Nacelle inlet assembly with composite lipskin

Patent metadata

Field	Value
Publication number	US-12163440-B2
Application number	US-202318165461-A
Country	US
Kind code	B2
Filing date	Feb 7, 2023
Priority date	Jul 15, 2022
Publication date	Dec 10, 2024
Grant date	Dec 10, 2024

Abstract

An inlet assembly of a nacelle includes an inlet cowl. The inlet cowl includes a lipskin that has a front section which defines the leading edge of the inlet cowl. The front section includes a composite panel and a metallic coating disposed along an exterior surface of the composite panel to protect the composite panel from damage. The lipskin defines perforations that penetrate through the composite panel and the metallic coating at the front section to convey a liquid through a thickness of the lipskin onto an exterior surface of the inlet cowl.

First claim

What is claimed is:

1. An inlet assembly of a nacelle, the inlet assembly comprising:
an inlet cowl comprising:
a lipskin that includes a front section that defines a leading edge of the inlet cowl, the front section including a composite panel and a metallic coating that defines an exterior surface of the lipskin to protect the composite panel from damage, the lipskin defining perforations that penetrate through the composite panel and the metallic coating at the front section, the lipskin including a first protrusion and a second protrusion that project from an interior surface of the lipskin; and
a plenum back wall affixed to the first and second protrusions to define a plenum at the front section that is open to the perforations, wherein a thickness of the plenum is defined between the interior surface of the lipskin and the plenum back wall and a length of the plenum is defined between the first and second protrusions, wherein the plenum is configured to receive an anti-ice liquid therein and the perforations are configured to convey the anti-ice liquid through a thickness of the lipskin onto the exterior surface of the lipskin.

2. The inlet assembly of claim 1 , wherein the composite panel includes a carbon fiber reinforced polymer (CFRP) material.

3. The inlet assembly of claim 1 , wherein the metallic coating includes a nickel cobalt alloy.

4. The inlet assembly of claim 1 , wherein the composite panel and the metallic coating of the lipskin define an outer barrel portion of the inlet cowl and extend a full length of the inlet cowl from the leading edge to an aft edge of the inlet cowl.

5. The inlet assembly of claim 1 , wherein an electrically conductive layer is sandwiched between the composite panel and the metallic coating.

6. The inlet assembly of claim 1 , wherein the inlet cowl defines a cavity between the leading edge, an inner barrel portion of the inlet cowl, and an outer barrel portion of the inlet cowl, and the inlet cowl lacks a bulkhead that fluidly separates two portions of the cavity.

7. The inlet assembly of claim 6 , further comprising one or more circumferentially extending support frames within the cavity, wherein the circumferentially extending support frames define openings to permit fluid flow therethrough.

8. The inlet assembly of claim 6 , further comprising one or more longitudinally extending support frames within the cavity, wherein the longitudinally extending support frames define openings to permit fluid flow therethrough.

9. The inlet assembly of claim 1 , further comprising a membrane fully contained within the plenum between the interior surface of the lipskin and the plenum back wall and covering the perforations, the membrane configured to distribute the anti-ice liquid among the perforations.

10. The inlet assembly of claim 9 , wherein the membrane is designed to absorb the anti-ice liquid to distribute the anti-ice liquid along a length of the membrane within the plenum.

11. The inlet assembly of claim 1 , wherein the plenum back wall includes a first flange that is bonded to a first ramp surface of the first protrusion and a second flange that is bonded to a second ramp surface of the second protrusion to affix the plenum back wall to the lipskin, wherein contact interfaces at the first and second ramp surfaces have respective vectors that are not parallel to tangent lines of the lipskin proximate to the first and second ramp surfaces.

12. The inlet assembly of claim 1 , wherein the first and second protrusions include a foam material and are integrated with the composite panel of the lipskin.

13. The inlet assembly of claim 1 , wherein the first and second protrusions comprise a rigid, closed-cell foam.

14. A method for providing an inlet assembly of a nacelle, the method comprising:
forming an inlet cowl that includes a leading edge, the inlet cowl forming step comprising:
curing a carbon fiber reinforced polymer (CFRP) material to form a composite panel of a lipskin, the lipskin including a front section that defines the leading edge of the inlet cowl, the lipskin including a first protrusion and a second protrusion that project from an interior surface of the lipskin;
applying a metallic coating to define an exterior surface of the lipskin to protect the composite panel from damage; and
forming perforations that continuously extend through both the composite panel and the metallic coating, the perforations located along the front section of the lipskin and configured to deliver a liquid through a thickness of the lipskin onto an exterior surface of the inlet cowl;

affixing a plenum back wall to the first and second protrusions to define a plenum at the front section that is open to the perforations, wherein a thickness of the plenum is defined between the interior surface of the lipskin and the plenum back wall and a length of the plenum is defined between the first and second protrusions, wherein the plenum is configured to receive an anti-ice liquid therein and the perforations are configured to convey the anti-ice liquid through a thickness of the lipskin onto the exterior surface of the lipskin.

15. The method of claim 14 , wherein applying the metallic coating comprises electroplating the metallic coating along the composite panel.

16. The method of claim 14 , wherein forming the perforations comprises laser drilling the perforations to have micron scale diameters.

17. The method of claim 14 , wherein affixing the plenum back wall to the first and second protrusions comprises bonding first and second flanges of the plenum back wall to respective ramp surfaces of the first and second protrusions.

18. The method of claim 14 , further comprising applying a membrane along the interior surface of the composite panel prior to bonding the plenum back wall such that the membrane is fully contained within the plenum between the interior surface of the lipskin and the plenum back wall when the plenum back wall is affixed to the first and second protrusions, the membrane configured to distribute the liquid among the perforations.

19. The method of claim 14 , wherein the inlet cowl is formed to have an outer barrel portion that extends to an aft edge of the inlet cowl, wherein the CFRP material is applied and cured and the metallic coating is applied such that the composite panel and the metallic coating of the lipskin extend from the leading edge to the aft edge of the outer barrel portion.

20. An inlet assembly of a nacelle, the inlet assembly comprising:
an inlet cowl including a leading edge, an inner barrel portion, and an outer barrel portion, the inlet cowl comprising:
a lipskin that includes a front section that defines the leading edge of the inlet cowl, the front section including a composite panel and a metallic coating that defines an exterior surface of the lipskin to protect the composite panel from damage, the lipskin defining perforations that penetrate through the composite panel and the metallic coating at the front section, the lipskin including a first protrusion and a second protrusion that project from an interior surface of the lipskin; and
an acoustic panel coupled to the lipskin and extending along the inner barrel portion; and
a fluid ice protection system (FIPS), the FIPS including a plenum back wall affixed to the first and second protrusions to define a plenum at the front section that is open to the perforations, wherein a thickness of the plenum is defined between the interior surface of the lipskin and a front surface of the plenum back wall, an

Assignees

• Boeing Co

Inventors

• Rust Charles William
• Weidler Iii John Alfred
• Moselage Iii John Henry
• Wheeler Timothy James

Classifications

• F05D2300/603

  Composites; e.g. fibre-reinforced · CPC title

• F05D2300/43

  Synthetic polymers, e.g. plastics; Rubber · CPC title

• F05D2300/17

  Alloys · CPC title

• F05D2240/14

  Casings or housings protecting or supporting assemblies within · CPC title

• F05D2230/90

  Coating; Surface treatment · CPC title