Doosan Heavy Industries & Construction Co., Ltd

Kyung Kook Kim

Sang Eon Lee

Ki Baek Kim

Sung Chul Jung

U Jin Roh

Jong Seon Kim

Dong Hwa Kim

Mu Hyoung Lee

Victor Shemyatovskiy

Tae Sung Ahn

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. The gas turbine includes a compressor section, a combustor section, and the turbine section assembled in a reverse order with respect to the disassembly method.

Method of disassembling and assembling gas turbine and gas turbine assembled thereby

A method of assembling and disassembling a gas turbine carries out various disassembly and reassembly processes depending on circumstances. In one process, a first-stage blade assembly and a first-stage vane assembly of a turbine section are disassembled from a gas turbine by sequential steps of disassembling a combustor assembly; disassembling a first-stage vane assembly; and disassembling a first-stage blade assembly. In another process, a fourth-stage blade assembly of a turbine section is disassembled from a gas turbine by sequential steps of disassembling a diffuser loading slot from a rear diffuser; and disassembling a fourth-stage blade assembly from a turbine disk. In another process, a rear bearing assembly of a turbine section is disassembled from a gas turbine by sequential steps of disassembling a rear diffuser cover from a rear diffuser; and supporting one end of a rotor shaft and disassembling a rear bearing from a rotor shaft support.

Method of assembling and disassembling gas turbine and gas turbine assembled thereby

Disclosed herein is a system for cooling a gas turbine. The system for cooling a gas turbine cools a turbine disk unit by individually supplying cooling air to each of a plurality of turbine disks.

System for cooling gas turbine

A disk assembly may include: a first disk engaged with a compressor section of a gas turbine; a second disk engaged with a turbine section of the gas turbine; and a third disk disposed between the first and second disks, and transferring torque applied to the second disk to the first disk. The third disk has a plurality of legs formed on an inner circumferential surface thereof, the plurality of legs being in contact with an outer circumferential surface of a tie bolt of the gas turbine.

Disk assembly and Turbine including the same

A disk assembly includes a first disk, a second disk and a third disk. The first disk is engaged with a compressor section of a gas turbine. The second disk is engaged with a turbine section of the gas turbine. The third disk is disposed between the first and second disks and transfers a rotational torque applied to the second disk to the first disk. A through-hole is defined through the third disk along an axial direction of the gas turbine. A distance between the third disk and a tie rod is less than each of distances between the first and second disks and the tie rod, such that spaces are defined by surfaces of the third disk respectively in communication with the compressor section and the turbine section.

Disk assembly and turbine including the same

The present invention relates to a gas turbine which includes a cooling system provided with cooling air supply paths bypassed through an outside casing and, more specifically, to a gas turbine including a cooling system and a cooling method, wherein, in order to supply cooling air to a plurality of turbine blades and other devices provided to the inside of the gas turbine, cooling air supply paths are not provided to the rotor center shaft of the gas turbine but provided around the outer casing of the gas turbine so as to achieve the increased effect in the aerodynamic efficiency of the compressor and the turbine. According to the above structure and method, it may be possible to provide the cooling air supply paths not to the rotor center shaft of the gas turbine but around the outer casing of the gas turbine, thereby finally achieving the increased effect in the aerodynamic efficiency of the compressor and the turbine.

Gas turbine compressing cooling system provided with cooling air supply paths around outer casing

A sealing assembly includes a first sealing member disposed on a fixed body and a second sealing member disposed on a rotating body while facing the first sealing member, such that when the second sealing member rotates, the first sealing member and the second sealing member work in conjunction with each other to generate flow of fluid in a reverse direction and form a fluid barrier, thereby preventing leakage of the fluid.

Sealing assembly

A foreign substance removal apparatus for a gas turbine includes a combustor casing having a first cooling air passage formed in a tangential direction of a combustor in a gas turbine in order to move cooling air into the combustor, a first foreign substance collection unit disposed on a flow path in the first cooling air passage in order to primarily filter foreign substances contained in the cooling air, a second cooling air passage extending radially toward a turbine blade in a circumferential direction of a torque tube located in the combustor, and a second foreign substance collection unit disposed on a flow path in the second cooling air passage and communicating with the second cooling air passage to secondarily filter foreign substances contained in the cooling air introduced through the first cooling air passage.

Foreign substance removal apparatus for gas turbine

Disclosed herein is a cooling apparatus of a gas turbine including a compressor disk unit mounted in a gas turbine and provided with compressor cooling passages; the torque tube units provided in an adhering state to each other while being adjacent to the compressor disk unit and provided with a cooling air supply passage communicating with the compressor disk cooling passage; and a turbine disk unit provided with a turbine disk cooling passage communicating with the cooling air supply passage of the torque tube unit, in which the torque tube units are disposed between the compressor disk unit and the turbine disk unit and coupled therewith in an adhering state to each other along an axial direction of a rotation shaft mounted in the gas turbine and the cooling air supply passage is open in horizontal direction along the axial direction from an edge of the torque tube unit.

Gas turbine cooling apparatus

A supporting device for a gas turbine includes a base frame; a fixing member installed on the base frame so as to support one end of a gas turbine; and an absorbing member installed on the base frame so as to support the other end of the gas turbine. The absorbing member having lower stiffness than the fixing member so as to deform in first and second directions when the gas turbine thermally expands.

Supporting device for gas turbine

Disclosed are a shroud impeller of a centrifugal compressor and a method of manufacturing the same where the shroud impeller includes a rotary hub connected to a driving shaft, a plurality of blades radially provided about a rotational axis of the rotary hub, and an integral shroud bonded onto top ends of the blades.

Growing community of inventors

Daejeon, South Korea

Kyung Kook Kim