Uncertainty Analysis of Compressor Stability Margin Under Inlet Guide Vane Angular Adjustment Error

During aeroengine operation, the inlet guide vane (IGV) angle of compressors undergoes active adjustment to enhance off-design performance and extend stable operating ranges. However, practical measurement reveals that mechanical actuation limitations induce deviations between actual IGV angles and the ideal setpoints. In this paper, experiment and numerical simulation were carried out to elucidate the mechanism of stall in a compressor with IGV, demonstrating that the instability originates from the passage blockage caused by tip clearance leakage vortex breakdown. Furthermore, the non-intrusive polynomial chaos methodology was used to quantify uncertainty impacts of IGV angular adjustment errors (within 1°) on compressor aerodynamic stability. The key findings indicate: the probability distribution of stability margin variations (ΔSM) is similar to that of the IGV angular adjustment errors, and the control strategies favoring larger positive pre-swirl angles can enhance the stability (maximum 1% ΔSM improvement) but with a lower precision angle adjustment.