Patent ID: 7815415

Claim:
A mounting structure in a gas turbine, comprising: an air separator that includes a cylindrical member arranged to form a clearance communicating with an opening to an outer peripheral face of a rotor in a radial direction of the rotor, the cylindrical member having a flange at one end and the other end being defined by an edge of the opening; and a rotor blade rotary disk disposed on an outer face of the rotor and formed on an upstream end of the rotor with respect to an axial flow direction of core gases, the rotor blade rotary disk having a disk recess portion forming an annular recess around the axial center of the rotor; a flange outer peripheral face disposed on an outer periphery of the flange, the flange outer peripheral face formed on a downstream end of the flange with respect to an axial flow direction of core gases, is parallel to the axial center of the rotor, and is tightly sealed with a disk recess inner peripheral face opposed to the flange outer peripheral face to form a wall of an air passage configured to provide cooling air to turbine blades and to reduce air leakage from the air passage, wherein the disk recess inner peripheral face is formed on an upstream end of the rotor blade rotary disk with respect to an axial flow direction of core gases, is disposed in the disk recess portion, is parallel to the axial center of the rotor, and is formed around the axial center in an annular shape; and wherein the clearance is formed in an inner side of the flange outer peripheral face, the flange outer peripheral face is placed on an outer peripheral side of the disk recess portion and is secured to the rotor blade disk at the outer peripheral side of the disk recess portion, and the portion of the flange in contact with the rotary disk is entirely in face to face contact with the rotary disk.