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Thrust reverser with variable nozzleA thrust reverser is provided for both modulating and reversing bypass flow discharged from a fan through a bypass duct of a turbofan gas turbine engine. The reverser includes an aft cowl joined to a forward cowl and having an aft end surrounding a core engine to define a discharge fan nozzle of minimum flow throat area. The aft cowl is axially translatable relative to the forward cowl from a first position fully retracted against the forward cowl, to a second position partially extended from the forward cowl, and to a third position fully extended from the forward cowl. A plurality of cascade turning vanes are disposed between the forward and aft cowls, and a plurality of thrust reversing deflector doors are pivotally mounted to the aft cowl and bound the bypass duct. The deflector doors are selectively deployed from a stowed position corresponding with the first and second positions of the aft cowl for allowing unrestricted flow of the bypass flow through the fan nozzle. The doors also have a deployed position corresponding with the third position of the aft cowl for substantially deflecting the bypass flow from discharging through the fan nozzle to discharging through the cascade vanes for effecting thrust reverse. Axial translation of the aft cowl between the first and second positions varies flow area of the fan nozzle to vary thrust effected by the discharged bypass flow.
Document ID
20080004632
Acquisition Source
Legacy CDMS
Document Type
Other - Patent
Authors
Butler, Lawrence
Date Acquired
August 24, 2013
Publication Date
August 12, 1997
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
Patent Application Number: US-PATENT-APPL-SN-694808
Patent Number: US-PATENT-5,655,360
Funding Number(s)
CONTRACT_GRANT: NAS3-25953
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Patent
US-PATENT-5,655,360
Patent Application
US-PATENT-APPL-SN-694808
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