Component for a gas turbine engine

摘要

A turbine blade (30) for a gas turbine engine is provided with improved cooling at a radially outer portion of the trailing edge (34). A tip flag path (50) is provided with a first pedestal array (62) to increase the heat transfer at the area. In addition, a second pedestal array (64) replaces the metering holes (46) which has been positioned radially inwardly of the tip strip (48). The two pedestal arrays (62, 64) provide improved heat transfer at an area which has been subject to burning and spallation in the prior art.