Numerical simulation analysis of the tip-cutting method in a compressor of a heavy duty gas turbine

To fulfill the demands of one compressor redesign, the method of tip-cutting based on correcting location was proposed and deduced, which was named equal stream tube. Using this method, the redesign of inlet guide vane and the first two stages including five rows of cascade was carried out. Three dimensional numerical simulation was performed to verify the method feasibility. Furthermore the influence on the redesign compressor caused by tip-cutting was analyzed. The results indicate that this method can ensure quick and accurate tip-cutting according to various value of mass flow. The redesigned compressor can satisfy the mass flow requirement and keep the same pressure ratio as well as high aerodynamic performance, without any optimization. This method will not cause serious flow mismatch problem.