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NASA low-speed centrifugal compressor for fundamental researchA new centrifugal compressor facility being built by the NASA Lewis Research Center is described; its purpose is to obtain 'benchmark' experimental data for internal flow code verification and modeling. The facility will be heavily instrumented with standard pressure and temperature probes and have provisions for flow visualization and laser Doppler velocimetry. The facility will accommodate rotational speeds to 2400 rpm and will be rated at pressures to 1.25 atm. The initial compressor stage for testing is geometrically and dynamically representative of modern high-performance stages with the exception of Mach number levels. Design exit tip speed for the initial stage is 500 ft/sec with a pressure ratio of 1.17. The rotor exit backsweep is 55 deg from radial. The facility is expected to be operational in the first half of 1985.
Document ID
19830055135
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Wood, J. R.
(NASA Lewis Research Center Cleveland, OH, United States)
Adam, P. W.
(NASA Lewis Research Center Cleveland, OH, United States)
Buggele, A. E.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 11, 2013
Publication Date
June 1, 1983
Subject Category
Research And Support Facilities (Air)
Report/Patent Number
AIAA PAPER 83-1351
Accession Number
83A36353
Distribution Limits
Public
Copyright
Other

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