Abstract: The present disclosure relates to a dissolved air flotation system using ambient air, and more particularly, to a dissolved air flotation system that is capable of allowing ambient air to be introduced in front of a pump to generate micro air bubbles with the water discharged from the pump, so that the ambient air may be used instead of compressed air.

Abstract: A method of assembling and disassembling a gas turbine carries out various disassembly and reassembly processes depending on circumstances. In one process, a first-stage blade assembly and a first-stage vane assembly of a turbine section are disassembled from a gas turbine by sequential steps of disassembling a combustor assembly; disassembling a first-stage vane assembly; and disassembling a first-stage blade assembly. In another process, a fourth-stage blade assembly of a turbine section is disassembled from a gas turbine by sequential steps of disassembling a diffuser loading slot from a rear diffuser; and disassembling a fourth-stage blade assembly from a turbine disk. In another process, a rear bearing assembly of a turbine section is disassembled from a gas turbine by sequential steps of disassembling a rear diffuser cover from a rear diffuser; and supporting one end of a rotor shaft and disassembling a rear bearing from a rotor shaft support.

Abstract: A cyclone type liquid-vapor separator includes a chamber including: an internal space wherein the treatment liquid introduced into the internal space is depressurized and evaporated; a vapor outlet formed on a top of the chamber and through which vapors generated through the evaporation is discharged; and a concentrated liquid outlet formed on a bottom of the chamber and through which the concentrated treatment liquid is discharged; an inlet part coupled to a side surface of the chamber in a tangent line direction of an inner peripheral surface of the chamber, the treatment liquid introduced into the chamber is turned in the form of vortexes along the inner peripheral surface of the chamber, and at least one partition wall disposed in an area between the inlet part and the vapor outlet of the internal space of the chamber and protruding from the inner peripheral wall of the chamber to prevent mist contained in the vapors from moving upwardly.

Abstract: A sealing assembly for a gas turbine includes a plurality of sealing housings interposed between adjacent turbine disks of a multistage turbine, each sealing housing coupled to a turbine vane of a corresponding stage; and a sealing plate unit installed between adjacent sealing housings to seal a gap between the adjacent sealing housings. Each sealing housing includes a horizontal housing segment and a pair of vertical housing segments each having a lower end connected to horizontal housing segment. The sealing plate unit includes a horizontal plate installed in the horizontal housing segment, and a pair of vertical plates respectively installed in the pair of vertical housing segments. The horizontal housing segment includes a horizontal slot facing an adjacent sealing housing to receive the horizontal plate, and each vertical housing segment includes a vertical slot facing an adjacent sealing housing to receive a corresponding vertical plate.

Abstract: An apparatus for controlling a wind power generator unit includes a deviation detection unit to detect an angular deviation between windward and a current rotation direction of a nacelle after a wind power generator is installed so as to face the windward, and a control unit to receive data detected by the deviation detection unit and to control a brake state and a yawing state of a yaw brake unit, wherein when the nacelle rotates out of a preset deviation range, the control unit temporarily releases frictional force of a brake pad coming into close contact with a disk so as to control a brake operation state of the yaw brake unit.

Abstract: A steam turbine includes a platform (100) including a front part on an upstream side of the platform, a rear part opposite the front part, and a side part extending between the front part and the rear part; a vane (200) provided on an upper surface of the platform, the vane including a leading edge facing the front part and a trailing edge extending from the front part via the side part to the rear part; and a dovetail (300) formed integrally with the platform. The dovetail slant angle (DSA) is created when the horizon is drawn at an angle formed by a dovetail center axis (DCA) of the dovetail and a rotation axis (RA), and the stagger angle (SA) corresponds to an angle formed by the leading edge and the trailing edge of the vane. The dovetail slant angle is less than the stagger angle.

Abstract: A rotor, installable in a casing of a turbine and configured to be rotated by a flow of combustion gas and cooled by a flow of compressed air, has an improved structure to keep a tip clearance constant during operation of a gas turbine. The rotor includes a disk having an outer circumferential surface; a platform installed on the outer circumferential surface of the disk; and a blade airfoil formed on an upper surface of the platform, the blade airfoil having an airfoil end situated opposite to the platform, the airfoil end having an upstream side and a downstream side with respect to a flow direction of the combustion gas, wherein the blade airfoil is formed so that, when the rotor is installed in the casing, the downstream side of the airfoil end is closer to an inner surface of the casing than the upstream side of the airfoil end.

Abstract: Disclosed herein is a disk assembly for a gas turbine compressor, which comprises a partition wall formed to partition a space between disks for a gas turbine compressor to optimize a cooling fluid path.

Abstract: A combustion duct assembly for a gas turbine includes a liner, an annular spring seal and a transition piece. The annular spring seal is outwardly convex and coupled to an outer face of the downstream side of the liner. The transition piece has includes an inner wall and an outer wall that surrounds the inner wall. The convex part of annular spring seal is operable to elastically engage the inner wall of the transition piece. An end portion of the downstream side of the annular spring seal is fixed to the line. The annular spring seal includes a plurality of through holes formed in an upstream side of a point where the annular spring seal comes into contact with the inner wall. The liner includes a plurality of vent holes formed in an inner area surrounded by the spring seal.

Abstract: A rotor disc sealing device, which seals a leakage gap generated in a space between facing surfaces of rotor discs to be coupled to one another, can include: slots formed in the facing surfaces of the rotor discs; a sealing plate formed of a hard material and inserted into the slots; and an auxiliary plate formed of a soft material and coupled to one side of the sealing plate.

Abstract: A rotor and a generator including the same are capable of reducing a pressure loss of a cooling fluid, of increasing a flow rate of a cooling fluid flowing to a rotor coil, and of having improved cooling performance. The rotor includes a rotor shaft; a rotor coil wound around the rotor shaft; a rotor coil protection ring surrounding the rotor coil at one end of the rotor shaft and being spaced apart from the rotor shaft to form a clearance space between the rotor coil protection ring and the rotor shaft; and a fan coupled to the rotor shaft opposite the rotor coil, interposing the rotor coil protection ring, to blow a cooling fluid toward the rotor coil, at least part of the blown cooling fluid flowing to the rotor coil being guided through the clearance space by surfaces of the rotor coil protection ring.

Abstract: A particle removal device for a gas turbine includes a suction inlet formed in one side of a region below a first vane so as to introduce a compressed air discharged from a compressor, a combusted gas generated in a combustor flowing through the first vane, an acceleration flow path for accelerating the compressed air introduced through the suction inlet so as to separate particles from the compressed air by centrifugal force, a particle collector provided at one end of the acceleration flow path so as to collect the separated particles, and a particle discharger communicating with the particle collector so as to discharge the collected particles to an outside.

Abstract: A gas turbine and a method for replacing a bearing thereof to easily adjust a clearance of a bearing housing and a bearing covering a tie rod, such that the bearing can be easily replaced is disclosed.

Abstract: An energy storage system includes one or more new and renewable energy power stations generating power with a new or renewable energy source, and an energy storage facility including a plurality of energy storage apparatuses to be charged by one of an external power grid supplying power to a power load and the one or more new and renewable energy power stations, and to be discharged to supply the power to the power load, wherein the plurality of energy storage apparatuses have different charging and/or discharging periods.

Abstract: A flow guide structure for a casing flange, and a casing and a turbomachine having the same, include a flange portion connecting an upper casing and a lower casing and a flow guide positioned at the flange portion to guide fluid to flow close to the flange portion, whereby steam flow resistance is reduced around an inner casing flange of a turbine and the steam flow is smoothed.

Abstract: A turbine blade, installed on a rotor disk of a turbine and configured to rotate the turbine by a force of flowing gas, includes a root configured to be coupled to the rotor disk; a platform integrally formed with an upper portion of the root, the platform having opposite sides respectively extending in an axial direction of the rotor disk; an airfoil integrally formed with an upper portion of the platform; and an angel wing configured to be removably coupled to each of the opposite sides of the platform. When coupled, the angel wing protrudes from the platform in the axial direction. The turbine blade, which may be included in the turbine of a gas turbine, is capable of improving the castability and adjusting a clearance between an airfoil and a turbine rotor disk such that space between the airfoil and the turbine rotor disk can be reliably sealed.

Abstract: A apparatus may extract temperature for each region of a feed water and steam system of a thermoelectric power plant with respect to a combustible combination including one or more combustibles, extract one or more vectors for each region from the temperatures extracted for each region, generate one or more combustible clusters, each cluster including one or more combustible combinations having similar properties from the extracted vectors, and extract a characteristic component of a combustible combination that increases or decreases a boiler performance index from among one or more combustible combinations included in the one or more combustible clusters.

Abstract: Disclosed herein is a system for cooling a gas turbine. The system for cooling a gas turbine cools a turbine disk unit by individually supplying cooling air to each of a plurality of turbine disks.

Abstract: An exhaust diffuser that is mounted at an outlet of a gas turbine to eject exhaust gas to the outside and includes hollow cylindrical internal diffuser guide and external diffuser guide. Further, the exhaust diffuser includes struts disposed between the internal diffuser guide and the external diffuser guide to space the internal diffuser guide and the external diffuser guide at a predetermined distance from each other, ejection areas formed on an outer side of the internal diffuser guide and having ejection holes for ejecting exhaust gas in a flow direction of exhaust gas, and suction areas formed on the outer side of the internal diffuser guide, disposed close to the ejection areas, and having suction holes for suctioning exhaust gas in the opposite direction to a flow direction of the ejected exhaust gas.

Abstract: The magnetic field communication system for measuring the flutter of the turbine blade includes a sensor module placed on an outer surface of the turbine blade to sense a signal on the flutter of the turbine blade; an interface converting the signal on the flutter sensed by the sensor module into a magnet field signal to transmit it to the outside of a casing surrounding the turbine blade; and an adaptor receiving the magnetic field signal to generate a power source of the system, and analyzing the magnetic field signal to determine the degree of the flutter of the turbine blade.