基于多目标遗传算法的高压压气机气动布局优化研究

Research on aerodynamic layout optimization of gas turbine high-pressure compressor based on multi-objective genetic algorithm

为了提升高压压气机设计点效率,通过多目标遗传算法开展高效率高压压气机的一维气动布局研究。确定了遗传算法种群的相关参数和高压压气机一维优化方案参数的限制条件与控制形式;分析了高压压气机的流路形式,切线速度、负荷系数、进口绝对气流角等参数的一维分布形式。结果表明,当高压压气机流路为近等中径形式,叶尖切线速度在294~352 m/s范围时效率较高。负荷系数轴向分布形式对压气机设计点效率无明显影响,但是一级转子负荷在0.275以上时,高效率的方案占比较高;在避免末级静子气流折转角过大的前提下,中间级转子进口绝对气流角降低亦可有效提高压气机的工作点效率;压气机最优方案的设计点效率达到88.46%,喘振裕度达到16.29%。研究结果可为高压压气机气动布局优化提供参考。

In order to improve the efficiency of high-pressure compressor design points,a multi-objective genetic algorithm was used to study the one-dimensional aerodynamic layout of high-efficiency high-pressure compressors.The relevant parameters of the genetic algorithm population and the limiting conditions and control mode of one-dimensional optimization scheme parameters of the high-pressure compressor were determined.Analyses were conducted on the one-dimensional distribution of parameters such as flow path form,tangential velocity,load coefficient and inlet airflow angle of the high-pressure compressor.The results show that when the flow path of the high-pressure compressor is nearly equal diameter form and the tangential velocity at the blade tip is within the range of 294 to 352 m/s,higher efficiency can be achieved.In addition,it is found that the axial distribution of the load coefficient has no significant impact on the efficiency of the compressor design point,but the proportion of high-efficiency schemes is higher when the first stage rotor load coefficient is above 0.275.On the premise of avoiding excessive deflection angle of the final stage stator airflow,reducing the inlet airflow angle of the intermediate stage rotor can also effectively improve the efficiency of the compressor operating point.The optimal design point efficiency of the compressor reaches 88.46%,and the surge margin reaches 16.29%.The research results can provide reference for optimizing the aerodynamic layout of high-pressure compressors.