无阻流门叶栅式反推力装置数值研究  

Numerical Research on a Blockerless Thrust Reverser

作　　者：陈著[1] 单勇[1] 张靖周[1] 狄虎威[1] 

机构地区：[1]南京航空航天大学能源与动力学院,南京江苏210016

出　　处：《航空计算技术》2012年第6期50-53,共4页Aeronautical Computing Technique

基　　金：中央高校基本科研业务费专项基金项目资助(NZ2012109)

摘　　要：借助CFD技术对无阻流门叶栅式反推力装置开展了数值研究工作。反推力装置内部流线分布揭示了二次流喷口下游产生的旋涡结构缩减外涵通道正向流通面积、迫使外涵流体由叶栅通道流出产生反推力的流动特征。在叶栅通道结构尺寸一定的情况下,反推力性能由二次流喷射位置、喷射流量、喷射角度共同决定。随着喷射流量的增加,反推力性能提高,且存在一个临界二次流流量;当喷射角度增加,反推力性能反而下降,二次流逆喷产生的效果要优于垂直喷射方式。在二次流流量和角度一定的状况下,喷射位置对旋涡结构和大小没有影响,对外涵通道的堵塞效果却不同,喷射位置倾向于叶栅通道中间位置为佳。Based on CFD technology, the numerical study on the blockerless engine thrust reverser was performed. The streamline in thrust reverser reveals that the vortices form at the downstream of the sec- ondary flow and block the bypass flow passage. The bypass flow is forced to flow along the cascade passage and produce the reverse thrust. The performances of the blockerless engine thrust reverser are codetermined by the secondary flowrate, injection position, and injection angle. With the increase of the secondary flowrate, the performance of reverse thrust is enhanced. It exists a critical flowrate where all of the bypass flow could be drove to fold up to the cascades. With the increase of the injection angle, the performance of reverse thrust is dropped. The way of converse injection is superior to that of vertical injection. To the fixed flowrate and injection angle, the injection position has no effect on the vortices structure and intensity. But the blockd action on the bypass passage differs in different injection position. The injection point is apt to setup at middle of the cascade passage.

关 键 词：无阻流门反推力装置 推力性能 流动特性 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]