Abstract: Using oxidizer rich preburner is valuable in the design of LOX/Kerosene liquid propellant rocket engine.The important technology is how to design it’s construction under the conditions of high pressure,high flow intensity and high mixture ratio,ensure preburner could work steadily and dependably when engine’s thrust changes at a large range,and ensure the temperature deviation is small.Through theory analysis and subscale experiment investigation,this paper gets the means of construction and parameter design for centrifugal in jector with inlet mixing withdraw length and secondary injection when engine’s thrust change at a large range.The result is valuable for fullscale preburner design

Key words: Hydrocarbons oxygen engine;High pressure staged combustion rocket engine;Oxidizer rich propellant;Precombustion chamber;Combustion test;Numerical calculation

摘要： 通过数值计算， 分析了富氧预燃室喷注单元的结构设计及其对燃烧的影响， 并使用具有三个喷注单元的缩尺预燃室， 对液氧／煤油的富氧燃烧进行了试验评价。数值计算和试验表明， 燃气温度的均匀性与燃烧室长度有关； 对带缩进长度和二次喷注的喷注单元， 应合理地选择缩进长度及缩进室的混合比； 富氧预燃室能正常可靠地点火和工作， 能满足大范围推力调节的要求。

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;数值计算