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Dual output variable pitch turbofan actuation systemAn improved actuating mechanism was provided for a gas turbine engine incorporating fan blades of the variable pitch variety, the actuator adapted to rotate the individual fan blades within apertures in an associated fan disc. The actuator included means such as a pair of synchronizing ring gears, one on each side of the blade shanks, and adapted to engage pinions disposed thereon. Means were provided to impart rotation to the ring gears in opposite directions to effect rotation of the blade shanks in response to a predetermined input signal. In the event of system failure, a run-away actuator was prevented by an improved braking device which arrests the mechanism.
Document ID
19770007082
Acquisition Source
Legacy CDMS
Document Type
Other - Patent
Authors
Griswold, R. H., Jr.
(GE Cincinnati, United States)
Broman, C. L.
(GE Cincinnati, United States)
Date Acquired
August 8, 2013
Publication Date
November 30, 1976
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
Patent Application Number: US-PATENT-APPL-SN-579375
Patent Number: NASA-CASE-LEW-12419-1
Patent Number: US-PATENT-3,994,128
Accession Number
77N14025
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Patent
NASA-CASE-LEW-12419-1|US-PATENT-3,994,128
Patent Application
US-PATENT-APPL-SN-579375
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