Multifunctional erosion protection strip

Patent metadata

Field	Value
Publication number	US-10035578-B2
Application number	US-201314646050-A
Country	US
Kind code	B2
Filing date	Nov 20, 2013
Priority date	Nov 20, 2012
Publication date	Jul 31, 2018
Grant date	Jul 31, 2018

Abstract

An airfoil article including a composite skin having a first surface and a second surface opposite first surface, forming a leading edge. The leading edge is during use subjected to an airflow meeting the leading edge at stagnation points. The leading edge includes an elongated member. The outer surface of the elongated member is arranged flush with the first surface of the composite skin such that an essentially smooth aerodynamic surface of the leading edge is formed. The elongated member is adapted to serve as an erosion protection of the leading edge and to function as an electrode of a plasma generating system.

First claim

The invention claimed is:

1. An airfoil article including a composite skin, the composite skin having a first surface and a second surface opposite to said first surface, the composite skin forming a leading edge and adapted to during use be subjected to an airflow meeting the leading edge at stagnation points, where the airflow is divided into a first and second airflow, and at which stagnation points the local velocity of the airflow is essentially zero, the leading edge comprising:
an elongated member comprising an electrically conductive material, the elongated member having an inner surface and an outer surface opposite to said inner surface, wherein the outer surface of said elongated member is arranged flush with the first surface of the composite skin such that an essentially smooth aerodynamic surface of the leading edge is formed, the elongated member has an extension in a length direction being essentially parallel with an imaginary line intersecting with the stagnation points of a zero angle of attack and a width extending in a chordwise direction and tapering in a direction from one distal end to another end along the leading edge, and
wherein the elongated member is configured to serve as an erosion protection of the leading edge and constitutes an electrode of a plasma generating system.

2. The airfoil article according to claim 1 , wherein the elongated member is further adapted to serve as a heating element of a de-/anti-icing system.

3. The airfoil article according to claim 1 , wherein the elongated member is adapted to serve as a conductor of a lightning conductor system.

4. The airfoil article according to claim 1 , wherein the elongated member is adapted to operate using alternating current.

5. The airfoil article according to claim 1 , wherein the elongated member is adapted to operate using a direct current and/or an alternating current superposed on a direct current.

6. The airfoil article according to claim 1 , wherein a length of the elongated member corresponds with at least a longitudinal length of the leading edge.

7. The airfoil article according to claim 1 , wherein the elongated member is a metal matrix composite.

8. The airfoil article according to claim 1 , wherein the elongated member is ceramic.

9. The airfoil article according to claim 1 , wherein the elongated member is metallic.

10. The airfoil article according to claim 1 , wherein a trailing edge of the airfoil article comprises a second elongated member having an outer surface flush with the outer surface of the composite skin, the second elongated member being provided to follow an imaginary line intersecting with the trailing edge.

11. The airfoil article according to claim 1 , wherein a width and a thickness of the elongated member, in combination with material selection of the elongated member, are determined such that the elongated member will be flexible in at least a length direction and/or a width direction of the elongated member, such that the elongated member can conform with a curvature of the leading edge.

12. The airfoil article according to claim 1 , wherein the elongated member is divided in lengthwise sections.

13. The airfoil article according to claim 1 , further comprising:
a barrier coating between the elongated member and the composite skin.

14. The airfoil article according to claim 1 , wherein the elongated member is fit into a recessed area of the composite skin, wherein a depth of the recessed area is essentially equal to the thickness of the elongated member after curing of the composite skin.

15. The airfoil article according to claim 1 , wherein the elongated member in the chordwise direction comprises a middle section and two outer sections, the elongated member has a greater thickness in the middle section than a thickness of each of the two outer sections.

16. The airfoil article according to claim 1 , wherein the airfoil article forms a leading edge part, designed to be replaceably fixed to an adjacent leading edge part, the article further comprising:
a first transverse scarf joint and a second transverse scarf joint adapted to fit adjacent leading edge parts.

17. An aircraft, comprising:
at least one airfoil article including a composite skin, the composite skin having a first surface and a second surface opposite to said first surface, the composite skin forming a leading edge and adapted to during use be subjected to an airflow meeting the leading edge at stagnation points for a zero angle of attack, where the airflow is divided into a first and second airflow, and at which stagnation points the local velocity of the airflow is essentially zero, the leading edge comprising:
an elongated member comprising an electrically conductive material, the elongated member having an inner surface and an outer surface opposite to said inner surface wherein the outer surface of said elongated member is arranged flush with the first surface of the composite skin such that an essentially smooth aerodynamic surface of the leading edge is formed, the elongated member has an extension in a length direction being essentially parallel with an imaginary line intersecting with the stagnation points and a width extending in a chordwise direction and tapering in a direction from one distal end to another end along the leading edge, and
wherein the elongated member is configured to serve as an erosion protection of the leading edge and constitutes an electrode of a plasma generating system; and a plasma generating system.

18. A system for an airfoil article, the airfoil article including a composite skin having a first surface and a second surface opposite to said first surface, the composite skin forming a leading edge and being adapted during use to be subjected to an airflow meeting the leading edge at stagnation points for a zero angle of attack, where the airflow is divided into a first and second airflow, and at which stagnation points a local velocity of the airflow is essentially zero, the leading edge comprising an elongated member comprising an electrically conductive material, the elongated member having an inner surface and an outer surface opposite to said inner surface wherein the outer surface of said elongated member, is arranged flush with the first surface of the composite skin such that an essentially smooth aerodynamic surface of the leading edge is formed, the elongated member has an extension in a length direction being essentially parallel with an imaginary line intersecting with stagnation points and a width extending in a chordwise direction at least covering stagnation points of a first angle of attack and stagnation points of a second angle of attack and an area therebetween and tapering in a direction from one distal end to another end along the leading edge, wherein the elongated member is configured to serve as an erosion protection of the leading edge, the system further comprising:
a plasma generating system comprising an actuator with a first electrode and a second electrode for generation of a plasma, wherein the elongated member constitutes said first electrode, and
at least one control unit electrically coupled to said elongated member for controlling an electrical power supply to the elongated member.

19. The system according to claim 18 , further comprising:
an anti-/de-icing system comprising a resistive heating element for heating of at least a part of a leading edge of the airfoil, wherein the elongated member constitutes said heating element.

20. The system according to claim

Assignees

• Saab Ab

Inventors

• Nordin Pontus
• Strindberg Göte

Classifications

• B64C2230/12

  by using electromagnetic tiles, fluid ionizers, static charges or plasma · CPC title

• F05D2240/303

  related to the leading edge of a rotor blade · CPC title

• F01D5/282

  Selecting composite materials, e.g. blades with reinforcing filaments · CPC title

• B64C23/00

  Influencing air flow over aircraft surfaces, not otherwise provided for · CPC title

• B64D45/02

  Lightning protectors; Static dischargers · CPC title