Gas turbine engines including lean stator vanes and methods...

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

Patent

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F01D 9/02 (2006.01)

Patent

CA 2613766

A turbine nozzle assembly (50) is provided. The turbine nozzle assembly (50) includes a radially inner band (56), at least one stator vane (52,122) extending radially outward from the inner band, the stator vane includes an airfoil (53) including a root portion (184) and a tip portion (182), the root portion extending from the inner band with a negative lean, the tip portion formed with a positive lean.

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