喷口中心线与补燃室轴线的角度增加对碰撞有催进作用，但影响效果相对较小；
The increase of the angle between centerline of nozzle orifice and axis of secondary combustor can promote collision number, but the effect is small.
首先建立研究静止增程固体火箭冲压发动机补燃室燃烧特性的物理和数学模型。
Physical and mathematic model of investigating combustion characteristics of secondary combustion chamber for static extended solid rocket ramjet was established.
研究表明，补燃室压强的变化对燃烧效率的影响是有限的，喷管损失主要与喷管结构尺寸有关；
The results show that the effect of combustion efficiency on chamber pressure is limited, nozzle loss is mainly caused by its structure and size.
提高空燃比，可增强补燃室中燃气的回流和轴向涡流强度，加大掺混力度，从而提高燃烧效率。
The intensity of the gas backflow and axial swirl ond the dilution in the afterburner are enhanced by increasing the air-to-fuel ratio, and then the combustion efficiency is improved.
本文从实验和数值模拟两方面，对静止和旋转增程固体火箭发动机补燃室燃烧流场进行了研究。
The combustion flow field in secondary combustion chamber for static and spinning extended solid rocket ramjet were studied experimentally and numerically in detail.
超声速进气道的性能优劣决定了补燃室流场内的压强和空气流量，进而影响到冲压发动机的工作性能。
The performance of supersonic inlet determines the pressure and the air flux in combustor, then affect the work of ramjet.
混合发动机燃烧效率比较低，使用预燃室和补燃室、合理设计喷注器以及采用扰流装置，可以提高燃烧效率；
The combustion efficiency of hybrid rocket motor is very low. In order to increase combustion efficiency, we can use vaporization chamber and mixing chamber.
硼颗粒在通过固体火箭冲压发动机的燃气发生器喷管进入补燃室的过程中，颗粒通常都会受到高速气流的作用。
The effects of various parameters on boron particle ignition of ducted rocket secondary chamber were studied with the model developed by the King.
考虑了进气道尺寸、进气夹角、头部距离、一次喷嘴扩张比和喷嘴数目等结构因素对补燃室掺混与燃烧性能的影响。
The effect of inlet size, inlet Angle, dome height, primary nozzle expansion ratio and nozzle Numbers on combustion efficiency were taken into account.
研究还发现，硼颗粒的点火燃烧主要取决于硼颗粒在补燃室内的滞留时间和所处的环境温度，而与补燃室的长度没有直接关系。
The study also shows that the ignition and combustion of boron particle lie on the resorting time and the environment temperature, and have no direct relationship with after-burning chamber's length.
为了分析发动机设计参数对反应流场的影响，用不同的条件进行计算，并由此分析了补燃室几何结构和液体燃料初始颗粒直径对燃烧效率的影响。
Calculations were carried out under different chamber configurations and initial droplet diameters, from which the effects of these conditions on the combustion efficiency were analyzed.
气液同轴直流离心式喷嘴对补燃发动机燃烧室高频燃烧稳定性有显著影响。
The bipropellant gas-liquid coaxial orifice-swirl injector has great effects on the high-frequency combustion instability of the LOX/kerosene staged combustion cycled engine.
气液同轴直流离心式喷嘴对补燃发动机燃烧室高频燃烧稳定性有显著影响。
The bipropellant gas-liquid coaxial orifice-swirl injector has great effects on the high-frequency combustion instability of the LOX/kerosene staged combustion cycled engine.
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