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

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.