INDUSTRIAL GAS TURBINE ENGINE WITH FIRST AND SECOND STAGE ROTOR COOLING

摘要

An industrial gas turbine engine with first and stage turbine rotor blade cooling circuit in which the blade cooling air flows through a central passage within the rotor of the engine, flows through a space between first and second stage rotors, separates into two flows with one flow going to the first stage blades and the second flow going to the second stage blades, the two flows then collecting in a common manifold, where the spent blade cooling air flows forward through the first stage rotor and along a rotor cooling passage and into a stator cavity, where the cooling air then is discharged into a combustor.