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The Influence of Blade Negative Curving on the Endwall and Blade Surface Flows FREE

[+] Author Affiliations
Zhongqi Wang, Wanjin Han

Harbin Institute of Technology, Harbin, China

Paper No. 95-GT-441, pp. V001T01A106; 7 pages
doi:10.1115/95-GT-441
From:
  • ASME 1995 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Houston, Texas, USA, June 5–8, 1995
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7878-1
  • Copyright © 1995 by ASME

abstract

In order to explore the mechanism reducing the energy losses by use of negative curved blades, an experiment was carried out on turbine rectangular cascades with straight and negative curved blades of high turning angle and low aspect ratio. Ink trace technology was employed to show the flows on the endwalls and blade surfaces. The pressures were measured in detail with static pressure taps on the endwalls and blade surfaces. Experimental results indicate that when negative curved blades are used, a separating saddle of inlet boundary layers goes forward into the passage and approaches the pressure surface, as the streamwise adverse pressure gradient on the cascade inlet endwall becomes lower, compared with that of straight blade cascade. In addition, the static pressure contours are almost parallel lines perpendicular to the endwall on the front part of the suction surface and the curves which internal normals with the positive slopes near the endwall direct to the midspan from high pressure to lower pressure on the middle, this leads to the separation of free vortex sheet pattern on the suction surface. As a result, it is delayed that the separation lines converge towards midspan.

Copyright © 1995 by ASME
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