Patent ID: 6419452
Filing Date: 2002-07-16
Classification: F01D,F05D

Abstract:
A gas turbine comprising:a rotor disc having a peripheral surface with a plurality of circumferentially spaced, generally U-shaped grooves; a plurality of axial entry turbine blades carried by said disc at circumferentially spaced locations thereabout and forming a portion of a first stage of the turbine; said blades having generally radially extending cooling passages for flowing a cooling medium within the blades; a plurality of plates each having at least one U-shaped projection for engaging in a corresponding U-shaped groove of said plurality of grooves thereof, each said plate interposed between an adjacent pair of said blades and having locking projections to lock said blades against axial movement relative to said disc whereby the cooling passages are left free for flowing the cooling medium; and a plurality of axial entry blades for a second stage of the gas turbine and carried by a rotor disc of the second stage about a peripheral surface thereof, a plurality of plates for locking said blades of said second stage against axial movement, each of said second-stage locking plates being interposed between an end portion of a foot of a corresponding second stage blade and said second-stage rotor disc and provided with ends for retaining said second stage blades against axial movement.