Doosan Enerbility Patente

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.

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.

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 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 (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 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).

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.

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 an airfoil (2000_1, 2000_2, 2000_3, 2000_4) including a suction surface (2400), a pressure surface (2300), a leading edge (2100), a trailing edge (2200), and a through hole (2500, 2500_2, 2500_3, 2500_4). The suction surface (2400) protrudes with an outward convex curved surface. The pressure surface (2300) is formed on a surface opposite to the suction surface and has a curved surface recessed concavely. The leading edge (2100) is arranged at an upper stream of an air flow and formed where front ends of the pressure surface (2300) and the suction surface (2400) are joined. The trailing edge (2200) is arranged at a lower stream of the air flow and formed where rear ends of the pressure surface (2300) and the suction (2400) surface are joined. The through hole (2500, 2500_2, 2500_3, 2500_4) is formed through the airfoil (2000_1, 2000_2, 2000_3, 2000_4) in a direction from the pressure surface (2300) to the suction surface (2400).

A turbine having a guide baffle and a gas turbine including the turbine are provided. The turbine includes a turbine vane carrier having an inner circumferential surface to which a plurality of turbine vanes are coupled, a turbine casing having an inner portion on which the turbine vane carrier is mounted, the turbine casing being provided with a cooling air inlet configured to supply cooling air towards the turbine vane carrier, and a guide baffle mounted on an outer circumferential portion of the turbine vane carrier and configured to guide the cooling air supplied through the cooling air inlet to an outer circumferential surface of the turbine vane carrier.

A ring segment cooling structure with enhanced cooling performance, a ring segment (1600), and a gas turbine (1300) including the same. The ring segment cooling structure includes a cooling channel (1630) and a rib turbulator (1637). The cooling channel is formed inside a shield wall (1611) of a ring segment mounted to a turbine casing that accommodates blades (1400) and is formed in a wavy shape so as to allow cooling air to flow through the cooling channel. The rib turbulator is installed in the wavy-shaped cooling channel.

Proposed is an anti-icing device, and a compressor and a gas turbine including the same, which is configured to prevent external air introduced into the compressor from freezing and causing damage to an inner portion of the gas turbine, and the anti-icing device includes an inlet guide vane installed behind an intake through which external air is introduced, and controlling a flow of the introduced external air, and a heating unit installed at the inlet guide vane and configured to heat the inlet guide vane such that the external air is prevented from condensing.

A compressor blade having a forward and rearward swept profile and a gas turbine including the compressor blade are provided. The compressor blade includes an airfoil including stacked sections having a predetermined thickness formed in a form of a closed curve, which connects a concave curve and a convex curve, extending in a radial span between a hub and a shroud, extending in a direction of a chord line between a leading edge and a trailing edge, and extending in a thickness direction between a pressure surface and a suction surface, wherein the airfoil is formed with sections having a predetermined thickness stacked to be inclined in a radial direction, and includes a swept profile formed such that the leading edge and the trailing edge are inclined forward or rearward of the chord line, and the swept profile includes a first area swept rearwards from the hub, a second area swept forwards from a position opposite to the first area to the shroud, and a third area that is not swept and is located between the first area and the second area.

A gas turbine (100) includes a blade (230), in which a root part (235) is formed and a block assembly groove (237) is formed, a disk (210), in which a disk slot (213), into which the root part (235) is inserted, is formed, a block insertion groove (215) is formed, and a pin insertion hole (216) is formed; and a fixing assembly (250) configured to fix an axial position and a radial position of the blade (230) with respect to the disk (210). The fixing assembly (250) includes: a block part (251) inserted into the block assembly groove (237) and the block insertion groove (215); and a pin part (255) passing through the pin insertion hole (216) to be coupled to the block part (251).

A blade-disk assembly (200) for a gas turbine (100) includes a blade (230) having a root part (235), a disk (210) having a disk slot (213), into which the root part (235) is inserted, and a fixing block (250) inserted into a block assembly groove (237) of the blade (230) and a block insertion groove (215) of the disk in a circumferential direction (D2) to retain an axial position of the blade (230) with respect to the disk (210).The gas turbine (100) includes a compressor (110) configured to draw in and compress external air, a combustor (104) configured to mix fuel with the external air compressed in the compressor (110) and to combust a mixture of fuel and the compressed air, and a turbine (120), which comprises the blade-disk assembly (200), in which the blade (230) and the disk (210) are assembled and rotated by a combustion gas discharged from the combustor (104).

Disclosed is a method for dismantling metal equipment of a heat transport system in a containment building at a nuclear power plant, the metal equipment including a heat transport pump, a steam generator, a pressurizer, a condenser, and a D2O tank, including: a first dismantling step of dismantling the heat transport pump; a second dismantling step of dismantling the steam generator after the first dismantling step; a third dismantling step of dismantling the pressurizer after the second dismantling step; and a fourth dismantling step of dismantling the condenser and the D2O tank after the third dismantling step.

Disclosed is a method for dismantling a D20 tank of a heavy water reactor installed on an inner wall of a containment building and surrounded by a concrete structure, the method including cutting and opening a front surface of the concrete structure so as to dismantle the D20 tank, descending the D20 Tank by using an dedicated dismantling apparatus, and taking the D20 tank out of the containment building by using a crane, and a dismantling apparatus.

According to an embodiment of the disclosure, a method of removing radionuclides from radioactive metal waste is provided including a preheating step of preheating atmospheric gas to a target temperature; a supply step of supplying the atmospheric gas to the radioactive metal waste upon the atmospheric gas being preheated to the target temperature in the preheating step; an oxidation step of oxidizing a surface region of the radioactive metal waste by the atmospheric gas; and a removal step of removing an oxidized layer generated in the oxidation step.

Airfoil (1000), turbine blade (200) including the airfoil, and gas turbine (1) including the turbine blade. The airfoil includes a suction side (1100), a pressure side (1200), a leading edge (1300), a trailing edge (1400), a cooling flow passage (1500) configured to guide cooling fluid introduced from a lower portion of the suction side and the pressure side, to one or more flow channels respectively at the suction side and the pressure side, and then discharge the cooling fluid to a region rearward of the trailing edge, and a flow guide part (1600) provided in each of the one or more flow channels and forming a cooling space.

Proposed is proposed a reactor vibration measurement device (100) for measuring vibration of a reactor (1) in which a head (10) and a body (20) are coupled to each other by a plurality of stud coupling means (30), the device including an acceleration sensor (110) configured to be in close contact with the head and supported by a bracket (B), a fixed part (120) fixed between the plurality of stud coupling means that couple the head and the body to each other on the head, a rotating part (130) rotatably coupled to an upper portion of the fixed part, and a bracket support part (140) connected to a first side of the rotating part and configured to support the bracket that supports the acceleration sensor, the bracket support part being movable upward and downward at the first side of the rotating part.

Proposed is a reactor (10) sampling device for collecting samples from an inner wall of a reactor, the device including a main body part (100) having a receiving space (100a) and an opening part (100b) disposed to be in close contact with the inner wall, a sampling tool part (200) disposed in the receiving space of the main body part and having a tool head (211) configured to collect samples from the inner wall of the reactor through the opening part, a vertical movement part (300) connected to the main body part and configured to move the main body part upward and downward, and a sample discharge part (400) communicating with the receiving space and configured to discharge the samples collected by the sampling tool part to the outside of the main body part.

Disclosed is a sealing assembly. The sealing assembly 20 includes a first sealing part 410 that seals a first target sealing part defined along a first direction, a second sealing part 420 that seals a second target sealing part defined along a second direction that crosses the first direction, and is provided adjacent to an end of the first sealing part for connection thereto, and a first extending sealing part 418 that integrally extends from the end of the first sealing part 410, is configured to be bent, is disposed to cover a gap between the first sealing part and the second sealing part, and is connected to the second sealing part. Accordingly, a structure and an assembling process may be simplified while a sealing performance thereof is enhanced.

A cooling segment (11) includes a segment body (342) and a cooling flow path (344) provided in the segment body, so that a cooling medium is movable in the cooling flow path. The cooling flow path comprises a first twist flow path (344a) helically extending around a preset reference line, and a second twist flow path (344b) helically extending around the reference line collectively with the first twist flow path. A gas turbine (10) includes a compressor (100) configured to suck in and compress air; a combustor (200) configured to mix the air, which is compressed by the compressor, with fuel and combust an air-fuel mixture, and a turbine (300). The turbine includes a turbine casing (310), a turbine vane (330) provided on an inner surface of the turbine casing, a turbine blade (320) rotatably provided in the turbine casing, and the cooling segment (11) provided on the inner surface of the turbine casing and configured to be exposed to combustion gas discharged from the combustor.

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Jet nozzle (1500) is formed on an inner surface of a combustor (1000) to supply fluid into an interior of a liner (1200) of the combustor in a direction intersecting with a progress direction of combustion gases primarily combusted in a combustion chamber (1210) in the interior of the liner. The jet nozzle includes a fluid inlet (1510), through which fluid is externally introduced, and a fluid outlet (1520) including a first fluid outlet member (1521), through which a portion of the fluid introduced through the fluid inlet is discharged so as to be rotated in one direction, and a second fluid outlet member (1522), through which the rest of the fluid is discharged so as to be rotated in a direction different from the rotation direction of the fluid discharged from the first fluid outlet member.