Calculating method for multi-stage axial compressors with impulse bladings and constant tip diameter

摘要

This report gives an approximate calculating method for the design pointperformance of multi-stage axial compressors with impulse-type bladings and constanttip diameters. Computing programs for Monroe-1880 programmable calculatorsare presented to establish the compressor performance and the bladingparameters for arbitrary conditions with minimum effort. The report was prepared to permit evaluations of the applicability of suecompressors in advanced propulsion units for air-superiority aircraft, or in light-weight lift engines for military VTOL aircraft.