Gas turbine engines including multi-curve stator vanes and...

F - Mech Eng,Light,Heat,Weapons – 01 – D

Patent

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F01D 9/02 (2006.01)

Patent

CA 2613787

A turbine nozzle assembly (50) is provided. The turbine nozzle assembly (50) includes a radially inner band (56), at least one stator vane (52) extending radially outward from the inner band, the stator vane includes an airfoil (53) including a root portion (284) extending from the inner band to a tip portion (282), the airfoil further including at least one lean directional change (174,176,182,184,186) and a plurality of sweep directional changes (196,198,202,204,206) defined between the root portion and the tip portion.

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