塞式喷管热试实验和数值模拟  

Hot-firing tests and numerical simulation of aerospike nozzles

作　　者：王长辉[1] 刘宇[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：《北京航空航天大学学报》2007年第9期1009-1012,共4页Journal of Beijing University of Aeronautics and Astronautics

基　　金：中国博士后科学基金资助项目(20060400038)

摘　　要：以气氢/气氧为推进剂,对三单元直排塞式喷管发动机进行了热试实验和数值模拟研究.介绍了实验系统及实验发动机主要零部件的结构和设计参数,给出了实验参数测量结果、实验照片和数据分析.数值模拟研究了塞式喷管的流场特点,数值预示了实验塞式喷管发动机的高度特性曲线.无再生冷却塞式喷管发动机采用耐烧蚀材料钨渗铜加工内喷管和燃烧室内衬,碳钢材料加工塞锥.使用爆震波点火器点燃多个单元推力室,成功进行了热试实验.在2个压比下获得了塞式喷管性能数据,实验表明,塞式喷管具有良好的高度补偿能力和较高的喷管效率.在CNPR=50附近,效率达到92%~93.5%;在CNPR=350附近,效率达到95%~96%.预计在设计点的效率不低于98%.Hot-firing tests and numerical simulation were carried out on a 3-cell GH2/GO2 linear aerospike nozzle engine with round-to-rectangle primary nozzles. Test apparatus, structures and design parameters of the main parts concerned with the experimental engine were described. Data measured in the tests, experimental photograph and data analyses were presented. Aerospike nozzle flowfield was studied by numerical simulation and efficiency altitude characteristic of experimental aeropike nozzle engine was also predicted. The primary nozzle and inner layer of the combustion chamber were made of ablation-resistant W-Cu alloy and the aerospike ramp was made of steel. Detonation wave igniter was attempted to use on multi-cell aerospike nozzle and two short-duration hot-firing tests on the aerospike engine without generation cooling were executed successfully. The aerospike nozzle performance was obtained under two CNPH which is the the ratio of combustion chamber pressure to ambient pressure. It is shown that good altitude compensation of thrust and high efficiency was yielded in the tests. Near CNPR =50, efficiency is 92% to 93.5% and efficiency is 95% to 96% near CNPR = 350. The promising efficiency of more than 98% at design point can be expected.

关 键 词：火箭发动机 塞式喷管 实验 数值分析 性能 

分 类 号：V433.9[航空宇航科学与技术—航空宇航推进理论与工程]