Systems and methods for preventing liberation and damage to airfoils in a gas turbine

Patent metadata

Field	Value
Publication number	US-2025035011-A1
Application number	US-202418675913-A
Country	US
Kind code	A1
Filing date	May 28, 2024
Priority date	Jul 25, 2023
Publication date	Jan 30, 2025
Grant date	—

Abstract

The present application provides a replaceable galvanic protection anode system for preventing and limiting the effects of liberation and damage to airfoils in a gas turbine, wherein turbine components are covered by a sacrificial material. The galvanic protection layer of the replaceable anodes may include a sacrificial material, such as aluminum, wherein the material provides corrosion resistance to the substrate. Additionally, the galvanic protection layer may include a sacrificial conductive material insert for increasing the conductivity of the sacrificial material and further improve the corrosion resistance of the replaceable anodes.

First claim

We claim:

1 . A turbine protection system for reducing the effects of corrosion and turbine damage, comprising:
at least one component engaged with a compressor of the turbine, wherein the at least one component comprises an airfoil, a platform that defines a radially inner boundary of a gas path through the compressor, a dovetail, and a base; and one or more anodes attached to the component, wherein each of the one or more anodes comprises a sacrificial material configured to provide galvanic protection against corrosion.

2 . The turbine protection system of claim 1 , wherein the one or more anodes comprise aluminum, zinc, magnesium, lithium, or a combination thereof.

3 . The turbine protection system of claim 1 , further comprising a conductive material coated on the sacrificial material.

4 . The turbine protection system of claim 3 , wherein the conductive material is disposed between the sacrificial material and the anode.

5 . The turbine protection system of claim 3 , wherein the conductive material comprises channels, grooves, gaps, or holes for collecting and redirecting water.

6 . The turbine protection system of claim 3 , wherein the conductive material comprises bronze, iron, brass, or an alloy thereof.

7 . The turbine protection system of claim 1 , further comprising an adhesive for attaching the anode to the component.

8 . The turbine protection system of claim 1 , wherein the anode further comprises a protrusion and the component further comprises a groove, wherein the protrusion is configured to mate with the groove to secure the anode to the component.

9 . The turbine protection system of claim 1 , wherein the anode further comprises a first threaded portion and the component further comprises a second threaded portion, wherein the first and second threaded portions are configured to mate to secure the anode to the component.

10 . The turbine protection system of claim 1 , wherein the anode further comprises a magnet configured to secure the anode to the component.

11 . The turbine protection system of claim 1 , wherein the one or more anodes are detachably attachable to the at least one component.

12 . The turbine protection system of claim 1 , wherein the at least one anode is attached to the platform in the gas path.

13 . The turbine protection system of claim 1 , wherein the turbine protection system comprises two or more anodes, and wherein at least one anode is attached to the base.

14 . The turbine protection system of claim 1 , wherein the anode further comprises a textured surface configured to corrode in a predictable and precise pattern.

15 . The turbine protection system of claim 1 , wherein the sacrificial material is disposed between the anode and the component.

16 . The turbine protection system of claim 1 , wherein the sacrificial material comprises aluminum, zinc, magnesium, or a combination thereof.

17 . The turbine protection system of claim 1 , wherein the anode is attached to a distal end of the airfoil.

18 . The turbine protection system of claim 1 , further comprising one or more anodes attached to an inside surface of a compressor casing.

19 . A method for reducing corrosion on gas turbine components, the method comprising:
attaching a sacrificial material to a surface of a component engaged with a compressor of the gas turbine, wherein the component comprises an airfoil comprising a platform that defines a radially inner boundary of a gas path through a turbine, a dovetail, and a base, and attaching an anode to the sacrificial material.

20 . The method of claim 19 wherein the sacrificial material and anode are attached to the platform in the gas path.

Assignees

• Ge Infrastructure Technology Llc

Inventors

• Park Junyoung
• Breznak Jeffrey M
• Schaeffer Jon C

Classifications

• F05D2260/95

  Preventing corrosion · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F02C7/30

  Preventing corrosion {or unwanted deposits} in gas-swept spaces · CPC title

• F01D25/007 Primary

  Preventing corrosion · CPC title

• F01D5/286 Primary

  Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion (F01D5/288 takes precedence) · CPC title