2级涡轮内部流动定常与非定常计算差异研究  

Study of Differences between Steady and Unsteady Computation for Two-Stage Turbine Internal Flow

作　　者：杨杰[1] 周颖[1] 潘尚能[1] 卢聪明[1] 

机构地区：[1]中航工业航空动力机械研究所,湖南株洲412002

出　　处：《航空发动机》2016年第3期21-27,共7页Aeroengine

摘　　要：为获取进而认识涡轮内部流动状态,以某2级约化形式的动力涡轮为研究对象,分别对其进行定常和非定常数值计算和分析。研究表明:定常计算与非定常计算对涡轮内部流动的模拟结果,如叶片表面的压力分布、叶排进出口的气流角、叶片通道中的二次流流向涡、展向涡、叶片通道中的损失等,均存在差异;流动的非定常性越强,定常与非定常计算结果的差异越大,且该差异大小对于静叶与动叶呈相反的展向分布规律。In order to find out internal flow state of turbine, taking a scaled two-stage power turbine as the research object, both steady and unsteady computations were conducted. The study shows that there makes obvious difference in the results of both steady and unsteady computation on the internal flow of turbines, including the pressure distribution on blade surfaces, the inlet/outlet flow angles of blade rows,the secondary flow streamwise and spanwise vortex in blade passages, the flow loss in blade passages. Moreover, the stronger the unsteadies of the flow show, the larger differences between steady and unsteady computation results are, and the magnitude of the differences between steady and unsteady computation results tend to follow opposite spanwise distribution rules for stators and rotors.

关 键 词：涡轮 内部流动 定常 非定常 数值模拟 涡 航空发动机 

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]