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Experimental Investigation of the Effects of a Moving Shock Wave on Compressor Stator Flow

[+] Author Affiliations
Matthew D. Langford, Stephen A. Guillot

Techsburg, Inc., Blacksburg, VA

Andrew Breeze-Stringfellow, William Solomon

GE Aircraft Engines, Cincinnati, OH

Wing F. Ng

Virginia Polytechnic Institute and State University, Blacksburg, VA

Jordi Estevadeordal

Innovative Scientific Solutions, Inc., Dayton, OH

Paper No. GT2005-68722, pp. 1383-1395; 13 pages
doi:10.1115/GT2005-68722
From:
  • ASME Turbo Expo 2005: Power for Land, Sea, and Air
  • Volume 6: Turbo Expo 2005, Parts A and B
  • Reno, Nevada, USA, June 6–9, 2005
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-4730-6 | eISBN: 0-7918-3754-8
  • Copyright © 2005 by ASME

abstract

Linear cascade testing was performed to simulate the flow conditions experienced by stator blades in an axial compressor with supersonic relative Mach numbers at the inlet to the downstream embedded rotors. Experiments were conducted in a transonic blow-down wind tunnel with a nominal inlet Mach number of 0.65. A single moving normal shock introduced at the exit of the stator cascade simulated the bow shock from a downstream rotor. The shock was generated using a shock tube external to the wind tunnel. Pressure measurements indicated that the stator matched its design intent loading, turning and loss under steady flow conditions. Effects of the passing shock on the stator flow-field were investigated using shadowgraph photography and Digital Particle Image Velocimetry (DPIV). Measurements were taken with three different shock strengths. In each case, the passing shock induced a vortex around the trailing edge of the stator. The size and strength of these vortices were directly related to the shock strength. A suction side separation on the trailing edge of the stator was observed and found to correlate with the vortex blockage.

Copyright © 2005 by ASME

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