Accession Number : AD0767265

Title :   Off-Design Behavior for Axial Flow Compressor Stages with Invariable and Variable Geometry Blades,

Corporate Author : CINCINNATI UNIV OHIO DEPT OF AEROSPACE ENGINEERING

Personal Author(s) : Grahl,K. ; Tabakoff,W.

Report Date : SEP 1973

Pagination or Media Count : 67

Abstract : An application of a computer program is described for studying the off-design performance for single and multistage axial flow compressors. The calculation method allows one to determine the stage characteristics as a function of revolutions. This can be accomplished in a very short time with only a few geometrical and aerodynamical input data. The flow is described by the well-known streamline curvature method. The necessity of a good loss model is shown. Limitations of this method are described. Some computation examples for the first and fifth stages of a ten-stage NASA axial flow compressor are presented. The stage and overall characteristics for different compressors are considered for invariable and variable blade geometry. The off-design analytical results are compared with existing experimental results. (Author)

Descriptors :   (*AXIAL FLOW COMPRESSORS, AERODYNAMICS), CASCADE STRUCTURES, JET ENGINES, STABILITY, PERFORMANCE(ENGINEERING), OPTIMIZATION, GUIDE VANES, MATHEMATICAL MODELS

Subject Categories : Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE