涡轴发动机涡轮过渡段环形叶栅试验验证  

Annular Cascade Test Validation of an Inter-Turbine Duct For Turbo-shaftEngine

作　　者：吴小芳 周颖 刘长青 Wu Xiaofang;Zhou Ying;Liu Changqing(Hunan Key Laboratory of Turbomachinery on Small and Medium Aero-Engine,AECC Hunan Aviation Powerplant Research Institute,Zhuzhou 412002,China)

机构地区：[1]中国航发湖南动力机械研究所中小型航空发动机叶轮机械湖南省重点实验室,湖南株洲412002

出　　处：《航空科学技术》2021年第2期38-43,共6页Aeronautical Science & Technology

摘　　要：本文以涡轴发动机涡轮过渡段(ITD)为研究对象,进行了环形叶栅试验,获取了过渡段在-15°~15°迎角下过渡段的损失特性。试验结果表明,总压损失随着马赫数的增加而增加,且呈二次曲线关系。在进口迎角为-5°~0°时,涡轮过渡段总压损失最低,在正迎角时,涡轮过渡段总压损失较大,且偏离支板倾斜方向越大,损失越大。试验同时获得了设计状态过渡段内部气动参数分布,可为该涡轮过渡段支板叶型的优化设计提供一定的试验依据。By taking the inter-turbine duct(ITD)of a turbo-shaft engine as the research object,an annular cascade test was performed to obtain the loss characteristics at the inter-turbine duct as the inflow angle varified from-15°to 15°.The test results show that the total pressure loss increases with the increase of Mach number and presents a two degree curve relation.The total pressure loss of the ITD is the lowest when the inflow angle ranges from-5°to 0°,and the loss is higher when the inflow angle is positive.The greater the deviation from the strut blade is,the higher the loss is.The aerodynamic parameter distribution of the transition section obtained from the test at the design condition can provide a certain experimental basis for the optimal design of the strut blade for this type of ITD.

关 键 词：涡轮过渡段 环形叶栅 试验 变迎角 马赫数 

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]