Stall Margin Improvement in an Axial Compressor by Continuous and Pulsed Tip Injection

Stall and surge are strong limitations in the operating range of compressors thus one major limits jet engine performance. A promising way to push stability limit compression machines is inject a small amount flow at blade tip alter physical mechanism responsible for stall onset. This study focuses on experimental performance such system. To do so, an axial compressor test bench was equipped with 40 actuators connected auxiliary pressurised air supply They were able generate high-speed blowing just rotor blades. The opening each actuator controlled by electromagnetic valve. allowed generating continuous or pulsed jets frequencies up 500 Hz different duty cycles. control system investigated various strategies, where injected rate, injection angle, number injectors, frequency cycle systematically varied. paper concluded energy balance configurations. best authors’ knowledge, this constitutes rarely seen analysis literature.