Patent ID: 7192245
Filing Date: 2007-03-20
Classification: F01D,F05D

Abstract:
1. A rotor assembly for a gas turbine engine, the rotor assembly comprising: a rotor disk, the rotor disk having an outer periphery provided with a plurality of blade retention slots, each slot being configured and disposed to a receive a root portion of a corresponding radially-extending and internally-cooled blade; a plurality of cooling air deflectors mounted on the rotor assembly to redirect air from a forward side of the rotor disk to a manifold at a bottom side of a corresponding blade retention slot, each deflector having an inlet oriented to collect air in the direction of rotation of the rotor disk, and an outlet in registry with the corresponding manifold; and an annular L-seal between a rotor disk and a coverplate attached on a forward side of the rotor disk, the L-seal having a radially-extending flange portion on which are located the cooling air deflectors, each deflector having an inlet located on a forward side of the L-seal and an outlet in fluid communication with an opposite side thereof.