ZINC-DIFFUSED ALLOY COATING FOR CORROSION/HEAT PROTECTION

• US 20050058848A1
• Filed: 05/19/2004
• Published: 03/17/2005
• Est. Priority Date: 09/23/2002
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: Henry M. Hodgens, Thomas R. Hanlon
• Inventors: Hodgens, Henry M., Hanlon, Thomas R.
• Granted Patent: US 6,869,690 B1
• Time in Patent Office: Days
• US Class Current: 428/610
• CPC Class Codes: C23C 10/60 After-treatment
• CPC Class Codes: C23C 22/34 containing fluorides or complex fluorides
• CPC Class Codes: C23C 2222/10 Use of solutions containing trivalent chromium but free of hexavalent chromium
• CPC Class Codes: C23C 28/021 including at least one metal alloy layer
• CPC Class Codes: C23C 28/023 only coatings of metal elements only
• CPC Class Codes: C23C 28/025 with at least one zinc-based layer
• CPC Class Codes: C23C 28/028 Including graded layers in composition or in physical properties, e.g. density, porosity, grain size
• CPC Class Codes: Y10S 428/941 Solid state alloying, e.g. diffusion, to disappearance of an original layer
• CPC Class Codes: Y10T 428/12458 having composition, density, or hardness gradient
• CPC Class Codes: Y10T 428/12792 Zn-base component
• CPC Class Codes: Y10T 428/12799 Next to Fe-base component [e.g., galvanized]
• CPC Class Codes: Y10T 428/12937 Co- or Ni-base component next to Fe-base component

Abstract

The present invention relates to a zinc-diffused nickel alloy coating for corrosion and heat protection and to a method for forming such a coating. The coating method broadly comprises the steps of forming a plain nickel or nickel alloy coating layer on a substrate, applying a layer of zinc over the nickel or nickel alloy coating layer, and thermally diffusing the zinc into the nickel alloy coating layer. The coating method may further comprise immersing the coated substrate in a phosphated trivalent chromium conversion solution either before or after the diffusing step. The substrate may be a component used in a gas turbine engine, which component is formed from a steel material.

Claims

1-18. -18. (cancelled)

19. A substrate having at least one surface and a coating on said at least one surface, said coating having a first layer formed from nickel or a nickel alloy applied to said at least one surface and a second layer formed from zinc applied over said first layer, said first layer having zinc atoms diffused therein, and said substrate being formed from a deoxidized low carbon steel.

21. A substrate according to claim 19, wherein said substrate comprises a component used in a gas turbine engine.

22. A substrate according to claim 19, wherein said coating provides corrosion resistance and heat resistance at temperatures in excess of 900°

F.

23. A substrate according to claim 19, wherein said second layer has nickel atoms diffused therein.

24. A substrate according to claim 23, wherein said first layer is a nickel alloy layer formed by an alloy selected from the group consisting of a nickel cobalt alloy, a nickel iron alloy, a nickel manganese alloy, a nickel molybdenum alloy, and a nickel tin alloy.

20. (cancelled)

25. (cancelled)

26. A component for use in a gas turbine engine comprising:

a steel substrate formed from a low carbon steel; and

a zinc diffused nickel alloy coating on said steel substrate, said coating having a first layer formed from a nickel alloy deposited on and in contact with a surface of said substrate and a second layer formed from zinc deposited on said first layer and said first layer having zinc atoms diffused therein.

28. A component according to claim 26, wherein said nickel alloy layer is formed from a nickel cobalt alloy.

29. A component according to claim 26, wherein said nickel alloy layer is formed from a nickel iron alloy.

30. A component according to claim 26, wherein said nickel alloy layer is formed from a nickel manganese alloy.

31. A component according to claim 26, wherein said nickel alloy layer is formed from a nickel molybdenum alloy.

32. A component according to claim 26, wherein said nickel alloy layer is formed from a nickel tin alloy.

27. A method for forming a corrosion and heat protective coating on a gas turbine engine component comprising the steps of:

providing a substrate formed from a low carbon steel;

forming a nickel alloy coating layer on said substrate;

applying a layer of zinc over said nickel alloy coating layer; and

diffusing the zinc into said nickel alloy coating layer.

33. A method according to claim 27, wherein said nickel alloy coating layer forming step comprises depositing a nickel cobalt alloy on said substrate.

34. A method according to claim 27, wherein said nickel alloy coating layer forming step comprises depositing a nickel iron alloy on said substrate.

35. A method according to claim 27, wherein said nickel alloy coating layer forming step comprises depositing a nickel manganese alloy on said substrate.

36. A method according to claim 27, wherein said nickel alloy coating layer forming step comprises depositing a nickel molybdenum alloy on said substrate.

37. A method according to claim 27, wherein said nickel alloy coating layer forming step comprises depositing a nickel tin alloy on said substrate.