两相流环缝塞式喷管理想型面的设计方法  

An ideal method for the two-phase ring plug nozzle design

作　　者：谢侃[1] 刘宇[1] 任军学[1] 廖云飞[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100083

出　　处：《固体火箭技术》2007年第3期223-228,共6页Journal of Solid Rocket Technology

基　　金：国家自然科学基金项目(50476002)

摘　　要：目前固体火箭发动机塞式喷管没有成熟的理论设计方法,设计方法需考虑两相流因素和极限粒子流线的几何约束。在常滞后两相流假设下提出改进的Angelino理想型面法设计两相流环缝塞式喷管,证明了常滞后两相流中的普朗特-迈耶函数关系式,并给出了最终设计公式。用F luent软件计算了改进法设计的喷管型面性能。算例结果表明,与未考虑两相流效应的纯气相理想型面相比,该法设计的型面长度缩短近33%,推力增大约1%,证明了提出常滞后两相流假设的合理性及改进法设计两相流环缝塞式喷管的有效性。At present, there is no mature method for the solid propellant plug nozzle design. The design method needs to take into account the two-phase flow factor and the geometric restriction of the limiting particle streamline. An improved Angelino method was proposed to design the two-phase ring plug nozzle on the assumption that the two-phase flow has a constant velocity drag coefficieut. The Prandfl-Meyer formula for the constant drag two-phase flow was verified and design formula was given. Contour performance of plug nozzle designed by the improved method was calculated by using the Fluent software. Compared with gas-phase contour of nozzle without considering two-phase effect, the contour length of the plug nozzle designed by the improved method was reduced by 33%, and the thrust was increased by 1%. The results show that the constant drag two-phase flow assumption is rational, and the improved Angelino method is effective for the two-phase ring plug nozzle design.

关 键 词：固体推进剂火箭发动机 两相流 塞式喷管 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]