Plurality of individually controlled inlet guide vanes in a turbofan engine and corresponding controlling method
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-017/16
F01D-009/06
출원번호
US-0719868
(2004-12-01)
등록번호
US-8641367
(2014-02-04)
국제출원번호
PCT/US2004/040151
(2004-12-01)
§371/§102 date
20070522
(20070522)
국제공개번호
WO2006/059999
(2006-06-08)
발명자
/ 주소
Norris, James W.
Nordeen, Craig A.
출원인 / 주소
United Technologies Corporation
대리인 / 주소
Carlson, Gaskey & Olds
인용정보
피인용 횟수 :
3인용 특허 :
75
초록▼
A tip turbine engine according to the present invention includes a plurality of independently variable inlet guide vanes for the fan and/or for the compressor. An actuator is operatively coupled to each of the flaps, such that each actuator can selectively vary the flap of its associated inlet guide
A tip turbine engine according to the present invention includes a plurality of independently variable inlet guide vanes for the fan and/or for the compressor. An actuator is operatively coupled to each of the flaps, such that each actuator can selectively vary the flap of its associated inlet guide vane. In one embodiment, the inlet guide vanes each include a pivotably mounted flap that is variable independently of the flaps of at least some of the other inlet guide vanes. In another embodiment, the inlet guide vanes each include at least one fluid outlet or nozzle directing pressurized air, as controlled by the associated actuator, to control inlet distortion.
대표청구항▼
1. A turbine engine comprising: a fan having a plurality of fan blades, at least one of the fan blades defines a compressor chamber extending radially therein; anda plurality of individually-controlled inlet guide vanes (IGVs) mounted at an inlet to the turbine engine, further including a plurality
1. A turbine engine comprising: a fan having a plurality of fan blades, at least one of the fan blades defines a compressor chamber extending radially therein; anda plurality of individually-controlled inlet guide vanes (IGVs) mounted at an inlet to the turbine engine, further including a plurality of actuators, each of the plurality of actuators independently controlling only one of the plurality of IGVs, wherein the plurality of actuators are radially outward of a bypass airflow path for bypass air generated by the fan. 2. The turbine engine of claim 1 further including an axial compressor, the plurality of IGVs mounted in front of the axial compressor. 3. The turbine engine of claim 1 wherein each of the plurality of IGVs includes a pivotably mounted flap portion. 4. The turbine engine of claim 3 wherein the plurality of IGVs include a first IGV and a second IGV, a first actuator selectively pivoting the flap portion of the first IGV, a second actuator selectively pivoting the flap portion of the second IGV independently of the flap portion of the first IGV. 5. The turbine engine of claim 3, wherein each of the plurality of actuators is operatively connected to a corresponding pivotably mounted flap portion of each IGV via linkage. 6. The turbine engine of claim 5, wherein the linkage includes a torque rod routed through a fan inlet guide vane to a compressor inlet guide vane. 7. The turbine engine of claim 6, wherein the torque rod is coupled to a trailing edge of the flap via a torque rod lever within a splitter. 8. The turbine engine of claim 3, wherein the pivotably mounted flap portions of each of the plurality of IGVs are pivotable in groups of two or more such that each flap of a group rotates the same amount. 9. The turbine engine of claim 1 further including an axial compressor radially inward of the plurality of IGVs, the plurality of IGVs mounted upstream of at least one of the axial compressor and the fan. 10. The turbine engine of claim 9 wherein the IGVs are fan IGVs mounted upstream of the fan blades, the turbine engine further including a plurality of independently variable compressor IGVs upstream of a plurality of compressor blades in the axial compressor. 11. The turbine engine of claim 1 wherein each of the IGVs includes at least one fluid outlet, the turbine engine further including at least one actuator controlling a flow of fluid from the at least one fluid outlet of each IGV to independently control air flow past the IGV, wherein each IGV has a pivotable portion. 12. The turbine engine of claim 11 wherein the at least one actuator includes a plurality of actuators, each controlling fluid flow from the at least one fluid outlet of one of the plurality of IGVs. 13. The turbine engine of claim 1, further including a rotationally fixed static inner support structure including a splitter, a static inner support housing and a static outer support housing located coaxial to an engine centerline. 14. The turbine engine of claim 1, further including a gearbox assembly arranged to provide a speed increase at a ratio of 3.34-to-one. 15. The turbine engine of claim 1 wherein the plurality of IGVs includes a first IGV and a pair of immediately adjacent IGVs, wherein the first IGV and the pair of immediately adjacent IGVs are each independently controlled by separate actuators of the plurality of actuators. 16. A plurality of inlet guide vane assemblies for a turbine engine comprising: a plurality of variable inlet guide vanes (IGVs), each IGV including at least one fluid outlet for controlling inlet airflow distortion; anda plurality of independent actuators, each of the plurality of independent actuators associated with only one of the IGVs, each actuator capable of varying a supply of pressurized fluid to its associated IGV independently of at least one other IGV, further including an axial compressor further including a plurality of compressor blades, the plurality of IGVs mounted upstream of the plurality of compressor blades. 17. The plurality of inlet guide vane assemblies of claim 16, wherein the plurality of IGVs include a plurality of fan IGVs and a plurality of compressor IGVs. 18. The turbine engine of claim 16 wherein the plurality of IGVs includes a first IGV and a pair of immediately adjacent IGVs, wherein the first IGV and the pair of immediately adjacent IGVs are each independently supplied with pressurized fluid by separate actuators of the plurality of independent actuators. 19. The assembly of claim 16, wherein a linkage for each IGV supplies a pressurized fluid to the at least one fluid outlet. 20. A turbine engine comprising: a fan having a plurality of fan blades, at least one of the fan blades defines a compressor chamber extending radially therein; anda plurality of individually-controlled inlet guide vanes (IGVs) mounted at an inlet to the turbine engine, further including a plurality of actuators, each independently controlling one of the plurality of IGVs, wherein the plurality of actuators are radially outward of a bypass airflow path for bypass air generated by the fan, wherein a linkage for each IGV supplies a pressurized fluid and wherein each IGV includes at least one fluid outlet for controlling inlet airflow distortion, each of the plurality of actuators controlling a flow of fluid through the at least one fluid outlet of its associated IGV. 21. The turbine engine of claim 20, wherein the pressurized fluid is bleed air from an axial compressor. 22. The turbine engine of claim 20, wherein the pressurized fluid is bleed air from a combustor inlet.
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