EXPERIMENTAL INVESTIGATION OF AN IMPULSE-TYPE SUPERSONIC COMPRESSOR ROTOR HAVING A TURNING OF 73° AT THE MEAN RADIUS

摘要

A l6-Inch-diameter supersonic impulse rotor with guide vanes was designed and tested in Freon-12. The rotor had inlet and exit hub-tip radius ratios of O.575 and O.75, respectively. The blade-passage design was based on the two-dimensional vortex-flow theory modified to account partially for the three-dimensional compressions.