Inlet Guide Vane Stagger Effects on Multistage Compressor Performance and Stall Inception

The effects of variable inlet guide vanes on compressors have been evaluated throughout the turbomachinery industry for decades. These vanes improve both the performance and stability of a machine-the extent to which is highly dependent on the individual machine and the conditions of operation. Evaluating their effects on compressor stall inception via experimental investigations can inform model development and validation since commonly used RANS and URANS tools face limitations in accurately predicting and modeling stall events. The current literature on variable inlet guide vane restaggering, however, is dominated by numerical investigations. This study offers a unique experimental investigation into restaggering effects on compressor stall behavior by evaluating experimental results from different variable inlet guide vane stagger angles in a high-pressure axial compressor. Previous investigations have shown that variable inlet guide vane restaggering may change the stall inception mechanism of axial flow compressors. This investigation found a distinct change in the stage matching of the machine without altering the stall inception mechanism, further demonstrating the need for experimental investigations to inform the specific effects that restaggering inlet guide vanes offers comparable compressors.