Gas turbine engine blade tip treatment

Patent metadata

Field	Value
Publication number	US-10094227-B2
Application number	US-201514803497-A
Country	US
Kind code	B2
Filing date	Jul 20, 2015
Priority date	Aug 4, 2014
Publication date	Oct 9, 2018
Grant date	Oct 9, 2018

Abstract

A fan blade and method of manufacturing a fan blade includes a metallic fan blade body with a crystalline oxidation layer and immersing the crystalline oxidation layer in a solution of ceramic nanosheets in suspension. A fan blade for a gas turbine engine includes a metallic fan blade body having a tip with a crystalline oxidation layer, wherein the crystalline oxidation layer includes pores containing ceramic nanosheets.

First claim

What is claimed:

1. A method of manufacturing a fan blade comprising:
immersing at least a crystalline oxidation layer of a metallic fan blade body in a solution of ceramic nanosheets in suspension, the ceramic nanosheets having a charge of a first polarity; and
applying a potential of a second polarity to the fan blade body while the crystalline oxidation layer is immersed in the solution of ceramic nanosheets in suspension, wherein the second polarity is different than the first polarity.

2. The method according to claim 1 , wherein the fan blade body includes a tip, the tip including the crystalline oxidation layer.

3. The method according to claim 1 , wherein:
the crystalline oxidation layer includes a plurality of pore channels therein; and
said applying a potential electrophoretically drives at least some of the ceramic nanosheets into at least some of the pore channels.

4. The method according to claim 1 , wherein the crystalline oxidation layer is an aluminum oxide hard coating layer.

5. The method according to claim 4 , wherein the aluminum oxide hard coating layer is a MIL-A-8625F Type III coating.

6. The method according to claim 1 , wherein the ceramic nanosheets comprise a ceramic selected from the group consisting of: MoS 2 , MoSe 2 , WS 2 , MoSi 2 , WSe 2 , TiS 2 , TaS 2 , and ZrS 2 .

7. The method according to claim 1 , wherein the first polarity is negative and the second polarity is positive.

8. The method according to claim 1 , wherein the potential is a DC potential.

9. The method according to claim 1 , wherein the fan blade body comprises one of a 7000 series and a 2000 series aluminum alloy.

10. The method according to claim 1 , wherein the ceramic nanosheets are formed by a process comprising the steps of:
intercalating lithium cations between layers of a ceramic starting material to produce an intercalated ceramic structure; and
exfoliating the intercalated ceramic structure to produce the ceramic nanosheets.

11. The method according to claim 1 , further comprising the step of adhering a sheath to a leading edge of the fan blade body.

12. The method according to claim 11 , wherein the adhering step includes arranging an adhesive-saturated scrim between the sheath and the leading edge.

13. The method according to claim 12 , further comprising the step of coating the fan blade body with polyurethane to provide a fan blade contour along with the sheath.

14. The method according to claim 13 , wherein the crystalline oxidation layer is left exposed subsequent to the coating step.

15. A fan blade for a gas turbine engine comprising:
a metallic fan blade body including a tip with a crystalline oxidation layer;
wherein the crystalline oxidation layer includes a plurality of pore channels; and
wherein at least some of the plurality of pore channels include ceramic nanosheets.

16. The fan blade according to claim 15 , wherein the fan blade body includes a tip, the tip including the crystalline oxidation layer.

17. The fan blade according to claim 15 , wherein the crystalline oxidation layer is an aluminum oxide hard coating layer.

18. The fan blade according to claim 15 , wherein the aluminum oxide hard coating layer is a MIL-A-8625F Type III coating.

19. The fan blade according to claim 15 , wherein the ceramic nanosheets comprise a ceramic selected from the group consisting of: MoS 2 , MoSe 2 , WS 2 , MoSi 2 , WSe 2 , TiS 2 , TaS 2 , and ZrS 2 .

20. The fan blade according to claim 15 , wherein the metallic fan blade body comprises one of a 7000 series and a 2000 series aluminum alloy.

Assignees

• United Technologies Corp

Inventors

• Ding Zhongfen

Classifications

• C25D11/022

  Anodisation on selected surface areas · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F05D2220/36

  specially adapted for the fan of turbofan engines · CPC title

• F05D2300/2112

  Aluminium oxides · CPC title

• C25D11/26

  of refractory metals or alloys based thereon · CPC title