Gas turbine engine with fan-tied inducer section
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-007/36
F02C-007/042
F02C-007/047
F02K-003/072
출원번호
US-0788913
(2015-07-01)
등록번호
US-9850821
(2017-12-26)
발명자
/ 주소
Kupratis, Daniel Bernard
Schwarz, Frederick M.
출원인 / 주소
United Technologies Corporation
대리인 / 주소
Carlson, Gaskey & Olds, P.C.
인용정보
피인용 횟수 :
0인용 특허 :
3
초록▼
A gas turbine engine includes a shaft, a speed reduction device driven by the shaft, and a fan including a fan rotor driven by the speed reduction device. A compressor section has a plurality of compressor stages driven by the shaft. At least one inducer stage is positioned aft of the fan and couple
A gas turbine engine includes a shaft, a speed reduction device driven by the shaft, and a fan including a fan rotor driven by the speed reduction device. A compressor section has a plurality of compressor stages driven by the shaft. At least one inducer stage is positioned aft of the fan and coupled for rotation with the fan rotor. The at least one inducer stage is positioned upstream of the compressor section.
대표청구항▼
1. A gas turbine engine comprising: a shaft defining an axis of rotation;an epicyclic gear train driven by the first shaft;a fan including a fan rotor driven by the epicyclic gear train;a compressor section comprising a plurality of compressor stages driven by the shaft; andat least one inducer stag
1. A gas turbine engine comprising: a shaft defining an axis of rotation;an epicyclic gear train driven by the first shaft;a fan including a fan rotor driven by the epicyclic gear train;a compressor section comprising a plurality of compressor stages driven by the shaft; andat least one inducer stage positioned aft of the fan and coupled for rotation with the fan rotor, and wherein the at least one inducer stage is positioned upstream of the compressor section. 2. The gas turbine engine according to claim 1, wherein the at least one inducer stage comprises one or more inducer blades fixed for rotation with the fan rotor and a core inlet stator fixed to a non-rotating engine structure. 3. The gas turbine engine according to claim 2, wherein the core inlet stator is positioned radially outward of the inducer blades and is connected to a strut that is supported by at least one bearing such that the shaft can rotate relative to the strut. 4. The gas turbine engine according to claim 3, wherein the strut is further supported by a thrust bearing such that the fan rotor can rotate relative to the strut. 5. The gas turbine engine according to claim 1, wherein the at least one inducer stage comprises a plurality of inducer stages coupled to the fan rotor. 6. The gas turbine engine according to claim 5, wherein each inducer state comprises one or more blades fixed for rotation with the fan rotor and a core stator fixed to a non-rotating engine structure, and wherein the core stator includes one or more vanes. 7. The gas turbine engine according to claim 1, wherein the compressor section includes at least a first compressor driven by the shaft and a second compressor driven by a second shaft and which rotates faster than the first compressor. 8. The gas turbine engine according to claim 7, wherein the first compressor is positioned immediately aft of the at least one inducer stage. 9. The gas turbine engine according to claim 7, wherein the at least one inducer stage is positioned forward of the an epicyclic gear train. 10. The gas turbine engine according to claim 7, including a turbine section that includes at least a first turbine that is driven by the shaft and a second turbine that is driven by the second shaft and rotates faster than the first turbine. 11. The gas turbine engine according to claim 2, wherein the core inlet stator is a variable vane. 12. The gas turbine engine according to claim 2, wherein the core inlet stator is heated for anti-icing. 13. The gas turbine engine according to claim 2, wherein the one or more inducer blades are heated for anti-icing. 14. The gas turbine engine according to claim 10, wherein the turbine section includes three turbine rotors, with the first turbine including a first turbine rotor that drives the fan and the first compressor, and with the second turbine including a second turbine rotor that drives the second compressor, and with a third turbine rotor driving a third compressor. 15. The gas turbine engine according to claim 1, including a turbine section with a high pressure turbine and a low pressure turbine, and with each of the low pressure turbine and the high pressure turbine driving a compressor rotor of the compressor section. 16. The gas turbine engine as recited in claim 15, wherein the epicyclic gear train is positioned intermediate the fan and the compressor rotor driven by the low pressure turbine. 17. The gas turbine engine according to claim 1 wherein the epicyclic gear train comprises a gearbox including a sun gear in meshing engagement with star gears and a ring gear in meshing engagement with the star gears, and wherein the ring gear drives the fan, and wherein the gearbox has a gear reduction ratio of greater than about 2.3. 18. The gas turbine engine according to claim 1 wherein the epicyclic gear train comprises a gearbox including a sun gear in meshing engagement with a plurality of planetary gears supported by a planet carrier and a ring gear in meshing engagement with the planet gears, and wherein the ring gear is fixed and the planet carrier provides input to the fan, and wherein the gearbox has a gear reduction ratio of greater than about 2.3. 19. A gas turbine engine comprising: a first shaft defining an axis of rotation;an epicyclic gear train driven by the first shaft;a fan section including at least one fan blade coupled to a fan rotor wherein the fan rotor is driven by the epicyclic gear train;a compressor section comprising at least a low pressure compressor driven by the first shaft and a high pressure compressor driven by a second shaft;a turbine section comprising at least a low pressure turbine configured to drive the first shaft and a high pressure turbine configured to drive the second shaft; andat least one inducer stage positioned aft of the fan blade and coupled for rotation with the fan rotor about the axis of rotation, and wherein the at least one inducer stage is positioned forward of the compressor section. 20. The gas turbine engine according to claim 19, wherein the low pressure compressor is positioned aft of the epicyclic gear train. 21. The gas turbine engine according to claim 19, wherein the at least one inducer stage comprises one or more inducer blades fixed for rotation with the fan rotor and a core inlet stator fixed to a non-rotating engine structure, and wherein the core inlet stator is positioned radially outward of the inducer blades and is connected to a strut that is supported by at least one bearing such that the first shaft can rotate relative to the strut. 22. The gas turbine engine according to claim 19, wherein the at least one inducer stage comprises a plurality of inducer stages coupled to the fan rotor, and wherein each inducer stage comprises one or more inducer blades fixed for rotation with the fan rotor and a core inlet stator fixed to a non-rotating engine structure, and with the core stator including one or more vanes. 23. The gas turbine engine according to claim 19, wherein the at least one inducer stage is positioned forward of the epicyclic gear train. 24. The gas turbine engine as recited in claim 19, wherein the low pressure turbine is one of at least three turbine rotors, and with the low pressure turbine driving the fan via a first turbine rotor, and wherein a second turbine rotor drives the high pressure compressor, and wherein a third turbine rotor drives a third compressor. 25. The gas turbine engine as recited in claim 19, wherein the high pressure turbine drives a compressor rotor of the high pressure compressor and the low pressure turbine drives a compressor rotor of the low pressure compressor. 26. The gas turbine engine as recited in claim 25, wherein the epicyclic gear train is positioned intermediate the fan and the compressor rotor driven by the low pressure turbine.
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이 특허에 인용된 특허 (3)
Suciu, Gabriel L.; Norris, James W.; Nordeen, Craig A.; Merry, Brian, Fan-turbine rotor assembly for a tip turbine engine.
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