Gas turbine components and methods of assembling the same

Patent metadata

Field	Value
Publication number	US-11274562-B2
Application number	US-201716608214-A
Country	US
Kind code	B2
Filing date	Apr 25, 2017
Priority date	Apr 25, 2017
Publication date	Mar 15, 2022
Grant date	Mar 15, 2022

Abstract

A gas turbine component includes a substrate and a corrosion resistant layer coupled to the substrate. The corrosion resistant layer includes zirconium silicate and is configured to protect the substrate from exposure to a vanadium corrodent.

First claim

What is claimed is:

1. A gas turbine component comprising:
a substrate; and
a corrosion resistant layer coupled directly against said substrate without an intermediate layer extending between the corrosion resistant layer and the substrate, wherein said corrosion resistant layer comprises zirconium silicate, wherein said corrosion resistant layer is configured to protect said substrate from exposure to a vanadium corrodent and to act as a thermal barrier coating on said substrate.

2. A gas turbine component in accordance with claim 1 , wherein said component comprises only said substrate and said corrosion resistant layer.

3. A gas turbine component in accordance with claim 1 , wherein said corrosion resistant layer comprises a corrosion prevention material mixed with a bonding material, wherein the corrosion prevention material is 100% zirconium silicate and the corrosion resistant layer is not mixed with other corrosion prevention materials.

4. A gas turbine component in accordance with claim 1 , wherein said corrosion resistant layer comprises an outermost layer of said component.

5. A gas turbine component in accordance with claim 1 , wherein said corrosion resistant layer comprises a thickness in a range of approximately 0.0005 inches and approximately 0.030 inches.

6. A gas turbine component in accordance with claim 1 , further comprising a thermal barrier coating coupled to said corrosion resistant layer.

7. A gas turbine component in accordance with claim 6 , wherein said corrosion resistant layer is coupled between said thermal barrier coating and said substrate.

8. A gas turbine component in accordance with claim 6 , wherein said component comprises only said thermal barrier coating, said substrate, and said corrosion resistant layer.

9. A gas turbine component in accordance with claim 6 , wherein said thermal barrier coating comprises a thickness in a range of approximately 0.001 inches and approximately 0.050 inches.

10. A method of assembling a gas turbine component, said method comprising:
providing a substrate; and
applying a corrosion resistant layer directly against the substrate without an intermediate layer between the corrosion resistant layer and the substrate, wherein the corrosion resistant layer comprises zirconium silicate, and wherein the corrosion resistant layer is configured to protect the substrate from exposure to a vanadium corrodent and to act as a thermal barrier coating on said substrate.

11. A method in accordance with claim 10 , wherein applying the corrosion resistant layer includes applying only the corrosion resistant layer to the substrate such that the corrosion resistant layer is the only layer of material applied against the substrate.

12. A method in accordance with claim 10 , wherein applying the corrosion resistant layer includes applying the corrosion resistant layer that comprises a corrosion prevention material mixed with a bonding material, wherein the corrosion prevention material is 100% zirconium silicate and the corrosion resistant layer is not mixed with other corrosion prevention materials.

13. A method in accordance with claim 10 , wherein applying the corrosion resistant layer to the substrate comprises:
applying a thermal barrier coating to the corrosion resistant layer such that the corrosion resistant layer is between the substrate and the thermal barrier coating
wherein the thermal barrier coating and the corrosion resistant layer are the only materials applied to the substrate.

14. A turbine for use in a gas turbine engine, said turbine comprising:
a turbine blade; and
a corrosion resistant layer coupled directly to said turbine blade without an intermediate layer between the corrosion resistant layer and said turbine blade, wherein said corrosion resistant layer comprises zirconium silicate, wherein said corrosion resistant layer is configured to protect said turbine blade from exposure to a vanadium corrodent and to act as a thermal barrier coating on said-turbine blade.

15. A turbine in accordance with claim 14 , wherein said turbine blade is only coated with said corrosion resistant layer.

16. A turbine in accordance with claim 14 , wherein said corrosion resistant layer comprises an outermost layer of said turbine blade.

17. A turbine in accordance with claim 14 , further comprising a thermal barrier coating coupled to said corrosion resistant layer, wherein said corrosion resistant layer is coupled between said thermal barrier coating and said turbine blade.

18. A turbine in accordance with claim 17 , wherein said thermal barrier coating comprises YSZ and does not comprise zirconium silicate.

19. A turbine in accordance with claim 17 , wherein said turbine blade is formed from at least one of a metallic alloy and a ceramic material.

Assignees

• Gen Electric

Inventors

• Zhao Jianzhi
• Lin Chuan
• Wang Shizhong
• Lal Mihir Kumar
• Everhart Richard Todd

Classifications

• F01D5/288 Primary

  Protective coatings for blades · CPC title

• C23C4/134

  Plasma spraying · CPC title

• F05D2260/95

  Preventing corrosion · CPC title

• F05D2300/13

  Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W · CPC title

• C04B41/52

  Multiple coating or impregnating {multiple coating or impregnating with the same composition or with compositions only differing in the concentration of the constituents, is classified as single coating or impregnation} · CPC title