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Aircraft thrust controlAn integrated control system for coaxial counterrotating aircraft propulsors driven by a common gas turbine engine. The system establishes an engine pressure ratio by control of fuel flow and uses the established pressure ratio to set propulsor speed. Propulsor speed is set by adjustment of blade pitch.
Document ID
20080005933
Acquisition Source
Headquarters
Document Type
Other - Patent
Authors
Walker, Neil
Day, Stanley G.
Collopy, Paul D.
Bennett, George W.
Date Acquired
August 24, 2013
Publication Date
September 20, 1988
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
Patent Number: US-PATENT-4,772,180
Patent Application Number: US-PATENT-APPL-SN-902231
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Patent
US-PATENT-4,772,180
Patent Application
US-PATENT-APPL-SN-902231

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