Accession Number : ADA185712

Title :   Post Stall Behavior in Axial-Flow Compressors.

Descriptive Note : Final rept. Mar 83-Jan 87,

Corporate Author : VIRGINIA POLYTECHNIC INST AND STATE UNIV BLACKSBURG CENTER FOR TURBOMACHINERY AND PROPULSION RESEARCH

Personal Author(s) : O'Brien, Walter F

PDF Url : ADA185712

Report Date : 20 Aug 1987

Pagination or Media Count : 67

Abstract : A multi-element research program was conducted to improve understanding of the role of cascade losses in compressor post-stall behavior. Experiments in a special wind tunnel designed for high-angle-of-attack investigations included surface and smoke flow visualizations and hot film anemometer velocity measurements. Results showed the details of the stall development in a cascade, and the effect of stagger on measured flow losses. Predictions of a Navier-Stokes model for separated cascade flows were compared with experimental results. An improved compressor stage model predicts post-stall characteristics, and illustrates the application of the results to compression system analysis. Keywords: Cascades (Fluid dynamics); Flow measurements; Stalling behavior; Propagating stalls.

Descriptors :   *AXIAL FLOW COMPRESSORS, *CASCADES(FLUID DYNAMICS), *STALLING, ANGLE OF ATTACK, CASCADE STRUCTURES, COMPRESSION, COMPRESSORS, FLOW, FLOW SEPARATION, FLOW VISUALIZATION, FLUID DYNAMICS, LOSSES, MEASUREMENT, MODELS, NAVIER STOKES EQUATIONS, SMOKE, SYSTEMS ANALYSIS, WIND TUNNELS, GAS TURBINES, JET ENGINES, MATHEMATICAL PREDICTION, PROPAGATION

Subject Categories : Fluid Mechanics
      Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE