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Stalled and stall-free performance of axial-flow compressor stage with three inlet-guide-vane and stator-blade settingsThe performance of the first stage of a transonic, multistage compressor was mapped over a range of inlet-guide-vane and stator-blade settings. Both stall-free and deep-stall performance data were obtained. For the settings tested, as stall was encountered and flow was further reduced, a relatively sharp drop in pressure ratio occurred and was followed by a continuing but more gradual reduction in pressure ratio with reduced flow. The position of the stall line on the map of pressure ratio against equivalent weight flow was essentially unaffected over the range of inlet-guide-vane and stator-blade settings.
Document ID
19770016169
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Urasek, D. C. (NASA Lewis Research Center Cleveland, OH, United States)
Steinke, R. J. (NASA Lewis Research Center Cleveland, OH, United States)
Cunnan, W. S. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
May 1, 1977
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA-TN-D-8457
E-8222
Accession Number
77N23113
Funding Number(s)
PROJECT: RTOP 505-04
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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