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Reverse pitch fan with divided splitterA guide vane arrangement is described for improving gas turbine performance in the reverse thrust mode. This flow straightening method produces low losses in the fluid entering a core engine during reverse thrust operations and allows large supercharging of the core engine during forward thrust.
Document ID
19770010116
Acquisition Source
Legacy CDMS
Document Type
Other - Patent
Authors
Smith, L. H., Jr. (GE Cincinnati, Ohio, United States)
Date Acquired
August 8, 2013
Publication Date
February 1, 1977
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
Patent Number: NASA-CASE-LEW-12760-1
Patent Application Number: US-PATENT-APPL-SN-569925
Patent Number: US-PATENT-4,005,574
Accession Number
77N17059
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Patent
NASA-CASE-LEW-12760-1|US-PATENT-4,005,574
Patent Application
US-PATENT-APPL-SN-569925

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