At the Institute of Aeronautics and Astronautics of the Technical University of Berlin, a linear stator cascade test facility for active flow control investigations has been developed and tested at high speed flow conditions. The compressor blades were designed as critically loaded controlled diffusion airfoils (CDA) for an upstream Mach number of M = 0.75 and a Reynolds number of Re = 1.1 ? 10~6 based on the axial chord. An analysis of the baseline cascade flow reveals complex three-dimensional secondary flow phenomena. The paper will show how these can be supressed by active flow control (AFC) methods to receive a higher stage pressure ratio or a lower total pressure loss respectively and where limits can be found. For this purpose, actuators for steady and pulsed blowing through a side wall slit have been developed. A detailed investigation of the base flow and first tests of the actuation method in the cascade test rig have been carried out to investigate the effect of AFC.
展开▼
