摘要
本文探讨了空气进气畸变指数对双水平进气布局固体火箭冲压发动机补燃室的性能影响。由于在不同工作姿态下,固体火箭冲压发动机进气道出口截面的流场结构不同,设计对应不同进气道流场结构的空气进气畸变模拟装置。根据进气畸变图谱形状和畸变指数两个重要因素进行方案设计,并采用数值计算的方法,对不同空气畸变图谱、进气堵塞比的补燃室掺混燃烧性能进行仿真分析。结果表明,相对于基准工况,随着堵塞比的增大,补燃室的总压恢复系数呈现出先小幅减小后快速减小的趋势;在相同畸变图谱下,随着堵塞比的增大,补燃室温升效率基本呈现先小幅减小后增大的趋势,且堵塞比在42%时温升效率均低于无畸变情况下的基准工况。
This paper studies the influence of air intake distortion index on the performance of the after-burning chamber of a solid ramjet with double horizontal intake.Due to the flow field structure of outlet section of inlet under different working attitude of ramjet,a corresponding air inlet distortion simulation device is designed.The scheme is designed for the two important factors of the air intake distortion atlas form and the distortion index,and numerical calculation method is used to simulate and analyze the after-burning combustion performance of the combustion chamber with different air intake distortion atlas form and air intake blockage ratio.Results show that relative to the working condition of the benchmark,the total after-burning chamber pressure recovery coefficient slightly decreases first and then rapidly along with the increase of the blockage.Under the same distortion atlas form,the efficiency of temperature rise of after-burning chamber shows a trend of slightly decrease and then increase with the increase of the blockage.When the blockage ratio arrives at 42%,the efficiency of temperature rise is lower than the benchmark condition without distortion.
作者
张喆
陈志明
张磊扬
郝雯
Zhang Zhe;Chen Zhiming;Zhang Leiyang;Hao Wen(China Airborne Missile Academy,Luoyang 471009,China)
出处
《航空科学技术》
2022年第2期22-28,共7页
Aeronautical Science & Technology
