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

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