Metallic-coated polymer thrust reverser cascades

1. A thrust reverser cascade for a gas turbine engine, comprising:

a plurality of turning vanes, at least one of the plurality of turning vanes comprising

a core formed from at least one polymer, and

at least one metallic coating applied to at least a portion of an outer surface of the core.

2. The thrust reverser cascade of claim 1 , wherein the at least one metallic coating comprises nickel.

3. The thrust reverser cascade of claim 1 , wherein the at least one metallic coating is formed from a metallic material selected from the group consisting of nickel and nickel alloys.

4. The thrust reverser cascade of claim 1 , wherein the at least one metallic coating is formed from a metallic material selected from the group consisting of nickel, nickel alloys, copper, silver, iron, gold, palladium, rhodium, chromium, zinc, tin, cadmium, and combinations thereof.

5. The thrust reverser cascade of claim 1 , wherein the at least one polymer is a thermoplastic material selected from the group consisting of polyethylene, polyetherimide, polyether ether ketone, polyether ketone ketone, polysulfone, polyamide, polyphenylene sulfide, polyester, polyimide, and combinations thereof.

6. The thrust reverser cascade of claim 1 , wherein the at least one polymer is a thermoset material selected from the group consisting of polyimides, addition polyimides, epoxy cured with aliphatic and/or aromatic amines and/or anhydrides, cyanate esters, phenolics, polyesters, polybenzoxazine, polyurethanes, polyacrylates, polymethacrylates, silicones, and combinations thereof.

7. The thrust reverser cascade of claim 1 , wherein the core further comprises at least one reinforcing material selected from the group consisting of carbon fibers, glass fibers, aramid fibers, metal fibers, and combinations thereof.

8. The thrust reverser cascade of claim 1 , wherein the at least one metallic coating is applied to the outer surface of the core by a method selected from the group consisting of electroplating, electroless deposition, and electroforming.

9. The thrust reverser cascade of claim 1 , wherein the thrust reverser cascade is incorporated in a thrust reverser disposed in a nacelle of the gas turbine engine, the thrust reverser comprising a translating sleeve, and at least one actuator capable of actuating movement of the translating sleeve between a stowed position and a deployed position.

10. A gas turbine engine, comprising:

a fan section;

a core engine located downstream of the fan section, the core engine comprising

a compressor section,

a combustor located downstream of the compressor section, and

a turbine section located downstream of the combustor;

a nacelle surrounding the fan section and the core engine and defining a bypass duct between the nacelle and the core engine; and

a thrust reverser disposed in the nacelle comprising

a translating sleeve,

at least one actuator capable of actuating movement of the translating sleeve between a stowed position and a deployed position, and

at least one thrust reverser cascade comprising a plurality of turning vanes, at least one of the plurality of turning vanes comprising a core formed from at least one polymer and at least one metallic coating applied to at least a portion of an outer surface of the core.

11. The gas turbine engine of claim 10 , wherein the thrust reverser further comprises at least one blocker door, and the at least one actuator is capable of actuating the movement of the at least one blocker door between a stowed position and a deployed position.

12. The gas turbine engine of claim 10 , wherein the at least one metallic coating comprises nickel.

13. The gas turbine engine of claim 10 , wherein the at least one metallic coating is formed from a metallic material selected from the group consisting of nickel, nickel alloys, copper, silver, iron, gold, palladium, rhodium, chromium, zinc, tin, cadmium, and combinations thereof.

14. The gas turbine engine of claim 13 , wherein the at least one polymer is a thermoplastic material selected from the group consisting of polyethylene, polyetherimide, polyether ether ketone, polyether ketone ketone, polysulfone, polyamide, polyphenylene sulfide, polyester, polyimide, and combinations thereof.

15. The gas turbine engine of claim 13 , wherein the at least one polymer is a thermoset material selected from the group consisting of polyimides, addition polyimides, epoxy cured with aliphatic and/or aromatic amines and/or anhydrides, cyanate esters, phenolics, polyesters, polybenzoxazine, polyurethanes, polyacrylates, polymethacrylates, silicones, and combinations thereof.

16. The gas turbine engine of claim 13 , wherein the core further comprises at least one reinforcing material selected from the group consisting of carbon fibers, glass fibers, aramid fibers, metal fibers, and combinations thereof.

17. A method for fabricating a thrust reverser cascade for a gas turbine engine, comprising:

forming a core in a shape of a turning vane from at least one polymer;

applying a metallic coating to an outer surface of the core to provide a metallic-coated polymeric turning vane; and

assembling the thrust reverser cascade from a plurality of turning vanes, at least one of the plurality of turning vanes being the metallic-coated polymeric turning vane.

18. The method according to claim 17 , wherein forming the polymer in the shape of the turning vane is performed using a method selected from the group consisting of injection molding, compression molding, blow molding, additive manufacturing, and composite layup.

19. The method according to claim 17 , further comprising activating the outer surface with a catalyst layer followed by metallizing the outer surface with a conductive layer, prior to applying the metallic coating.

20. The method according to claim 19 , wherein applying the metallic coating to the outer surface is carried out by a method selected from the group consisting of electroplating, electroless deposition, and electroforming.