Cooled highly twisted airfoil for a gas turbine engine

摘要

A cooled highly twisted airfoil (1) includes an integrally formed continuous warped wall (12) defined as a surface of revolution about an axis (13) with the axis determined such that the axis intersects the plane of a section along a desired centerline. Such an internal wall structure separates adjacent cooling cavities (10) and (11) and includes relatively precisely aligned impingement holes (14) for directing cooling air to the leading edge (6) of a highly twisted airfoil. Such a structure minimizes the complexity of the ceramic core and die inserts required to cast such an airfoil, thereby decreasing manufacturing costs while increasing the overall cooling efficiency of the blade.