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Transonic Flow Losses of Two Steam Turbine Blades at Large Incidences

[+] Author Affiliations
S.-M. Li, T.-L. Chu, Y.-S. Yoo, W. F. Ng

Virginia Polytechnic Institute and State University, Blacksburg, VA

Paper No. GT2002-30334, pp. 89-98; 10 pages
doi:10.1115/GT2002-30334
From:
  • ASME Turbo Expo 2002: Power for Land, Sea, and Air
  • Volume 5: Turbo Expo 2002, Parts A and B
  • Amsterdam, The Netherlands, June 3–6, 2002
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-3610-X | eISBN: 0-7918-3601-0
  • Copyright © 2002 by ASME

abstract

A linear cascade experiment has been conducted to investigate transonic flow losses of two nozzle blade profiles for high-pressure steam turbines. Experimental incidences were changed from −34° to 35°, while exit Mach numbers were varied from 0.60 to 1.15. Reynolds numbers were tested between 7.4×105 and 1.6×106 . Flow visualization techniques, such as shadowgraph, Schlieren, and surface color oil were used to document the flow. Measurements were made using downstream traverses with Pitot probe, upstream total pressure probe, and sidewall static pressure taps. Losses were found to be rather constant at subsonic flows. At transonic and low supersonic flows, the loss increased steeply, as high as 700% more when compared with the loss level at subsonic flows. For all the tested Mach numbers, the maximum relative increase of loss level was only about 100% due to the very large variation of incidences. Thus the effect of Mach numbers on losses is much greater than that of the very large incidences for the transonic and low supersonic flows. A frequently used shock wave loss correlation was found not suitable to predict the losses of the tested blades. Using the current experimental data, a modified loss correlation to account for the shock wave effects has been proposed for the transonic and low supersonic flows. Comparison was made between the modified loss correlation and the data of three other turbine cascades in the literature. Large improvement was obtained with the modified loss correlation as compared with the existing correlation.

Copyright © 2002 by ASME

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