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NASA low-speed centrifugal compressor for 3-D viscous code assessment and fundamental flow physics researchA low speed centrifugal compressor facility recently built by the NASA Lewis Research Center is described. The purpose of this facility is to obtain detailed flow field measurements for computational fluid dynamic code assessment and flow physics modeling in support of Army and NASA efforts to advance small gas turbine engine technology. The facility is heavily instrumented with pressure and temperature probes, both in the stationary and rotating frames of reference, and has provisions for flow visualization and laser velocimetry. The facility will accommodate rotational speeds to 2400 rpm and is rated at pressures to 1.25 atm. The initial compressor stage being tested is geometrically and dynamically representative of modern high-performance centrifugal compressor stages with the exception of Mach number levels. Preliminary experimental investigations of inlet and exit flow uniformly and measurement repeatability are presented. These results demonstrate the high quality of the data which may be expected from this facility. The significance of synergism between computational fluid dynamic analysis and experimentation throughout the development of the low speed centrifugal compressor facility is demonstrated.
Document ID
19920032956
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hathaway, M. D.
(U.S. Army, Propulsion Directorate, Cleveland OH, United States)
Wood, J. R.
(NASA Lewis Research Center Cleveland, OH, United States)
Wasserbauer, C. A.
(NASA Lewis Research Center; Sverdrup Technology, Inc. Cleveland, OH, United States)
Date Acquired
August 15, 2013
Publication Date
June 1, 1991
Subject Category
Aerodynamics
Report/Patent Number
ASME PAPER 91-GT-140
Accession Number
92A15580
Distribution Limits
Public
Copyright
Other

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