Accession Number : AD0757250

Title :   Experimental Determination of Turning Angle and Losses of Axial Compressor Inlet Guide Vanes.

Descriptive Note : Master's thesis,

Corporate Author : NAVAL POSTGRADUATE SCHOOL MONTEREY CALIF

Personal Author(s) : Wheeler,William Richard

Report Date : DEC 1972

Pagination or Media Count : 47

Abstract : 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)

Descriptors :   (*CASCADE STRUCTURES, EFFICIENCY), (*AXIAL FLOW COMPRESSORS, INLET GUIDE VANES), FLOW FIELDS, GAS TURBINES, AXIAL FLOW COMPRESSOR BLADES, BOUNDARY LAYER CONTROL, WAKE, CAMBER, MATHEMATICAL MODELS, THESES

Subject Categories : Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE