High pressure compressor rotor thermal conditioning using discharge pressure air
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-005/08
F02C-009/18
F04D-029/32
F02C-003/04
F01D-019/02
F02C-006/08
F02C-007/18
출원번호
US-0878018
(2015-10-08)
등록번호
US-10107206
(2018-10-23)
발명자
/ 주소
Forcier, Matthew P.
Hiester, Paul J.
Murphy, Andrew J.
출원인 / 주소
United Technologies Corporation
대리인 / 주소
Carlson, Gaskey & Olds, P.C.
인용정보
피인용 횟수 :
0인용 특허 :
2
초록▼
A compressor for use in a gas turbine engine comprises a compressor rotor including blades and a disc, with a bore defined radially inwardly of the disc. A high pressure air tap includes a lower temperature tapped path and a higher temperature tapped path and a valve for selectively delivering one o
A compressor for use in a gas turbine engine comprises a compressor rotor including blades and a disc, with a bore defined radially inwardly of the disc. A high pressure air tap includes a lower temperature tapped path and a higher temperature tapped path and a valve for selectively delivering one of the lower temperature tapped path and the higher temperature tapped path into the bore of the disc. The valve is operable to selectively block flow of either of the lower pressure and higher pressure tapped paths to the bore of the disc, with the disc including holes to allow air from compressor chambers to communicate with the bore of the disc. A gas turbine engine and a method of operating a gas turbine engine are also disclosed.
대표청구항▼
1. A compressor for use in a gas turbine engine comprising: a compressor rotor including blades in at least one compressor chamber and a disc, with a bore defined radially inwardly of said disc; anda high pressure air tap including a lower temperature tapped path and a higher temperature tapped path
1. A compressor for use in a gas turbine engine comprising: a compressor rotor including blades in at least one compressor chamber and a disc, with a bore defined radially inwardly of said disc; anda high pressure air tap including a lower temperature tapped path and a higher temperature tapped path and a valve for selectively delivering one of said lower temperature tapped path and said higher temperature tapped path into said bore of said disc, and said valve being operable to selectively block flow of either of said lower temperature and higher temperature tapped paths to said bore of said disc, with said disc including holes to allow air from said at least one compressor chamber to communicate with said bore of said disc. 2. The compressor as set forth in claim 1, wherein said lower temperature tapped path passes through a heat exchanger before reaching said valve. 3. The compressor as set forth in claim 1, wherein said valve allows flow from said higher temperature tapped path when the associated engine is moving from a lower power operation to a higher power operation. 4. The compressor as set forth in claim 3, wherein said valve delivers said lower temperature tapped path to said bore of said disc when said engine is at higher power operation. 5. The compressor as set forth in claim 4, wherein said valve blocks flow of both said higher temperature and lower temperature tapped paths when said engine is operating at other lower power settings. 6. The compressor as set forth in claim 5, wherein air from the compressor chamber passes radially inwardly through the holes in said disc, and into said bore of said disc when said valve blocks flow of both said higher temperature tapped path and said lower temperature tapped path. 7. The compressor as set forth in claim 4, wherein said valve communicates said higher temperature tap path radially inwardly of said blades, through said disc, and into said bore when said engine is operating at other lower power settings. 8. The compressor as set forth in claim 1, wherein a seal blocks flow of air at a radially inner portion of said compressor section from passing upstream. 9. A gas turbine engine comprising: a compressor section, a combustor, and a turbine section;said compressor section including a compressor rotor including blades in at least one compressor chamber and a disc, with a bore defined radially inwardly of said disc; anda high pressure air tap including a lower temperature tapped path and a higher temperature tapped path and a valve for selectively delivering one of said lower temperature tapped path and said higher temperature tapped path into said bore of said disc, and said valve being operable to selectively block flow of either of said lower temperature tapped path and said higher temperature tapped path to said bore of said disc, with said disc including holes to allow air from said at least one compressor chamber to communicate with said bore of said disc. 10. The gas turbine engine as set forth in claim 9, wherein said lower temperature tapped path passes through a heat exchanger before reaching said valve. 11. The gas turbine engine as set forth in claim 9, wherein said valve allows flow from said higher temperature tapped path when the associated engine is moving from a lower power operation to a higher power operation. 12. The gas turbine engine as set forth in claim 11, wherein said valve delivers said lower temperature tapped path to said bore of said disc when said engine is at higher power operation. 13. The gas turbine engine as set forth in claim 12, wherein said valve blocks flow of both said higher temperature and lower temperature tapped paths when said engine is operating at other lower power settings. 14. The gas turbine engine as set forth in claim 13, wherein air from the compressor chamber passes radially inwardly through the holes in said disc, and into said bore of said disc when said valve blocks flow of both said higher temperature tapped path and said lower temperature tapped path. 15. The gas turbine engine as set forth in claim 12, wherein said valve communicates said higher temperature tap path radially inwardly of said blades, through said disc, and into said bore when said engine is operating at other lower power settings. 16. The gas turbine engine as set forth in claim 9, wherein a seal blocks flow of air at a radially inner portion of said compressor section from passing upstream. 17. A method of operating a gas turbine engine including the steps of: tapping air from a compressor section exit, the compressor section having a rotor including blades in at least one compressor chamber and a disc, with a bore defined radially inwardly of said disc;the high pressure air tap including a lower temperature tapped path and a higher temperature tapped path and a valve selectively delivering one of said lower temperature tapped path and said higher temperature tapped path into said bore of said disc, and said valve selectively blocking flow of either, or both, of said lower temperature tapped path and said higher temperature tapped paths to said bore of said disc; andwherein air from the at least one compressor chamber passes radially inwardly through holes in said disc, and into said bore of said disc when said valve blocks flow of both said higher pressure and lower pressure paths. 18. The method as set forth in claim 17, wherein said lower temperature tapped path passes through a heat exchanger before reaching said valve. 19. The method as set forth in claim 17, wherein said valve communicates said higher temperature tap path radially inwardly of said blades, through said disc, and into said bore when said engine is operating at some lower power settings.
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이 특허에 인용된 특허 (2)
Weiner Harvey I. (South Windsor CT) Allard Kenneth L. (Wilbraham MA), Active clearance control.
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