Aerodynamics of Advanced Axial-Flow Turbomachinery

摘要

A multi-task research program on the aerodynamics of advanced axial-flow turbomachinery was completed at Iowa State University. Program components were intended to result in direct contributions to the improvement of axial-flow fan, compressor, and turbine design procedures. A detailed experimental investigation of intrapassage flow in a large-scale, curved, rectangular cross-section channel representative of turbomachinery passages was carried out. The use of stator geometry modification to improve stage performance through better secondary flow control was investigated via laboratory tests of baseline and modified version of a two-stage compressor. Aerodynamic variables which influence surface boundary layer development in compressor and turbine airfoil cascades were restudied in order to determine sources of differences between linear cascade performance and performance of equivalent cascade geometries in multistage turbomachine blade rows.