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Experimental study of low aspect ratio compressor bladingThe effects of low aspect ratio blading on aerodynamic performance were examined. Four individual transonic compressor stages, representative of the inlet stage of an advanced high pressure ratio core compressor, are discussed. The flow phenomena for the four stages are investigated. Comparisons of blade element parameters are presented for the two different aspect ratio configurations. Blade loading levels are compared for the near stall conditions and comparisons are made of loss and diffusion factors over the operating range of incidence angles.
Document ID
19800002791
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Reid, L. (NASA Lewis Research Center Cleveland, OH, United States)
Moore, R. D. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 4, 2013
Publication Date
January 1, 1979
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-79280
E-217
Report Number: NASA-TM-79280
Report Number: E-217
Meeting Information
Meeting: Ann. Intern. Gas Turbine Conf.
Location: New Orleans, LA
Country: United States
Start Date: March 9, 1980
End Date: March 13, 1980
Sponsors: Am. Soc. of Mech. Engr.
Accession Number
80N11037
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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