Cooled turbine blades for a gas turbine engine

摘要

The blade has a front edge cooling channel (14) radially extending into a blade leaf (8) relative to an axis of rotation of a gas turbine engine, and including nozzle-shaped air guiding channels (12). The cooling channel extends into the blade leaf up to a blade base (6) for producing wall-sided cooling air stream with high peripheral speed. The air guiding channels open into the cooling channel in a region of the blade base with tangential speed components. The air guiding channels are connected with a cavity (13) formed at the blade base or subjected with air via an air channel (17).