静叶前缘气膜冷却特性的数值模拟及改进设计  

Numerical simulation and design improvement of leading-edge film cooling in an inlet guide vane

作　　者：刘捷[1] 安柏涛[1] 蒋洪德[2] 刘建军[1] 

机构地区：[1]中国科学院工程热物理研究所,北京100190 [2]清华大学热能工程系,北京100084

出　　处：《航空动力学报》2009年第2期331-339,共9页Journal of Aerospace Power

基　　金：国家863计划(2004AA503010);国家973计划(2007CB210108)

摘　　要：对某重型燃气轮机的第一级透平静叶前缘气膜冷却特性进行了数值模拟研究,计算采用CFX5商业程序,主要研究了叶片前缘,尤其是滞止线附近的气膜冷却效果、传热及冷气喷射对气动性能的影响.通过对原始设计的计算结果进行分析,给出了针对静叶前缘气膜冷却结构的两种改进设计,得到的计算结果与原始设计相比,获得了更好的冷气覆盖效果.The numerical investigations on the leading-edge film cooling of an inlet guide vane were performed and described in this paper. The program CFX was employed to obtain the numerical solution. The original design was simulated to obtain flow and heat transfer characteristics of the leading edge film cooling. The film cooling characteristics and interactions between jets and mainstream around the leading edge, especially near the stagnation line, were analyzed in detail. To provide better coolant coverage around the leading edge, the cooling configuration was modified based upon the analysis and understanding of the 3-D prediction for the original design. The modified designs were compared with the original design, providing better coolant coverage around the leading edge.

关 键 词：前缘气膜冷却 数值模拟 冷却效率 燃气轮机 改进设计 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]