Method and apparatus to facilitate cooling turbine engines
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-001/00
F02G-003/00
출원번호
UP-0750500
(2007-05-18)
등록번호
US-7757492
(2010-08-09)
발명자
/ 주소
Intile, John Charles
Poyyapakkam, Madhavan
Rao, Ganesh Pejawar
Kaleeswaran, Karthick
출원인 / 주소
General Electric Company
대리인 / 주소
Armstrong Teasdale LLP
인용정보
피인용 횟수 :
6인용 특허 :
10
초록▼
A method facilitates assembling a gas turbine engine including a combustor assembly and a nozzle assembly. The method comprises providing a transition piece including a first end, a second end, and a body extending therebetween, where the body includes an inner surface, an opposite outer surface, co
A method facilitates assembling a gas turbine engine including a combustor assembly and a nozzle assembly. The method comprises providing a transition piece including a first end, a second end, and a body extending therebetween, where the body includes an inner surface, an opposite outer surface, coupling the first end of the transition piece to the combustor assembly, and coupling the second end of the transition piece to the nozzle assembly such that a turbulator extending helically over the outer surface of the transition piece extends from the transition piece first end to the transition piece second end to facilitate inducing turbulence to cooling air supplied to the combustor assembly.
대표청구항▼
What is claimed is: 1. A method for assembling a gas turbine engine including a combustor assembly and a nozzle assembly, said method comprises: providing a transition piece including a first end, a second end, and a body extending therebetween, where the body includes an inner surface, an opposite
What is claimed is: 1. A method for assembling a gas turbine engine including a combustor assembly and a nozzle assembly, said method comprises: providing a transition piece including a first end, a second end, and a body extending therebetween, where the body includes an inner surface, an opposite outer surface; coupling the first end of the transition piece to the combustor assembly; and coupling the second end of the transition piece to the nozzle assembly such that a turbulator having a semi-circular cross-sectional shape extends helically and continuously in a single structure over the entire outer surface of the transition piece extends from the transition piece first end to the transition piece second end to facilitate inducing turbulence to cooling air supplied to the combustor assembly. 2. A method is accordance with claim 1 wherein providing a transition piece further comprises coupling a turbulator helically about the outer surface of the transition piece. 3. A method in accordance with claim 2 wherein said coupling a turbulator helically about the outer surface further comprises coupling the turbulator to the outer surface using a braising process. 4. A method in accordance with claim 1 wherein providing a turbulator further comprises providing a transition piece including a turbulator formed integrally with the transition piece. 5. A method in accordance with claim 2, wherein said coupling a turbulator helically about the outer surface further comprises coupling the turbulator to the outer surface using one of a welding process and a machining process. 6. A transition piece for a gas turbine engine, said transition piece comprises: a first end; a second end; and a body extending therebetween, said body comprises an inner surface, an opposite outer surface, and a turbulator extending helically and continuously in a single structure over the entire outer surface, said turbulator comprises a semi-circular cross-sectional shape, wherein said turbulator is configured to facilitate cooling said transition piece. 7. A transition piece in accordance with claim 6 wherein said first end has a substantially rectangular cross-sectional profile. 8. A transition piece in accordance with claim 7 wherein said second end has a substantially circular cross-sectional profile. 9. A transition piece in accordance with claim 6 wherein said turbulator is coupled to said outer surface. 10. A transition piece in accordance with claim 6 wherein said turbulator is formed integrally with said body. 11. A transition piece in accordance with claim 6 wherein said turbulator is coupled to said outer surface using one of a braising process, a welding process, and a machining process. 12. A transition piece in accordance with claim 6 wherein said turbulator facilitates extending the useful life of said transition piece by efficiently cooling said transition piece. 13. A gas turbine engine comprising: a combustion assembly; and a transition piece coupled to said combustion assembly and extending downstream therefrom, said transition piece comprises a first end, a second end, and a body extending therefrom, said body comprises an inner surface, an outer surface, and a turbulator extending helically and continuously in a single structure over the entire outer surface, from said first end to said second end, wherein said turbulator comprises a semi-circular cross-sectional shape. 14. A gas turbine engine in accordance with claim 13 wherein said turbulator is coupled to said outer surface. 15. A gas turbine engine in accordance with claim 14 wherein said turbulator is coupled to said outer surface via a braising process. 16. A gas turbine engine in accordance with claim 13 wherein said turbulator is formed integrally with said body. 17. A gas turbine engine in accordance with claim 13 wherein said turbulator is coupled to said outer surface using one of a welding process and a machining process. 18. A gas turbine engine in accordance with claim 13 wherein said turbulator facilitates extending the useful life of said transition piece by efficiently cooling said transition piece.
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이 특허에 인용된 특허 (10)
Martling, Vincent C.; Xiao, Zhenhua, Advanced cooling configuration for a low emissions combustor venturi.
Sato Isao (Hitachi JPX) Kato Fumio (Hitachi JPX) Uchiyama Yoshihiro (Hitachi JPX) Iizuka Nobuyuki (Hitachi JPX) Hata Tsuneyuki (Hitachi JPX), Combustor of gas turbine with features for vibration reduction and increased cooling.
Bintz Miles F. (Schenectady NY) Dehmer ; deceased Raymond L. (late of Clifton Park NY by Mary Mae Dehmer ; administrator), Liquid-cooled transition member to turbine inlet.
Johnson, Robert Alan; Loprinzo, Anthony Joseph; Lee, Ching-Pang; Abuaf, Nesim; Hasz, Wayne Charles; Morton, Harmon Lindsay, Method and apparatus for enhancing heat transfer in a combustor liner for a gas turbine.
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