Patent ID: 6077035
Filing Date: 2000-06-20
Classification: F01D,Y02T,Y10S

Abstract:
In a gas turbine engine including a forward stator assembly and a rotor assembly having:an air cooled rotor disc with an axis, a forward radially outward edge, and a circumferential array of blade retention slots;a plurality of air cooled rotor blades with blade bases retained in each one of said slots, the rotor blades having blade platforms and blade airfoils radially extending outboard of the disc into a hot annular gaspath, the rotor blades disposed equidistantly about the circumference of the rotor disc with a radially extending gap between each adjacent rotor blade;a circular coverplate having: an annular disc sealing edge engaging the rotor disc and blade bases radially inward of the disc forward edge; and an annular stator sealing edge forming running seal means with the stator assembly for separating cooling air from the hot gaspath;a cooling air leakage path from the running seal means to the gaspath being defined between the stator assembly, coverplate, rotor disc and rotor blades;wherein the improvement comprises:cooling air leakage deflection means extending circumferentially from the coverplate, for deflecting cooling air leakage, flowing from the running seal through the cooling air leakage path, away from the gaps between the blades and for deflecting cooling air leakage forwardly around the blade platform lip, onto an outward surface of the blade platform, and into the gaspath at an acute angle relative to rearwardly axial flow therein, wherein the cooling air leakage deflection means comprise a forwardly extending deflector flange contiguous with the disc sealing edge of the coverplate.