脉冲爆震发动机部分填充效应理论分析  

Theoretical Analysis of Partial-Filling Effect of Pulse Detonation Engine

作　　者：严宇 杨岸龙 范玮[2] 洪流 

机构地区：[1]西安航天动力研究所液体火箭发动机技术重点实验室,陕西西安710100 [2]西北工业大学动力与能源学院,陕西西安710072

出　　处：《推进技术》2015年第9期1361-1368,共8页Journal of Propulsion Technology

摘　　要：为了研究脉冲爆震发动机的部分填充效应,建立了不依赖于实验数据的通用理论分析模型。将该理论模型得到的计算结果与实验数据进行对比,误差在15%以内。并应用该模型进行了一些算例计算,计算结果表明:部分填充能显著增加比冲,理论比冲最高能接近600s;比冲增益随填充系数的减小而增大,最后趋于某一上限值,计算中,该上限值最高达到4;采用氧气作氧化剂时不仅比采用空气作氧化剂时的比冲更高,而且比冲增益也更大;不可燃气体密度越大,部分填充产生的比冲增益越大;背压降低,部分填充产生的比冲增益也随之减小。In order to investigate the partial-filling effect of pulse detonation engines,a general analyzing model independent on experimental data was established. Discrepancy between calculated result by this model and experimental data by others is within 15%, which proved the accuracy of the model. The calculated results indicate that partial-filling can dramatically increase specific impulse,which approaches nearly 600s in present research. It is also found that specific impulse augmentations increase as fill fraction decreases and then approaches an upper limitation,the maximal value of which achieved 4 in present calculations. When using oxygen as oxidizer,not only specific impulse but also specific impulse augmentations are larger than air. The specific impulse augmentation of partial-filling is in proportion to inert gas density. As the back pressure decreases , the specific impulse augmentation decreases.

关 键 词：脉冲爆震发动机 部分填充 理论分析 性能 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程]