Numerical Simulation And Flow Field Analysis Of Transonic Axial Compressor

As one of the key components of gas turbine,the performance of compressor has great influence on the whole gas turbine system.The performance of the compressor is affected by unstable flow such as surge and rotation stall.Surge not only restricts the performance,but also dose harm for the safety of the compressor seriously.Transonic compressor has a high-pressure ratio,and its flow field is more complex.Due to the shock wave,tip leakage flow will interact with it,and the leakage vortex is broken at the near stall.These phenomenons have a great impact on the rotating stall.Therefore,it is very important to simulate the internal flow field of transonic compressor.In this paper,numerical simulation of the NASA Stage 35 is carried out,using CFX software to simulate it in three kinds of conditions,drawing the characteristic curve of the compressor.The distribution law of total pressure ratio,total temperature ratio,efficiency and airflow angle at the outlet of the compressor is studied and compared with the experimental data.The mach number,static pressure and air flow angles of the compressor were analyzed under the three typical working conditions(design condition,stall condition,choked condition).Besides,the unsteady calculation of the compressor was carried out at 100%speed.The calculation results are plotted as the characteristic curves of flow rate,pressure ratio,temperature ratio and efficiency,and compared with the steady state calculation results and experimental values.The static pressure distribution of the surface of the moving blade was analyzed by analyzing the static pressure distribution of the surface pressure of 158000Pa,156000Pa and 150000Pa,respectively.By analyzing the distribution of relative pressure at 95%Flow and dynamic pressure of the top of the leakage stream,the leakage of the top of the vortex and the development of the situation were studied to explore the leakage vortex with the time of the law.