METHOD AND SYSTEM TO FACILITATE COOLING TURBINE ENGINES

摘要

An engine assembly including a nozzle assembly. The nozzle assembly includes an inner band, an outer band (183) including an aft flange (504) and a radial inner surface (522), the aft flange including a plurality of cooling holes (508) configured to direct cooling fluid (526) therefrom at an oblique discharge angle (.alpha.), and at least one airfoil vane (510) extending between the inner band and the outer band.