Abstract: To make sure that the prebumer could work steadily and dependably when engine’s thrust change at a large range, and the temperature deviation is small, adopting dual-propellent injector with withdraw chamber and secondary spray, this paper investigated the combustion character of the oxidizer-rich prebumer 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℃, and the combustion gas stage time must be longer than 10ms, 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 prebumer design.

Key words: Hydrocarbons-oxygen engine;High pressure staged combustion rocket engine;Oxidizer-rich propellant;Precom- bustion chamber;Combustion test;Scale model

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。

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