Art analysis was made 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 employing approxi¬mately 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 covers inlet hub-tip-radius ratios of 0.6, 0.5, and 0.4, the prac¬tical range of design specific mass flows for each, and the number of stages sufficient to give an exit hub-tip ratio of approximately 0.9.
展开▼
