燃气轮机多级轴流压气机快捷一体化气动设计与性能优化研究

Research on Fast Integrated Aerodynamic Design and Performance Optimization of the Multistage Axial Compressor of Gas Turbine

基于子午流面正反问题流线曲率法、改进Powell算法和叶型参数化方法,构建轴流压气机快捷气动设计、性能分析与优化平台,对某燃气轮机9级轴流高压压气机开展一体化气动设计和多目标优化。结果表明:该平台可自动有效实现多级轴流压气机快速设计、多工况性能分析和优化流程;优化改善了压气机各叶排流动和负荷匹配,实现了多工况扩稳增效;优化后设计点流量、总压比、绝热效率及设计转速下喘振裕度分别为25.97 kg/s,5.038,88.25%和33.33%;相比优化前,设计转速下裕度提升了5.39%,80%相对转速下裕度和目标工况点效率分别提升了7.56%和2.71%。

Based on a meridional flow streamline curvature method for solving the forward and inverse problems,combined with an improved Powell search algorithm and a blade profile parameterization method,a platform for the fast aerodynamic design,performance analysis and optimization of the axial compressor is established.The integrated aerodynamic design and multi-objective optimization of a 9-stage axial high-pressure compressor in a certain gas turbine are performed.The results show that the platform can automatically and effectively realize the processes including the fast design,multi-condition performance analysis and optimization of the multistage axial compressor.The optimization has improved the matchings of flow and load at each blade row of the compressor and achieved the stability expansion and efficiency increase for multiple operating conditions.The mass flow rate,total pressure ratio and adiabatic efficiency of the design point and the surge margin at the design rotate speed after optimization are 25.97 kg/s,5.038,88.25%and 33.33%respectively.Compared with the original design,the surge margin at the design rotate speed has been increased by 5.39%.The surge margin at the relative rotate speed of 80%and the efficiency of the corresponding object operating point have been increased by 7.56%and 2.71%respectively.