非定常环境中叶栅总压恢复系数的数值研究  

Numerical Investigation of Total-Pressure Recovery Coefficient of Cascade in Unsteady Environment

作　　者：闫朝[1] 季路成[1] 于海力[1] 徐建中[1] 

机构地区：[1]中国科学院工程热物理研究所,北京100080

出　　处：《航空动力学报》2004年第1期113-117,共5页Journal of Aerospace Power

基　　金：国家自然科学基金资助项目(59906012);国家重点基础研究发展规划项目资助(G1999022305);中国科学院知识创新工程资助项目(KGCX2-301)

摘　　要：利用以Ni格式和隐式双时间步法求解二维非定常N-S方程为基础的数值模拟方法研究了流动的非定常性对涡轮叶栅总压恢复系数的影响,并与文中提出的定常模型和准定常模型进行了对比。结果发现,非定常流动能够提高叶栅的总压恢复系数,但这是建立在与准定常流相比较的层面上,而和定常流比较时,非定常流只会使总压恢复系数下降。A numerical method based on Ni and implicit dual-time steps scheme for solving the 2-D unsteady N-S equations is applied to investigating the influence of unsteadiness on the total-pressure recovery coefficient of turbine cascade, results of which are compared with that of the steady model and quasi-steady model introduced in this paper. Calculated results show that the unsteadiness of flow can increase the total-pressure recovery coefficient of cascade, when compared with quasi-steady flow. The unsteady flow tends to decrease the total-pressure recovery coefficient when compared with steady flow.

关 键 词：非定常流 数值模拟 涡轮叶栅 总压恢复系数 航空发动机 定常模型 

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]