基于近似技术的涡轮叶片气动优化设计

Blade aerodynamic optimization design based on approximation method

根据五次多项式方法进行三维涡轮叶片的参数化建模,采用N-S方程和湍流模型进行三维流场分析计算,以K-S函数法作为优化方法,利用近似技术加速循环优化速度,建立了一种基于近似技术的涡轮叶片的气动优化方法。将气动效率和总压比作为目标函数,对涡轮叶片进行多目标气动优化、形状优化。算例表明本文提出的涡轮叶片优化设计方法是有效的。

The design of aeroengine must consider many disciplines such as aerodynamics, heat transfer, structure, vibration, longevity and reliability. As the requirements of design increase, traditional design methods are too difficult to meet these needs, it is necessary to introduce a novel design method which can consider the interaction of disciplines and obtain system optimum design. This paper presents an optimization method for designing the profiles of turbine blade based on aerodynamic analysis. The pro- posed method is capable of addressing multiple objectives and constrains without relying on user input. A quintic polynomial is applied to create the three-dimensional blade model, and a three-dimensional Navier-Stokes solver is used to solve the flow field around the turbine blade. The objective functions are the aerodynamic efficiency of turbine and its total pressure ratio. The optimization is carried out with the K-S function technique and approximation technique to accelerate the iterative cycle. Numerical simulations show that the method is effective for blade aerodynamic optimization design.