1. 上海交通大学 航空航天学院， 上海 200240； 2. 中国商用飞机有限责任公司， 上海 200120；3. 中国商用飞机有限责任公司北京民用飞机技术研究中心， 北京 102211
出版日期:2019-04-28发布日期:2019-04-28通讯作者:陈迎春，男，研究员，电话(Tel.):021-20865010；E-mail:chenyingchun@comac.cc.作者简介:王鹏（1976-），男，博士生，高级工程师，主要研究方向为民用飞机先进制造.基金资助:国家自然科学基金资助项目（51576124）Experimental and Numerical Research on the Aerodynamic Performance of Wide-Body Aircrafts Thrust Reverser Cascade
WANG Peng,CUI Yuchao,CHEN Yingchun,ZHANG Xiaodong,DENG Zhi,LU Shaopeng,TENG Jinfang1. School of Aeronautics and Astronautics, Shanghai Jiao Tong University, Shanghai 200240, China; 2. Commercial Aircraft Corporation of China, Ltd. (COMAC), Shanghai 200120, China; 3. Beijing Aeronautical Science and Technology Research Institute of COMAC, Beijing 102211, China
Online:2019-04-28Published:2019-04-28摘要/Abstract
摘要： 针对自主设计的宽体客机大涵道比涡扇发动机反推格栅，在栅前马赫数Main分别为 0.18、0.30 和 0.35 这3种典型工况下进行了实验与数值模拟研究，获得了反推格栅的气动性能和流场特性，并验证校准了反推格栅的数值模拟方法.数值模拟与实验测量的对比结果表明：数值模拟可以较准确地预测反推格栅的性能；反推格栅的出口总压恢复系数及出口落后角分布均与实验值较为吻合.
关键词: 反推格栅, 气动性能, 流场, 实验研究, 数值模拟
Abstract: In this paper, experimental and numerical simulation methods were employed to investigate the aerodynamic performance and flow field characteristics of an independent design thrust reverser cascade of high bypass ratio turbofan engine for wide-body aircrafts. The numerical simulation was calibrated through experiments at three typical operating points of 0.18, 0.30 and 0.35 inlet Mach number. The results of the comparison between numerical simulation and experimental measurements show that the average total pressure recovery coefficient and the deviation angle of numerical simulation are in good agreement with the experimental results.
Key words: thrust reverser cascade, aerodynamic performance, flow field, experimental investigation, numerical simulation
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