Variable-cycle gas turbine engine with front and aft FLADE stages
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02K-003/065
F02K-003/075
F02K-003/06
F02K-003/062
출원번호
US-0956674
(2010-11-30)
등록번호
US-9016041
(2015-04-28)
발명자
/ 주소
Baughman, John Lewis
Eheart, Raymond
출원인 / 주소
General Electric Company
대리인 / 주소
General Electric Company
인용정보
피인용 횟수 :
4인용 특허 :
16
초록▼
A gas turbine engine includes: a front fan having at least one rotor carrying fan blades disposed within a fan duct, and drivingly connected to a low pressure turbine, the front fan including at least one row of outer fan blades disposed outwardly of and connected to the fan blades, the outer fan bl
A gas turbine engine includes: a front fan having at least one rotor carrying fan blades disposed within a fan duct, and drivingly connected to a low pressure turbine, the front fan including at least one row of outer fan blades disposed outwardly of and connected to the fan blades, the outer fan blades extending across an outer bypass duct which circumscribes the fan duct; a core engine located between the front fan and the low pressure turbine; an aft fan disposed downstream of the low pressure turbine, having at least one rotor carrying aft turbine blades disposed within an aft turbine duct, the aft turbine further including at least one row of aft fan blades disposed outwardly of and connected to the aft turbine blades, and extending across an aft fan duct that surrounds the core engine; and apparatus operable to selectively throttle flow through the outer bypass duct.
대표청구항▼
1. A gas turbine engine, comprising: a front fan having at least one stage, each stage comprising a rotor carrying an annular array of fan blades disposed within a fan duct, the front fan drivingly connected to a low pressure turbine, the front fan further including at least one row of outer fan bla
1. A gas turbine engine, comprising: a front fan having at least one stage, each stage comprising a rotor carrying an annular array of fan blades disposed within a fan duct, the front fan drivingly connected to a low pressure turbine, the front fan further including at least one row of outer fan blades disposed radially outwardly of and connected to the fan blades, the row of outer fan blades radially extending across an outer bypass duct which circumscribes the fan duct;a core engine operable to produce a stream of pressurized combustion gases, the core engine axially located between the front fan and the low pressure turbine, wherein the fan blades of the front fan extend across an inner bypass duct that surrounds the core engine, and;an aft fan disposed downstream of the low pressure turbine, having at least one stage, each stage comprising a rotor carrying an annular array of aft turbine blades disposed within an aft turbine duct, the aft turbine further including at least one row of aft fan blades disposed radially outwardly of and connected to the aft turbine blades, and extending radially across an aft fan duct that surrounds the core engine and the inner bypass duct, wherein airflow of the aft fan duct and airflow of the outer bypass duct are completely physically separated from each other at all points upstream of an exit of the aft fan; andapparatus operable to selectively throttle flow through the outer bypass duct. 2. The engine of claim 1 wherein an array of variable-incidence-angle outer guide vanes are positioned in the outer bypass duct upstream of the outer fan blades. 3. The engine of claim 1 wherein the aft fan comprises a plurality of stages of aft turbine blades driving a spool which in turn drive a single row of aft fan blades. 4. The engine of claim 1 wherein the aft fan comprises two rows of aft turbine blades carrying corresponding rows of aft fan blades, the blade rows configured to rotate in opposite directions. 5. The engine of claim 1 wherein the aft fan comprises two spools, each spool comprising one or more rows of aft turbine blades and one row of aft fan blades, the two spools configured to rotate in opposite directions. 6. The engine of claim 1 wherein the aft fan comprises: two spools, each spool comprising one or more rows of aft turbine blades and one row of aft fan blades; anda row of stator vanes positioned between the rows of aft fan blades;wherein the two spools are configured to rotate in the same direction. 7. The engine of claim 1 wherein variable-angle inlet guide vanes are disposed in the outer bypass duct upstream of the front fan blades. 8. The engine of claim 1 wherein the outer bypass duct is in flow communication with an annular manifold which in turn communicates with at least one offtake duct. 9. The engine of claim 1 wherein the outer bypass duct is in flow communication with the interior of a streamlined centerbody positioned downstream of the aft fan. 10. The engine of claim 9 wherein the centerbody includes a plurality of openings configured to discharge cooling air. 11. The engine of claim 9 wherein the centerbody includes an aft-facing nozzle. 12. The engine of claim 1 wherein flow exiting the aft fan is segregated from flow exiting the core engine. 13. The engine of claim 1 wherein flow exiting the aft fan is mixed with flow exiting the core engine. 14. The engine of claim 1 wherein the core engine includes, in sequential flow order: a compressor, a combustor, and a high-pressure turbine. 15. The engine of claim 1 further comprising an electrical generator drivingly connected to the front fan. 16. The engine of claim 1 further including a core drive fan stage including a row of core drive fan blades extending from and driven by compressor blades of the core engine. 17. The engine of claim 16 wherein the core drive fan blades are located in a duct which communicates with an inner bypass duct that circumscribes the core engine and communicates with the fan duct. 18. The engine of claim 17 wherein variable-angle guide vanes are disposed in the duct upstream of the core drive fan blades.
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.
Wadia, Aspi Rustom; Turner, Alan Glen; Dziech, Aaron Michael; Szucs, Peter Nicholas; Decker, John Jared, FLADE fan with different inner and outer airfoil stagger angles at a shroud therebetween.
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