Structural panel with woven element core

Patent metadata

Field	Value
Publication number	US-10800134-B2
Application number	US-201615182131-A
Country	US
Kind code	B2
Filing date	Jun 14, 2016
Priority date	Jun 14, 2016
Publication date	Oct 13, 2020
Grant date	Oct 13, 2020

Abstract

A structural panel includes a first skin, a second skin and a core. The core is connected to the first skin and the second skin. The core includes a corrugated sheet of wire mesh that includes a plurality of corrugations. Each of the corrugations extends vertically between and engages the first skin and the second skin.

First claim

What is claimed is:

1. An aircraft propulsion system, comprising:
a gas turbine engine;
a nacelle; and
a structural panel comprising a first skin, a second skin and a core;
the first skin having a first side surface, a second side surface, and a thickness extending there between;
the second skin having a first side surface, a second side surface, and a thickness extending there between; and
the core extending between the first side surface of the first skin and the first side surface of the second skin, which core includes a plurality of geometric structures formed of a wire mesh, which geometric structures extend between and are attached to the first skin and the second skin;
wherein the structural panel is included in the gas turbine engine or the nacelle.

2. The aircraft propulsion system of claim 1 , wherein the plurality of geometric structures include a plurality of corrugations.

3. The aircraft propulsion system of claim 2 , wherein each of the corrugations is formed by a first side portion, a second side portion, and an intermediate portion that extends between the first side portion and the second side portion.

4. The aircraft propulsion system of claim 2 , wherein the corrugations are non-linear.

5. The aircraft propulsion system of claim 2 , wherein the panel has a length and the corrugations extend substantially an entirety of the length.

6. The aircraft propulsion system of claim 1 , wherein the wire mesh is configured from a plurality of wires woven together.

7. The aircraft propulsion system of claim 1 , wherein the wire mesh is formed of a plurality of metal wires, a plurality of polymeric wires, a plurality of ceramic wires, or some combination thereof.

8. The aircraft propulsion system of claim 1 , wherein the wire mesh is formed of a plurality of wires of a first gauge, and at least one second wire of a second gauge, which second gauge is different from the first gauge.

9. The aircraft propulsion system of claim 1 , wherein the wire mesh is formed of a plurality of wires of a first cross-sectional shape, and at least one second wire of a second cross-sectional shape, which second cross-sectional shape is different from the first cross-sectional shape.

10. The aircraft propulsion system of claim 1 , wherein the first skin and the second skin are substantially non-perforated.

11. The aircraft propulsion system of claim 2 , wherein the plurality of geometric structures include a plurality of locally enclosed structures.

12. The aircraft propulsion system of claim 1 , wherein the plurality of geometric structures include a plurality of locally enclosed structures.

13. The aircraft propulsion system of claim 12 , wherein each of the locally enclosed structures is formed by at least one side wall, and wherein the side wall and at least one of the first skin or second skin defines an enclosed region.

14. The aircraft propulsion system of claim 13 , wherein the locally enclosed structures all have the same shape.

15. The aircraft propulsion system of claim 13 , wherein the locally enclosed structures include at least one first type having a first geometric shape, and at least one second type having a second geometric shape, which first geometric shape is different from the second geometric shape.

16. An aircraft propulsion system, comprising:
a gas turbine engine;
a nacelle; and
a structural panel comprising a first skin, a second skin and a core;
the first skin having a first side surface, a second side surface, and a thickness extending there between;
the second skin having a first side surface, a second side surface, and a thickness extending there between; and
the core extending between the first side surface of the first skin and the first side surface of the second skin, wherein at least a first portion of the core is attached to the first skin and at least a second portion of the core is attached to the second skin;
wherein the core includes a plurality of wire elements, which wire elements are configured to permit relative movement there between in a manner that at least partially dissipates intermittent excitation forces applied to the structural panels; and
wherein the structural panel is included in the gas turbine engine or the nacelle.

17. The aircraft propulsion system of claim 16 , wherein the plurality of wire elements include metal wires, polymeric wires, or ceramic wires, or some combination thereof.

18. The aircraft propulsion system of claim 16 , wherein the plurality of wires includes wires of a first gauge and wires of a second gauge, which second gauge is different from the first gauge.

19. The aircraft propulsion system of claim 1 , wherein the structural panel is included in the gas turbine engine.

20. The aircraft propulsion system of claim 1 , wherein the wire mesh comprises a plurality of polymeric wires and/or a plurality of ceramic wires.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Sharon John A
• Homma Kenji
• Hawkes Justin R
• Braunwart Paul R
• Sun Ellen Y

Classifications

• B32B15/14

  next to a fibrous or filamentary layer · CPC title

• B32B15/043

  of metal (B32B15/01 takes precedence) · CPC title

• B32B5/024

  Woven fabric · CPC title

• B32B2605/12

  Ships · CPC title

• B32B2605/08

  Cars · CPC title