Gas turbine engine component cooling scheme

摘要

A gas turbine engine component (28) includes a platform (30) and an airfoil (32) extending from the platform (30). The platform (30) includes an outer surface (38). A cover plate (52) is positioned adjacent to the outer surface (38) of the platform (30). A cooling channel (54) extends between the outer surface (38) and the cover plate (52) and receives cooling air to cool the platform (30) and the airfoil (32).