Patent ID: 7021893

Claim:
A component for use in a gas turbine engine comprising: an airfoil portion having a trailing edge; a coolant passageway having a plurality of coolant outlets formed by a plurality of spaced apart ribs; means for maximizing thermal performance of said component by reducing a relative diffusion angle between an injected coolant flow and a streamline direction if a fluid passing over said airfoil portion; said maximizing means comprising a non-linear array of teardrop shaped assemblies positioned adjacent said trailing edge and said teardrop shaped assemblies forming a plurality of injection slots for injecting a fan shaped coolant flow into said fluid passing over said airfoil portion; a pedestal array intermediate said coolant passageway and said trailing edge; and each said teardrop shaped assembly having a central longitudinal axis aligned with an axis of a respective coolant outlet formed by two of said spaced apart ribs, wherein a trailing edge of each of said teardrop shaped assemblies extends beyond said trailing edge of said airfoil portion.