基于多学科涡轮叶片气动设计优化

Aerodynamic Design Optimization of Turbine Blade Based on Multidiscipline

涡轮叶片设计涉及到的学科有气动、强度、振动、结构、工艺、材料及传热等。由于其设计过程的复杂性,本文主要在气动、强度和传热3个学科的基础上,针对某型号涡轮级叶片的气动设计进行仿真优化分析的基础研究。其中涉及到涡轮叶片气动设计过程中的参数化建模、设计优化仿真集成以及设计优化模型的建立等,同时分析了设计中存在多变量优化策略的实施,初步实现了涡轮叶片在气动设计过程中耦合流场、应力场和温度场的优化仿真计算,最后对优化前后的结果进行对比分析。

Design of the gas turbine blade includes many disciplines, such as aerodynamtcs, mtensity, osdilation, structure, arts and crafts, material, thermodynamics, etc. Due to the complexity of the design process, the aerodynamic design for some turbine blades is simulated based on three disciplines of aerodynamics, intensity and thermodynamics. Research problems involve parametric modeling, design optimization modeling, simulation optimization integrating, and optimization planning, etc. Meanwhile, the optimization strategy for design variables is analyzed. The optimization simulation and the computation of the coupling flow field, the stress field and the temperature field of the turbine blade aerodynamic design are implemented. Results of optimization variables, constraints and objectives before optimization and after optimization are compared.