Gas turbine engines including multi-curve stator vanes and methods of assembling the same
AssigneeGeneral Electric Company
InventorsScott Andrew Burton, Chander Prakash, Joseph Machnaim, David Glenn Cherry, Robert John Beacock, Ching-Pang Lee, Scott Michael Carson
Life of this patent
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Abstract
A stator vane that may be used in engine assemblies. The stator vane includes an airfoil having a first sidewall and a second sidewall that is coupled to the first sidewall at a leading edge and at a trailing edge. The airfoil extends radially from a root portion to a tip portion. Each of the leading and trailing edges includes at least one lean directional change and a plurality of sweep directional changes that are defined between the root portion and the tip portion.
Claims15
A method for assembling a gas turbine engine, said method comprising:
- coupling at least one stator assembly including at least one stator vane extending from an inner band within the gas turbine engine, wherein the at least one stator vane extends from a root portion extending from the inner band to a tip portion, and wherein the at least one stator vane includes a midpoint defined approximately halfway between the root portion and the tip portion, and a leading edge that includes a plurality of sweep directional changes defined between the root portion and the midpoint and at least one lean directional change and a plurality of sweep directional changes defined between the root portion and the tip portion;
- and
- coupling at least one turbine blade assembly including at least one rotor blade downstream from the stator assembly.
A turbine nozzle assembly comprising:
- a radially inner band;
- and
- at least one stator vane extending radially outward from said inner band, said stator vane comprising an airfoil comprising a root portion extending from said inner band to a tip portion and a leading edge extending between said root portion and said tip portion, and a midpoint defined approximately halfway between said root portion and said tip portion, said airfoil further comprising at least one lean directional change and a plurality of sweep directional changes defined between said root portion and said tip portion, and said leading edge comprises at least two sweep directional changes defined between said root portion and said midpoint.
A stator vane comprising an airfoil comprising:
- a first sidewall;
- and
- a second sidewall coupled to said first sidewall at a leading edge and at a trailing edge, said airfoil extending radially from a root portion to a tip portion, each of said leading and trailing edges comprising at least one lean directional change and a plurality of sweep directional changes defined between said root portion and said tip portion, said airfoil further comprises a midpoint defined approximately halfway between said root portion and said tip portion, and said leading edge comprises at least two sweep directional changes defined between said root portion and said midpoint.
Dependencies are inferred from the claim text.