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Performance Characteristics of an Axial-flow Transonic Compressor Operating up to Tip Relative Inlet Mach Number of 1.34

John W. R. Creagh

Abstract

Performance data are presented for a transonic axial-flow compressor rotor designed to operate at a tip speed of 1300 ft/sec with maximum relative tip Mach number of 1.37. The compressor had an inlet diameter of 16 inches, a hub-tip diameter ratio of 0.5 and design specific weight flow of 31.1 (lb/sec/(sq ft frontal area). Experimental values of relative total-pressure-loss coefficient were considerably higher than the assumed values. This disparity, hub choking, and application of the simple radial-equilibrium concept are discussed. The data of this report are used to extend previously presented correlation plots of compressor design parameters to higher Mach numbers.

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Key concepts: Mach number, Transonic, Gas compressor, Axial compressor, Inlet, Mechanics, Overall pressure ratio, Rotor (electric)