Reactive orthotropic lattice diffuser for noise reduction

Patent metadata

Field	Value
Publication number	US-9227719-B2
Application number	US-201313764062-A
Country	US
Kind code	B2
Filing date	Feb 11, 2013
Priority date	Mar 11, 2011
Publication date	Jan 5, 2016
Grant date	Jan 5, 2016

Abstract

An orthotropic lattice structure interconnects porous surfaces of the flap with internal lattice-structured perforations to equalize the steady pressure field on the flap surfaces adjacent to the end and to reduce the amplitude of the fluctuations in the flow field near the flap end. The global communication that exists within all of the perforations provides the mechanism to lessen the pressure gradients experienced by the end portion of the flap. In addition to having diffusive effects (diffusing the incoming flow), the three-dimensional orthogonal lattice structure is also reactive (acoustic wave phase distortion) due to the interconnection of the perforations.

First claim

The invention claimed is:

1. A flap of the type that is movably connected to an aircraft wing to provide control of an aircraft in flight, the flap comprising:
an elongated flap structure defining inboard and outboard ends and forward and rearward portions extending between the inboard and outboard ends, the elongated flap structure defining an upper side extending between the inboard and outboard ends and between the forward and rearward portions, and a lower side, wherein the upper side generally faces upwardly in use, and the lower side generally faces downwardly in use, and wherein the inboard end defines an inwardly-facing inboard end surface and the outboard end defines an outwardly-facing outboard end surface, and wherein the upper and lower sides define inboard and outboard end portions adjacent the inboard and outboard end surfaces, respectively, that tend to generate noise to form a noise source in use, and wherein:
at least a portion of at least one of the inboard and outboard end surfaces and at least one of the inboard and outboard end portions of the upper and lower sides include a perforated portion having perforations that are connected to corresponding perforations internal to the flap, wherein the internal perforations are located within at least one of the inboard and outboard end portions, wherein the internal perforations comprise an approximately orthogonal lattice arrangement, and wherein the connecting corresponding perforations comprise the substantially same cross-sectional shape and dimensions.

2. The flap of claim 1 , wherein the internal perforations comprise perforations extending into the flap from at least one of the inboard and outboard ends, wherein such extensions scale approximately with the flap edge maximum thickness t max .

3. The flap of claim 1 , wherein all perforations comprise the substantially same cross-sectional shape and dimensions.

4. The flap of claim 1 , wherein all perforations comprise a substantially uniform repeating pattern.

5. The flap of claim 1 , wherein the perforations for the at least a portion of at least one of the inboard and outboard end surfaces and the at least one of the inboard and outboard end portions of the upper and lower sides define a non-uniform pattern.

6. The flap of claim 1 , wherein the perforations for the at least a portion of at least one of the inboard and outboard end surfaces and the at least one of the inboard and outboard end portions of the upper and lower sides vary in at least one of cross-section shape and dimensions.

7. The flap of claim 1 , wherein all perforations have a substantially octagonal cross-sectional shape.

8. The flap of claim 1 , wherein one or more perforations has a cross-section which varies in size along its length.

9. The flap of claim 1 , wherein perforations for the at least a portion of at least one of the inboard and outboard end surfaces and the at least one of the inboard and outboard end portions of the upper and lower sides comprise a porosity of less than approximately 40 percent.

10. The flap of claim 1 , wherein the global communication between all perforations lessens the pressure gradients experienced by the inboard and outboard ends of the flap, and alters both the steady and unsteady components of the flow field at the inboard and outboard ends of the flap.

11. The flap of claim 1 , wherein the global communication between all perforations diffuses the incoming flow around the inboard and outboard ends of the flap and distorts the acoustic wave phase.

12. The flap of claim 1 , wherein the perforations for the at least a portion of at least one of the inboard and outboard end surfaces and the at least one of the inboard and outboard end portions of the upper and lower sides increase in size from the forward portion to the rearward portion.

13. The flap of claim 12 , wherein the perforations have a substantially uniform diameter.

14. The flap of claim 1 , wherein all perforations have a substantially circular cross-sectional shape.

15. The flap of claim 14 , wherein s/d, the ratio of perforation spacing s between the centers of two adjacent perforations to the perforation diameter d, is within the range of approximately 1.4<s/d<approximately 2.0.

16. The flap of claim 14 , wherein all perforations have the substantially same dimension.

17. A method of reducing aircraft noise, the method comprising:
determining at least one frequency of excess noise generated, at least in part, at an end of a wing flap when the wing flap is in a deployed position;
determining a specific geometry of perforations in at least a portion of at least one of an inboard and outboard end surface and at least one of an inboard and outboard end portion of the upper and lower sides, and the geometry of corresponding connecting perforations internal to the flap and located within at least one of the inboard and outboard end portions, wherein the internal perforations comprise an approximately orthogonal lattice arrangement, that will, in use, absorb at least a substantial portion of sound at the frequency of the excess noise; and
providing the determined specific geometry in the flap.

18. A method of reducing noise in a lift producing isolated airfoil tip, the method comprising:
determining at least one frequency of excess noise generated, at least in part, at an end of the airfoil;
determining a specific geometry of perforations in surfaces of the airfoil and corresponding connecting perforations internal to the airfoil, wherein all perforations are in global communication, further wherein the internal perforations comprise an approximately orthogonal lattice arrangement, that will, in use, absorb at least a substantial portion of sound at the frequency of the excess noise; and
providing the determined specific geometry in the airfoil.

Assignees

• Nasa

Inventors

• Khorrami Mehdi R

Classifications

• B64C9/18 Primary

  by single flaps · CPC title

• B64C1/40 Primary

  Sound or heat insulation {, e.g. using insulation blankets} · CPC title

• B64C2230/14

  achieving noise reductions · CPC title

• Y02T50/10

  Drag reduction · CPC title

• B64C2230/22

  by using a surface having multiple apertures of relatively small openings other than slots · CPC title