Composite aerospace component
An aerospace component, for example, used in a gas turbine engine, includes the following structurally-integrated layers: a metallic layer and a composite layer having reinforcing fibers embedded in a matrix material. The aerospace component can also include an insulating layer disposed between the metallic layer and the composite layer where the insulating layer has a thermal conductivity that is lower than a thermal conductivity of the composite layer.
1. An aerospace component comprising the following structurally-integrated layers:
a metallic layer; and
a composite layer having reinforcing fibers embedded in a matrix material, the composite layer being devoid of openings extending therethrough; and
an insulating layer disposed between the metallic layer and the composite layer;
wherein:
the insulating layer has a thermal conductivity that is lower than a thermal conductivity of the composite layer;
the metallic layer, the insulating layer and the composite layer define a wall resistant to a differential air pressure across the wall; and
the aerospace component is a backing sheet of an acoustic liner.
2. The aerospace component of claim 1 , wherein the metallic layer comprises a perforated sheet.
3. The aerospace component of claim 1 , wherein the metallic layer comprises a mesh.
4. The aerospace component of claim 1 , wherein the metallic layer comprises any one of the following: copper, a nickel-based alloy, a titanium-based alloy, and a ferrous alloy.
5. The aerospace component of claim 1 , wherein the reinforcing fibers comprise carbon reinforcing fibers and the matrix material comprises a polymer.
6. The aerospace component of claim 1 , wherein the insulating layer comprises at least one of the following: a fiber-reinforced composite material comprising glass fibers and a polymer fiber in a polymer matrix material.
7. The aerospace component of claim 1 , wherein the metallic layer is a first metallic layer and the aerospace component comprises a second metallic layer disposed between the insulating layer and the composite layer.
8. The aerospace component of claim 7 , wherein the first metallic layer comprises copper.
9. The aerospace component of claim 8 , wherein the first and second metallic layers each have openings extending therethrough.
10. The aerospace component of claim 9 , wherein the second metallic layer comprises any one of the following: copper, a nickel-based alloy, a titanium-based alloy, and a ferrous alloy.
11. An acoustic liner comprising: a perforated facing sheet; and a backing sheet spaced apart from the facing sheet, the backing sheet comprising the following structurally-integrated layers:
a metallic layer; and
a composite layer having reinforcing fibers embedded in a matrix material, the composite layer being devoid of openings extending therethrough; and
an insulating layer disposed between the metallic layer and the composite layer;
wherein:
the insulating layer has a thermal conductivity that is lower than a thermal conductivity of the composite layer; and
the metallic layer, the insulating layer and the composite layer define a wall resistant to a differential air pressure across the wall.
12. The acoustic liner of claim 11 , wherein: the reinforcing fibers comprise carbon reinforcing fibers and the matrix material comprises a polymer; and the insulating layer comprises at least one of the following: a fiber-reinforced composite material comprising glass fibers and a polymer fiber in a polymer matrix material.
13. The acoustic liner of claim 12 , wherein:
the metallic layer is a first metallic layer and the backing sheet comprises a second metallic layer disposed between the insulating layer and the composite layer;
the first metallic layer comprises copper; and
the first and second metallic layers each have openings extending therethrough.
14. A gas turbine engine comprising:
an engine core; and
a bypass duct disposed around the engine core, the bypass duct including an acoustic liner, the acoustic liner including a perforated facing sheet for interfacing with a flow of air in the bypass duct and a backing sheet spaced apart from the facing sheet, the backing sheet comprising the following structurally-integrated layers:
a metallic layer;
a composite layer having reinforcing fibers embedded in a matrix material, the composite layer being devoid of openings extending therethrough; and
an insulating layer disposed between the metallic layer and the composite layer;
wherein:
the insulating layer has a thermal conductivity that is lower than a thermal conductivity of the composite layer; and
the metallic layer, the insulating layer and the composite layer define a wall resistant to a differential air pressure across the wall.
15. The gas turbine engine of claim 14 , wherein the metallic layer is disposed between the facing sheet and the composite layer.
16. The gas turbine engine of claim 14 , wherein:
the reinforcing fibers comprise carbon reinforcing fibers and the matrix material comprises a polymer; and
the insulating layer comprises at least one of the following: a fiber-reinforced composite material comprising glass fibers and a polymer fiber in a polymer matrix material.