Geared low fan pressure ratio fan exit guide vane stagger angle
A fan exit guide vane assembly for a gas turbine engine includes a plurality of guide vanes having a pressure side and a suction side extending between a leading edge and a trailing edge. The vanes further include a span extending between a root and tip with a stagger angle defined as an angle between a longitudinal axis parallel to an engine axis of rotation and a line connecting the leading edge and the trailing edge that is less than about 15°.
1. A gas turbine engine comprising:
a turbine driven fan rotor including a plurality of fan blades rotatable about an axis;
a core engine including a turbine section that drives the fan rotor;
a duct circumscribing the fan rotor and defining a passageway aft of the fan rotor about the core engine; and
a fan exit guide vane assembly including a plurality of fan exit guide vanes positioned downstream of the fan rotor within the duct, wherein each of the plurality of fan exit guide vanes includes a stagger angle of less than 15° within a midspan portion relative to a line parallel to the axis, and the stagger angle varies along a span between a root and a tip as shown by percent average span location values set out in Table 1.
2. The gas turbine engine as recited in claim 1 , wherein the stagger angle is less than 12° within the midspan portion.
3. The gas turbine engine as recited in claim 1 , wherein the stagger angle is between 8° and 12° within the midspan portion.
4. The gas turbine engine as recited in claim 1 , wherein the midspan portion is between 40% and 85% of a total span of the plurality of fan exit guide vanes.
5. The gas turbine engine as recited in claim 1 , wherein a difference between a maximum stagger angle and a minimum stager angle for each of the plurality of fan exit guide vanes is less than 6°.
6. The gas turbine engine as recited in claim 1 , wherein the duct defines a bypass duct with a bypass ratio being defined as a portion of air delivered into the bypass duct divided by an amount of air delivered into the core engine, with the bypass ratio being greater than 6.0.
7. The gas turbine engine as recited in claim 6 , wherein the bypass ratio is greater than 10.0.
8. The gas turbine engine as recited in claim 1 , wherein a fan pressure ratio across the plurality of fan blades is less than 1.5.
9. The gas turbine engine as recited in claim 1 , wherein each of the plurality of fan exit guide vanes support at least a portion of the core engine.
10. The gas turbine engine as recited in claim 1 , including a geared architecture driven by the turbine section for rotating the fan rotor about the axis.
11. A fan exit guide vane assembly for a gas turbine engine comprising:
a plurality of guide vanes including a pressure side and a suction side extending between a leading edge and a trailing edge and a span extending between a root and tip, wherein a stagger angle defined as an angle between a longitudinal axis parallel to an engine axis of rotation and a line connecting the leading edge and the trailing edge is less than 15° within a midspan portion, and the stagger angle varies along a span between a root and a tip as shown by percent average span location values set out in Table 1.
12. The fan exit guide vane assembly as recited in claim 11 , wherein the stagger angle varies along the span from the root to the tip with a difference between a maximum stagger angle and a minimum stagger angle along the span is less than 6°.
13. The fan exit guide vane assembly as recited in claim 11 , wherein the stagger angle is less than 12° within the midspan portion.
14. The fan exit guide vane assembly as recited in claim 11 , wherein the midspan portion is between 40% and 85% of a total span for each of the plurality of guide vanes.
15. A method of assembling a fan exit guide vane assembly comprising:
forming a plurality of guide vanes to include a pressure side and a suction side extending between a leading edge and a trailing edge and a span extending between a root and tip, wherein a stagger angle defined as an angle between a longitudinal axis parallel to an engine axis of rotation and a line connecting the leading edge and the trailing edge is less than 15° within a midspan portion and the stagger angle varies along a span between a root and a tip as shown by percent average span location values set out in Table 1; and arranging the plurality of guide vanes for assembly within a bypass duct.
16. The method as recited in claim 15 , including forming each of the plurality of guide vanes to include a stagger angle between 8° and 12° within the midspan portion.
17. The method as recited in claim 15 , including forming each of the plurality of guide vanes to include a varying stagger angle between the root and the tip with a difference between a maximum stagger angle and a minimum stagger angle for each of the plurality of guide vanes is less than 6°.