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Volume 1: Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery
The effects of stepped tip gaps and clearance levels on the performance of a transonic axial-flow compressor rotor were experimentally determined. A two-stage compressor with no inlet guide vanes was tested in a modem transonic compressor research facility. The first-stage rotor was unswept and was tested for an optimum tip clearance with variations in stepped gaps machined into the casing near the aft tip region of the rotor. Nine casing geometries were investigated consisting of three stepdoi:10.1115/97-gt-007 fatcat:4bntapg4brg3jfebyslta7hdv4