GAS TURBINE BLADE SQUEALER TIP, CORRESPONDING MANUFACTURING AND COOLING METHODS AND GAS TURBINE ENGINE

摘要

Gas turbine engine blade squealer tip includes that cooling slit is formed in the downstream guidance cooling gas stream in suction side water rail forward position along inward flange sound tip pressure side rail. Some embodiments include end vertical empennage sucking siding track close to cooling bath. It is segmented before the opposite turbine shroud abradable surface of suction side rail embodiment abrasion, may be with pressure side rail, reducing possibility, on the pressure side shoe frictionally heats. A possibility that cooler pump siding track is reduced during turbine engine operation squealer tip corrodes.