Gas turbine engine having support structure with swept leading edge

1. A nacelle assembly for a gas turbine engine comprising:

a core casing defined about an axis;

a fan nacelle mounted at least partially around the core nacelle;

a guide vane extending between the core casing and the fan nacelle; and

a support structure extending radially from the core casing to the fan nacelle, wherein the support structure has a leading edge that is swept and the support structure is aft of the guide vane relative to the axis,

wherein the leading edge has an angle relative to a radial axis of the gas turbine engine, the angle is from 10 degrees to 20 degrees, and

wherein the support structure comprises an upper bifurcation and a lower bifurcation each defining a respective one of the leading edge, the angle of the leading edge corresponding to the upper bifurcation being different from the angle of the leading edge corresponding to the lower bifurcation.

2. The nacelle assembly of claim 1 , wherein an interface between the core casing and the support structure is further upstream than an interface between the fan nacelle and the support structure relative to a direction of flow.

3. The nacelle assembly of claim 1 , wherein opposing sides of the support structure are contoured between the leading edge and a trailing edge.

4. The nacelle assembly of claim 1 , wherein the leading edge extends radially from the core casing to the fan nacelle.

5. A gas turbine engine having the nacelle assembly of claim 1 , wherein the gas turbine engine is a geared gas turbine engine.

6. The nacelle assembly of claim 1 , wherein the guide vane is swept.

7. A gas turbine engine comprising:

a fan, a compressor section, a combustor section, and a turbine section, the turbine section configured to drive a shaft to rotatably drive the fan and the compressor;

a geared architecture rotatably coupling the shaft and the fan; and

a nacelle having an inner wall providing a bypass duct configured to receive bypass air from the fan, a support structure extending radially from a core of the gas turbine engine to the inner wall, the support structure having at least one leading-edge that is swept, and the support structure being downstream of a plurality of guide vanes in the bypass duct,

wherein the at least one leading edge has an angle relative to a radial axis of the gas turbine engine, the angle is from 10 degrees to 20 degrees, and

wherein the support structure comprises an upper bifurcation and a lower bifurcation each defining a respective one of the at least one leading edge, the angle of the at least one leading edge corresponding to the upper bifurcation being different from the angle of the at least one leading edge corresponding to the lower bifurcation.

8. The gas turbine engine of claim 7 , wherein the at least one leading edge extends radially from the core to the inner wall.

9. The gas turbine engine of claim 7 , wherein each guide vane of the plurality of guide vanes is swept.

10. The gas turbine engine of claim 9 , wherein at least one guide vane of the plurality of guide vanes is circumferentially aligned with the support structure.

11. A method of influencing flow within a gas turbine engine, comprising:

providing a support structure within a bypass flowpath, the support structure having a swept leading edge downstream of a guide vane in the bypass flowpath,

wherein the swept leading edge has an angle relative to a radial axis of the gas turbine engine, the angle is from 10 degrees to 20 degrees, and

wherein the support structure comprises an upper bifurcation and a lower bifurcation each defining a respective one of the swept leading edge, the angle of the swept leading edge corresponding to the upper bifurcation being different from the angle of the swept leading edge corresponding to the lower bifurcation.

12. The method of claim 11 , wherein the guide vane is swept.