Method for producing a perforated nacelle inlet assembly

Patent metadata

Field	Value
Publication number	US-12077320-B2
Application number	US-202318165714-A
Country	US
Kind code	B2
Filing date	Feb 7, 2023
Priority date	Jul 15, 2022
Publication date	Sep 3, 2024
Grant date	Sep 3, 2024

Abstract

A method for producing a nacelle inlet assembly includes forming a composite panel that has a carbon fiber reinforced polymer (CFRP) material. The composite panel is formed to have a curved contour that represents at least a portion of an annular barrel shape. The method includes applying a metallic coating to the composite panel to form a lipskin. The metallic coating is applied such that the metallic coating defines an exterior surface of the lipskin and the composite panel defines an interior surface of the lipskin. The method includes laser drilling a plurality of perforations through the lipskin. The laser drilling involves emitting a laser beam that impinges upon the interior surface of the lipskin and penetrates the CFRP material of the composite panel before penetrating the metallic coating and exiting the lipskin through the exterior surface.

First claim

What is claimed is:

1. A method for producing a nacelle inlet assembly, the method comprising:
forming a composite panel that includes a carbon fiber reinforced polymer (CFRP) material, the composite panel formed to have a curved contour that represents at least a portion of an annular barrel shape;
applying a metallic coating to the composite panel to form a lipskin, the metallic coating applied such that the metallic coating defines an exterior surface of the lipskin and the composite panel defines an interior surface of the lipskin; and
laser drilling a plurality of perforations through the lipskin, wherein the laser drilling comprises emitting a laser beam that impinges upon the interior surface of the lipskin and penetrates the CFRP material of the composite panel before penetrating the metallic coating and exiting the lipskin through the exterior surface.

2. The method of claim 1 , wherein the perforations are laser drilled through the lipskin at different locations within a perforation zone of the lipskin that encompasses a leading edge of the lipskin, and a percent open area of the perforation zone is less than 2%.

3. The method of claim 1 , wherein the perforations are laser drilled through the lipskin to have an average exit diameter at the exterior surface of less than 100 microns.

4. The method of claim 3 , wherein the average exit diameter at the exterior surface of is less than 60 microns.

5. The method of claim 1 , wherein the perforations are laser drilled through the lipskin to have an average entry diameter at the interior surface of less than 400 microns.

6. The method of claim 5 , wherein the average entry diameter at the interior surface is less than 100 microns.

7. The method of claim 1 , wherein forming the composite panel comprises laying up multiple plies of CFRP material in a stack on a mandrel and curing the stack.

8. The method of claim 1 , wherein the metallic coating is applied via electroplating.

9. The method of claim 1 , wherein the metallic coating comprises a nickel cobalt (NiCo) alloy.

10. The method of claim 1 , further comprising operating a fume extractor device concurrent with the laser drilling, the fume extractor device configured to extract gaseous byproducts from the air that are produced by the laser drilling of the lipskin.

11. The method of claim 1 , wherein the lipskin is one section of the annular barrel shape, and the method comprises assembling multiple sections of the lipskin together to complete the annular barrel shape prior to laser drilling the perforations through the lipskin.

12. The method of claim 1 , further comprising assembling an inlet cowl by coupling an acoustic panel to the lipskin after the laser drilling.

13. The method of claim 12 , further comprising assembling an inlet assembly by installing one or more support frames within a cavity defined between an inner side of the inlet cowl and an outer side of the inlet cowl.

14. The method of claim 12 , further comprising assembling an inlet assembly by coupling a plenum back wall along the interior surface of the lipskin to define a plenum that is fluidly connected to the perforations.

15. The method of claim 1 , wherein the perforations are laser drilled to have between 0.5 mm and 1.5 mm pitch between the perforations.

16. The method of claim 1 , wherein the perforations are laser drilled by a single fiber laser device, and laser beam emitted by the fiber laser device has a wavelength of about 532 nm.

17. A method for producing a nacelle inlet assembly, the method comprising:
forming a composite panel that includes a carbon fiber reinforced polymer (CFRP) material, the composite panel formed to have a curved contour that represents at least a portion of an annular barrel shape;
applying a metallic coating to the composite panel to form a lipskin, the metallic coating including a nickel cobalt (NiCo) alloy, the metallic coating defining an exterior surface of the lipskin and the composite panel defining an interior surface of the lipskin; and
laser drilling a plurality of perforations through the lipskin, wherein the laser drilling comprises emitting a laser beam that impinges upon the interior surface of the lipskin and penetrates the CFRP material of the composite panel before penetrating the metallic coating and exiting the lipskin through the exterior surface,
wherein the perforations are laser drilled through the lipskin to have an average entry diameter at the interior surface of less than 100 microns and an average exit diameter at the exterior surface of less than 60 microns.

Assignees

• Boeing Co
• Cav Advanced Tech Ltd

Inventors

• Rust Charles William
• Weidler Iii John Alfred
• Wood Martin

Classifications

• B23K26/382

  by boring · CPC title

• B64D29/00

  Power-plant nacelles, fairings or cowlings · CPC title

• B64D15/06

  Liquid application · CPC title

• B23K26/0823

  Devices involving rotation of the workpiece · CPC title

• B23K2103/172

  wherein at least one of the layers is non-metallic · CPC title