Method and apparatus for cleaning a turbofan gas turbine engine
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B08B-003/02
B08B-009/00
출원번호
UP-0354873
(2009-01-16)
등록번호
US-7815743
(2010-11-08)
발명자
/ 주소
Asplund, Peter
Hjerpe, Carl-Johan
출원인 / 주소
Gas Turbine Efficiency AB
대리인 / 주소
DLA Piper LLP (US)
인용정보
피인용 횟수 :
10인용 특허 :
13
초록▼
Device for cleaning a gas turbine engine, and in particular an engine of turbofan type. The present invention further relates to a method for cleaning such an engine. The device comprises a plurality of nozzles arranged to atomize cleaning liquid in the air stream in an air inlet of the engine up-st
Device for cleaning a gas turbine engine, and in particular an engine of turbofan type. The present invention further relates to a method for cleaning such an engine. The device comprises a plurality of nozzles arranged to atomize cleaning liquid in the air stream in an air inlet of the engine up-stream of a fan of the engine. According to the invention, a first nozzle is arranged at a position such that the cleaning liquid emanating from the first nozzle impinges the surfaces of the blades substantially on the pressure side; a second nozzle is arrange at a position such that the cleaning liquid emanating from the second nozzle impinges the surfaces of the blades substantially on the suction side; and a third nozzle is arranged at a position such that the cleaning liquid emanating from the third nozzle passes substantially between the blades and enters an inlet of the core engine. Thereby, the different types of fouling found on the fan and in the core engine compressor of turbofan engine can be removed in an efficient manner.
대표청구항▼
The invention claimed is: 1. A device for cleaning a gas turbine engine, said engine comprising (a) at least one engine shaft; (b) a fan rotatably arranged on said shaft comprising a plurality of fan blades mounted on a hub and extending substantially in a radial direction, each of said blades comp
The invention claimed is: 1. A device for cleaning a gas turbine engine, said engine comprising (a) at least one engine shaft; (b) a fan rotatably arranged on said shaft comprising a plurality of fan blades mounted on a hub and extending substantially in a radial direction, each of said blades comprising a pressure side and a suction side; and (c) a core engine comprising a compressor unit and turbines for driving said compressor unit and said fan; said device comprising: one or more nozzles arranged to atomize cleaning liquid in said an air stream in an air inlet of said engine, wherein said one or more nozzles comprises at least one of: a first nozzle located at a position relative a center line of said engine and arranged such that said cleaning liquid emanated from said first nozzle is regulated in a direction so that a substantial portion of said cleaning liquid emanated impinges said surfaces of said blades on said pressure side and a limited portion impinges said surfaces of said blades on said suction side or passes between said blades; a second nozzle located at a position relative said center line of said engine and arranged such that said cleaning liquid emanated from said second nozzle is regulated in a direction so that a substantial portion of said cleaning liquid emanated impinges said surfaces of said blades on said suction side and a limited portion impinges said surfaces of said blades on said pressure side or passes between said blades; or a third nozzle located at a position relative said center line of said engine and arranged such that said cleaning liquid emanated from said third nozzle is regulated in a direction so that a substantial portion of said cleaning liquid emanated passes between said blades and enters an inlet of said core engine and a limited portion impinges said surfaces of said blades. 2. A device of claim 1, wherein said first nozzle and said second nozzle are arranged so that said cleaning liquid emanated from said first nozzle and said second nozzle, respectively, form a spray which, at impingement against a blade, comprises a width, along an axis substantially parallel with said radial extension of said blades of said fan, substantially equal to a length of a leading edge of said blade. 3. A device of claim 1, wherein said first nozzle is arranged at a first tangential angle (X) relative to said center line of said engine, said second nozzle is arranged at a second tangential angle (Z) relative to said center line of said engine, and said third nozzle is arranged at a third tangential angle (Y) relative to said center line of said engine. 4. A device of claim 3, wherein said first tangential angle (X) is greater than 40 degrees. 5. A device of claim 3, wherein said second tangential angle (Z) is greater than −20 degrees and less than 20 degrees. 6. A device of claim 3, wherein said third tangential angle (Y) is greater than 20 degrees. 7. A device of claim 3, wherein said first tangential angle (X) is greater than 60 degrees and less than 80 degrees. 8. A device of claim 3, wherein said second tangential angle (Z) is substantially zero degrees. 9. A device of claim 3, wherein said third tangential angle (Y) is greater than 25 degrees and less than 30 degrees. 10. A device of claim 1, wherein said first nozzle is arranged at a first tangential angle (X) relative to said center line of said engine, or said second nozzle is arranged at a second tangential angle (Z) relative to said center line of said engine, or said third nozzle is arranged at a third tangential angle (Y) relative to said center line of said engine. 11. A device of claim 10, wherein said first tangential angle (X) is greater than 40 degrees. 12. A device of claim 10, wherein said second tangential angle (Z) is greater than −20 degrees and less than 20 degrees. 13. A device of claim 10, wherein said third tangential angle (Y) is greater than 20 degrees. 14. A device of claim 1, wherein each of said first nozzle, said second nozzle, and said third nozzle are arranged at a point more than 100 mm in an axial direction upstream said leading edge of said fan. 15. A device of claim 1, wherein each of said first nozzle, said second nozzle, and said third nozzle are located at a position, in a radial direction, at a point less than a diameter of said fan and greater than a diameter of said hub of said fan. 16. A device of claim 1, wherein each of said first nozzle, said second nozzle, and said third nozzle are arranged at a point more than 500 mm and less than 1000 mm upstream said leading edge of said fan. 17. A method for cleaning a gas turbine engine, said engine comprising (a) at least one engine shaft; (b) a fan rotatably arranged on a first shaft and comprising a plurality of fan blades mounted on a hub and extending substantially in a radial direction, each of said blades comprising a pressure side and a suction side; and (c) a core engine comprising a compressor unit and turbines for driving said compressor unit and said fan; said method comprising the steps of: (i) providing one or more nozzles arranged to atomize cleaning liquid in an air stream in an air inlet of said engine, and (ii) applying cleaning liquid emanated from at least one of: a first nozzle arranged such that said cleaning liquid emanated from said first nozzle is controlled such that a substantial portion of said cleaning liquid emanated impinges said surfaces of said blades on said pressure side and a limited portion impinges said surfaces of said blades on said suction side or passes between said blades; a second nozzle arranged such that said cleaning liquid emanated from said second nozzle is controlled such that a substantial portion of said cleaning liquid emanated impinges said surfaces of said blades on said suction side and a limited portion impinges said surfaces of said blades on said pressure side or passes between said blades; or a third nozzle arranged such that said cleaning liquid emanated from said third nozzle is controlled such that a substantial portion of said cleaning liquid emanated impinges said surfaces of said blades between said blades and enters an inlet of said core engine and a limited portion impinges said surfaces of said blades. 18. A method of claim 17, further comprising the step of: forming a spray of said cleaning liquid emanated from said first nozzle and said second nozzle, respectively, which, at impingement against said leading edge, comprises a width, along an axis substantially parallel with said radial extension of said blades of said fan, substantially equal to a length of a leading edge of a blade. 19. A method of claim 17, further comprising the steps of: directing said cleaning liquid emanated from said first nozzle at a first tangential angle (X) relative to said center line of said engine, directing said cleaning liquid emanated from said second nozzle at a second tangential angle (Z) relative to said center line of said engine, and directing said cleaning liquid emanated from said third nozzle at a third tangential angle (Y) relative to said center line of said engine. 20. A method of claim 19, wherein said first tangential angle (X) is greater than 40 degrees. 21. A method of claim 19, wherein said second tangential angle (Z) is greater than −20 degrees and less than 20 degrees. 22. A method of claim 19, wherein said third tangential angle (Y) is greater than 20 degrees. 23. A method of claim 17, further comprising the steps of: directing said cleaning liquid emanated from said first nozzle at a first tangential angle (X) relative to said center line of said engine, or directing said cleaning liquid emanated from said second nozzle at a second tangential angle (Z) relative to said center line of said engine, or directing said cleaning liquid emanated from said third nozzle at a third tangential angle (Y) relative to said center line of said engine. 24. A method of claim 23, wherein said first tangential angle (X) is greater than 40 degrees. 25. A method of claim 23, wherein said second tangential angle (Z) is greater than −20 degrees and less than 20 degrees. 26. A method of claim 23, wherein said third tangential angle (Y) is greater than 20 degrees. 27. A method of claim 17, further comprising the step of: arranging each of said first nozzle, said second nozzle, and said third nozzle at a point more than 100 mm in an axial direction upstream said leading edge of said fan. 28. A method of claim 17, further comprising the step of: arranging each of said first nozzle, said second nozzle, and said third nozzle at a position, in a radial direction, at a point less than said diameter of said fan and greater than a diameter of said hub of said fan. 29. A device for cleaning a gas turbine engine, said engine comprising (a) at least one engine shaft; (b) a fan rotatably arranged on a first shaft and comprising a plurality of fan blades mounted on a hub and extending substantially in a radial direction wherein each of said blades include a pressure side and a suction side; and (c) a core engine comprising a compressor unit and turbines for driving said compressor unit and said fan; said device comprising: one or more nozzles arranged to atomize cleaning liquid in an air stream in an air inlet of said engine, wherein said one or more nozzles comprises at least one of: a first nozzle located at a position transverse a center line of said engine such that said cleaning liquid emanated from said first nozzle is sprayed at a first angle relative to a center line of the engine and in a direction so that a substantial portion of said cleaning liquid emanated impinges said surfaces of said blades on said pressure side and a limited portion impinges said surfaces of said blades on said suction side or passes between said blades; a second nozzle located at a position transverse said center line of said engine such that said cleaning liquid emanated from said second nozzle is sprayed at a second angle relative to said center line that is different than said first angle, and in a direction so that a substantial portion of said cleaning liquid emanated impinges said surfaces of said blades on said suction side and a limited portion impinges said surfaces of said blades on said pressure side or passes between said blades; or a third nozzle located at a position transverse said center line of said engine such that said cleaning liquid emanated from said third nozzle is sprayed at a third angle relative to said center line that is different than both said first angle and said second angle, and in a direction so that a substantial portion of said cleaning liquid emanated passes substantially between said blades and enters an inlet of said core engine and a limited portion impinges said surfaces of said blades. 30. A device of claim 29 further comprising: two or more nozzles arranged to atomize cleaning liquid in said air stream in an air inlet of said engine, wherein said two or more nozzles comprises at least two of said first nozzle, said second nozzle or said third nozzle. 31. A device for cleaning a gas turbine engine, said engine comprising (a) at least one engine shaft; (b) a fan rotatably arranged on a first shaft and comprising a plurality of fan blades mounted on a hub and extending substantially in a radial direction, each of said blades comprising a pressure side and a suction side; and (c) a core engine comprising a compressor unit and turbines for driving said compressor unit and said fan; said device comprising: at least one nozzle arranged to atomize cleaning liquid in an air stream in an inlet of said core engine, said nozzle located at a position relative said center line of said engine such that at least a substantial portion of said cleaning liquid emanated from said at least one nozzle passes substantially between said blades and enters said inlet of said core engine. 32. A device of claim 31, wherein said nozzle is arranged at a tangential angle (Y) relative to said center line of said engine. 33. A device of claim 32, wherein said tangential angle (Y) is greater than 20 degrees. 34. A device of claim 32, wherein said tangential angle (Y) is greater than 25 degrees and less than 30 degrees. 35. A device of claim 31, wherein said nozzle is located at a position, in a radial direction, at a point less than said diameter of said fan and greater than a diameter of said hub of said fan. 36. A method for cleaning a gas turbine engine, said engine comprising (a) at least one engine shaft; (b) a fan rotatably arranged on a first shaft and comprising a plurality of fan blades mounted on a hub and extending substantially in a radial direction, each of said blades comprising a pressure side and a suction side; and (c) a core engine comprising a compressor unit and turbines for driving said compressor unit and said fan; comprising the steps of: (i) providing one or more nozzles arranged to atomize cleaning liquid in an air stream in an inlet of said core engine; and (ii) directing cleaning liquid emanated from said one or more nozzles such that at least a substantial portion of said cleaning liquid emanated from said at least one nozzle passes substantially between said blades and enters said inlet of said core engine. 37. A method of claim 36, further comprising the step of: directing said cleaning liquid emanated from said nozzle at a tangential angle (Y) relative to said center line of said engine. 38. A method of claim 37, wherein said tangential angle (Y) is greater than 20 degrees. 39. A method of claim 37, wherein said tangential angle (Y) is greater than 25 degrees and less than 30 degrees. 40. A method of claim 36, further comprising the step of: arranging said nozzle at a position, in a radial direction, at a point less than said diameter of said fan and greater than a diameter of said hub of said fan.
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이 특허에 인용된 특허 (13)
McDermott Peter (London GB2) ..AP: Rochem Technical Services Holding AG (CHX 03), Apparatus for cleaning a gas turbine engine.
Hornak Steven S. (Monroe CT) Lowdermilk Robert S. (Shelton CT) Miller Robert A. (Bridgeport CT), Removable wash spray apparatus for gas turbine engine.
Miller, Karen Warren; Iasillo, Robert Joseph; Lemmon, Matthew Francis, Method of monitoring for combustion anomalies in a gas turbomachine and a gas turbomachine including a combustion anomaly detection system.
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