Method and system to facilitate cooling turbine engines

Details Method and system to facilitate cooling turbine engines Method and system to facilitate cooling turbine engines

F - Mech Eng,Light,Heat,Weapons

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F01D 9/02 (2006.01) F01D 25/14 (2006.01) F02C 7/18 (2006.01) F02K 1/38 (2006.01)

Patent

CA 2603312

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.

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