Abstract: A gas turbine includes a housing in which combustion gas flows; a rotor section rotatably installed in the housing; and a turbine blade configured to rotate the rotor section by receiving a rotational force from the combustion gas and to be cooled by a cooling fluid flowing in a cooling path, the turbine blade including a tip side provided with tip cooling holes through which a portion of the cooling fluid in the cooling path is discharged from the turbine blade. The tip cooling holes include a first tip cooling hole formed in a pressure surface of the turbine blade, and a second tip cooling hole formed in a suction surface of the turbine blade. The gas turbine can easily maintain a gap between the tip side of the turbine blade and an inner circumferential surface of the housing, preventing degradation of the turbine blade efficiency.

Abstract: A transition piece can include: an inner transition piece providing a gas channel; a plurality of cooling rings disposed on the inner transition piece; a plurality of film holes formed on the inner transition piece; and a plurality of impingement holes formed on the plurality of cooling rings, wherein the plurality of film holes are arranged to correspond to the plurality of cooling rings. Each of the plurality of cooling rings includes a cavity such that the plurality of film holes connect the cavity to the gas channel and the plurality of impingement holes connect the cavity to an outside of the inner transition piece.

Abstract: A wind farm supervision monitoring method includes: displaying, by a user interface (UI) unit, a location of the site server on a map along with a dashboard menu, a navigation menu, and an alarm & event menu; collecting, by a data collection unit, data about status monitoring of each wind turbine from the site server; detecting, by an abnormality status detection unit, an abnormality status of each wind turbine based on the data about the status monitoring of each wind turbine and issuing an alarm based on the detecting the abnormality status; providing, by a supervision unit, a turbine operation status of each wind turbine using the dashboard menu, managing operation and maintenance; and establishing, by the supervision unit, an operation and maintenance plan for the detected abnormality status of the wind turbine.

Abstract: A gas turbine includes a housing; a rotor rotatable by a fluid flowing through the housing; a bearing for rotatably supporting the rotor; and a support structure configured to support the bearing with respect to the housing. The support structure includes an inner casing accommodating the bearing; an outer casing fastened to the housing; and a strut extending between the inner and outer casings, and at least one of the inner casing and the outer casing includes a diaphragm that is deformable in a radial direction of the rotor. Each casing includes a strut root connected to the strut, a strut platform surrounding the strut root and being formed as the diaphragm; and a main body surrounding the strut platform. Damage to the support structure due to thermal expansion can be prevented, and the support structure can be easily designed to avoid resonance between the support structure and the rotor.

Abstract: A gas turbine blade has a trench part of a film cooling unit for cooling a blade part that is formed at a tip of a film cooling hole part. As a result, cooling efficiency of the blade can be improved since the blade part is sufficiently cooled even during introduction of a large amount of cooling air, durability of the blade can be increased by inhibiting the blade from being damaged due to hot gas since the trench part is formed to have a minimum width, and efficiency of a gas turbine can be increased by an improvement in film efficiency.

Abstract: Provided is a combustor of a gas turbine including a combustion liner where combustion occurs, a transition piece connected to the combustion liner to allow combustion gases to pass through, and a honeycomb seal ring disposed between the combustion liner and the transition piece to prevent compressed air from leaking through a gap between the combustion liner and the transition piece. The honeycomb seal ring is inserted into the exit portion of the combustion liner to prevent compressed air from leaking when the combustion liner and the transition piece are coupled with each other.

Abstract: Provided is a sealing structure for sealing a peripheral area of a fan of a generator.

Abstract: Disclosed is a bioreactor for treating sewage comprising an aerobic tank including a mixing cell for receiving sewage to be supplied from an inlet and mixing the sewage with activated sludge and an aerobic reactor tank in which the activated sludge adsorbs organic substance existing in the sewage; a backwashing cartridge filter for removing floc resulting from growth of the activated sludge adsorbing the organic substance; and an anaerobic tank for carrying out a denitrification process for denitrifying treated water flowed through the backwashing cartridge filter using anaerobic ammonium oxidation (anammox) bacteria wherein the backwashing cartridge filter allows the sewage discharged from the aerobic tank to pass through the cartridge filter and separates the floc and the treated water using difference in size between the floc contained in the sewage and pores in the cartridge filter, and wherein foreign matter adsorbed on the cartridge filter is easily removed by means of washing water to be injected into

Abstract: A fiber filtering apparatus includes: an enclosure including an upper box and a lower box communicating with the upper box; a strainer installed in the upper box along a longitudinal direction; a plurality of fiber yarn media configured to be fixed to upper and lower fixing means each coupled to upper and lower parts of the strainer; a plurality of fiber ball media configured to be embedded in the lower box to form a second filtering layer; a first pipe configured to be formed on one side wall on the lower part of the upper box and introduced with raw water during filtration and drain backwashing water during backwashing; and a second pipe formed on one side wall on a lower part of the lower box and drain filtered water during the filtration and introduced with washing water during the backwashing.

Abstract: A turbine blade in an industrial gas turbine includes a blade surface to be cooled by a film of cooling fluid, a plurality of cooling holes on the blade surface through which cooling fluid flows, each cooling hole including an inlet portion and an outlet portion, and a trench on the blade surface surrounding at least one outlet portion of the cooling hole, the trench extending in an axial direction and a radial direction from the outlet portion of the cooling hole, wherein the outlet portion of the cooling hole has a shape configured to generate a first stage diffusion of the cooling fluid and a wall of the trench is positioned in the axial direction from the outlet portion of the cooling hole to generate a second stage diffusion of the cooling fluid, thereby forming the film of cooling fluid.

Abstract: A turbine vane of a multi-stage arrangement of turbine vanes cooled by compressed air supplied from a compressor of a gas turbine has an improved structure capable of preventing an unintended removal of cooling holes along with the intended removal of an excess portion of a shroud. The turbine vane includes an airfoil configured to be installed on an inner peripheral surface of a turbine casing in which combustion gas supplied from a combustor flows and to guide combustion gas from a front-stage blade to a rear-stage blade; and a pair of shrouds coupled to the airfoil, at least one of the shrouds having a plurality of cooling holes formed toward the airfoil, wherein the plurality of cooling holes are formed along an imaginary line that is spaced apart from and surrounds the airfoil.

Abstract: A nozzle, a combustor, and a gas turbine are capable of uniformly pre-mixing fuel and air. The nozzle includes an integrated swirler comprising an inner tube configured to provide a first pre-mixing passage through which pre-mixed air flows, an outer tube configured to partially enclose the inner tube and form an outer fuel passage through which fuel flows, and a plurality of vanes coupled with the outer tube, each vane having an exhaust hole through which fuel exits; a fuel injector including an inner fuel passage through which fuel flows and being configured to be inserted into the inner tube of the integrated swirler; and a peg having an outer surface in which are formed a plurality of injection holes communicating with the inner fuel passage, the injection holes configured to inject the fuel of the inner fuel passage into the first pre-mixing passage.

Abstract: A noise reducing wall system is provided. The noise reducing wall system includes first and second board layers facing in parallel with each other along a longitudinal direction thereof, a heat insulation member surrounded by the first and second board layers, and a stud connection structure that fastens the first and second board layers using a stud bolt passing through the heat insulation member to connect the first board layer and the second board layer. The stud bolt connects the first and second board layers in a thickness direction and has a bent portion extending in the longitudinal direction and disposed at an intermediate point in the thickness direction.

Abstract: A compressor, which is mounted to a gas turbine and generates high temperature and high pressure compressed air and supplies the compressed air to a combustor, the compressor including: a plurality of main disks provided on an outer circumferential surface of a rotation shaft along a circumferential direction, and spaced apart from each other at predetermined intervals such that a portion of the compressed air flows toward the rotation shaft; and a reinforcing disk mounted to each space defined by the plurality of main disks spaced apart from each other, the reinforcing disk having the rotation shaft in common with the main disks, and being provided with a passage formed in a direction from an outer circumferential surface thereof toward the rotation shaft.

Abstract: A data prediction method and apparatus generate plant normal state prediction data based on measurement data of multiple tags and a plant prediction model, to enhance accuracy of anomaly/fault prediction by providing precise prediction data in the normal state even in a plant anomaly/fault condition. The method includes generating primary prediction data by performing primary prediction based on the measurement data and the plant prediction model; selecting an anomalous state tag among the multiple tags, the selected anomalous state tag determined as data of an anomalous state based on measurement data corresponding to the primary prediction data; updating the plant prediction model by using the measurement data of only normal state tags; and generating secondary prediction data by performing secondary prediction based on the measurement data of the normal state tags and the updated plant prediction model. Secondary prediction is performed only when an anomalous state tag is selected.

Abstract: Disclosed herein is a water purifying system, including: a raw water tank configured to store raw water; a filter unit configured to include a plurality of filtration modules for purifying the raw water and a plurality of valves for feeding or cutting off the raw water; a raw water pump configured to feed the raw water from the raw water tank to the filter unit; and a backwash module configured to feed backwash water to the filter unit, in which some of permeate water permeated by the filter unit is fed to the backwash module to be used as the backwash water and a feed pressure of the backwash water is fed by the raw water pump.

Abstract: A gas turbine includes an outer casing having an annular shape; an inner casing disposed inside the outer casing; and a plurality of struts, each strut having a first end fixed to an outer surface of the inner casing, a second end fixed to an inner surface of the outer casing, and an inclined portion for guiding a flow of combustion gas, wherein the inclined portion is inclined from a front side to a rear side.

Abstract: A combined power generation system performing pressure difference power generation includes a pressure difference power generation facility generating electricity by using a pressure change of natural gas; a gas turbine power generation facility including a compressor, a combustor, a turbine, and a generator; and a heating unit to heat the natural gas discharged from the pressure difference power generation facility. A first bypass channel enables the natural gas to bypass the pressure difference power generation facility, and a second bypass channel enables the natural gas to bypass the heating unit. The heated natural gas is heated to a high temperature and then introduced into the combustor of the gas turbine power generation facility. Since the natural gas to be used in the gas turbine power generation facility is preliminarily heated while passing through the preceding power generation facility, the generation efficiency of the gas turbine power generation efficiency is improved.

Abstract: A gas turbine vane includes a sidewall having a plurality of film holes formed therein and defining an airfoil having a leading edge and a trailing edge, a cut-back formed at the trailing edge of the airfoil defined by the sidewall, an insert spaced apart from an inner surface of the sidewall and installed within the sidewall while having a plurality of insert holes formed therein, and a plurality of posts extending from the sidewall. The plurality of insert holes are formed in a plurality of rows, the insert holes of each row are arranged at a distance from the leading edge to the trailing edge, and a surface of the insert is positioned on the posts.

Abstract: A combustor reduces combustion vibration and the generation of nitrogen oxides and includes a burner to mix fuel with compressed air and to eject the mixture; a liner that is coupled to one end of the burner and forms a combustion chamber in which the fuel-air mixture is combusted to produce high-pressure gas; a transition piece to receive a flow of the high-pressure gas from the liner and to discharge the high-pressure gas to a turbine; a plurality of resonance modules disposed on an outer circumferential surface of the liner at positions spaced apart from each other along a circumferential direction of the liner; and a fuel supply unit coupled to each of the plurality of resonance modules and configured to supply fuel to each of the plurality of resonance modules. The resonance modules may be disposed on an outer circumferential surface of the transition piece instead of the liner.