气氢/气氧塞式喷管模型发动机实验  

Tests on GH_2/GO_2 model engine with aerospike nozzle

作　　者：王长辉[1] 刘宇[1] 王一白[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：《推进技术》2007年第1期73-77,共5页Journal of Propulsion Technology

基　　金：国家"八六三"资助项目(863-2-1-3-1)

摘　　要：以气氢／气氧为推进剂，对圆转方内喷管单元直排塞式喷管进行了热试实验研究。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。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，成功进行了多次短时间热试实验。在三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效率。在CNPR=110附近，效率达到93％～95％；在CNPR=450附近，效率达到96％～98％；在CNPR=1000附近，效率达到93％～96％．预计在设计点的效率不低于98％。Hot-firing tests were carried out on a 1-cell GH2/GO2 linear,aerospike nozzle engine with round-to-rectangle primary nozzle. Test apparatus, structures and design parameters of the main parts of the experimental engine are described. 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. Five short duration hot firing tests on the aerospike engine without generation cooling were executed successfully. The aerospike nozzle performance was obtained under different CNPR （ CNPR is the the ratio of combustion chamber pressure pc to ambient pressure pc）. It is shown that good altitude compensation of thrust and high effieieneies were yielded in the tests. If CNPR = 110, efficiency is from 93% to 95%. If CNPR =450, efficiency is from 96% to 98% and efficiency is from 93% to 96% if CNPR = 1000. 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 热试车 性能分析 

分 类 号：V431[航空宇航科学与技术—航空宇航推进理论与工程]