Gas turbine engine with axial movable fan variable area nozzle
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B63H-003/10
F02K-001/18
B64D-033/04
F02K-001/30
F02K-001/72
B64D-031/00
F01D-005/06
F01D-025/24
F02K-003/06
F04D-029/32
F04D-029/38
F04D-029/52
F04D-029/56
B64D-027/16
F02C-007/36
출원번호
US-0712238
(2017-09-22)
등록번호
US-10174715
(2019-01-08)
발명자
/ 주소
Kohlenberg, Gregory A.
Zamora, Sean P.
출원인 / 주소
UNITED TECHNOLOGIES CORPORATION
대리인 / 주소
Carlson, Gaskey & Olds, P.C.
인용정보
피인용 횟수 :
0인용 특허 :
63
초록▼
A method of designing a turbofan engine according to an exemplary aspect of the present disclosure includes, among other things, providing a fan section including a plurality of fan blades, providing a low pressure turbine driving the plurality of fan blades through a gear train, providing a fan nac
A method of designing a turbofan engine according to an exemplary aspect of the present disclosure includes, among other things, providing a fan section including a plurality of fan blades, providing a low pressure turbine driving the plurality of fan blades through a gear train, providing a fan nacelle and a core nacelle, the fan nacelle at least partially surrounding the core nacelle, providing a fan bypass flow path defined between the core nacelle and the fan nacelle, and providing a fan variable area nozzle in communication with the fan bypass flow path and defining a fan nozzle exit area between the fan nacelle and the core nacelle.
대표청구항▼
1. A method of designing a turbofan engine comprising: providing a fan section including a plurality of fan blades, the plurality of fan blades having a design angle of incidence;providing a low pressure turbine driving the plurality of fan blades through a gear train, the low pressure turbine havin
1. A method of designing a turbofan engine comprising: providing a fan section including a plurality of fan blades, the plurality of fan blades having a design angle of incidence;providing a low pressure turbine driving the plurality of fan blades through a gear train, the low pressure turbine having a pressure ratio greater than 5:1, and the gear train having a gear reduction ratio of greater than 2.5:1;providing a fan nacelle and a core nacelle, the fan nacelle at least partially surrounding the core nacelle;providing a fan bypass flow path defined between the core nacelle and the fan nacelle, and a bypass ratio greater than 10:1;providing a fan variable area nozzle in communication with the fan bypass flow path and defining a fan nozzle exit area between the fan nacelle and the core nacelle;providing a controller in communication with the fan variable area nozzle; andcausing the fan variable area nozzle to vary the fan nozzle exit area to adjust fan bypass air flow in the fan bypass flow path in a plurality of flight conditions in response to the controller such that an angle of incidence on the plurality of fan blades in the plurality of flight conditions is maintained close to the design angle of incidence of the plurality of fan blades. 2. The method as recited in claim 1, further comprising causing the fan variable nozzle to decrease the fan nozzle exit area for a cruise operating condition in response to the controller. 3. The method as recited in claim 2, further comprising causing the fan variable nozzle to increase the fan nozzle exit area for a landing operating condition in response to the controller. 4. The method as recited in claim 3, wherein the fan variable area nozzle includes a plurality of sectors, and each of the plurality of sectors are simultaneously moveable. 5. The method as recited in claim 4, further comprising providing a two stage high pressure turbine, and wherein the gear train includes a planetary gear system. 6. The method as recited in claim 5, further comprising providing a low spool including a low pressure compressor and the low pressure turbine, the low spool driving the low pressure compressor and the planetary gear system. 7. The method as recited in claim 6, wherein the low pressure turbine is a three stage low pressure turbine. 8. The method as recited in claim 3, wherein the plurality of fan blades include a fixed stagger angle. 9. The method as recited in claim 8, wherein the controller causes the fan variable area nozzle to vary the fan nozzle exit area and adjust the bypass ratio, and wherein the controller is an engine controller. 10. The method as recited in claim 1, further comprising providing a duct defined between the fan nacelle and the core nacelle forward of the fan variable area nozzle, the duct having a duct maximum area, and wherein the duct maximum area is greater than the fan nozzle exit area with the fan variable area nozzle in a fully open position. 11. The method as recited in claim 3, wherein the fan variable area nozzle has a maximum required effective area, and the fan nozzle exit area with the fan variable area nozzle in a fully open position is greater than the maximum required effective area of the fan variable area nozzle. 12. The method as recited in claim 11, wherein the fan variable area nozzle includes a plurality of sectors, and each of the plurality of sectors are simultaneously moveable. 13. The method as recited in claim 11, wherein the duct has a duct area distribution that is tailored such that the duct maximum area is greater than the fan nozzle exit area with the fan variable area nozzle in the fully open position. 14. The method as recited in claim 11, wherein the fan variable area nozzle includes a first fan nacelle section, and a second fan nacelle section movably mounted relative the first fan nacelle section and moveable axially relative the first fan nacelle section. 15. The method as recited in claim 14, further comprising moving the second fan nacelle section along an engine axis of rotation relative to the first fan nacelle section to define an auxiliary port extending between the first fan nacelle section and the second fan nacelle section. 16. The method as recited in claim 15, wherein the second fan nacelle section defines a trailing edge of the fan variable area nozzle. 17. The method as recited in claim 3, wherein the fan variable area nozzle has an effective area increase limit, the fan nozzle exit area has a maximum effective area increase, and the fan variable area nozzle achieves the maximum effective area increase of the fan nozzle exit area in operation before the fan variable area nozzle has reached the effective area increase limit. 18. The method as recited in claim 17, further comprising providing a duct defined between the fan nacelle and the core nacelle forward of the fan variable area nozzle, wherein the duct has a duct area distribution and outer wall curvature that is tailored such that the maximum effective area increase of the fan nozzle exit area is achieved in operation before the fan variable area nozzle has reached the effective area increase limit. 19. The method as recited in claim 17, wherein the fan variable area nozzle includes a plurality of sectors, and each of the plurality of sectors are simultaneously moveable. 20. A method of designing a turbofan engine comprising: providing a fan section including a plurality of fan blades, the plurality of fan blades having a design angle of incidence; providing a low pressure turbine having a pressure ratio greater than 5:1; driving the plurality of fan blades through a gear train, the gear train including a planetary gear system having a gear reduction ratio of greater than 2.5:1; providing a fan nacelle and a core nacelle, the fan nacelle at least partially surrounding the core nacelle; providing a fan bypass flow path defined between the core nacelle and the fan nacelle, and a bypass ratio greater than 10:1; providing a fan variable area nozzle in communication with the fan bypass flow path, and defining a fan nozzle exit area between the fan nacelle and the core nacelle; providing a controller in communication with the fan variable area nozzle; and causing the fan variable area nozzle to vary the fan nozzle exit area in response to the controller in a plurality of flight conditions in response to the controller such that the engine changes to a more favorable fan operating line and avoids an instability region of the fan section; causing the fan variable nozzle to decrease the fan nozzle exit area for a cruise operating condition in response to the controller;causing the fan variable nozzle to increase the fan nozzle exit area for a landing operating condition in response to the controller;wherein the fan variable area nozzle has a maximum required effective area, and the fan nozzle exit area with the fan variable area nozzle in a fully open position is greater than the maximum required effective area of the fan variable area nozzle. 21. The method as recited in claim 20, further comprising providing a two stage high pressure turbine, and a low spool including a low pressure compressor and the low pressure turbine, the low spool driving the low pressure compressor and the planetary gear system, and wherein the plurality of fan blades include a fixed stagger angle. 22. The method as recited in claim 20, wherein the fan variable area nozzle includes a plurality of sectors, and each of the plurality of sectors are simultaneously moveable. 23. The method as recited in claim 22, further comprising providing a low spool including a low pressure compressor and the low pressure turbine, the low spool driving the low pressure compressor and the planetary gear system, and wherein the plurality of fan blades include a fixed stagger angle. 24. The method as recited in claim 23, further comprising causing the fan variable area nozzle to vary the fan nozzle exit area to adjust fan bypass air flow in the fan bypass flow path in response to the controller in the plurality of flight conditions such that an angle of incidence of the plurality of fan blades in the plurality of flight conditions is maintained close to the design angle on incidence of the plurality of fan blades. 25. The method as recited in claim 20, further comprising providing a duct defined between the fan nacelle and the core nacelle forward of the fan variable area nozzle, the duct having a duct maximum area, wherein the duct maximum area is greater than the fan nozzle exit area with the fan variable area nozzle in a fully open position. 26. The method as recited in claim 25, further comprising causing the fan variable area nozzle to vary the fan nozzle exit area to adjust fan bypass air flow in the fan bypass flow path in response to the controller in the plurality of flight conditions such that an angle of incidence of the plurality of fan blades in the plurality of flight conditions is maintained close to the design angle of incidence on the plurality of fan blades. 27. The method as recited in claim 26, wherein the fan variable area nozzle has an effective area increase limit, the fan nozzle exit area has a maximum effective area increase, and the fan variable area nozzle achieves the maximum effective area increase of the fan nozzle exit area in operation before the fan variable area nozzle has reached the effective area increase limit.
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