GAS TURBINE COOLING APPARATUS

摘要

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.

主权项

1. A cooling apparatus of a gas turbine, comprising:
a compressor disk unit configured to be mounted in a gas turbine and provided with compressor disk cooling passages; a plurality of torque tube units disposed adjacent the compressor disk unit and configured to couple to each other, each torque tube unit including a cooling air supply passage that communicates with the compressor disk cooling passage; and a turbine disk unit including a turbine disk cooling passage configured to communicate with the cooling air supply passages of the torque tube units, wherein the torque tube units are disposed between the compressor disk unit and the turbine disk unit along an axial direction of a rotation shaft mounted in the gas turbine, the torque tube units are coupled to the compressor disk unit and the turbine disk unit, and the cooling air supply passage is open in a horizontal direction along the axial direction from an edge of the torque tube units.