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作 者:童佳慧 李博[1] 苏嘉殷 徐猛 邱宇宸 TONG Jiahui;LI Bo;SU Jiayin;XU Meng;QIU Yuchen(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)
机构地区:[1]南京航空航天大学能源与动力学院,南京210016
出 处:《航空动力学报》2023年第5期1166-1175,共10页Journal of Aerospace Power
摘 要:针对一种带旁通的双S弯进气道开展了气动设计和性能仿真研究。探索了改变第一S弯长度对进气道的影响,通过流场流动和砂粒轨迹的分析,对初始设计的模型进行修正,然后在修正后的基准模型的基础上,采用数值模拟方法,重点研究了不同扫气比和过渡截面面积比对进气道管道内流动特性和排砂效率的影响。结果表明:第一S弯的长度过小则气动性能好但不利于排砂,过大则气动性能差但排砂效果好。过渡截面面积比在减小的过程中,进气道气动性能略微下降。当形成分离涡后,总压损失迅速增大,但出口总压畸变指数降低。面积比过大或者过小都不利于进气道排砂。随着扫气比增大,排砂性能提高,进气道出口总压恢复基本稳定,畸变增大。The aerodynamic design and performance simulation of a serpentine inlet with bypass were studied.The influence of alternating the first S-bend length on the inlet was explored.Through the analysis of the flow field and sand particles trajectories,the protype was modified.Then,on the basis of the modified benchmark model,the influences of different scavenge flow ratios and transition section area ratios on flow characteristics and sand separation efficiency in the inlet duct were emphatically studied by means of numerical simulation.The results showed that if the length of the first S-bend was too small,the aerodynamic performance was better but not favorable for sand separation;if the length was too large,the aerodynamic performance was worse but the sand separation effect was better.In the process of decreasing transition area ratio,the aerodynamic performance of inlet decreased slightly.When separation vortices were formed,the total pressure loss increased rapidly,but the outlet total pressure distortion coefficient decreased.And too large or too small area ratio was not conducive to the sand separation of inlet.With the increase of scavenge flow ratio,the performance of sand separation efficiency was improved,the total pressure recovery at the outlet was basically stable and the distortion was increased.
关 键 词:进气道 旁通 涡桨发动机 气动性能 排砂 面积比
分 类 号:V211.48[航空宇航科学与技术—航空宇航推进理论与工程]
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