HIGH PRESSURE TURBINE COOLING OF GAS TURBINE ENGINE

摘要

A gas turbine engine (10) having improved high pressure turbine cooling is disclosed. Relatively cool intermediate pressure (P2x) air is tapped off from a region of a compressor section prior to full compression. The cooling air is lead via conduits to the high pressure turbine, where the rotor and finally the blades of the turbine are cooled. Additionally the diverted air may be used to seal a rear bearing compartment and cool the main shaft within the engine.