A General Theory of Flow-Instability Inception in Turbomachinery

摘要: A general eigenvalue theory on flow stability in turbomachinery is proposed with the emphasis flow-instability onset. Based this theory, a stall-inception model including effects of complex solid geometry developed for multistage fan/compressors system. The capacity present to predict point assessed against experimental data both low-speed and transonic single rotor. Comparisons simplified two-dimensional are performed identify nonnegligible spanwise distribution flowfield configuration unstable mode concerned fan/compressors. It verified that capable predicting mass at stall-onset subsonic reasonable accuracy, it sustainable terms computation cost industrial application.