Accession Number : AD0778808
Title : Calculating Method for Multi-Stage Axial Compressors with Impulse Bladings and Constant Tip Diameter.
Descriptive Note : Interim rept. Jul 73-Jun 74,
Corporate Author : NAVAL POSTGRADUATE SCHOOL MONTEREY CALIF
Personal Author(s) : Vavra,M. H.
Report Date : MAR 1974
Pagination or Media Count : 73
Abstract : 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-1180 programmable 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)
Descriptors : *Jet engines, *Axial flow compressors, Axial flow compressor blades, Axial flow, Entropy, Mathematical models, Computer programming, Control sequences
Subject Categories : Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE