MEMS-SPMT喷管内的粘性和热损失研究  

Study on viscous and heat loss in nozzle of MEMS-SPMT

作　　者：吴素丽[1] 胡松启[1] 张斌[1] 刘迎吉[1] 刘凯[1] 王鹏飞[1] 

机构地区：[1]西北工业大学燃烧、热结构与内流场重点实验室,西安710072

出　　处：《固体火箭技术》2012年第1期57-63,共7页Journal of Solid Rocket Technology

基　　金：总装备部预研基金资助项目;西北工业大学创业种子基金资助

摘　　要：微喷管内流体对壁面的粘性力和热传导可显著影响火箭发动机性能。通过出口亚声速层面积与出口面积比、推力和比冲损失等参数,评估了S-A和低Re数k-ε湍流模型、壁面初始温度和喷管构型因素对微喷管内粘性和热损失效应的影响。结果表明,两种湍流模型在计算粘性边界层上有一定的差异,粘性力造成推力损失22%;换热既减小粘性边界层尺寸,降低粘性作用,也降低微喷管比冲;升高微喷管壁面初始温度,能降低热量损失,增大其尺寸能减小粘性损失,二者均能提高比冲。Characteristics of the rocket motor can be largely affected by viscous force and heat transfer of fluid to the wall of micro-nozzles. In this paper, the effects of turbulence models （S-A and low Re k-e models） , initial temperature and size of the micronozzle on viscous and heat loss were evaluated through parameters like the area ratio of subsonic layer to outlet, thrust and impulse loss et al. The results show that two turbulence models have some differences in calculating the subsonic layer; thrust losses attain 22% due to viscouse effects;heat transfer reduces not only the size of viscous boundary layer and the corresponding viscous effects, but also the impulse of micro-nozzle. Heat loss can be decreased through increasing initial temperature of the micro-nozzles wall, and viscous loss can be reduced by enlarging its size, thus improve impulse of the micro-nozzles.

关 键 词：MEMS-固体微推力器 粘性损失 换热损失 亚声速边界层 微推力 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]