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Results of an Advanced Fan Stage Over a Wide Operating Range of Speed and Bypass Ratio: Part II—Comparison of CFD and Experimental Results

[+] Author Affiliations
Mark L. Celestina, Kenneth L. Suder

NASA Glenn Research Center, Cleveland, OH

Sameer Kulkarni

Case Western Reserve University, Cleveland, OH

Paper No. GT2010-23386, pp. 465-475; 11 pages
  • ASME Turbo Expo 2010: Power for Land, Sea, and Air
  • Volume 7: Turbomachinery, Parts A, B, and C
  • Glasgow, UK, June 14–18, 2010
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4402-1 | eISBN: 978-0-7918-3872-3
  • Copyright © 2010 by ASME


NASA and GE teamed to design and build a 57% engine scaled fan stage for a Mach 4 variable cycle turbofan/ramjet engine for access to space with multipoint operations. This fan stage was tested in NASA’s transonic compressor facility. The objectives of this test were to assess the aerodynamic and aero mechanic performance and operability characteristics of the fan stage over the entire range of engine operation including: 1) sea level static take-off; 2) transition over large swings in fan bypass ratio; 3) transition from turbofan to ramjet; and 4) fan wind-milling operation at high Mach flight conditions. This paper will focus on an assessment of APNASA, a multistage turbomachinery analysis code developed by NASA, to predict the fan stage performance and operability over a wide range of speeds (37% to 100%) and bypass ratios.

Copyright © 2010 by ASME



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