大涵道比发动机涡轮过渡段气动改型设计  

Retrofit Design of Intermediate Turbine Duct of High Bypass Ratio Engine

作　　者：郭泽润 蒋首民 孔庆国[2] 周琨[2] 

机构地区：[1]中国航天科工集团31研究所高超声速冲压发动机技术重点实验室,北京100074 [2]北京航空航天大学能源与动力工程学院,北京100191

出　　处：《航空发动机》2015年第4期18-23,共6页Aeroengine

基　　金：高超声速冲压发动机技术重点实验室开放基金(20120101014)资助

摘　　要：大涵道比发动机的发展对涡轮过渡段设计提出了更高的要求。依据涡轮过渡段设计流程的5个步骤对某大涵道比发动机过渡段进行气动设计,并且对原型进行3维校核分析。总结过渡段内流动的特点,在原型的基础上进行改型设计。结果表明:通过控制流向面积分布规律能够确定过渡段沿流向的压力分布,选择合理的流向面积分布规律形式、改变过渡段流道型线的曲率能够改善当地的局部流动,获得更好的设计。改型设计消除了原型设计中存在的流动分离,并且减小了二次流损失,增大了过渡段的总压恢复系数。The development of high bypass ratio engine has put forward higher requirements of the design technology of intermediate turbine duct. According to the five steps of the intermediate turbine duct （ITD） design, an aerodynamic design of the ITD of a high bypass ratio aereengine was performed, and three-dimensional analysis was done thereto. The flow field in the ITD was analyzed, while the features of the ITD were summarized, and a new design was carried out based on that. The results show that by controlling the flow area distribution of the ITD, the pressure distribution along the flow direction can be determined. By choosing a reasonable distribution of the flow area and curvature of the ITD, a better design can be obtained. The new design eliminated flow separation area, reduced the secondary flow loss and improved total pressure recovery coefficient of the ITD.

关 键 词：涡轮过渡段 气动设计 流动分离 二次流 大涵道比发动机 

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]