An investigation was conducted to determine some of the basic problems and effects involved in a change of solidity accomplished by a change in the number of blades in an axial-flow-compressor rotor row and, in a complete stage.nA complete stage designed to obtain a high total-pressure ratio by combining high blade loading and high relative inlet Mach number was installed in a 14-inc'h-tip-diameter compressor with a hub-tip diameter ratio of 0.8 at the rotor leading edge. The stage was designed using 44 rotor blades (solidity of 1.50 at mean radius) and 46 stator blades (solidity = 1.56 at mean radius). Performance of rotors containing 44, 30, and 22 of the original rotor blades (mean radius solidities of 1.50, 1.02, and 0.75, respectively) was determined with no stator blades installed, and performance of the stage with half of the rotor and stator blades removed was obtained for comparison with previously reported results of an investigation of the complete high-solidity stage.
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