TURBINE VANE WITH A PLATFORM CAVITY HAVING A DOUBLE FEED FOR COOLING FLUID

摘要

A turbine vane for a gas turbine engine includes a platform with a cavity along the trailing edge having a double feed arrangement for injecting cooling fluid into the cavity. Various construction details are developed that provide a cavity having improved heat transfer due to the elimination of dead zones. In a particular embodiment, a turbine vane includes a platform cavity having a first inlet located on the pressure side of the platform and forward of an attachment rail and a second inlet located on the suction side and forward of the attachment rail. The cavity includes a plurality of trip strips and a plurality of film cooling passages. The trip strips extend from the corners of the cavity and are angled to encourage cooling fluid to flow into the corners. The film cooling passages direct the exiting cooling fluid to form a film of cooling fluid over the platform flow surface.