Theoretical effect of inlet hub-tip-radius ratio and design specific mass flow on design performance of axial-flow compressors

Report presenting an analysis of the effect at design condition of inlet hub-tip-radius ratio and mass flow per unit frontal area on the allowable rotor-tip speed, pressure ratio, and power input per unit frontal area of multistage axial-flow compressors with approximately symmetrical velocity diagrams at all radii, constant total enthalpy along the radius, a maximum Mach number of 0.8 for all stages, and a prescribed empirical turning limitation. The analysis indicated that for any given hub-tip-radius ratio, the design rotor speed and pressure ratio per stage decrease with increasing design mass flow per unit frontal area.