Patent ID: 8152436

Claim:
A turbine rotor comprising: a disc mounted for rotation about an axis, said disc having axially spaced-apart front and rear faces and a rim extending circumferentially between said front and rear faces; a circumferential array of turbine blades extending radially outwardly from the rim of the disc, each turbine blade having a platform, an airfoil portion extending from a gaspath side of the platform, and a root portion depending from an undersurface of the platform opposite the gaspath side, the root portion of each of the turbine blades being received in a corresponding slot defined in the rim of the disc, each pair of adjacent slots being separated by a peripheral land; and a circumferential array of inter-blade cavities defined between the undersurface of the platforms and the peripheral lands of the rim, each of the inter-blade cavities having a substantially closed upstream end in fluid flow communication with an inlet defined between the disc and the blades for channeling a flow of coolant from the front face to the rear face of the disc through said inter-blade cavities, wherein said inter-blade cavities are in fluid flow communication with corresponding ones of said slots defined in the rim of the disc, and wherein at least a first portion of the coolant flowing through the inter-blade cavities is discharged through a rear end of the slots.