Patent ID: 8403631

Claim:
A gas turbine engine, comprising: a compressor section, a combustor section and a turbine section; and said turbine section including at least one component having at least one platform and an airfoil extending from said at least one platform, wherein said platform includes an outer surface, a cover plate and a cooling channel extending between said outer surface and said cover plate, and said cooling channel receives cooling air to cool said at least one platform and said airfoil; an airfoil boss and opposing side rails extending from said outer surface in a direction opposite from said airfoil, wherein said airfoil boss and said opposing side rails extend an equal distance from said outer surface to receive said cover plate; and wherein the cooling air is communicated through an inlet hole in said cover plate and into said cooling channel to cool said at least one platform, and subsequently communicated through a side inlet of said airfoil boss to cool said airfoil.