Accession Number : AD0752585

Title :   The Low Hub-Tip Ratio Supersonic Axial-Flow Compressor. Volume I.

Descriptive Note : Final rept. 1 Jul 71-30 Jun 72,

Corporate Author : VON KARMAN INST FOR FLUID DYNAMICS RHODE-SAINT-GENESE (BELGIUM)

Personal Author(s) : Breugelmans,Frans A. E.

Report Date : JUN 1972

Pagination or Media Count : 51

Abstract : The report describes the test results of a supersonic axial flow compressor stage with a tip Mach number of 2.0. Volume I discusses especially the inlet stall, the associated flow field and the stage performance. Methods are proposed to eliminate the stall problem. (Author)

Descriptors :   (*AXIAL FLOW COMPRESSORS, STALLING), COMPRESSOR ROTORS, COMPRESSOR STATORS, SUPERSONIC FLOW, FLOW FIELDS, CASCADE STRUCTURES, PRESSURE, PERFORMANCE(ENGINEERING)

Subject Categories : Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE