Airfoil for a turbofan engine
An airfoil is provided defining a spanwise direction, a chordwise direction, a root end, a tip end, a leading edge end, and a trailing edge end. The airfoil includes: a leading edge extending from the leading edge end; a body extending along the spanwise direction between the root end and the tip end, the body including a plurality of cavity walls defining a plurality of cavities, each of the plurality of cavities having an inlet located at the leading edge; and a porous face sheet positioned on at least one inlet of the plurality of cavities.
1. An airfoil defining a spanwise direction, a chordwise direction, a root end, a tip end, a leading edge end, and a trailing edge end, the airfoil comprising:
a leading edge extending from the leading edge end;
a body extending along the spanwise direction between the root end and the tip end, the body comprising a plurality of cavity walls defining a plurality of cavities, each of the plurality of cavities having an inlet located at the leading edge; and
a porous face sheet positioned on at least one inlet of the plurality of cavities, wherein the porous face sheet is a plurality of porous face sheets,
wherein the airfoil defines a pressure side and a suction side,
wherein the plurality of porous face sheets include a plurality of first side porous face sheets located on the pressure side of the airfoil and a plurality of second side porous face sheets located on the suction side of the airfoil; and
wherein the plurality of porous face sheets alternate between the plurality of first side porous face sheets and the plurality of second side porous face sheets along the spanwise direction of the airfoil.
2. The airfoil of claim 1 , wherein each cavity of the plurality of cavities includes only one inlet.
3. The airfoil of claim 2 , wherein each cavity of the plurality of cavities extends generally parallel to a camber line of the airfoil.
4. The airfoil of claim 1 , wherein the leading edge defines a plurality of peaks and a plurality of valleys alternatingly arranged along the spanwise direction.
5. The airfoil of claim 4 , wherein each of the inlets of the plurality of cavities is positioned in a valley of the plurality of valleys, and wherein each of the plurality of porous face sheets are positioned in a valley of the plurality of valleys.
6. The airfoil of claim 5 , wherein the airfoil comprises a plurality of impermeable portions, wherein each of the impermeable portions of the plurality of impermeable portions are positioned on a peak of the plurality of peaks.
7. The airfoil of claim 1 , wherein the plurality of porous face sheets include a pressure side porous face sheet and a suction side porous face sheet, and wherein the pressure side porous face sheet is located on the pressure side of the airfoil and the suction side porous face sheet is located on the suction side of the airfoil.
8. The airfoil of claim 1 , wherein the airfoil includes a cavity group that comprises the plurality of cavities, wherein the cavity group comprises a first cavity having a first depth and a second cavity having a second depth, wherein the first depth differs from the second depth by at least ten percent and up to two thousand percent.
9. The airfoil of claim 1 , wherein a cavity wall of the plurality of cavity walls is oriented obliquely relative to the spanwise direction and the chordwise direction.
10. The airfoil of claim 1 , wherein the porous face sheet is a plurality of porous face sheets and the airfoil comprises a plurality of impermeable portions, wherein at least one impermeable portion is positioned between two porous face sheets of the plurality of porous face sheets along the spanwise direction.
11. The airfoil of claim 1 , wherein the airfoil is an outlet guide vane for a propulsion system, wherein the propulsion system is a turbofan engine, a hybrid electric propulsion system, or an electric propulsion system, and wherein the propulsion system comprises a fan section having a fan, and wherein the outlet guide vane is positioned downstream of the fan.
12. A turbofan engine comprising:
a fan section that comprises a fan having a plurality of fan blades;
a turbomachine disposed downstream from the fan section, the turbomachine comprising a compressor section, a combustion section, and a turbine section in serial flow arrangement; and
a plurality of circumferentially-spaced outlet guide vanes that are positioned downstream of the fan, wherein each of the outlet guide vanes define a spanwise direction, a chordwise direction, a root end, a tip end, a leading edge end, and a trailing edge end, each of the outlet guide vanes comprising:
a leading edge extending from the leading edge end;
a body extending along the spanwise direction between the root end and the tip end, the body comprising a plurality of cavity walls defining a plurality of cavities, each of the plurality of cavities having an inlet located at the leading edge; and
a porous face sheet positioned on at least one inlet of the plurality of cavities,
wherein the porous face sheet is a plurality of porous face sheets,
wherein each of the outlet guide vanes define a pressure side and a suction side,
wherein the plurality of porous face sheets include a plurality of first side porous face sheets located on the pressure side of the airfoil and a plurality of second side porous face sheets located on the suction side of the airfoil; and
wherein the plurality of porous face sheets alternate between the plurality of first side porous face sheets and the plurality of second side porous face sheets along the spanwise direction of the airfoil.
13. The turbofan engine of claim 12 , wherein each cavity of the plurality of cavities is a closed cavity.
14. The turbofan engine of claim 12 , wherein each cavity of the plurality of cavities extends generally parallel to a camber line of the airfoil.
15. The turbofan engine of claim 12 , wherein the leading edge defines a plurality of peaks and a plurality of valleys alternatingly arranged along the spanwise direction, wherein each of the inlets of the plurality of cavities is positioned in a valley of the plurality of valleys, and wherein each of the plurality of porous face sheets are positioned in a valley of the plurality of valleys.
16. The airfoil of claim 15 , wherein the airfoil comprises a plurality of impermeable portions, wherein each of the impermeable portions of the plurality of impermeable portions are positioned on a peak of the plurality of peaks.
17. The airfoil of claim 12 , wherein the plurality of porous face sheets include a pressure side porous face sheet and a suction side porous face sheet, and wherein the pressure side porous face sheet is located on the pressure side of each of the outlet guide vanes and the suction side porous face sheet is located on the suction side of each of the outlet guide vanes.
18. The turbofan engine of claim 12 , wherein the airfoil includes a cavity group that comprises the plurality of cavities, wherein the cavity group comprises a first cavity having a first depth and a second cavity having a second depth, wherein the first depth differs from the second depth by at least ten percent and up to two thousand percent.
19. The turbofan engine of claim 12 , wherein a cavity wall of the plurality of cavity walls is oriented obliquely relative to the spanwise direction and the chordwise direction.
20. The turbofan engine of claim 12 , wherein the porous face sheet is a plurality of porous face sheets and the airfoil comprises a plurality of impermeable portions, wherein at least one impermeable portion is positioned between two porous face sheets of the plurality of porous face sheets along the spanwise direction.