Gas turbine engine booster having rotatable radially inwardly extending blades and non-rotatable vanes
IPC분류정보
국가/구분 |
United States(US) Patent
등록
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국제특허분류(IPC7판) |
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출원번호 |
US-0275813
(2008-11-21)
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등록번호 |
US-8166748
(2012-05-01)
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발명자
/ 주소 |
- Schilling, Jan Christopher
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출원인 / 주소 |
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대리인 / 주소 |
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인용정보 |
피인용 횟수 :
10 인용 특허 :
10 |
초록
▼
A gas turbine engine booster includes one or more rotatable booster stages having booster blades extending radially inwardly from a rotatable drum and one or more non-rotatable vane stages having booster vanes extending radially outwardly from a non-rotatable shell. The booster stages may be interdi
A gas turbine engine booster includes one or more rotatable booster stages having booster blades extending radially inwardly from a rotatable drum and one or more non-rotatable vane stages having booster vanes extending radially outwardly from a non-rotatable shell. The booster stages may be interdigitated with the vane stages. The booster may be co-rotatable or counter-rotatable with respect to a fan stage of an aircraft gas turbine engine. The booster may be driven by a single turbine or one of counter-rotatable turbines or though a gearbox by these turbines. The booster blades and the booster vanes extend across a core engine inlet duct having an entrance downstream of the first fan stage. A fan section with the booster may have counter-rotatable first and second fan stages with fan blades of the second fan stages connected to and mounted radially outwardly of the rotatable drum.
대표청구항
▼
1. A gas turbine engine booster comprising: one or more rotatable booster blade rows of rotatable booster blades extending radially inwardly from a rotatable drum,one or more non-rotatable booster vane rows of non-rotatable booster vanes extending radially outwardly from a non-rotatable annular stru
1. A gas turbine engine booster comprising: one or more rotatable booster blade rows of rotatable booster blades extending radially inwardly from a rotatable drum,one or more non-rotatable booster vane rows of non-rotatable booster vanes extending radially outwardly from a non-rotatable annular structure, andthe booster blade rows being interdigitated with the booster vane rows. 2. An aircraft gas turbine engine fan section comprising: a fan stage including a fan blade row,a gas turbine engine booster axially located downstream of the fan stage,the booster including one or more rotatable booster rows having rotatable booster blades extending radially inwardly from a rotatable drum, andthe booster including one or more non-rotatable booster vane rows having non-rotatable booster vanes extending radially outwardly from a non-rotatable annular structure, andthe booster blade rows being interdigitated with the booster vane rows. 3. An aircraft gas turbine engine fan section as claimed in claim 2, further comprising a core engine inlet duct having an entrance downstream of the fan stage and the booster blades and the booster vanes extending across the core engine inlet duct. 4. An aircraft gas turbine engine fan section as claimed in claim 2, further comprising: comprising:the fan stage being a counter-rotatable first fan stage counter-rotatable with respect to a counter-rotatable second fan stage,the counter-rotatable first and second fan stages including first and second fan blade rows respectively, andthe gas turbine engine booster axially located substantially between the first and second fan stages. 5. An aircraft gas turbine engine fan section as claimed in claim 4, further comprising a core engine inlet duct having an entrance downstream of the first fan stage and the booster blades and the booster vanes extending across the core engine inlet duct. 6. An aircraft gas turbine engine fan section as claimed in claim 5, further comprising the entrance to the core engine inlet duct being upstream of the second fan stage. 7. An aircraft gas turbine engine fan section as claimed in claim 4, further comprising fan blades of the second fan blade row being connected to and mounted radially outwardly of the rotatable drum. 8. An aircraft gas turbine engine fan section as claimed in claim 7, further comprising a core engine inlet duct having an entrance downstream of the first fan stage and the booster blades and the booster vanes extending across the core engine inlet duct. 9. An aircraft gas turbine engine fan section as claimed in claim 8, further comprising the entrance to the core engine inlet duct being upstream of the second fan stage. 10. An aircraft gas turbine engine comprising: an engine fan section including a fan stage having at least one fan blade row,a core engine downstream of the fan section and including a high pressure rotor with a high pressure turbine,a low pressure turbine downstream of the core engine,a gas turbine engine booster axially located downstream of the fan stage,the booster including one or more rotatable booster blade rows having rotatable booster blades extending radially inwardly from a rotatable drum,the booster including one or more non-rotatable vane rows having non-rotatable booster vanes extending radially outwardly from a non-rotatable annular structure, andthe booster blade rows being interdigitated with the booster vane rows. 11. An aircraft gas turbine engine as claimed in claim 10, further comprising: a core engine inlet duct to the core engine,the core engine inlet duct having an entrance downstream of the fan stage and the booster blades, andthe booster vanes extending across the core engine inlet duct. 12. An aircraft gas turbine engine as claimed in claim 10, further comprising: the fan stage being a counter-rotatable first fan stage counter-rotatable with respect to a counter-rotatable second fan stage,the counter-rotatable first and second fan stages including first and second fan blade rows respectively, andthe gas turbine engine booster axially located substantially between the first and second fan stages. 13. An aircraft gas turbine engine as claimed in claim 12, further comprising a core engine inlet duct having an entrance downstream of the first fan stage and the booster blades and the booster vanes extending across the core engine inlet duct. 14. An aircraft gas turbine engine as claimed in claim 13, further comprising the entrance to the core engine inlet duct being upstream of the second fan stage. 15. An aircraft gas turbine engine as claimed in claim 12, further comprising fan blades of the second fan blade row being connected to and mounted radially outwardly of the rotatable drum. 16. An aircraft gas turbine engine as claimed in claim 15, further comprising a core engine inlet duct having an entrance downstream of the first fan stage and the booster blades and the booster vanes extending across the core engine inlet duct. 17. An aircraft gas turbine engine as claimed in claim 16, further comprising the entrance to the core engine inlet duct being upstream of the second fan stage. 18. An aircraft gas turbine engine comprising: an engine fan section including a single fan stage having fan blades,a core engine downstream of the fan section and including a high pressure rotor with a high pressure turbine,a low pressure turbine downstream of the core engine,a gas turbine engine booster axially located downstream of the fan stage,the booster including one or more rotatable booster blade rows having rotatable booster blades extending radially inwardly from a rotatable drum,the booster including one or more non-rotatable vane rows having non-rotatable booster vanes extending radially outwardly from a non-rotatable annular structure,the booster blade rows being interdigitated with the booster vane rows,a reduction gearbox drivenly connected to the low pressure turbine by a low pressure shaft,the reduction gearbox drivenly connected to the fan stage, andthe rotatable drum and the booster blades drivenly connected to the low pressure shaft. 19. An aircraft gas turbine engine as claimed in claim 18, further comprising: a core engine inlet duct to the core engine,the core engine inlet duct having an entrance downstream of the single fan stage and the booster blades, andthe booster vanes extending across the core engine inlet duct.
이 특허에 인용된 특허 (10)
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Seda, Jorge F., Aircraft engine with inter-turbine engine frame.
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Seda, Jorge F.; Dunbar, Lawrence W.; Gliebe, Philip R.; Szucs, Peter N.; Brauer, John C.; Johnson, James E.; Moniz, Thomas; Steinmetz, Gregory T., Aircraft engine with inter-turbine engine frame supported counter rotating low pressure turbine rotors.
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Orlando, Robert Joseph; Moniz, Thomas Ory; Baughman, John Lewis, Aircraft gas turbine engine having variable torque split counter rotating low pressure turbines and booster aft of counter rotating fans.
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Seda, Jorge F.; Dunbar, Lawrence W.; Szucs, Peter N.; Brauer, John C.; Johnson, James E., Counter rotating aircraft gas turbine engine with high overall pressure ratio compressor.
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Moniz, Thomas Ory; Orlando, Robert Joseph, Counterrotatable booster compressor assembly for a gas turbine engine.
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Prentice, Ian Francis; Crall, David William; Busbey, Bruce Clark; Glynn, Christopher Charles; Bond, Donald Ray, Counterrotatable booster compressor assembly for a gas turbine engine.
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Romani Giuseppe,CAX, Integrated fan / low pressure compressor rotor for gas turbine engine.
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Taylor John B. (Cincinnati OH), Unducted, counterrotating gearless front fan engine.
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Giffin ; III Rollin G. (Cincinnati OH), Variable specific thrust turbofan engine.
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Baughman, John Lewis; Orlando, Robert Joseph; Moniz, Thomas Ory, Variable torque split aircraft gas turbine engine counter rotating low pressure turbines.
이 특허를 인용한 특허 (10)
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Kuhne, Craig Miller; Glynn, Christopher Charles; Vondrell, Randy M.; Breeze-Stringfellow, Andrew; Murrow, Kurt David; Zatorski, Darek T.; Yeager, Donald Scott; Dinsmore, Nicholas Rowe; Martin, Samuel Jacob; Bradley, Donald Albert, Engine architecture with reverse rotation integral drive and vaneless turbine.
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Sheridan, William G., Fundamental gear system architecture.
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Sheridan, William G.; McCune, Michael E.; Schwarz, Frederick M.; Kupratis, Daniel Bernard; Suciu, Gabriel L.; Ackermann, William K.; Husband, Jason, Fundamental gear system architecture.
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Suciu, Gabriel L.; Merry, Brian D.; Dye, Christopher M.; Johnson, Steven B., Gas turbine engine compressor arrangement.
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Sheridan, William G., Gear system architecture for gas turbine engine.
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McCune, Michael E.; Husband, Jason; Schwarz, Frederick M.; Kupratis, Daniel Bernard; Suciu, Gabriel L.; Ackermann, William K., Geared architecture for high speed and small volume fan drive turbine.
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McCune, Michael E.; Husband, Jason; Schwarz, Frederick M.; Kupratis, Daniel Bernard; Suciu, Gabriel L.; Ackermann, William K., Geared architecture for high speed and small volume fan drive turbine.
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McCune, Michael E.; Husband, Jason; Schwarz, Frederick M.; Kupratis, Daniel Bernard; Suciu, Gabriel L.; Ackermann, William K., Geared architecture for high speed and small volume fan drive turbine.
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McCune, Michael E.; Husband, Jason; Schwarz, Frederick M.; Kupratis, Daniel Bernard; Suciu, Gabriel L.; Ackermann, William K., Geared architecture for high speed and small volume fan drive turbine.
-
Orlando, Robert Joseph; Moniz, Thomas Ory; Stuart, Alan Roy, Turbine engine assembly and methods of assembling same.
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