轴流压气机可控扩散叶型的数值优化设计  

NUMERICAL OPTIMIZATION PROGRAM FOR DESIGNING CONTROLLED DIFFUSION COMPRESSOR BLADING

作　　者：刘波[1] 周新海[1] 严汝群[1] 

机构地区：[1]西北工业大学

出　　处：《航空动力学报》1991年第1期9-12,共4页Journal of Aerospace Power

摘　　要：本文采用数值优化技术进行轴流压气机可控扩散叶型设计 ,选择叶栅总压损失系数为目标函数 ,对初始叶型在设计与非设计状态的全部工况范围内的气动性能 ,进行优化计算。应用该数值优化设计系统完成了高进口马赫数、大弯度压气机静子叶栅的试验件设计。实验结果表明 ,在设计与非设计工况下 ,所设计的叶栅气动性能良好 ,达到了预定的设计目标 ,验证了本文方法的可靠性与适用范围。A numerical optimitization design procedure has been worked out for generation of the Controlled Diffusion Airfoil(CDA)of axial-flow compressors.The cascade total pressure loss coefficient is chosen as an objective function.The numerical optimization design procedure is composed of four programs,i.e.,the program for optimization of the prescribed velocity distribution,the initial blade profile generation program,the program for compressible,inviscid flow computation and the program for inverse boundary layer computation.At first the initial blade shape is generated,then the design procedure can be used to optimize the initial blade profile at design and off-design conditions until the final shape of the blade is satisfactory.In order to demonstrate the feasibility of the procedure,the numerical optimization design program was carried out for a compressor stator blade at hub section with high loading and large flow turning angle.The designed cascade has been tested.The test data show that the flow at design conditions is shock-free.Compared with the conventional cascade,the Controlled Diffusion Airfoil(CDA)cascade designed can enlarge the incidence angle range,increase critical Mach number and strengthen the tail edge of the blade.Besides,the CDA cascade has much smaller losses and deviation angle than the conventional cascade.It is verified that the design procedure is feasible for the generation of the Controlled Diffusion Airfoils.

关 键 词：压气机 轴流式 叶型 优化设计 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程]