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Effect of a part span variable inlet guide vane on TF34 fan performanceExperimental aerodynamic and performance data were obtained from a TF34 engine. Part span variable inlet guide vanes mounted in front of the fan on the TF34 engine were tested to demonstrate the feasibility of modulating air flow and thrust for vertical takeoff aircraft systems. The fan was mapped to stall for a range of speeds and variable inlet guide were settings. Modulated fan tip performance and unmodulated hub performance were evaluated with a without an extended fan bypass splitter. The effect of a crosswind distortion screen on performance was also evaluated.
Document ID
19820004202
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Alvarez, J. (General Electric Co. Lynn, MA, United States)
Schneider, P. W. (General Electric Co. Lynn, MA, United States)
Date Acquired
September 4, 2013
Publication Date
September 1, 1981
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA-CR-165458
R81AEG030
Report Number: NASA-CR-165458
Report Number: R81AEG030
Accession Number
82N12075
Funding Number(s)
CONTRACT_GRANT: NAS3-21624
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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