引气风斗流动特性数值模拟  

Numerical Simulation of Flow Characteristic on Air Bleeding Manifold

作　　者：何盼[1] 卢少鹏[1] 羌晓青[1] 滕金芳[1] 

机构地区：[1]上海交通大学航空航天学院,上海200240

出　　处：《科学技术与工程》2017年第18期327-330,共4页Science Technology and Engineering

基　　金：先进航空发动机协同创新中心项目资助

摘　　要：引气风斗是航空发动机高压涡轮主动间隙控制系统中的重要零件,其流动特性将对发动机性能产生影响,为此采用数值模拟方法对引气风斗流动特征和损失机理进行研究。结果表明:在进口马赫数0.46工况下,主流的流动先减速后变化平稳;气流在引气风斗第一转弯处上、下壁面附近出现流动分离,并诱发对涡的形成,导致出口截面流场的不均匀性;引气风斗壁面型线曲率及截面积的变化对引气管道内流场结构影响显著,下壁面第一转弯处的剧烈偏转是引起流动分离及损失的主要来源,出口截面总压恢复系数按质量平均为0.967。Air bleeding manifold is an important component in the active clearance control system. The internal flow characteristics of the air bleeding manifold will have great influence on engine performance.The internal flow characteristic and the flow loss were investigated by using numerical simulation. The results show that the main flow decelerated at first and then changed gently at the typical entrance Mach number 0.46. Meanwhile, the flow separation occurred at the upside and downside near the first bend, which also induced the vortex pair and caused the non-uniformity of the flow field at the outlet. In addition, the profile of air bleeding manifold and the cross-section area had greatly influence on the flow structure, and the strong deflection of the first bend at downside surface was the main factors causing the flow separation and loss. The total pressure recovery coefficient at outlet was 0.967 by mass average.

关 键 词：引气风斗 总压恢复系数 流动特征 损失机理 数值模拟 

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]