改进的流线曲率通流计算方法及在双涵道压缩系统设计中的应用  

Improved streamline curvature throughflow method and its application in a bypass compression system design

作　　者：邵伏永[1] 杨金广[2] 刘振德[3] 胡骏[1] 

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016 [2]北京动力机械研究所,北京100074 [3]哈尔滨工业大学能源科学与工程学院,黑龙江哈尔滨150001

出　　处：《航空动力学报》2008年第6期1072-1076,共5页Journal of Aerospace Power

摘　　要：基于轴对称的S2流面理论,发展了一套流线曲率通流计算方法.为了提高计算的收敛性、稳定性和计算精度,对求解过程中的流线曲率计算、松弛因子的选取等方面进行了改进;提出了一种简单易行的叶片力的处理方法,使得该方法可以计算叶片排以内的区域;为了计算风扇和轴流、离心以及组合压气机构成的双涵道压缩系统,发展了一种计算速度快、稳定性好的双涵道计算方法.最后将改进的通流计算方法用于一双涵道压缩系统的反设计,验证了其可行性.Based on axisymmetric S2 stream surface theory, a streamline curvature throughflow method is presented in this paper. Improvements on streamline curvature calcu-lation and relaxation factor determination were made, which enhanced the convergence, sta bility and precision of this method. A simple blade force handling method was also proposed for computing flow field in the blade passage. At the same time, a bypass compression system computational method was integrated, which was stable and fast, and which enabled this method to solve arbitrary regions in bypass compression systems composed of fans and any type of high pressure compressors （axial-flow, centrifugal and combined type etc. ）. Finally this method was which demonstrat applied to an inverse design of a fan/high pressure compressor system, ed its validity.

关 键 词：航空 航天推进系统 流线曲率 通流 双涵道压缩系统 

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]