Patent ID: 7794207

Claim:
A disk of a disk rotor for a gas turbine comprising: a central portion having a central axis pass-through hole, a first collar situated at a first end and a second collar situated at a second end of the central portion; an intermediate portion disposed around the central portion; an outer portion disposed around the intermediate portion, the outer portion having a series of axial pass-through holes configured to receive a series of tie rods and having a series of slots configured to house a corresponding series of vanes, wherein the series of holes is positioned in the outer portion of the disk so as to obtain high dynamic characteristics of the rotor and at the same time a sufficient useful life thereof, and each slot has a reference point for placing a corresponding vane, an angle between the reference point of a slot and a central point of the closest hole of the series of holes is between 2 and 10 sexagesimal degrees, and the reference point is defined by an intersection of (i) a central axis of the slot in a middle side section of the disk with (ii) an extension of a side surface of the outer portion, the axis of the slot being radial from an axial direction of the disk and the central point is defined by a radial line extending from said central axis pass through hole through the center of the closest hole in the middle section of the disk.