Protective finish for wing tip devices

Patent metadata

Field	Value
Publication number	US-9845162-B2
Application number	US-201313887211-A
Country	US
Kind code	B2
Filing date	May 3, 2013
Priority date	May 3, 2013
Publication date	Dec 19, 2017
Grant date	Dec 19, 2017

Abstract

The present disclosure provides a system, method, and apparatus for a protective finish for an airfoil. In one or more embodiments, the disclosed method involves providing a sheath, and applying the sheath to the surface of the airfoil. In one or more embodiments, the sheath wraps around the surface of the airfoil from the leading edge of the airfoil towards the trailing edge of the airfoil. In at least one embodiment, the sheath covers approximately 50 percent to approximately 70 percent of the chord length of the airfoil. In some embodiments, the sheath is manufactured from at least one polymer, such as a polyurethane and/or a floropolymer. In one or more embodiments, the airfoil is a winglet, a raked wing tip, and/or a wing.

First claim

We claim:

1. A method for reducing disruptions to laminar airflow on an airfoil, the method comprising:
preventing airflow from contacting steps of paint layers on the airfoil via applying a sheath to a surface of the airfoil by wrapping the sheath around the surface of the airfoil from a leading edge of the airfoil towards a trailing edge of the airfoil, the sheath at least one of: covering, and eliminating the steps; and
eliminating disruptions to laminar airflow generating from an edge of an erosion cap on a leading edge of the airfoil via replacing the erosion cap via the sheath covering approximately 50 percent to approximately 70 percent of a chord length of the airfoil.

2. The method of claim 1 , wherein the method further comprises:
eliminating airflow contacting an apparatus securing the erosion cap to the airfoil; and
manufacturing the sheath from at least one polymer.

3. The method of claim 1 , wherein the method further comprises:
the sheath extending aft from the leading edge at least to a last point, along the chord length, designed for natural laminar flow on the airfoil; and
manufacturing the sheath from a polyurethane protective tape.

4. The method of claim 1 , wherein the method further comprises manufacturing the airfoil to have a monocoque carbon fiber architecture.

5. The method of claim 1 , wherein the method further comprises printing an image on a first side of the sheath, which is significantly transparent, wherein the image is located between the first side of the sheath and the surface of the airfoil such that the image shows through a second side of the sheath.

6. The method of claim 1 , wherein the applying of the sheath to the surface of the airfoil is achieved by an adhesion of an adhesive surface of the sheath to the surface of the airfoil.

7. The method of claim 1 , wherein the method further comprises manufacturing the sheath to be contoured corresponding to a shape of the airfoil.

8. A method for expanding an erosion control area and reducing disruptions to laminar airflow on an airfoil, the comprising:
replacing an existing erosion cap apparatus, extending aft approximately 10% of a wing chord line, via applying a sheath comprising a shape contoured corresponding to a shape of the airfoil, to the airfoil via wrapping the sheath around the surface of the airfoil from a leading edge of the airfoil towards a trailing edge of the airfoil and covering approximately 50 percent to approximately 70 percent of a chord length of the airfoil, and positioning an edge of the sheath, nearest the trailing edge of the airfoil, aft from the leading edge at least to a last point, along the chord length, designed for natural laminar flow on the airfoil.

9. The method of claim 8 , further comprising eliminating a disruption to laminar airflow caused by a paint step on the airfoil, via covering the paint step with the sheath, and wherein the sheath is manufactured from at least one polymer.

10. The method of claim 9 , further comprising eliminating a disruption to laminar airflow caused by a paint step on the airfoil, via removing the paint step and painting an image on a side of the sheath contacting the airfoil, and wherein the at least one polymer is at least one of a polyurethane and a floropolymer.

11. The method of claim 8 , wherein the sheath is manufactured from a polyurethane protective tape.

Assignees

• Boeing Co

Inventors

• Campbell Jr Darrell D

Classifications

• B64C23/065

  at the wing tips · CPC title

• Y10T156/10

  Methods of surface bonding and/or assembly therefor · CPC title

• B64D45/00 Primary

  Aircraft indicators or protectors not otherwise provided for · CPC title

• B64D2045/009

  Fire detection or protection; Erosion protection, e.g. from airborne particles · CPC title

• Y02T50/164

  Cross-Sectional Technologies · mapped topic