三单元气氢/气氧塞式喷管发动机实验  

Tests on GH_2/GO_2 engine of 3-cell aerospike nozzle

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：《航空动力学报》2007年第5期818-822,共5页Journal of Aerospace Power

基　　金：国家863和国家博士后科学基金(20060400038)资助项目

摘　　要：以气氢/气氧为推进剂,对三单元直排塞式喷管模型发动机(内喷管和燃烧室内衬采用耐烧蚀材料钨渗铜,塞锥为碳钢)进行了热试实验研究.给出了实验结果,进行了数据分析.在两个压比(燃烧室压强与环境反压之比)下,获得了塞式喷管性能数据和塞锥表面5个测点处的压强分布.实验表明,塞式喷管具有良好的高度补偿能力和较高的效率.在压比值为50附近,效率达到92%-93.5%;在压比值为350附近,效率达到95%-96%.数值模拟的预示结果与实验数据吻合较好.Hot-firing tests were carried out on a 3-cell GH2/GO2 linear aerospike nozzle engine with round-to-rectangle primary nozzles. The primary nozzles and inner layer of the combustion chambers were made of ablation-resistant W-Cu alloy and the aerospike ramp was made of steel. Data measured in the tests and data analyses were presented. The aerospike nozzle performance and pressure at five locations along aerospike ramp were obtained under two NPR （nozzle pressure ratio） ,which is the ratio of combustion chamber pressure to ambient pressure. It is shown that test aerospike nozzle has good altitude compensability of thrust. High nozzle thrust efficiencies were yielded in the tests. Near NPR value of 50,nozzle efficiency was 92% to 93.5% and nozzle efficiency is 95% to 96% near NPR value of 350. Numerically predicted results are in good agreements with test data.

关 键 词：航空、航天推进系统 火箭发动机 塞式喷管 热试车 性能 

分 类 号：V433.92[航空宇航科学与技术—航空宇航推进理论与工程]