Abstract: A distribution network system having a plurality of nodes using a scheme for data-centric object-oriented communication (DDS) effectively manages the frequently occurring connections for each node and the real-time addition or deletion of a node. Each node includes a gateway connected to a Wide Area Network (WAN) and configured to transmit and receive a message using a Real-Time Publish-Subscribe (RTPS) protocol that applies simple tunneling to communicate as if all nodes communicate in a Local Area Network (LAN), and to insert magic information into a header of the message, the inserted magic information including source IP information of the message, destination IP information of the message, and destination User Datagram Protocol (UDP) information of the message.

Abstract: Disclosed herein is a method for controlling a surge margin of a gas turbine and an extraction device for a gas turbine. The method for controlling the surge margin of the gas turbine and the extraction device for the gas turbine may support stable operation of a compressor unit in the gas turbine, thereby improving the efficiency of the gas turbine and minimizing vibration and noise of the gas turbine.

Abstract: A combustor includes a flow guide installed in an air channel to simultaneously implement collision cooling and convection cooling of a combustor liner and a transition piece. The air channel is formed by an inner casing and an outer casing which are spaced apart from each other by a predetermined distance, through which combustion air is introduced to the combustor in order to produce a fuel-air mixture. The flow guide is attached to an inner surface of the outer casing and extending a predetermined length towards the inner casing so as to guide the combustion air flowing through the air channel toward a surface of the inner casing. The flow guide includes a channel inlet formed on an upstream side; a channel outlet formed on a lower surface facing the inner casing; and a guide channel communicating with each of the channel inlet and the channel outlet.

Abstract: A rotary shaft support structure supports each of both ends of a rotary shaft passing through a center of a gas turbine and includes a main body arranged around a circumference of the rotary shaft and mounted to each of a compressor casing and a turbine casing of the gas turbine; a pad member disposed between the main body and the circumferential surface of the rotary shaft and biased against the circumferential surface of the rotary shaft for supporting the rotary shaft; a pivot protrusion protruding from the pad member toward the main body; and a pivot housing for receiving the pivot protrusion to rotatably support the pad member. The mechanical bias is supplied by a spring member seated in the mounting groove to bias the pivot housing against the pivot protrusion. The rotary shaft support structure exhibits performance as a bearing by absorbing some of an applied load.

Abstract: Disclosed herein may be a sealing structure for turbines, and a turbine and a gas turbine having the sealing structure. The sealing structure is mounted on a sealing housing of a vane sealing assembly of the turbine to prevent combustion gas passing through a blade of the turbine from being drawn into an internal space between a disk of the turbine and the sealing housing. The sealing structure may include a mounting plate mounted to the sealing housing, and baffles which are provided on the mounting plate at positions spaced apart from each other and protrude toward the disk. Therefore, thanks to the sealing structure, turbulent currents are generated in the flow of combustion gas that passes through the turbine blade. The generated turbulent currents block space between the sealing structure and the turbine disk, thus preventing the combustion gas from flowing into the internal space.

Abstract: A turbine stator, into which combustion gas supplied from a combustor of a gas turbine flows, has an improved structure capable of preventing circumferential movement of turbine vanes. The turbine stator, which may be included in a turbine of a gas turbine having the improved structure, includes a casing including first and second casings constituting respective casing halves, the first and second casings having a fastening groove formed on at least one contact surface between the first casing and the second casing; a plurality of vane airfoils configured to be installed on an inner peripheral surface of the casing and arranged in a multi-stage manner in a flow direction of the combustion gas; and a stop configured to be fixed with respect to a vane airfoil of the plurality of vane airfoils and to be inserted into the fastening groove to fix the vane airfoil to the casing.

Abstract: A cantilevered vane, for use with a rotary disc of a gas turbine, includes a root supported in a dovetail slot formed in a circumferential surface of the rotary disc; and an airfoil protruding a predetermined height from the root and having a J-shaped cross-section throughout a front-wing portion and a rear-wing portion of the airfoil. The airfoil includes a straight portion vertically extending upward from the root by a predetermined height; and a curved portion integrally formed with an upper end of the straight portion to cantilever toward one side of the airfoil, the curved portion being inclined at a predetermined angle with respect to the straight portion. Cooling fluid flows through a first channel formed in the straight portion and a second channel formed in the curved portion. The first channel includes front-wing and rear-wing channels for guiding the cooling fluid to the front-wing and rear-wing portions.

Abstract: Disclosed is a vane assembly fixed to a turbine casing of a turbine and configured to guide the flow of combustion gas having passed by a turbine blade airfoil. The vane assembly comprises a vane airfoil configured to guide the flow of the combustion gas, a platform portion combined with an end of the vane airfoil, carrier hook portions formed at respective periphery portions of the platform portion and provided with a thermal stress prevention slot on a surface facing the turbine casing, and a seal plate installed in the thermal stress prevention slot, thereby preventing a portion of compressed air produced by a compressor and supplied to the platform portion between the carrier hook portions from leaking out of the platform portion through the thermal stress prevention slot.

Abstract: A method of assembling and disassembling a gas turbine, and a gas turbine assembled thereby, improves work efficiency and reduces time and cost by carrying out various disassembly and reassembly processes depending on circumstances. In one process, a turbine section is disassembled from a gas turbine by sequential steps of disassembling an upper turbine case; disassembling a rear diffuser assembly and a rear bearing assembly; disassembling a combustor assembly; disassembling a vane assembly; and disassembling a blade assembly. In another process, first-stage to fourth-stage blade assemblies and first-stage to fourth-stage vane assemblies in a turbine section are disassembled from the gas turbine by sequential steps of disassembling an upper turbine case; disassembling a combustor assembly; disassembling a vane assembly; and disassembling a blade assembly.

Abstract: The disclosure relates to a carbon blade for a wind turbine with multiple down conductors, and more particularly, to a carbon blade for a wind turbine with multiple down conductors that includes multiple down conductors disposed thereon to reduce or prevent a potential difference between a plurality of points to be formed thereon from being generated.

Abstract: A fuel nozzle assembly includes an inner fuel nozzle; a plurality of outer fuel nozzles disposed radially around the inner fuel nozzle, each outer fuel nozzle including a central body for fuel injection, a shroud spaced apart from and surrounding the central body, the shrouds forming an outer periphery of the fuel nozzle assembly, and an inlet formed at one end of the shroud; and a peripheral rim formed at the inlets and disposed to cover at least a portion of the outer periphery. The fuel nozzle assembly is connected to an end plate of a combustion chamber. The one end of a corresponding shroud is disposed at a set distance from an end plate of a combustion chamber, the set distance depending on at least one of relative positions of the inner fuel nozzle and the plurality of outer fuel nozzles and an inlet radius of the corresponding shroud.

Abstract: A tip sealing structure for a blade includes a casing having an inner circumferential surface facing the blade; a blocking groove formed in the inner circumferential surface of the casing; and a movable seal provided on a tip of the blade and configured to move in a depth direction of the blocking groove. Since the seal is configured to move into the blocking groove, tighter sealing at the tip of the blade can be accomplished. A seal bracket of the moveable seal encloses a movement space open at one end and includes a seal stop formed at the open end. A brush body including top and bottom crossbars is disposed partially within the seal bracket, such that movement of the moveable seal is limited by the bottom crossbar being stopped by the seal stop. A first brush seal is mounted on the brush body and positioned in the blocking groove.

Abstract: Disclosed herein is a structure for multi-stage sealing of a turbine, including: an annular multi-stage sealing part disposed on an inner circumferential surface of a fixed body and having different heights of at least two stages; a barrier unit disposed at a central side of the multi-stage sealing part on the inner circumferential surface of the fixed body; and an annular multi-stage tooth part disposed to face the multi-stage sealing part or the barrier unit over an outer circumferential surface of a rotating body and provided with a plurality of teeth, having a relative height corresponding to different heights of the multi-stage sealing part or the barrier unit at an interval between the fixed body and the rotating body.

Abstract: A gas turbine blade includes a plurality of guide ribs spaced apart from each other in a movement direction of a cooling fluid in order to guide movement of the cooling fluid flowing along a cooling passage formed in the turbine blade, and an opening formed in each of the guide ribs in order to guide a portion of the cooling fluid to a bottom of the cooling passage between the guide ribs or to side walls adjacent to the bottom.

Abstract: Provided is a gas turbine including: a combustor positioned between a compressor and a turbine of a gas turbine; a cooling air discharge unit configured to receive compressed air from the compressor, receive cooling water from a power plant, and discharge cooling air having exchanged heat with the compressed air; and a supply unit configured to supply the cooling air discharged from the cooling air discharge unit to the turbine and the combustor.

Abstract: A strut shield collar can include: a tubular portion including a tubular inside surface and a tubular outside surface; a flange portion extended from the tubular portion toward an outside of the tubular portion and including a flange inside surface; and a grid type mesh formed on at least one of the tubular inside surface and the flange inside surface, wherein the grid type mesh comprises a groove portion and a rib portion, and the groove portion is thinner than the rib portion.

Abstract: A turbine blade with a cooling structure includes a root member coupled to a turbine disk; an inlet formed in the root member to introduce cooling air to the turbine blade; an airfoil coupled to the root member, the airfoil having a suction-side surface and a pressure-side surface; and an internal cooling channel disposed between the suction-side and pressure-side surfaces of the airfoil and configured to pass the cooling air throughout the airfoil from the inlet to an ejection hole formed on an upper surface of the airfoil. The turbine blade may be included in a turbine of a gas turbine and is provided to blow air passing through the cooling channel toward a leading edge and an upper surface of the airfoil, thereby reducing heat load and thermal stress applied to the turbine blade and preventing the turbine blade from being damaged by the heat load or thermal stress.

Abstract: The present invention relates to a structure for cooling a turbomachine's rotor part and a rotor and a turbomachine having the same. The structure for cooling a turbomachine's rotor part includes: a dovetail joint part disposed along an outer circumferential surface of a rotor wheel and having a plurality of mounting grooves in which dovetails of buckets are mounted and cooling slots disposed along the outer circumferential surface of the rotor wheel on the dovetail joint part and having a cooling fluid flowing therethrough.

Abstract: An air-collecting structure effectively cools a transition piece of a duct assembly in a gas turbine combustor. The structure includes a flow sleeve having a plurality of cooling holes and surrounding the transition piece, the cooling holes formed in a lateral side of the flow sleeve to receive a compressed cooling air and arranged in rows running parallel to each other in a longitudinal direction of the flow sleeve, the rows progressing up the lateral side from a lower row to a higher row; and a plurality of scoops arranged in correspondence with predetermined cooling holes among the plurality of cooling holes and configured to collect an amount of air according to row. Each scoop includes an inlet having a predetermined radius for collecting the compressed cooling air. The radius is constant for the scoops of any one row and increases from the lower row to the higher row.

Abstract: A cooling path structure for concentrated cooling of a seal area in a duct assembly and a gas turbine combustor having the same are provided. The cooling path structure includes a concentrated cooling guide plate facing the seal area to introduce compressed cooling air into the seal area through a plurality of first cooling holes and a plurality of second cooling holes respectively formed in the guide plate. The first cooling holes are formed along a first inlet axis such that the introduced cooling air approaches a central axis of the seal area in a forward direction, and the second cooling holes are formed along a second inlet axis such that the introduced cooling air approaches the central axis of the seal area in a backward direction. The first and second inlet axes each are inclined at an acute angle relative to the central axis of the seal area.