Numerical Simulation of Stall and Stall Control in Axial and Radial Compressors

Abstract

Abstract : The performance of gas turbine engines is limited by compressor stall, and further exacerbated by combat conditions. Stall control technologies developed at the Army Research Laboratory (ARL) Vehicle Technology Directorate (VTD) and NASA Glenn Research Center (GRC) have demonstrated the effectiveness of steady tip injection to increase the stable operating range of high-speed axial and centrifugal compressors. A major element lacking in the development of the stall control technology is a tundamental understanding of the fluid mechanic processes of stall inception, and how stall is mitigated by the stall control technology to achieve increased compressor stall range. Such understanding is essential for providing improved design guidance in implementing stall control technology in engines. As such, in parallel with the engine demonstrator tests we are generating time-accurate, full-annulus, three-dimensional Navier-Stokes code simulations of single-stage axial and centrifugal compressors for which detailed experimental data are available, both with and without stall control technology. This paper presents results of the TURBO simulations, which show predicted range extension with stall control technology compared to measurements, and characteristics of the compressor flow field with and without stall control technology.