Geared gas turbine engine with reduced oil tank size
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-007/36
F16H-057/04
F02K-003/06
F01D-025/20
F02C-007/06
F16H-057/08
출원번호
US-0595255
(2015-01-13)
등록번호
US-10054058
(2018-08-21)
발명자
/ 주소
Sheridan, William G.
McCune, Michael E.
출원인 / 주소
United Technologies Corporation
대리인 / 주소
Carlson, Gaskey & Olds, P.C.
인용정보
피인용 횟수 :
0인용 특허 :
21
초록▼
A gas turbine engine comprises a fan drive turbine for driving a gear reduction, which drives a fan rotor. A lubrication system supplies oil to the gear reduction. An oil tank is relatively small. The lubrication system operates to allow oil to remain in the oil tank for a dwell time of less than or
A gas turbine engine comprises a fan drive turbine for driving a gear reduction, which drives a fan rotor. A lubrication system supplies oil to the gear reduction. An oil tank is relatively small. The lubrication system operates to allow oil to remain in the oil tank for a dwell time of less than or equal to five seconds. A method of designing a gas turbine engine is also disclosed.
대표청구항▼
1. A gas turbine engine comprising: a fan drive turbine for driving a gear reduction, said gear reduction for driving a fan rotor; and a lubrication system for supplying oil to said gear reduction, with an oil tank and the lubrication system operable for allowing oil to remain in the oil tank for a
1. A gas turbine engine comprising: a fan drive turbine for driving a gear reduction, said gear reduction for driving a fan rotor; and a lubrication system for supplying oil to said gear reduction, with an oil tank and the lubrication system operable for allowing oil to remain in the oil tank for a dwell time of less than or equal to five seconds, and wherein said gear reduction includes a sun gear for driving intermediate gears, and there being oil baffles located circumferentially between said intermediate gears. 2. The gas turbine engine as set forth in claim 1, wherein said dwell time is less than or equal to 3.0 seconds. 3. The gas turbine engine as set forth in claim 2, wherein an oil capture gutter surrounds said gear reduction. 4. The gas turbine engine as set forth in claim 3, wherein said fan rotor delivering air into a bypass duct as propulsion air and into a core engine where it passes into a compressor section, with a bypass ratio defined as the ratio of air delivered into said bypass duct compared to the volume of air delivered into said core engine with said bypass ratio being greater than or equal to 6.0. 5. The gas turbine engine as set forth in claim 4, wherein said bypass ratio is greater than or equal to 10.0. 6. The gas turbine engine as set forth in claim 4, wherein a gear ratio of said gear reduction being greater than or equal to 2.3:1. 7. The gas turbine engine as set forth in claim 3, wherein said oil tank holds greater than or equal to 25 and less than or equal to 35 quarts of oil. 8. The gas turbine engine as set forth in claim 7, wherein said engine is rated greater than or equal to 15,000 and less than or equal to 35,000 lbs in rated thrust at take-off. 9. The gas turbine engine as set forth in claim 3, wherein said oil tank holds greater than or equal to 35 and less than or equal to 50 quarts of oil. 10. The gas turbine engine as set forth in claim 9, wherein said gas turbine engine having greater than or equal to 35,000 and less than or equal to 100,000 lbs in rated thrust at take-off. 11. The gas turbine engine as set forth in claim 1, wherein an oil capture gutter surrounds said gear reduction. 12. The gas turbine engine as set forth in claim 11, wherein said oil tank holds greater than or equal to 25 and less than or equal to 35 quarts of oil. 13. The gas turbine engine as set forth in claim 12, wherein said engine is rated greater than or equal to 15,000 and less than or equal to 35,000 lbs in rated thrust at take-off. 14. The gas turbine engine as set forth in claim 11, wherein said oil tank holds greater than or equal to 35 and less than or equal to 50 quarts of oil. 15. The gas turbine engine as set forth in claim 14, wherein said gas turbine engine having greater than or equal to 35,000 and less than or equal to 100,000 lbs in rated thrust at take-off. 16. The gas turbine engine as set forth in claim 1, wherein said oil tank holds greater than or equal to 25 and less than or equal to 35 quarts of oil, and said gas turbine engine is rated greater than or equal to 15,000 and less than or equal to 35,000 lbs in rated thrust at take-off. 17. The gas turbine engine as set forth in claim 1, wherein said oil tank holds greater than or equal to 35 and less than or equal to 50 quarts of oil, and said gas turbine engine having greater than or equal to 35,000 and less than or equal to 100,000 lbs in rated thrust at take-off. 18. A method of building a gas turbine engine comprising: providing a fan drive turbine for driving a gear reduction, said gear reduction for driving a fan rotor; and providing a lubrication system for supplying oil to said gear reduction, with an oil tank and the lubrication system operable for allowing oil to remain in the oil tank for a dwell time of less than or equal to five seconds, and wherein said clear reduction includes a sun clear for driving intermediate clears, and there being oil baffles located circumferentially between said intermediate clears. 19. The method as set forth in claim 18, wherein said dwell time is less than or equal to 3.0 seconds. 20. The method as set forth in claim 18, comprising: providing an oil capture gutter around said gear reduction. 21. The method as set forth in claim 18, wherein said fan rotor delivering air into a bypass duct as propulsion air and into a core engine where it passes into a compressor section, with a bypass ratio defined as the ratio of air delivered into said bypass duct compared to the volume of air delivered into said core engine with said bypass ratio being greater than or equal to 10.0. 22. The method as set forth in claim 18, wherein a gear ratio of said gear reduction being greater than or equal to 2.3:1. 23. The method as set forth in claim 18, wherein said oil tank holds greater than or equal to 25 and less than or equal to 35 quarts of oil. 24. The method as set forth in claim 23, wherein said engine is rated greater than or equal to 15,000 and less than or equal to 35,000 lbs in rated thrust at take-off. 25. The method as set forth in claim 18, wherein said oil tank holds greater than or equal to 35 and less than or equal to 50 quarts of oil. 26. The method as set forth in claim 25, wherein said gas turbine engine having greater than or equal to 35,000 and less than or equal to 100,000 lbs in rated thrust at take-off.
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