The Experimental Research on a New Method for Extending the Axial-Compressor's Stall Margin

Firstly, investigating the influences of unsteady disturbance on compressor's aerodynamic stability by exterior excitation, and then exploring the new method's outlook for engineering application by utilizing the unsteady wake impact cooperative effect in adjacent blades of compressor. Furtherly, the model experiment proved that the goal which increasing the compressor's aerodynamic performance and aerodynamic stability can be realized by optimizing the unsteady aerodynamic circumference configuration technique in compressor. The experiment results indicated that the stall margin can be increased greatly when excitation amplitude exceeded the threshold value and excitation frequency cooperated with the typical vortex shedding frequency, the stall margin can be increased 22.1 % relatively. On the other hand, the cooperative effects of WIE (Wake Impact Effect, WIE) at different correct rotating speed were investigated in detail.