Author(s)

V. A. Sedunin, O. V. Komarov, V. L. Blinov, A. V. Skorokhodov & A. O. Procopets

Abstract

This paper contains on-site test data of an axial compressor as part of an industrial gas turbine, as well as the process of Computational Fluid Dynamics (CFD) modelling, verification, research and modernization. The research method has been verified with actual test data gathered from the real gas turbine unit (GTU) test. The computational studies showed significant potential for improving aerodynamic efficiency and the surge margin of a compressor by better matching of inlet and outer groups of stages. A special design approach was used to improve aerodynamic parameters of the inlet system and certain middle stages. Computations made for the improved compressor model showed a 3% efficiency gain and 5% stall margin gain with possibilities for further modernization. Keywords: axial compressor of gas turbine, CFD computations, profiling of compressor blades, verification of computational model.

Keywords

axial compressor of gas turbine, CFD computations, profiling of compressor blades, verification of computational model.