基于渗透边界条件的叶轮机械气动设计反方法:解的存在性和唯一性探讨  

Transpiration Boundary Condition Based on Inverse Method for Turbomachinery Aerodynamic Design: on the Solution Existence and Uniqueness

作　　者：杨金广[1] 刘振德[1,2] 邵伏永[1] 吴虎[3] 

机构地区：[1]北京动力机械研究所,北京100074 [2]北京动力机械研究所激光推进及其应用国家重点实验室,北京100074 [3]西北工业大学动力与能源学院,陕西西安710072

出　　处：《推进技术》2015年第4期579-586,共8页Journal of Propulsion Technology

基　　金：国家自然科学基金(51076131)

摘　　要：通过集总参数分析,发现确定了反方法的定解条件——总切向力与出口气流角的关系。进而表明在多数情况下,反方法有两个物理解存在,而最终收敛到哪个解由渗透边界条件与定解条件的相容性决定。为了保证基于渗透边界条件的反方法收敛到期望解,文中基于质量流量强加的概念提出了一种处理措施,并通过例子验证了该措施的有效性。最后利用所发展的准三维反方法对跨声速压气机叶栅进行改型设计,效率增加了1.4%,展现了反方法在控制轴向载荷分布方面的优越性。By a lumped parameters analysis,it is found that the solution determination condition of the in？verse method can be expressed by function between outlet flow angle and total tangential force ,and in most case there are two physical solutions. The converged solution is determined by the consistence of the transpiration boundary condition and the solution determination condition. A technique is developed to force the solution con？verged to a desired solution. The developed Q3D design system is validated by a transonic compressor cascades case,and a 1.4%efficiency gain is obtained,which demonstrate the power of the inverse method to control the axi？al distribution of the pressure loading.

关 键 词：叶轮机械 气动设计 反方法 总切向力 渗透边界条件 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]