STABILITY ENHANCEMENT IN HIGH STAGE LOADING AXIAL COMPRESSOR OF GAS TURBINE ENGINES
he endwall regions has a major effect on the performance of all multistage axial compressor giving most on the losses and being involved in initiation of flow instability and stall. A new method of blade design has been developed that proved to be highly effective in suppression the flow separation in the corner regions between suction surfaces and end-wall and reducing unsteadiness caused by the passage of blades past one another. The paper presents some results of tests of multistage axial compressors having low aspect ratio blades with double curvature profiles. The new profile design gives lower noise along with improved aerodynamic and mechanical performances.