TURBOMACHINERY BLADE HAVING A PLATFORM RELIEF HOLE, PLATFORM COOLING HOLES, AND TRAILING EDGE CUTBACK

摘要

A method is disclosed that includes providing a turbomachinery blade having an airfoil connected to a platform in a root region of the turbomachinery blade. The airfoil has a trailing edge extending from the root region to a tip distal from the root region. The method further includes forming a blind relief hole in the platform proximate the trailing edge of the airfoil, and forming a plurality of cooling holes in the platform.