Accession Number : AD0856225

Title :   Propulsion System Flow Stability Program (Dynamic). Part XIII. Numerical Definition of Engine Face Distortion.

Descriptive Note : Final technical rept. on Phase 1,

Corporate Author : NORTH AMERICAN ROCKWELL CORP LOS ANGELES CA LOS ANGELES DIV

Personal Author(s) : Martin, Arnold W.

Report Date : DEC 1968

Pagination or Media Count : 35

Abstract : Those steady-state and dynamic distortion factors which, through test or analysis, have been found to reduce compressor surge margin have been listed; and the probable mechanisms by which they influence the compressor have been discussed. A multi-termed format has been derived for a numerical definition of distortion. Its definition and use are described. Recommendations for further analytic and experimental investigations into the mechanisms of compressor surge are presented. (Author)

Descriptors :   (*TURBOJET ENGINES, AXIAL FLOW COMPRESSORS), (*AXIAL FLOW COMPRESSORS, STALLING), DISTORTION, TURBULENCE, OSCILLATION, ACOUSTICS, TURBOJET INLETS, TURBULENT BOUNDARY LAYER, INTERACTIONS, RESPONSE.

Subject Categories : Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE