火箭发动机燃气射流喷水降噪研究  

Reduction of rocket engine jet noise by water injection

作　　者：徐悦[1] 周旭[1] 张志成[1] 陈钰[1] 刘利宏[1] 

机构地区：[1]中国人民解放军总装备部工程设计研究总院,北京100028

出　　处：《航空动力学报》2010年第4期816-820,共5页Journal of Aerospace Power

基　　金：国家自然科学基金(10904178);中国博士后科学基金(200902673;20080431377)

摘　　要：采用有限体积法预估喷水对火箭燃气射流气动噪声的抑制程度.建立并求解了守恒的控制体的质量、动量和能量方程,得到了燃气和水掺混后的等效射流参数,分析了水和燃气的质量流率比对等效射流参数和降噪效果的影响.计算结果和试验数据的结果基本吻合.结果显示,当水和燃气的质量流率比超过一个临界值之后,降噪效率会降低.A finite volume method was applied to determine rocket jet noise reduction due to water injection.Mass,momentum and energy equations based on the control volume were built and solved,and the equivalent jet parameters due to mix of the jet and water were obtained.The effect of the water-to-jet mass flow rate ratio on equivalent jet parameters and noise reduction was analyzed.The calculation results show the agreement with experimental data.The results indicate that the efficiency of noise reduction reduces when the mass flow rate ratio exceeds the critical value.

关 键 词：火箭发动机 射流噪声 有限体积法 等效射流参数 质量流率比 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]