Research on the adjustment mechanism of inlet guide vanes in axial compressors

To further elucidate the adjustment mechanism of inlet guide vanes in axial compressors of aero-engines, this paper investigates a 1.5-stage high-load compressor using numerical simulation methods. This study comprehensively examines the influence law of various setting angles of in-let guide vanes at different corrected speeds on compressor performance. The results indicate that positive pre-swirl adjustment of the inlet guide vane significantly extends the stable operating range of the compressor while improving pressure ratio and efficiency. By analyzing the pressure ratio, efficiency, and stability margin under different pre-swirl angles, an efficiency-optimized adjustment strategy was developed. This strategy enhances the stability margin of the compressor by 5.31%, 6.33%, and 3.84% at 85%, 75%, and 65% corrected speeds, respectively, demonstrating notable improvement. These findings provide a theoretical basis for optimizing inlet guide vane adjustment strategies in axial compressors.