1＋1/2对转涡轮非定常流动数值模拟  

Numerical simulation of unsteady flow in a vaneless counter-rotating turbine

作　　者：綦蕾[1] 潘尚能[2] 李维[2] 邹正平[1] 刘火星[1] 周杨[1] 

机构地区：[1]北京航空航天大学能源与动力工程学院,航空发动机气动热力科技重点实验室,航空发动机数值仿真研究中心,北京100191 [2]中国航空工业集团公司中国航空动力机械研究所,株洲412002

出　　处：《航空动力学报》2010年第8期1825-1835,共11页Journal of Aerospace Power

基　　金：国家自然科学基金(50776003)

摘　　要：为了掌握对转涡轮内部的复杂流动以改进航空燃气轮机的设计,利用数值模拟手段对所设计的1+1/2对转涡轮内部非定常流动进行了研究,将定常和非定常结果进行了详细的对比分析,结果表明:非定常结果与定常结果相比出功比减小,总效率约减小0.44%,流量基本不变,其中尾迹、激波、位势作用以及泄漏流等因素之间的相互作用是影响非定常特性的主要因素.In order to investigate the complex flow field in counter-rotating turbine and improve effectively the gas turbine design.A numerical study of unsteady flow in a vaneless counter-rotating turbine was presented in this paper.The steady and unsteady results were contrastively analyzed.It＇s found that the unsteady effect can decrease the specific work ratio appreciably,and increase the loss by about 0.44% efficiency points.However,the mass flow remains unchanged.The results show that the unsteady interactions from the wake,shockwave,potential field and the tip leakage flow have made great contributions to the unsteady effect.

关 键 词：对转涡轮 非定常流动 尾迹 激波 位势作用 叶尖泄漏涡 

分 类 号：V235.1[航空宇航科学与技术—航空宇航推进理论与工程]