Gas turbine vane with integral cooling flow control system

摘要

A turbine vane usable in a turbine engine and having at least one cooling system. The cooling system includes a leading edge cavity and a trailing edge cavity. The cavities may be separated with a metering rib having one or more metering orifices for regulating flow of cooling fluids to a manifold cooling system and to trailing edge exhaust orifices. In at least one embodiment, the trailing edge cavity may be a serpentine cooling pathway and the leading edge cavity may include a plurality of leading edge cooling paths.