Doosan Enerbility

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 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).

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).

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.

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.

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.