基于中弧线曲率控制的压气机叶型优化

Compressor Airfoil Optimization Based on Camber Curvature Control

关键词:  造型程序  中弧线曲率  可控扩散叶型  叶型优化  压气机

Key words:  Blade modeling program  Camber curvature  Controlled diffusion airfoil  Airfoil optimization  Compressor

摘要:

为提高压气机叶型优化设计水平，基于中弧线曲率控制方法编写了压气机叶片造型程序，将中弧线曲率控制参数作为优化变量，结合粒子群寻优算法对传统可控扩散叶型(CDA)进行了优化研究。结果表明：基于中弧线曲率控制的叶片造型程序能够对CDA叶型进行较好的拟合，拟合叶型的气动性能与设计要求较符。优化叶型在设计点的总压损失降低了约6.34%，优化叶型总压损失随攻角变化较为平缓。在一定攻角范围内，叶型中弧线曲率峰值的前移能够将吸力面马赫数峰值前移，提高叶型吸力面的扩压能力，降低总压损失。在大攻角工况下，改进的中弧线曲率分布能够显著降低叶型总压损失。将中弧线曲率控制参数作为优化变量进行CDA叶型的优化是可行的。

Abstract:

To improve the optimization quality of compressor blade, the compressor blade modeling program was developed based on the control-curvature-construction-method of the camber. The curvature control parameters of camber were taken as optimization variables. A traditional Controllable Diffusion Airfoil (CDA) was optimized by using the particle swarm optimization algorithm. Results show that the baseline CDA could be well fitted by using the blade modeling program, and the aerodynamic performance of the fitted airfoil is in conformity with the design requirements. The total pressure loss of the airfoil is reduced by 6.34% at the design point, while the total pressure loss curve of the optimized airfoil is flatter than the baseline. In a certain range of angle of attack, moving the peak curvature of the camber forward could move the peak of the Mach number on the suction surface forward and increase the diffusion capacity, which helps to reduce the total pressure loss of the airfoil. The total pressure loss was significantly reduced with the help of camber curvature distribution of the optimized airfoil under high angles of attack. It is feasible to optimize the design of CDA by using the camber curvature control parameter as the optimization variables.