Effects of Blade Number on the Efficiency of Centrifugal Compressor Impellers

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<jats:p>The results of a study directed towards identifying optimum blade numbers for aviation and turbocharger type centrifugal compressor impellers is presented. The study focused upon a simplified one dimensional frictional model supported by impeller test data over a wide specific speed range, plus limited correlation with computational fluid dynamic models.</jats:p> <jats:p>The study results indicated that optimum blade numbers were a function of specific speed, blade backsweep angle, and DeLaval number. With a backsweep angle of 45 degrees and DeLaval number of unity the optimum blade numbers were ≈ 30 and ≈ 15 at low and high specific speeds respectively. It was shown that efficiency decreased with low blade number primarily due to low momentum exchange i.e., low slip factor.</jats:p> <jats:p>In order to condense the analysis only the impeller component of the compressor stage was studied, wherein the geometry and operating conditions were characterized in terms of five parameters, with particular emphasis on specific speed.</jats:p>

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