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IyionsA Nut onuatAo onl3ut C ad Space Adrn nistraloni 1 Report No. NASA TM-1 03710 AVSCOM TR 91-C-003 4. Title and Subtitle Report Documentation Page 2. Government Accession No. 3. Recipient's Catalog No. 5. Report Date 6. Performing Organization Code 8. Performing Organization Report No. E-5938 10. Work Unit No. 505-62-21 1L161102AH45 11. Contract or Grant No. 13. Type of Report and Period Covered Technical Memorandum 14. Sponsoring Agency Code NASA Low-Speed Centrifugal Compressor for 3-D Viscous Code Assessment and Fundamental Flow Physics Research 7. Author(g) M.D. Hathaway, J.R. Wood, and C.A. Wasscrbauer 9. Performing Organization Name and Address NASA Lewis Research Center Cleveland, Ohio 44135-3191 and Propulsion Directorate U.S. Army Aviation Systems Command Cleveland, Ohio 44135-3191 112. Sponsoring Agency Name and Address National Aeronautics and Space Administration Washington, D.C. 20546-0001 and U.S. Army Aviation Systems Command St. Louis, Mo. 63120-1798 15. Supplementary Notes Prepared for the 36th International Gas Turbine and Aeroengine Congress and Exposition sponsored by the American Society of Mechanical Engineers, Orlando, Florida, June 3-6. 1991. M.D. Hathaway, Propulsion Directorate, U.S. Army Aviation Systems Command. J.R. Wood, NASA Lewis Research Center. C.A. Wasserbauer, Sverdrup Technology, Inc., Lewis Research Center Group, 2001 Aerospace Parkway. Brook Park, Ohio 44142. Responsible person, M.D. Hathaway, (216) 433-6250. 16. Abstract A 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 modelling 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 uniformity 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 computa- tional fluid dynamic analyses and experimentation throughout the development of the low speed centrifugal compressor facility is demonstrated. 17. Key Words (Suggested by Author(s)) Centrifugal compressor Low speed . Experiment Cotn1putation 19. Socurity Classif. (of this report) Unclassified 18. Distribution Statement Unclassified- Unlimited Subject Category 02 20. Security Classil. (ofthis page) 21. No,of pages Unclassified 14 22. Price A03PDF Image | NASA Low-Speed Centrifugal Compressor for 3-D Viscous Code
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