High spatial resolution upstream forced response in a transonic compressor

The acquisition of inlet guide vanes (IGV) unsteady surface pressure measurements at six spanwise locations, five chordwise locations, three axial spacings and three compressor operating points were discussed at 100% design speed. A significant effect was shown on the surface pressure response caused by changes in the compressor operating point and the axial row. Changes in the IGV/rotor row axial spacing from 12 to 26% of the IGV chord resulted in a nearly 50% reduction in the magnitude of the response at midspan. The results show that the pressure response is less sensitive to the parametric changes controlled at 5% span.