喉部形状设计对微喷管内流动及性能的影响  

Effects of throat shape design on propulsion performance of micronozzles

作　　者：刘赵淼[1] 张谭[1] 逄燕[1] 

机构地区：[1]北京工业大学机械工程及应用电子技术学院,北京100124

出　　处：《航空动力学报》2010年第10期2279-2284,共6页Journal of Aerospace Power

基　　金：国家自然科学基金(10502002)

摘　　要：采用连续介质方法和直接模拟Monte Carlo(DSMC)方法数值模拟研究了喉部宽度为34μm的二维Laval型微喷管内流场的流动状况.设计了三种不同喉部形状的微喷管:尖角型、圆角型和平角型.计算分析了喉部形状、扩张比等方面对流场结构及推进性能的影响.研究发现,圆角型微喷管的综合性能最优,平角型微喷管具有较大的比冲效率;适当增大扩张比能提高微喷管的性能.Characteristics of flow field in Laval micronozzles with 34 μm throat-width were studied numerically by using continuum and direct simulation Monte Carlo（DSMC） method.Three types of micronozzles with different throat shapes were designed,such as：sharp-corner,smooth-corner and flat-corner.Based on the geometric structure design,effects of throat shape and expansion ratio on flow field and propulsion performance were analyzed,respectively.It is discovered from the results that,the comprehensive propulsion performance of the micronozzle with smooth-corner throat is the best,while the micronozzle with flat-corner throat has much better specific impulse efficiency.When the expansion ratio becomes larger,both thrust and specific impulse will increase.

关 键 词：微喷管 喉部形状 推进性能 连续介质 直接模拟Monte Carlo(DSMC) 数值模拟 

分 类 号：V211.1[航空宇航科学与技术—航空宇航推进理论与工程]