Patent ID: 8511994

Claim:
A gas turbine engine component comprising: an airfoil, said airfoil extending from a leading edge to a trailing edge, and having a suction side having a suction wall and a pressure side having a pressure wall; cooling passages extending from a root of said airfoil toward a tip of said airfoil, and said cooling passages including a straight passage extending from said root toward said tip and adjacent said leading edge, and a serpentine passage having at least three connected paths and spaced from said straight passage toward said trailing edge; a respective pressure side cooling circuit provided between said pressure wall and each corresponding one of said at least three connected serpentine paths, and said straight passage, and a suction side cooling circuit provided between said suction wall and said straight passage, but there being no side cooling circuit between at least a downstream one of said at least three connected paths of said serpentine passage and said suction wall; each said pressure side cooling circuits and said suction side cooling circuit are all microcircuits and a thickness of said microcircuits measured between said suction or pressure wall and said cooling passages is between .030 and .010 inch: and there being no microcircuit cooling on said suction wall between a gage point and said trailing edge.