Enhanced protection for aluminum fan blade via sacrificial layer

Patent metadata

Field	Value
Publication number	US-10301950-B2
Application number	US-201414763058-A
Country	US
Kind code	B2
Filing date	Feb 21, 2014
Priority date	Mar 15, 2013
Publication date	May 28, 2019
Grant date	May 28, 2019

Abstract

A component is described which may comprise a structure formed from a material selected from the group consisting of aluminum and an aluminum alloy. The component may further comprise a sacrificial layer in electrical contact with at least a portion of a surface of the structure. The sacrificial layer may protect the surface from localized corrosion and may comprise an alloy that is more anodic than the material forming the structure. The alloy may be selected from the group consisting of an aluminum alloy and a zinc alloy.

First claim

What is claimed is:

1. A component, comprising:
a structure formed from a material selected from the group consisting of aluminum and an aluminum alloy, the structure being an airfoil of a gas turbine engine; and
a sacrificial layer in electrical contact with at least a portion of a surface of the structure, the sacrificial layer protecting the surface from localized corrosion and comprising an alloy that is more anodic than the material forming the structure, the alloy being selected from the group consisting of an aluminum alloy and a zinc alloy, wherein the sacrificial layer is deposited on an outer surface and an inner surface of the airfoil, wherein the sacrificial layer deposited on the inner surface of the structure is a metallic foam.

2. The component, according to claim 1 , wherein the sacrificial layer comprises an anodic element that is one of zinc, magnesium, beryllium, and combinations thereof.

3. The component, according to claim 2 , wherein the sacrificial layer has an electrochemical potential at least about 100 mV lower than the electrochemical potential of the material forming the structure.

4. The component, according to claim 2 , wherein the anodic element is present in a range from about 0.25 wt % to about 10 wt %.

5. The component, according to claim 2 , wherein the sacrificial layer further comprises a first element that is one of indium, barium, magnesium, mercury, gallium, thallium, and combinations thereof combined into a predominately aluminum alloy or layer that also contains from about 0.25 to about 5% zinc.

6. The component, according to claim 5 , wherein the sacrificial layer further comprises a second element that is one of iron, silicon, and combinations thereof combined into a predominately aluminum alloy or layer that also contains from about 0.25 to about 5% zinc.

7. The component, according to claim 5 , wherein the first element is present in the sacrificial layer at less than about 1 wt %.

8. The component, according to claim 6 , wherein the second element is present in the sacrificial layer up to about 1 wt %.

9. The component, according to claim 6 , wherein the sacrificial layer is deposited on the structure by at least one deposition method that is one of cold spraying, electroplating, chemical vapor deposition, physical vapor deposition, plasma spraying, slurry application, sintering, and diffusion bonding.

10. The component, according to claim 6 , further comprising a paint coating on the sacrificial layer.

11. The component, according to claim 1 , wherein the sacrificial layer is deposited on a wear pad of the airfoil.

12. An airfoil for a fan of a gas turbine engine comprising:
a blade portion;
a root portion, the fan blade being formed from a material selected from the group consisting of aluminum and an aluminum alloy; and
a sacrificial layer in electrical contact with at least a portion of a surface of the airfoil, the sacrificial layer protecting the surface from localized corrosion and comprising an alloy that is more anodic than the material forming the fan blade, the alloy being selected from the group consisting of an aluminum alloy and a zinc alloy, wherein the sacrificial layer is deposited on an inner surface of the structure as a metallic foam.

13. The airfoil, according to claim 12 , wherein the sacrificial layer comprises an anodic element that is one of zinc, magnesium, beryllium, and combinations thereof.

14. The airfoil, according to claim 13 , wherein the sacrificial layer further comprises a first element that is one of indium, barium, magnesium, mercury, gallium, thallium, and combinations thereof.

15. The airfoil, according to claim 14 , wherein the sacrificial layer further comprises a second element that is one of iron, silicon, and combinations thereof.

16. A gas turbine engine, comprising:
a fan section having a plurality of airfoils, at least one of the plurality of airfoils being formed from a material selected from the group consisting of aluminum and an aluminum alloy;
a sacrificial layer in electrical contact with a portion of a surface of the at least one of the plurality of airfoils, the sacrificial layer protecting the surface from localized corrosion and comprising an alloy that is more anodic than the material, the alloy being selected from the group consisting of an aluminum alloy and a zinc alloy, wherein the sacrificial layer is deposited on an outer surface and an inner surface of the airfoil, and wherein the sacrificial layer is-deposited on the inner surface of the structure is a metallic foam;
a compressor section downstream of the fan;
a combustor section downstream of the compressor;
a turbine section downstream of the combustor; and
a nacelle surrounding the fan, the compressor section, the combustor section, and the turbine section.

17. A gas turbine engine, comprising:
a fan;
a compressor section downstream of the fan, the compressor section having a plurality of airfoils, at least one of the plurality of airfoils being formed from a material selected from the group consisting of aluminum and an aluminum alloy;
a sacrificial layer in electrical contact with a portion of a surface of the at least one of the at least one of the plurality of airfoils, the sacrificial layer protecting the surface from localized corrosion and comprising an alloy that is more anodic than the material, the alloy being selected from the group consisting of an aluminum alloy and a zinc alloy, wherein the sacrificial layer is deposited on an inner surface of the structure as a metallic foam;
a combustor section downstream of the compressor;
a turbine section downstream of the combustor; and
a nacelle surrounding the fan, the compressor section, the combustor section, and the turbine section.

Assignees

• United Technologies Corp

Inventors

• Garosshen Thomas J

Classifications

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• F01D5/28 Primary

  Selecting particular materials; {Particular measures relating thereto;} Measures against erosion or corrosion · CPC title

• C23F13/08

  Electrodes specially adapted for inhibiting corrosion by cathodic protection; Manufacture thereof; Conducting electric current thereto · CPC title

• C23F13/14 Primary

  Material for sacrificial anodes · CPC title