The Study Of Modification Design Method On Gas Turbine Compressor

In this paper, the modification design on gas turbine compressor had been studied. The design method was based on the similarity theory and some parameters, which played very important roles in the compressor modification design. A code was developed in this paper, which was focused on one-dimensional middle-section(1D) calculation and S2 stream surface(S2) through-flow analysis. By means of this code, the performance of modelling compressor was researched in comparison with the results obtained from three-dimensional numerical simulation. Furthermore, a new kind of transonic blade was designed and applied to the modified compressor. Based on the calculation results, the new compressor design was proved to meet the aerodynamic design requirements well. Besides, the flow field of transonic stage was studied further to observe the performance of the self-developed transonic blade.