Patent ID: 6065932
Filing Date: 2000-05-23
Classification: F01D,F01M,F05D

Abstract:
A turbine comprising at least one rotatable disc carrying an annular array of aerofoil blades, each of said blades having an aerofoil portion operationally located in an annular gas passage extending through said turbine for flow of gas through said turbine, means being provided to direct cooling air into passages provided internally of said aerofoil blades to provide cooling thereof, said cooling air operationally flowing, at least partially, in radially outward directions over at least part of the upstream external surface of said at least one disc prior to a part of said cooling air being diverted to provide cooling of said aerofoil blades, a plurality of lock plates being provided on the downstream side of said at least one disc to provide locking at said blades on said at least one disc, means being provided radially inwardly of said aerofoil portions to direct at least some of the remaining cooling air towards said lock plates, each of said lock plates having an aperture therein, deflection means being provided on each of said respective lockplates and associated with each respective aperture in each said respective lockplate to deflect said cooling air directed towards said lock plates into a region downstream of said at least one disc in a direction having a circumferential component generally opposite to that in which said at least one disc operationally rotates.