几何因素对涡轮过渡段性能的影响  

Study of geometric factor influence on inter-turbine duct performance

作　　者：李同日[1] 刘火星[1] LI Tong-ri;LIU Huo-xing(School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics,Beijing 100191,China)

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100191

出　　处：《燃气涡轮试验与研究》2016年第4期6-12,共7页Gas Turbine Experiment and Research

摘　　要：为研究涡轮过渡段几何因素对其性能的影响,采用参数化方法进行过渡段子午流面造型,利用数值模拟方法对过渡段性能进行计算分析,同时借助试验结果予以对比验证。结果表明:长高比、扩张角会影响过渡段壁面曲率变化,大长高比、小扩张角过渡段扩压效果较好;相对于长高比、面积比,扩张角对过渡段总压恢复系数影响最大;进出口面积比直接影响过渡段扩压程度,但对过渡段总压损失影响较小;面积比增大18%,静压升系数最大可增加90%。To study the influence of geometric factors on the inter-turbine duct (ITD) performance, a para?metric method for inter-turbine duct meridional flow surface modeling was adopted, and numerical methodwas used to calculate and analyze the performance, and then compared with experimental results. The re?sults show that length height ratio and the area ratio will influence the changes of wall curvature in the in?ter-turbine duct. Large length height ratio and small slope angle have better diffuser effect. Compared withlength height ratio and area ratio, slope angle has more effects on the total pressure recovery coefficient ofITD. Area ratio directly influences the extent of the pressure in the inter-turbine duct, but the total pressureloss is less affected. Static pressure recovery will increase 90 percent when area ratio increases 18 percent.

关 键 词：航空发动机 涡轮过渡段 几何因素 长高比 面积比 扩张角 数值模拟 试验测量 

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]