Airfoil for a turbofan engine

Patent metadata

Field	Value
Publication number	US-11965425-B2
Application number	US-202217828112-A
Country	US
Kind code	B2
Filing date	May 31, 2022
Priority date	May 31, 2022
Publication date	Apr 23, 2024
Grant date	Apr 23, 2024

Abstract

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.

First claim

What is claimed is:

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, wherein the leading edge defines a plurality of peaks and a plurality of valleys alternatingly arranged along the spanwise direction;
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, wherein each of the inlets of the plurality of cavities is positioned in a valley of the plurality of valleys, wherein the plurality of cavities are empty; and
a plurality of porous face sheets positioned on at least one inlet of the plurality of cavities, wherein each porous face sheet of the plurality of porous face sheets are positioned in a valley of the plurality of valleys.

2. The airfoil of claim 1 , wherein each cavity of the plurality of cavities includes only one inlet, and wherein the plurality of cavity walls are adjacent to one another.

3. The airfoil of claim 1 , 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 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.

5. 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.

6. 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.

7. 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.

8. 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.

9. 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, wherein each cavity of the plurality of cavities is a closed cavity, and wherein the plurality of cavities are empty; and
a porous face sheet positioned on at least one inlet of the plurality of cavities.

10. The turbofan engine of claim 9 , wherein each cavity of the plurality of cavities extends generally parallel to a camber line of the airfoil, wherein the plurality of cavity walls are adjacent to one another.

11. The turbofan engine of claim 9 , 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 the porous face sheet is a plurality of porous face sheets and each of the plurality of porous face sheets are positioned in a valley of the plurality of valleys.

12. The airfoil of claim 11 , 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.

13. The turbofan engine of claim 9 , 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.

14. The turbofan engine of claim 9 , wherein a cavity wall of the plurality of cavity walls is oriented obliquely relative to the spanwise direction and the chordwise direction.

15. The turbofan engine of claim 9 , 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.

16. 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, wherein each cavity of the plurality of cavities is closed, and wherein the plurality of cavities are empty; and
a porous face sheet positioned on at least one inlet of the plurality of cavities.

17. The airfoil of claim 16 , wherein each cavity of the plurality of cavities extends generally parallel to a camber line of the airfoil, and wherein the plurality of cavity walls are adjacent to one another.

18. The airfoil of claim 16 , wherein the porous face sheet is a plurality of porous face sheets disposed along the leading edge.

19. The airfoil of claim 16 , 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.

20. The airfoil of claim 16 , wherein a cavity wall of the plurality of cavity walls is oriented obliquely relative to the spanwise direction and the chordwise direction.

Assignees

• Gen Electric

Inventors

• Wood Trevor Howard
• Ramakrishnan Kishore

Classifications

• F01D25/04 Primary

  Antivibration arrangements · CPC title

• F01D5/141

  Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147) · CPC title

• F01D5/145

  Means for influencing boundary layers or secondary circulations (for compressors F04D29/68) · CPC title

• F01D5/18 Primary

  Hollow blades, {i.e. blades with cooling or heating channels or cavities (structure of hollow blades in general F01D5/147)}; Heating, heat-insulating or cooling means on blades · CPC title

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title