Experiments have been performed in a supersonic cascade facility to elucidate the fluid dynamic phenomena and loss mechanism of a strong shock-wave turbulent boundary layer interaction in a compressor cascade. The cascade geometry is typical for a transonic fan tip section that operates with a relative inlet Mach number of 1.5, a flow turning of about 3 deg, and a static pressure ratio of 2.15. The strong oblique and partly normal blade passage shock-wave with a preshock Mach number level of 1.42 to 1.52 induces a turbulent boundary layer separation on the blade suction surface. The free-stream Reynolds number based on chord length was about 2.7 × 106. Cascade overall performance, blade surface pressure distributions, Schlieren photographs, and surface visualizations are presented. Detailed Mach number and flow direction profiles of the interaction region (lambda shock) and the corresponding boundary layer have been determined using a Laser-2-Focus anemometer. The obtained results indicated that the axial blade passage stream sheet contraction (axial velocity density ratio) has a significant influence on the mechanism of strong interaction and the resulting total pressure losses.
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July 1992
Research Papers
An Investigation of a Strong Shock-Wave Turbulent Boundary Layer Interaction in a Supersonic Compressor Cascade
H. A. Schreiber,
H. A. Schreiber
Deutsche Forschungsanstalt fu¨r Luft- und Raumfahrt e. V., Institut fu¨r Antriebstechnik, 5000 Ko¨ln 90, Federal Republic of Germany
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H. Starken
H. Starken
Deutsche Forschungsanstalt fu¨r Luft- und Raumfahrt e. V., Institut fu¨r Antriebstechnik, 5000 Ko¨ln 90, Federal Republic of Germany
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H. A. Schreiber
Deutsche Forschungsanstalt fu¨r Luft- und Raumfahrt e. V., Institut fu¨r Antriebstechnik, 5000 Ko¨ln 90, Federal Republic of Germany
H. Starken
Deutsche Forschungsanstalt fu¨r Luft- und Raumfahrt e. V., Institut fu¨r Antriebstechnik, 5000 Ko¨ln 90, Federal Republic of Germany
J. Turbomach. Jul 1992, 114(3): 494-503 (10 pages)
Published Online: July 1, 1992
Article history
Received:
February 19, 1991
Online:
June 9, 2008
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Schreiber, H. A., and Starken, H. (July 1, 1992). "An Investigation of a Strong Shock-Wave Turbulent Boundary Layer Interaction in a Supersonic Compressor Cascade." ASME. J. Turbomach. July 1992; 114(3): 494–503. https://doi.org/10.1115/1.2929170
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