed in the swirler body, the fuel manifold being connected to a fuel channel disposed in the center body while communicating with the fuel injection hole, and a turbulence alleviator formed at a fuel inlet of the fuel manifold to alleviate creation of turbulence of fuel flowing from the fuel channel to the fuel manifold.

Abstract: A saturator, configured for use in a water treating apparatus, includes a chamber, in which a first flow path through which first fluid flows is formed, and a plurality of porous membranes disposed in the first flow path, a second flow path formed within the plurality of porous membranes, through which second fluid flows. The first fluid is dissolved in the second fluid, or the second fluid is dissolved in the first fluid. Accordingly, a contact area between the first fluid and the second fluid is enlarged, and thus, a dissolving speed increases.

Abstract: A turbine vane includes an airfoil having a leading edge and a trailing edge, an inner shroud disposed at one end of the airfoil to support the airfoil, and an outer shroud disposed opposite to the inner shroud at the other end of the airfoil to support the airfoil, wherein a corner part is formed at a portion where the airfoil and the inner shroud or the outer shroud meet, the corner part including a first round portion connected in an arc shape to the inner shroud or the outer shroud, a first inclined portion connected to the first round portion and outwardly extending in an inclined shape, and a second round portion connected to the first inclined portion and outwardly extending in an arc shape.

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: A nozzle, a combustor, and a gas turbine, which are capable of atomizing fuel efficiently, are provided. A fuel injection device for the combustor may include a plurality of guide channels connected to a pilot fuel passage through which fuel is supplied, an injection chamber connected to the plurality of guide channels, the fuel being merged in the injection chamber, and an injection hole formed at a tip of the injection chamber to inject the fuel, and the injection chamber may include a decompression space to drop a pressure therein.

Abstract: A sealing assembly and a turbomachine including the sealing assembly are provided. The sealing assembly includes a sealing body configured to be inserted into an insertion hole of a second component adjacent to a first component, and a sealing protrusion, formed on one circumferential side of the sealing body, protruding toward one circumferential direction from the sealing body and configured to be inserted into a sealing groove formed on the other circumferential side of a sealing body of the first adjacent sealing assembly, the sealing body of the first adjacent sealing assembly being adjacent to the sealing body in a circumferential direction.

Abstract: A leaf spring inserted between a sealing member installed between various components of a gas turbine to prevent an inflow and outflow of gases and a mating sealing member, and a sealing assembly including the same are proposed. The leaf spring includes a curved body section, a locking protrusion protruding in one direction at an end of the body section so as to be fitted into the locking groove of the sealing member, and a detachment-prevention protrusion protruding in a direction opposite to the locking protrusion and configured to comes into contact with one surface of the mating sealing member and prevent the locking protrusion from being detached from the locking groove when the body section is compressed by the sealing member and the mating sealing member.

Abstract: Disclosed herein is a nozzle for a combustor that burns fuel containing hydrogen, which includes a plurality of mixing tubes through which air and fuel flow, a multi-tube configured to contain and support the mixing tubes, a fuel tube formed inside the multi-tube and through which fuel flows, a tip plate coupled to a tip of the multi-tube, and a front plate spaced apart from the tip plate to define a cooling space.

Abstract: A combined power generation system includes a gas turbine, a heat recovery steam generator (HRSG) configured to heat feedwater using combustion gases discharged from the gas turbine and having a high-pressure section, a medium-pressure section, and a low-pressure section having different pressure levels, an ammonia decomposer decomposing ammonia with the combustion gases discharged from the gas turbine, a first exhaust gas line through which the exhaust gases discharged from the gas turbine are transferred to the HRSG, a second exhaust gas line through which the exhaust gases discharged from the gas turbine are transferred to the ammonia decomposer, a third exhaust gas line through which the exhaust gases discharged from the ammonia decomposer are transferred to the HRSG, and a decomposed gas transfer tube connecting the ammonia decomposer and the combustor to transfer decomposed gases generated with the decomposition of ammonia to the combustor.

Abstract: A combustor nozzle using fuel containing hydrogen, a combustor and gas turbine including the same are provided. The nozzle for a combustor configured to burn fuel containing hydrogen includes a fuel supply duct including a plurality of injection tubes through which air and fuel flow and a fuel passage through which fuel flows, a plurality of swirlers formed on a side surface of each of the plurality of injection tubes to guide air outside the injection tube to be introduced thereinto for swirling, and a plurality of fuel inlet holes formed radially through the injection tube to communicate with the fuel passage and allow fuel to flow through the fuel passage to the injection tube.

Abstract: A capacitive adsorption module assembly is proposed. The capacitive adsorption module assembly includes a plurality of capacitive adsorption modules, each having a disk-shaped spacer configured to form a flow path through which feed flows, a cation exchange membrane attached to any one of an upper surface and a lower surface of the spacer, a first electrode attached to the cation exchange membrane, an anion exchange membrane attached to the other of the upper surface and the lower surface of the spacer, and a second electrode attached to the anion exchange membrane, wherein the capacitive adsorption modules are vertically stacked such that adjacent capacitive adsorption modules share or contact the first electrode or the second electrode, and at least one first terminal and second terminal passing through the stacked modules being provided.

Abstract: A strut provided in an exhaust diffuser and having an airfoil-shaped cross-section is provided. The strut may include a cut portion configured to be formed in a trailing edge in a span direction. The cut portion is configured to provide a stepped portion in at least a portion of the trailing edge.

Abstract: A micro-mixer capable of effectively mixing compressed air supplied from a compressor to a combustor and fuel supplied from a fuel nozzle, and a combustor including the same are provided. The micro-mixer includes a mixing passage including an inlet and an outlet, a fuel supply passage extending from one inner wall to the other inner wall of the mixing passage, and a fuel supply port formed in the fuel supply passage to supply fuel to the mixing passage.

Abstract: An operating guide system of a plant utilizing coal gasification includes a performance analyzer for analyzing performance of the plant by analyzing gasifier performance and synthesis gas cooler performance during an operation of the plant; an operation guide generator for generating an operation guide indicating control values for the operation of the plant based on the performance analysis of the plant; an action guide generator for generating an action guide indicating control values for controlling the plant to prevent an abnormal situation predicted in the plant based on the performance analysis of the plant; and a fuel determiner for determining gasification suitability of an analysis target fuel selected by a user before the plant is started, the gasification suitability including basic suitability and suitability of slag behavior.

Abstract: A micro-mixer bundle assembly and a combustor and a gas turbine having the same are provided. The micro-mixer bundle assembly includes a plurality of micro-mixers, each of the plurality of micro-mixers including an inlet portion formed on one side and through which a first fluid is introduced and a feed hole formed in a circumferential wall and through which a second fluid is fed, wherein the first fluid introduced through the inlet portion and the second fluid fed through the feed hole are mixed to form a fluid mixture which is injected into a combustion chamber, and a plurality of micro-mixer bundles, each of the plurality of micro-mixer bundles including the plurality of micro-mixers arranged therein, wherein a cross-sectional shape of an outlet of the micro-mixers disposed in one of the micro-mixer bundles is different from a cross-sectional shape of an outlet of the micro-mixers disposed in the other micro-mixer bundles.

Abstract: An apparatus for disassembling and assembling a lower vane carrier and a method for disassembling and assembling the lower vane carrier by using the apparatus are proposed. The apparatus includes a rolling jig that is mounted on the lower vane carrier mounted inside a lower turbine casing, a bolt member that passes through a region where the rolling jig and the lower vane carrier are in contact with each other, and a block member mounted adjacent to the bolt member and configured to prevent the bolt member from being separated.