System for protecting turbine engine surfaces from corrosion
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
C23F-013/06
C23F-013/14
C23F-013/18
출원번호
US-0785258
(2010-05-21)
등록번호
US-8268134
(2012-09-18)
발명자
/ 주소
Goller, George Albert
Dimascio, Paul Stephen
Hefner, Rebecca Evelyn
출원인 / 주소
General Electric Company
대리인 / 주소
Fletcher Yoder, P.C.
인용정보
피인용 횟수 :
4인용 특허 :
1
초록▼
According to various embodiments, a system includes a turbine engine component that includes a first material having a surface exposed to a fluid flow path and a sacrificial anode layer disposed on the surface. The sacrificial anode layer includes a second material that is electrochemically more act
According to various embodiments, a system includes a turbine engine component that includes a first material having a surface exposed to a fluid flow path and a sacrificial anode layer disposed on the surface. The sacrificial anode layer includes a second material that is electrochemically more active than the first material and the second material is configured to preferentially corrode to protect the first material from corrosion.
대표청구항▼
1. A system, comprising: a turbine engine component comprising a first material having a surface exposed to a fluid flow path, wherein the fluid flow path is disposed within a turbine engine; anda sacrificial anode layer disposed on the surface, wherein the sacrificial anode layer comprises a second
1. A system, comprising: a turbine engine component comprising a first material having a surface exposed to a fluid flow path, wherein the fluid flow path is disposed within a turbine engine; anda sacrificial anode layer disposed on the surface, wherein the sacrificial anode layer comprises a second material that is electrochemically more active than the first material, and the second material is configured to preferentially corrode to protect the first material from corrosion. 2. The system of claim 1, wherein the sacrificial anode layer comprises a patterned layer of the second material. 3. The system of claim 2, wherein the patterned layer comprises a plurality of sacrificial anode portions that are connected to one another. 4. The system of claim 2, wherein the patterned layer comprises a plurality of sacrificial anode portions that are disconnected from one another. 5. The system of claim 2, wherein the patterned layer comprises a patterned coating continuously adhered to the surface. 6. The system of claim 1, wherein the sacrificial anode layer comprises a third material that is electrochemically more active than the first material and the second material. 7. The system of claim 6, wherein the second material is disposed in a first pattern of a plurality of first sacrificial anode portions, the third material is disposed in a second pattern of a plurality of second sacrificial anode portions, and the first and second sacrificial anode portions are disposed side by side or one over another relative to the surface. 8. The system of claim 1, wherein the second material is at least greater than approximately 10 percent more electrochemically active than the first material. 9. The system of claim 1, wherein the second material comprises carbon steel, aluminum, mixed metal oxides, or a combination thereof. 10. The system of claim 1, wherein the turbine engine component is a part of a gas turbine combustor or a gas turbine section of a gas turbine engine, and the fluid flow path is a combustion gas path. 11. A system, comprising: a gas turbine engine comprising a first material having a surface exposed to a flow path of hot condensing combustion gas; anda patterned anode layer comprising a second material disposed on the surface, wherein the patterned anode layer is configured to protect the surface from corrosion by the hot condensing combustion gas. 12. The system of claim 11, wherein the second material is electrochemically more active than the first material, and the second material is configured to preferentially corrode to protect the first material from corrosion by the hot condensing combustion gas. 13. The system of claim 11, comprising a power source that supplies power to a transformer rectifier coupled to the patterned anode layer, wherein the transformer rectifier is configured to impress a current through the patterned anode layer to actively protect the first material from corrosion by the hot condensing combustion gas. 14. The system of claim 11, wherein the patterned anode layer is recessed into the surface to provide a smooth surface along the flow path. 15. The system of claim 11, wherein the patterned anode layer comprises a grid of the second material. 16. The system of claim 15, wherein the grid is a printed grid continuously adhered to the surface. 17. The system of claim 11, wherein the patterned anode layer comprises a third material that is different than the first and second materials. 18. A system, comprising: a patterned anode layer configured to protect a surface of a as turbine engine from corrosion by hot condensing combustion gas;a reference electrode in contact with the hot condensing combustion gas; anda controller configured to adjust a current to the patterned anode layer in response to feedback from the reference electrode. 19. The system of claim 18, comprising the gas turbine engine having the surface. 20. The system of claim 18, wherein the feedback from the reference electrode is indicative of an electrical potential difference across the reference electrode and the as turbine engine.
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이 특허에 인용된 특허 (1)
Gossett Robert M. (Akron OH) Baach Michael K. (Parma OH) Dong Dennis F. (Kingston FL CAX) Loftfield Richard E. (Jacksonville FL), Cathodic protection anode and systems.
Scipio, Alston Ilford; Davis, Dale Joel; Ekanayake, Sanji; Fernandez, Paul Robert, Gas turbine engine systems and methods for imparting corrosion resistance to gas turbine engines.
Roberts, III, Herbert Chidsey; Meschter, Peter Joel, Turbomachine component having an internal cavity reactivity neutralizer and method of forming the same.
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