Performance Prediction Of The Similar Design Axial Flow Compressor

With the development of gas turbine, as the core components of gas turbine,performance of compressors also needs to be constantly improved. High-performance compressors need to be developed. Based on the similarity principle, the compressor modeling design can not only get new design aerodynamic performance of compressor safely, but also reduce the amount of work and save lots of scientific research funds. It is a promising design method. In order to attain the goal of driving the new compressor under the low power of operation in the laboratory, similar principle is applied in this article to design the axial flow compressor. This paper addressed the following aspects:1. According to the existing parameters, 3D Pro-e model of the six and half stage compressor is established. The coordinate points of hub and shroud at different sections are got from its 3D Pro-e model. And the geomturbo file of the six and half stage, the three and half stage before and after modeling which can be identified by NUMECA are written.2. The six and a half stage original compressor is simulated by NUMECA software.Simulation results and design are compared in order to validate whether the geometric model can meet the requirements of design, grid and calculation method. Another simulation is conducted on the three and a half stage compressor. Brief analysis of its internal flow field is shown.3. The modeling design of three and a half stage compressor is based on similarity theory. Its numerical simulation is carried out and flow field is analyzed under the design and off-design condition respectively. Compressor working characteristic curve is also drawn.Influence of tip clearance on the compressor’s performance and the internal flow field is stated.4. In order to improve aerodynamic performance of the blade row, it was optimized with stacking line, the combination of stacking line and blade shape, which are following the objective of max efficiency. The changes of 3D blade shape, blade surface pressure and relative Mach number of different height are shown respectively.