Investigation of the aerodynamic performance of a transonic inlet stage of an axial flow compressor
説明
The features of a supercritical airfoil, designed as the stator blade of an axial flow compressor for gas turbines, are described and results of an experimental investigation of the airfoil are presented. The supercritical airfoil is designed to replace the stator blade of the NACA-65 airfoil in a transonic single-stage compressor. Comparison of the performance of both blades shows that the supercritical airfoil blade reduces pressure losses. In order to confirm the effects of the eliminated shock waves on the supercritical blade surfaces, two-dimensional cascade experiments are carried out in a high speed cascade wind tunnel. The velocity distributions along the blade surface, the pressure loss and the boundary layer behavior are described. Then, the twodimensional cascade of the supercritical airfoil is redesigned, in light of these findings, to enlarge the positive incidence characteristics and reduce pressure losses. The experimental results obtained with this redesigned cascade show the design targets are achieved.
収録刊行物
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- 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
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34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 1998-07-13
American Institute of Aeronautics and Astronautics (AIAA)