Analysis of basic design variables on the performance of an axial-flow compressor has indicated that the use of a design incorporating constant total enthalpy with symmetrical velocity diagram at all radii has several advantages over the more common vortex-flow-type compressor .A An investigation of a typical inlet stage of a multistage axial-flow compressor that was designed on this basis was therefore conducted. The stage, consisting of 19 rotor blades and 20 stator blades with 40 inlet guide vanes, had a hub-to-tip-radius ratio at the rotor inlet of 0.50 and a rotor-blade outside diameter of 14 inches. The ratio of the axial velocity component to the tip speed was set at 0.60 at the rotor-inlet hub. The rotor and stator blades were of constant cross section from hub to tip and had a modified NACA 65-(l2)l0 profile.nRotor-blade performance is presented as plots of angle of attack against turning angle and radial distribution of energy addition. The turning angles and, consequently, the energy addition were low compared with design values at design weight flow. This deviation was attributed largely to the fact that too little allowance was made for the decrease in turning angle due to the low solidities and high stagger angles encountered near the rotor-blade tip.
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