Experimental Determination of Turning Angle and Losses of Axial Compressor Inlet Guide Vanes.
NAVAL POSTGRADUATE SCHOOL MONTEREY CALIF
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The investigation experimentally determined the minimum loss incidence angle, deviation angle, and total-pressure loss coefficient for a cascade with airfoil-type blade profiles used as inlet guide vanes for an axial-flow compressor with an equivalent camber angle of 37.6 degrees and unit solidity. The experimental values were compared with values predicted using correlations based on compressor cascade tests. Author
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