Turbine vane with end-wall leading edge cooling

摘要

A first stage guide vane used in a gas turbine engine, the guide vane including an airfoil portion extending between an inner shroud and an outer shroud, each shroud having an extension to form a flow transition for the hot gas flow from the combustor to the guide vane, and where the leading edge of the shroud extensions include a plurality of diffusion cooling holes opening onto the surface of the shroud extension to provide film cooling. Each diffusion cooling hole is in fluid communication with a cooling supply channel that runs along the shroud extension to provide convective cooling of the shroud extension; the cooling supply channel includes a metering hole to regulate the flow of cooling air into the channel. In the preferred embodiment, each diffusion cooling hole includes a separate cooling supply channel and a metering hole in order to regulate the individual cooling diffusion hole cooling air flow to provide specific cooling requirements for the specific location of the diffusion hole.