HIGH PRESSURE TURBINE BLADE COOLING SCOOP

摘要

A turbine blade cooling system for use in a gas turbine engine are provided.The turbine blade(9)has a root portion(18)adapted for mounting to a rotor(10),and an airfoil portion extending from the root portion.A cooling air inlet duct(19)is provided and adapted to communicate with the cooling air plenum(20)when installed to the rotor.The air inlet duct has an inlet scoop portion(21)adapted to extend into the cooling air plenum(20)and an inlet scoop aperture(21)oriented and adapted to capture cooling air from the cooling air plenum as a consequence of turbine rotation when the blade is mounted to the rotor.Scooped air is provided to a cooling air channel(23)defined in an airfoil portion of the blade for the purpose of cooling the blade.The engine optionally includes a bearing gallery cooling air jacket in communication with the low pressure compressor stage for the purpose of cooling.