Doosan Enerbility

An austenitic stainless steel is provided. The austenitic stainless steel includes chromium (Cr), manganese (Mn), nickel (Ni), carbon (C), nitrogen (N), and silicon (Si), with iron (Fe) as a balance. By incorporating silicon in a specified range, the austenitic stainless steel exhibits an improved pitting corrosion potential compared to conventional STS 304L, thereby providing enhanced corrosion resistance. The austenitic stainless steel further demonstrates high cryogenic toughness, with an impact absorption energy of at least 41 J at a temperature of approximately -196°C.

An austenitic stainless steel is provided. The austenitic stainless steel includes chromium (Cr), manganese (Mn), nickel (Ni), carbon (C), nitrogen (N), and copper (Cu), with iron (Fe) as a balance. By incorporating copper in a specified range, the austenitic stainless steel exhibits an improved pitting corrosion potential compared to conventional STS 304L, thereby providing enhanced corrosion resistance. The austenitic stainless steel further demonstrates high cryogenic toughness, with an impact absorption energy of at least 41 J at a temperature of approximately -196°C.

A method for dismantling a calandria vessel (200) underwater is provided. The method for dismantling the calandria vessel underwater includes filling an inside of a concrete vault (100) in which a calandria vessel is installed with water; installing a manipulator (400) in the concrete vault; opening the concrete vault by dismantling an RM-deck (10) (reactivity-mechanism deck); dismantling an upper portion to cut and dismantle an upper portion of the calandria vessel and a fuel tube (300) disposed inside the upper portion of the calandria vessel using the manipulator; and dismantling a lower portion to cut and dismantle a lower portion of the calandria vessel and a fuel tube disposed inside the lower portion of the calandria vessel using the manipulator.

An austenitic stainless steel is provided. The austenitic stainless steel includes chromium (Cr), manganese (Mn), nickel (Ni), carbon (C), nitrogen (N), and boron (B), with iron (Fe) as a balance. By incorporating boron in a specified range, the austenitic stainless steel exhibits an improved pitting corrosion potential compared to conventional STS 304L, thereby providing enhanced corrosion resistance. The austenitic stainless steel further demonstrates high cryogenic toughness, with an impact absorption energy of at least 41 J at a temperature of approximately -196°C.

A method for dismantling a calandria vessel (200) underwater is provided. The method for dismantling the calandria vessel underwater includes filling an inside of a concrete vault (100) in which a calandria vessel is installed with water; opening the concrete vault by dismantling an RM-deck (10); installing a manipulator (400) on the calandria vessel; dismantling an upper portion to cut and dismantle an upper portion of the calandria vessel and a fuel tube (300) disposed inside the upper portion of the calandria vessel using the manipulator; and dismantling a lower portion to cut and dismantle a lower portion of the calandria vessel and a fuel tube disposed inside the lower portion of the calandria vessel using the manipulator.

A nozzle (1220) for a combustor (1200) and a gas turbine (1000) including the same are provided. The nozzle (1220) for the combustor (1200) includes a nozzle assembly (1400), which includes a cylindrical central nozzle module (1500) including a plurality of tubes (1530) arranged in parallel, a plurality of outer nozzle modules (1600) arranged around the central nozzle module (1500) and including a plurality of tubes (1630) arranged in parallel, a local cavity (1550) formed in a central portion of a front portion of the central nozzle module (1500), the local cavity (1550) being configured to allow gas to flow therein, and a local cavity (1650) formed in a central portion of a front portion of each of the plurality of outer nozzle modules (1600), the local cavity (1650) being configured to allow gas to flow therein.

A method for manufacturing a nozzle (1230) for a combustor (1200) is provided. The method for manufacturing the nozzle for the combustor includes primarily disposing a rear plate (1235a) at a location spaced apart from a front end of a mixing tube (1234), the mixing tube being inserted through the rear plate, secondarily disposing a front plate (1235b) on an outer circumferential surface of the front end of the mixing tube, the mixing tube being inserted through the front plate, and coupling an air tube (1233), which extends in a longitudinal direction, to the front end of the mixing tube in an extended configuration.

A nozzle (1230) for a combustor (1240) and a gas turbine (1300) including the same are provided. The nozzle (1230) for the combustor (1240) includes a center tube (1231) including a fuel passage (1231a) configured to allow fuel to flow therein, a nozzle shroud (1232) surrounding the center tube (1231) and including a shroud chamber (1232a), a plurality of nozzle vanes (1234) disposed between the center tube (1231) and the nozzle shroud (1232), each nozzle vane (1234) configured to guide a fuel flow and spray fuel, and a nozzle rod (1235) arranged offset from each nozzle vane (1234) and configured to spray the fuel between the plurality of nozzle vanes (1234).

A nozzle (1220) for a combustor (1200) and a gas turbine (1000) including the same are provided. The nozzle (1220) for the combustor (1200) includes a nozzle assembly (1400), which includes a cylindrical central nozzle module (1500) including a plurality of tubes (1530) arranged in parallel, a plurality of outer nozzle modules (1600) arranged around the central nozzle module (1500) and including a plurality of tubes (1630) arranged in parallel, a circumferential groove (1525) formed concavely between the central nozzle module (1500) and the plurality of outer nozzle modules (1600), radial grooves (1625) formed concavely between the plurality of outer nozzle modules (1600), and a plurality of pilot flow paths (1540, 1640) through which tubes (1530, 1630) of the plurality of tubes (1530, 1630) adjacent to the circumferential groove (1525) and the radial grooves (1625) are in fluid communication with the circumferential groove (1525) and the radial grooves (1625).

Proposed is a nozzle assembly, a combustor, and a gas turbine including the same, the nozzle assembly including a nozzle module unit including a plurality of tubes injecting fuel and compressed air into a combustion chamber of the gas turbine, and a casing accommodating the nozzle module unit therein, wherein the nozzle module unit includes a central nozzle module injecting fuel and compressed air and located at a central portion of the casing, and a plurality of outer nozzle modules located outside the central nozzle module while being spaced apart from the central nozzle module, and an anti-air-leakage sealing unit is installed among the inner circumferential surface of the casing, the central nozzle module, and the plurality of outer nozzle modules to prevent air leakage into the combustion chamber.