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Results of an Advanced Fan Stage Operating Over a Wide Range of Speed and Bypass Ratio: Part I—Fan Stage Design and Experimental Results

[+] Author Affiliations
Kenneth L. Suder, Scott A. Thorp

NASA Glenn Research Center, Cleveland, OH

Patricia S. Prahst

AP Solutions, Inc., Cleveland, OH

Paper No. GT2010-22825, pp. 329-342; 14 pages
doi:10.1115/GT2010-22825
From:
  • 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

abstract

NASA’s Fundamental Aeronautics Program is investigating turbine-based combined cycle (TBCC) propulsion systems for access to space because it provides the potential for aircraft-like, space-launch operations that may significantly reduce launch costs and improve safety. To this end, NASA and GE teamed to design a Mach 4 variable cycle turbofan/ramjet engine for access to space. To enable the wide operating range of a Mach 4+ variable cycle turbofan ramjet required the development of a unique fan stage design capable of multipoint operation to accommodate variations in bypass ratio (10X), fan speed (7X), inlet mass flow (3.5X), inlet pressure (8X), and inlet temperature (3X). In this paper, NASA has set out to characterize a TBCC engine fan stage aerodynamic performance and stability limits over a wide operating range including power-on and hypersonic-unique windmill operation. Herein, we will present the fan stage design, and the experimental test results of the fan stage operating from 15% to 100% corrected design speed. Whereas, in the companion paper [1], we will provide an assessment of NASA’s APNASA code’s ability to predict the fan stage performance & operability over a wide range of speed and bypass ratio.

Copyright © 2010 by ASME
Topics: Design

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