声腔深度和相对开口面积的确定  

Determination of the Depth and Fractional Open Area for Acoustic Cavity

作　　者：葛明龙[1] 郑孟伟[1] 

机构地区：[1]北京航天动力研究所,北京100074

出　　处：《火箭推进》2004年第4期15-21,共7页Journal of Rocket Propulsion

摘　　要：根据二维声腔模型的声学试验结果和四分之一波管的理论公式,给出了直孔(槽)声腔和四种有进口肋声腔的有效深度计算公式。用该公式对几个推力室进行验算,得到可借鉴的声速比数值范围。依据设置声腔的二十多个推力室的稳定性鉴定试验数据,统计得到声腔相对开口面积的经验公式。Based on the testing data of 2D acoustic model and theoretical equations for quarter wave tube, a new method for determining the effective depth of different type of acoustic cavities is presented. The sound velocity ratio for several practical thrust chambers can be obtained by the method. The result shows that this value varies from 0.50 to 0.78. Furthermore, according to the stability testing data of more than twenty types of thrust chambers, a new empirical equation for calculating the fractional open area of acoustic cavity is also given out.

关 键 词：相对开口面积 声腔 推力室 燃烧稳定性 液体火箭发动机 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]