边界层控制方法降低喷管喉衬烧蚀综述  

Review of nozzle boundary-layer control system for mitigation of nozzle throat erosion

作　　者：陈林泉[1] 王立武[1] 刘勇琼[2] 郑凯斌[1] 吴秋[1] 

机构地区：[1]中国航天科技集团公司四院四十一所,西安710025 [2]西安航天复合材料研究所,西安710025

出　　处：《固体火箭技术》2014年第3期324-329,共6页Journal of Solid Rocket Technology

基　　金：国家自然科学基金(51376166)

摘　　要：介绍了一种边界层控制方法,阐明了该方法降低喷管喉衬烧蚀的机理,通过降低喷管喉衬的温度和喷管边界层内氧化组分(H2O、CO2和OH)的浓度,从而降低喷管的烧蚀率。从理论研究和试验研究两方面阐述了该方法的国内外研究发展现状。在理论方面,介绍了该方法降低喷管喉衬烧蚀的效果,可降低喉衬烧蚀率80%以上;在试验方面,介绍了该方法降低喉衬烧蚀的验证性试验研究,可将喉衬烧蚀率降低到不可测量的程度。最后,总结了该方法目前的发展水平,分析了该方法存在的问题及发展趋势。A nozzle boundary-layer control system was introduced to reduce solid rocket motor nozzle erosion. This design not only reduces the temperature of nozzle throat surface but also reduces the mass fractions of the oxidizing gaseous species such as H2 O,CO2and OH in the combustion products,thus reducing the chemical attack on the nozzle throat surface. This paper gives an research status of this method at home and abroad in theoretical and experimental aspects. The effectiveness of this design for mitigating nozzle erosion was introduced in theoretical aspect,which can reduce nozzle erosion by more than 80%. In experimental aspect,the effectiveness of this system was demonstrated,and this method can achieve zero erosion rate. Research status of this method was summarized,and future work was analyzed.

关 键 词：固体火箭发动机 边界层控制方法 喷管 喉衬烧蚀 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]