Abstract
The performances of a shockless-in-rotor supersonic axial flow compressor are discussed on the basis of one dimensional flow analysis. Some characteristics are derived as follows in comparison with an ordinary shock-in-rotor supersonic axial flow compressor having the same inlet Mach number. 1) Normal shock loss can be avoidable in the entire passage including both rotor and stator. 2) The exit flow from rotor is turned in the opposite direction to the rotational one of rotor. 3) The absolute total pressure ratio per stage is small. 4) The starting problem is relieved. 5) The supersonic multistages may be easily put into practical use.
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