Calculating Method for Multi-Stage Axial Compressors with Impulse Bladings and Constant Tip Diameter.

摘要

The report gives an approximate calculating method for the design point performance of multi-stage axial compressors with impulse-type bladings and constant tip diameters. Computing programs for Monroe-1180programmable calculators are presented to establish the compressor performance and the blading parameters for arbitrary conditions with minimum effort. The report was prepared to permit evaluations of the applicability of such compressors in advanced propulsion units for air-superiority aircraft,or in light-weight lift engines for military VTOL aircraft. (Author)