Patent ID: 6267553
Filing Date: 2001-07-31
Classification: F01D,Y02T

Abstract:
In a gas turbine including a compressor for producing a main air stream, the compressor having a stator and a spool comprised of multiple axial stages extending between a first stage at a forward end of the compressor and a last stage at an aft end of the compressor, each stage including a rotor disk having a peripheral rim and multiple blades attached to the rim, the first stage rotor disk having a front stub shaft extending in a forward direction, the last stage rotor disk having a rear stub shaft extending in an aft direction, the improvement comprising:(a) a spacer disk disposed between adjacent rotor disks, the spacer disk having an outer portion and a web portion, the outer portion extending generally axially between the peripheral rims of the adjacent rotor disks, the outer portion having a forward end, an aft end and a center region between the forward end and the aft end, the web portion extending radially inward from the center region; and(b) a plurality of tie rods, each tie rod having a hollow interior for conducting air, the tie rods extending through the rotor disks and the spacer disks, the tie rods being tensionable to provide axial preload between the disks.