Aircraft part anti-icing treatment method

Abstract

A method for the anti-icing treatment of a surface of an aircraft part made of an organic matrix composites includes a texturing step in which the surface is irradiated with femtosecond laser pulses so as to render the surface superhydrophobic.

Claims

1. A method for treating a surface of an aircraft part made of organic matrix composites and for assembling said aircraft part, the method comprising: a texturing step in which the surface is irradiated by femtosecond laser pulses so as to make the surface superhydrophobic; and assembling a piezoelectric component with said aircraft part, the piezoelectric component forming a mechanical de-icing device being configured to generate vibration to break ice accumulated on the surface of the aircraft part.

2. The method according to claim 1, wherein the pulses have a duration of less than 900 femtoseconds.

3. The method according to claim 1, wherein the pulses have a duration of less than 600 femtoseconds.

4. The method according to claim 1, wherein the texturing step is preceded by a step of protecting the surface by applying an organic paint.

5. The method according to claim 4, wherein the paint comprises an epoxy base or a polyurethane base.

6. An assembly of the piezoelectric component and the aircraft part according to claim 1, the aircraft part being made of organic matrix composites.

7. The assembly according to claim 6, wherein the surface of the aircraft part made of organic matrix composites is provided with: micro-craters having a diameter less than 1 mm and a depth less than 10 ?m, and lashes having a dimension less than 1 ?m, the lashes being periodically spaced.

8. The assembly according to claim 7, wherein the micro-craters of the aircraft part made of organic matrix composites have a diameter between 1 ?m and 100 ?m.

9. The assembly according to claim 7, wherein the micro-craters of the aircraft part made of organic matrix composites have a depth between 600 nm and 1 ?m.

10. The assembly according to claim 7, wherein the lashes of the aircraft part made of organic matrix composites have a dimension between 1 nm and 800 nm, the lashes being periodically spaced.

11. The assembly according to claim 6, the aircraft part made of organic matrix composites being an air inlet section of the aircraft, said surface being a surface of a leading edge and/or a trailing edge of the air inlet section.

12. An aircraft propulsion unit comprising the assembly according to claim 6.

13. An aircraft comprising the propulsion unit according to claim 12.

14. An aircraft comprising the assembly according to claim 6.

15. The method according to claim 1, wherein the texturing step causes the surface to form a plurality of micro-craters.

16. The method according to claim 15, wherein the piezoelectric component is configured to break the ice accumulated on micro-crater surfaces of the plurality of micro-craters.

17. An aircraft propulsion unit comprising: an air inlet section comprising an air inlet lip made of organic matrix composites, the air inlet lip having a surface treated with a method comprising a texturing step in which the surface is irradiated by femtosecond laser pulses so as to make the surface superhydrophobic; and a piezoelectric component forming a mechanical de-icing device configured to generate vibration to break ice accumulated on vibrate the surface of the air inlet lip.

Description

DRAWINGS

(1) In order that the disclosure may be well understood, there will now be described various forms thereof, given by way of example, reference being made to the accompanying drawings, in which:

(2) FIG. 1 is a schematic view of an aircraft propulsion unit provided with a nacelle and an engine to which the teachings of the present disclosure are applied;

(3) FIG. 2 is a longitudinal sectional view of an air inlet section of the nacelle of the propulsion unit of FIG. 1; and

(4) FIG. 3 is a schematic view of a portion of a surface textured using the method according to the present disclosure.

(5) The drawings described herein are for illustration purposes only and are not intended to limit the scope of the present disclosure in any way.

DETAILED DESCRIPTION

(6) The following description is merely exemplary in nature and is not intended to limit the present disclosure, application, or uses. It should be understood that throughout the drawings, corresponding reference numerals indicate like or corresponding parts and features.

(7) FIG. 1 illustrates an aircraft propulsion unit comprising a nacelle 1 supporting an engine 2 of the turbojet engine type. The nacelle 1 is suspended from a pylon 3 connected to a wing (not shown) of the aircraft (not shown).

(8) This nacelle 1 comprises an air inlet section 10, a middle section 11, and a downstream section 12 which may provide for thrust reversal.

(9) With reference to FIG. 2, the air inlet section 10 comprises a lip 100 forming a leading edge and, in the extension of the lip 100, a section including an inner wall 111 and an outer wall 112 forming respective trailing edges. The outer wall 112 is radially away from the inner wall 111. The inner wall 111 is in contact with a cold air flow F passing through the nacelle 1.

(10) In this example, the inner 111 and outer 112 walls are made of organic matrix composites.

(11) In this example, the lip 100 delimits, with an inner partition 4, an annular inner space capable of receiving an anti-icing treatment device (not shown). This device may be a pneumatic or electrical de-icing or anti-icing device.

(12) In a non-limiting example of implementation of the present disclosure, a surface of the inner wall 111 of the air inlet section 10 is made superhydrophobic by irradiation with femtosecond laser pulses. The laser pulses may have a duration of less than 900 femtoseconds. In one form, the laser pulses have a duration of less than 600 femtoseconds.

(13) The hydrophobic characterization of a material is done by measuring the contact angle between the flat surface thereof and a drop of water placed on the surface thereof. The standard materials have an angle of less than 90?, the hydrophobic materials have an angle between 90? and 150?, and the superhydrophobic materials have an angle greater than 150?.

(14) The femtosecond laser irradiation is a surface texturing step which may give rise to micro-craters 50 and lashes 60.

(15) As illustrated in FIG. 3, the micro-craters 50 are separated by flattened tops 51 and the lashes 60 are periodically spaced in the micro-craters 50.

(16) In forms which are not shown, the textured surface may comprise lashes in the micro-craters and on the tops, or only at the tops.

(17) The superhydrophobic properties of the present disclosure may be obtained by the following:

(18) micro-craters 50 having a diameter D1 less than 1 mm and a depth less than 10 ?m. In one form, the micro-craters 50 have a diameter between 1 ?m and 100 ?m. In one form, the micro-craters 50 have a depth between 600 nm and 1 ?m, and

(19) lashes having a dimension D2 less than 1 ?m. In one form of the present disclosure, the lashes have a dimension D2 between 1 nm and 800 nm.

(20) Such a treatment method may also be implemented to texturize the outer surface 112 of the air inlet section 10, which allows making the nacelle 1 compatible with an open rotor type turbojet engine, that is to say having an unducted fan at the downstream section thereof.

(21) The lip 100 of the air inlet section 10 may also be made superhydrophobic using the method of the present disclosure. The superhydrophobic character of the air inlet lip advantageously allows using a piezoelectric component de-icing device. The piezoelectric component de-icing comprises vibrating the surface to be de-iced in order to break and remove the weak layers of ice accumulated on the lip. Thus, the use of a superhydrophobic surface in addition to a piezoelectric type mechanical de-icing device allows facilitating the unhooking of the ice, in that the adhesive force of the ice on the wall of the element to be de-iced is reduced.

(22) The present disclosure is not limited to the examples which have been described herein and many adjustments may be made to these examples without departing from the scope of the present disclosure. For example, the method according to the present disclosure may be implemented for texturing other aircraft parts such as a wing, an empennage, or any other portion of a nacelle or of the aircraft requiring a treatment against the accretion of frost, and more particularly any part comprising a surface constituting a trailing or leading edge.

(23) Unless otherwise expressly indicated herein, all numerical values indicating mechanical/thermal properties, compositional percentages, dimensions and/or tolerances, or other characteristics are to be understood as modified by the word about or approximately in describing the scope of the present disclosure. This modification is desired for various reasons including industrial practice, material, manufacturing, and assembly tolerances, and testing capability.

(24) As used herein, the phrase at least one of A, B, and C should be construed to mean a logical (A OR B OR C), using a non-exclusive logical OR, and should not be construed to mean at least one of A, at least one of B, and at least one of C.

(25) The description of the disclosure is merely exemplary in nature and, thus, variations that do not depart from the substance of the disclosure are intended to be within the scope of the disclosure. Such variations are not to be regarded as a departure from the spirit and scope of the disclosure.