富氧预燃室高压缩尺试验研究  

Experimental investigation of oxidizer-rich subscale preburner

作　　者：吴宝元[1] 葛李虎[1] 谭永华[1] 刘红军[1] 

机构地区：[1]陕西动力机械设计研究所,陕西西安710100

出　　处：《推进技术》2003年第2期104-108,共5页Journal of Propulsion Technology

摘　　要：为满足液氧/煤油发动机推力大范围变化和预燃室要在大范围工况条件下工作的要求,采用带缩进长度和二次喷注的双组元离心式喷注单元,对富氧预燃室进行了高压缩尺试验研究。头部二次喷注孔为矩形和圆形、身部4种不同长度的6台试验件的试验结果表明,缩尺试验的最好温度均匀性≤50℃,燃气平均停留时间为10ms左右,矩形和圆形喷注方案的缩进室混合比分别小于20和24时可以避免产生低频不稳定燃烧。所得结论可用于液氧/煤油发动机的研制,并对新型发动机的研制具有一定的借鉴作用。To make sure that the preburner could work steadily and dependably when engine's thrust change at a large range, and the temperature deviation is small, adopting dual-propellant injector with withdraw chamber and secondary spray, this paper investigated the combustion character of the oxidizer-rich preburner via high pressure subscale test. The six testers adopted with rectangle and round secondary spray in four different lengths were test. The results show that the best temperature deviation is less or equal to than 50°C, and the combustion gas stage time must be longer than 10 ms, and when the withdraw chamber mixture ratio is less than 20 and 24 at the case of rectangle and round secondary spray respectively, it is possible to avoid low-frequency combustion instability. The result is valuable for fullscale preburner design.

关 键 词：烃氧发动机 高压补燃火箭发动机 富氧推进剂 预燃室 燃烧试验 缩尺模型 

分 类 号：V434.3[航空宇航科学与技术—航空宇航推进理论与工程]