Nozzle for a coolable rotor blade

摘要

A coolable rotor stage assembly 14 of the turbine 10 of an axial flow gas turbine engine is disclosed. A cavity 18 for purge air is adjacent the rotor disk 22. A nozzle 34 for metering the flow of cooling air through the rotor blade, for forming a jet of high velocity air and for directing the cooling air from the root of the rotor blade inhibits recirculation, retards formation of the radial pumping boundary layer, decreases the thickness t of the radial pumping boundary layer and does work on the rotor blade.