火箭推进

固体火箭燃气超燃冲压发动机具有高比冲、结构简单、流量易调节等优点,然而在超音速空气流的补燃室中,如何让燃料更好地与空气掺混,增加颗粒停留时间,在较短时间内释放出更多的燃烧焓成为目前研究的重点。采用Realiazble k-ε湍流模型,单步涡团耗散模型,在King的硼颗粒点火燃烧模型的基础上考虑了硼颗粒在高速气流当中的气动剥离效应,利用龙格-库塔算法迭代计算硼颗粒点火燃烧过程,对燃气进气方向与轴向夹角从45°～180°的10种进气方式下的补燃室进行了三维两相燃烧流动计算,分析了各种进气角下的燃气燃烧效率、硼颗粒燃烧效率以及总燃烧效率。结果表明:当一次燃气喷射角度与轴向夹角逐渐增加时,燃气与颗粒燃烧效率逐渐增加,并在180°时燃烧效率和比冲为最高。

Solid rocket gas-fired scramjet has the advantages of high specific impulse,simple structure and easy flow adjustment. However,in the secondary combustion chamber with supersonic air flow,how to make the fuel mixed with air better,increase the residence time of gas and particles,and release more combustion enthalpy in a short time has become the focus of current research. Based on King's ignition and combustion model of boron particles,realiable k-ε turbulence model and single-step vortex dissipation model are adopted in this paper,and the aerodynamic stripping effect of boron particles in high-speed airflow is considered. The Runge Kutta algorithm is used to iteratively calculate the ignition and combustion process of boron particles. The three-dimensional two-phase combustion flow in the secondary combustion chamber under 10 intake modes with the angle between gas inlet direction and axial direction from 45° to 180° is calculated. In addition,the gas combustion efficiency under various intake angles,the combustion efficiency of boron particles and the overall combustion efficiency are analyzed. The results show that when the angle between the injection angle of primary gas and the axial angle increases gradually,the combustion efficiency of fuel gas and particles increases gradually,and the combustion efficiency and the specific impulse reach the highest at 180°.

引言
1 物理模型
2 计算模型
3 结果分析
4 结论

表1 各工况燃气喷射角度θ<br/>Tab.1 Gas injection angle θ under various working conditions

表1 各工况燃气喷射角度θ
Tab.1 Gas injection angle θ under various working conditions

图1 物理模型
Fig.1 Physical model

图2 各工况壁面温度分布云图<br/>Fig.2 Cloud image of wall temperature distribution under various working conditions

图2 各工况壁面温度分布云图
Fig.2 Cloud image of wall temperature distribution under various working conditions

图3 中心截面与沿轴向界面温度分布云图<br/>Fig.3 Cloud image of temperature distribution at central section and axial interface

图3 中心截面与沿轴向界面温度分布云图
Fig.3 Cloud image of temperature distribution at central section and axial interface

图4 补燃室头部马赫数分布云图<br/>Fig.4 Cloud image of Mach number distribution at the head of secondary combustion chamber

图4 补燃室头部马赫数分布云图
Fig.4 Cloud image of Mach number distribution at the head of secondary combustion chamber

图5 压力分布云图<br/>Fig.5 Cloud image of pressure distribution

图5 压力分布云图
Fig.5 Cloud image of pressure distribution

图6 颗粒粒径分布云图<br/>Fig.6 Cloud image of particle size distribution

图6 颗粒粒径分布云图
Fig.6 Cloud image of particle size distribution

图7 燃烧效率
Fig.7 Combustion efficiency

表2 各工况比冲与总压恢复系数<br/>Tab.2 Specific impulse and total pressure recovery coefficient under various working conditions

表2 各工况比冲与总压恢复系数
Tab.2 Specific impulse and total pressure recovery coefficient under various working conditions

图8 165°与180°的马赫数对比曲线图<br/>Fig.8 Mach number comparison curve at 165° and 180°

图8 165°与180°的马赫数对比曲线图
Fig.8 Mach number comparison curve at 165° and 180°

图9 165°与180°总压曲线图<br/>Fig.9 Curve of total pressure at 165° and 180°

图9 165°与180°总压曲线图
Fig.9 Curve of total pressure at 165° and 180°

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备注

引言

1 物理模型

2 计算模型

3 结果分析

4 结论

期刊信息