再生式液体发射药火炮喷雾燃烧理论及数值模拟研究
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摘要
为深入认识再生式液体发射药火炮(Regenerative Liquid Propellant Gun,RLPG)喷雾燃烧过程,研究压力振荡的产生机理及抑制措施,本文从RLPG燃烧室一维颗粒轨道模型建模与仿真、高速环形射流破碎雾化机理、多维多相反应流动建模与仿真等方面,研究了RLPG膛内喷雾燃烧过程及压力振荡现象。具体研究内容如下:
建立了RLPG燃烧室一维颗粒轨道模型,气相控制方程采用非稳态欧拉方程组,液相用拉格朗日方法描述,方程组的源项反映了气液两相之间的耦合,研究了欧拉一拉格朗日混和方程的数值算法。数值模拟了RLPG喷雾燃烧过程和压力振荡现象,得到了物理参量的时空分布。通过小波分析提取燃烧室低频信号进行试验压力频谱分析,分析了仿真压力振荡的产生机理;通过改变再生喷射结构参数及采用不同型号的发射药等方法讨论了抑制燃烧室纵向压力振荡的有关措施。
研究了轴对称两维多相反应流动数值计算方法。推导了二维轴对称气相控制方程及液滴运动方程在任意曲线坐标系下的方程形式。为了便于采用有限差分法离散控制方程,采用贴体坐标系统,将燃烧室变换成计算空间内矩形区域,研究了两种贴体网格生成方法,并对RLPG燃烧室进行了网格划分。采用二阶精度的MacCormack预估校正两步差分格式离散气相控制方程,给出了稳定性条件和人工粘性条件。基于运动控制体方法推导了活塞端面处和弹底网格的差分格式。对于液滴控制方程采用了求解析解的方法计算,推导了计算公式。分析了源项的计算方法,给出了气液两相耦合源项的详细计算式。
基于液体射流表面波理论和线性稳定性分析,建立了RLPG高速环形射流破碎雾化模型,并考虑了液滴的二次雾化过程。应用此模型计算了环形射流喷雾形态和主要雾化特性参数,包括贯穿度、滴径时空分布等,并讨论了各主要因素对环形射流雾化性能的影响。计算结果表明,环形射流向喷嘴下游运动过程中内部空腔不断收缩,最终聚并成与圆柱形类似的射流向前运动,喷雾场前缘多为大颗粒液滴;在轴向某一固定位置,平均直径随时间逐渐减小并趋于一稳态值;在空间上平均直径随轴向距离的增加先减小后增大呈凹谷型分布;通过增大喷射压力和减小喷口间隙可改善射流的雾化效果。该模型的建立进一步完善了基于环形喷嘴的RLPG喷雾燃烧过程多维多相流数学模型。
对RLPG再生喷射过程进行了试验研究,得到了燃烧室压力振荡信号,讨论了试验数据的信号处理方法。编写了RLPG喷雾燃烧过程多维多相流数值计算程序,考虑了环形射流的破碎雾化过程。通过数值模拟得到了二维条件下燃烧室热态流场中的射流形态,及各物理参量的时空分布规律。模拟出了燃烧室大幅高频压力振荡现象,通过分析燃烧室声学特性可知,压力振荡主振型为径向二阶振型,仿真结果与试验压力频谱分析结果基本吻合。从液体药燃烧稳定性和燃烧室内声学过程两方面分析了压力振荡的产生机理,讨论了压力振荡的抑制措施。
In order to better understand the spray combustion process and the phenomenon of pressure oscillation in regenerative liquid propellant guns (RLPGs), this dissertation studies the jets spray combustion theory and pressure oscillation mechanism. It is compused of following aspects: the modeling and simulation of one dimensional particle trajectory model in the combustion chamber, the high-speed annular jets atomization mechanism, and the modeling and simulation of multiphase multidimensional flow in chamber. The main content of this paper can be summarized as follows:
Firstly, a particle trajectory model of the combustion chamber of an RLPG is established, the gas field is described by unsteady Euler system while the liquid phase is described by the Lagrangian approach. The interaction of the two phases is expressed in the source terms of the equations. The numerical methods for the Euler and Lagrangian coupling euqations is studies. The spray combustion process is simulated by the code written by the author and the high-frequency oscillations are generated naturally. The time-space distributions of main physical parameters are analyzed. The low frequency signal of experimental data is extracted by the technique of wavelet method which is analysed by FFT and the mechanism of pressure oscillations simulated is analyzed. The effects of main structure parameters on the pressure oscillations are discussed.
The numerical method of an axially symmetric two-dimensional multiphase reaction flow is established. The form of gas phase governing equations in arbitrary curve coordinate system is derived. Due to the flow field is irregular in RLPG, the combustion chamber is transformed to the rectangular field in computational plane under boundary-fitted coordinate system. Two ways of boundary-fitted grids generation are applied to generate grids in the combustion chamber. The calculation is conducted with MacCormack's two steps of predicted-correction scheme. The stability condition and artifical viscosity are presented. The difference scheme for the two movement boundaries of piston and projectile are deduced, which ensure the physical conservation at these boundaries. The analytic method is used for calculating the liquid phase. The numerical method of source terms is analyzed and the calculating equations are presented in detail.
A high-speed liquid sheet spray model is presented for the annular jets in RLPG based on the linear stability analysis and surface wave breakup theory. In addition to the jets atomization, the drops breakup (secondary breakup) is considered. According to the above spray model, the spray structure and spray characteristic parameters are calculated and the influence of main spray factor on the spray characteristic parameters is studied simultaneously. The result indicates that the interior cavity of the annular jet keeps constriction, and gather like column ones finally while the annular jet moving down the injector orifice. There are mostly large droplets at the head of the spray field. The mean droplet diameter decreases with increase of time at a given cross section. The mean diameter decreases with increase of axial distance firstly, and increases later. It is distributed in valley form. The atomization effect can be improved by increasing injection pressure or decreasing the injector orifice size. The spray model is an important part of the interior ballistic multiphase multidimensional model of RLPG and will be used for the interior ballistic simulation.
The experimental research of RLPG spray combustion process is carried out and the signal of pressure oscillations in combustion chamber is obtained. The signal process method of wavelet analysis is applied to analyze the experimental data. To better understand and reduce pressure oscillations, a multiphase multidimentional model named SACFIG has been written for the spray combution process in the chamber. The annular jet spray model has been used for the two-dimentional code. The hot spray structure and time-space distributions of main physical parameters under two-dimentional condition are gained. The high-frequency combustion instability is generated in the combustion chamber. The dominant mode of computational pressure oscillation is the second radial mode which coincides with the experiment data well. The mechanisms of the pressure oscillations are studied by two aspects: acoustic process in the chamber and combustion instability. The suppression measures of pressure oscillations are discussed finally.
建立了RLPG燃烧室一维颗粒轨道模型,气相控制方程采用非稳态欧拉方程组,液相用拉格朗日方法描述,方程组的源项反映了气液两相之间的耦合,研究了欧拉一拉格朗日混和方程的数值算法。数值模拟了RLPG喷雾燃烧过程和压力振荡现象,得到了物理参量的时空分布。通过小波分析提取燃烧室低频信号进行试验压力频谱分析,分析了仿真压力振荡的产生机理;通过改变再生喷射结构参数及采用不同型号的发射药等方法讨论了抑制燃烧室纵向压力振荡的有关措施。
研究了轴对称两维多相反应流动数值计算方法。推导了二维轴对称气相控制方程及液滴运动方程在任意曲线坐标系下的方程形式。为了便于采用有限差分法离散控制方程,采用贴体坐标系统,将燃烧室变换成计算空间内矩形区域,研究了两种贴体网格生成方法,并对RLPG燃烧室进行了网格划分。采用二阶精度的MacCormack预估校正两步差分格式离散气相控制方程,给出了稳定性条件和人工粘性条件。基于运动控制体方法推导了活塞端面处和弹底网格的差分格式。对于液滴控制方程采用了求解析解的方法计算,推导了计算公式。分析了源项的计算方法,给出了气液两相耦合源项的详细计算式。
基于液体射流表面波理论和线性稳定性分析,建立了RLPG高速环形射流破碎雾化模型,并考虑了液滴的二次雾化过程。应用此模型计算了环形射流喷雾形态和主要雾化特性参数,包括贯穿度、滴径时空分布等,并讨论了各主要因素对环形射流雾化性能的影响。计算结果表明,环形射流向喷嘴下游运动过程中内部空腔不断收缩,最终聚并成与圆柱形类似的射流向前运动,喷雾场前缘多为大颗粒液滴;在轴向某一固定位置,平均直径随时间逐渐减小并趋于一稳态值;在空间上平均直径随轴向距离的增加先减小后增大呈凹谷型分布;通过增大喷射压力和减小喷口间隙可改善射流的雾化效果。该模型的建立进一步完善了基于环形喷嘴的RLPG喷雾燃烧过程多维多相流数学模型。
对RLPG再生喷射过程进行了试验研究,得到了燃烧室压力振荡信号,讨论了试验数据的信号处理方法。编写了RLPG喷雾燃烧过程多维多相流数值计算程序,考虑了环形射流的破碎雾化过程。通过数值模拟得到了二维条件下燃烧室热态流场中的射流形态,及各物理参量的时空分布规律。模拟出了燃烧室大幅高频压力振荡现象,通过分析燃烧室声学特性可知,压力振荡主振型为径向二阶振型,仿真结果与试验压力频谱分析结果基本吻合。从液体药燃烧稳定性和燃烧室内声学过程两方面分析了压力振荡的产生机理,讨论了压力振荡的抑制措施。
In order to better understand the spray combustion process and the phenomenon of pressure oscillation in regenerative liquid propellant guns (RLPGs), this dissertation studies the jets spray combustion theory and pressure oscillation mechanism. It is compused of following aspects: the modeling and simulation of one dimensional particle trajectory model in the combustion chamber, the high-speed annular jets atomization mechanism, and the modeling and simulation of multiphase multidimensional flow in chamber. The main content of this paper can be summarized as follows:
Firstly, a particle trajectory model of the combustion chamber of an RLPG is established, the gas field is described by unsteady Euler system while the liquid phase is described by the Lagrangian approach. The interaction of the two phases is expressed in the source terms of the equations. The numerical methods for the Euler and Lagrangian coupling euqations is studies. The spray combustion process is simulated by the code written by the author and the high-frequency oscillations are generated naturally. The time-space distributions of main physical parameters are analyzed. The low frequency signal of experimental data is extracted by the technique of wavelet method which is analysed by FFT and the mechanism of pressure oscillations simulated is analyzed. The effects of main structure parameters on the pressure oscillations are discussed.
The numerical method of an axially symmetric two-dimensional multiphase reaction flow is established. The form of gas phase governing equations in arbitrary curve coordinate system is derived. Due to the flow field is irregular in RLPG, the combustion chamber is transformed to the rectangular field in computational plane under boundary-fitted coordinate system. Two ways of boundary-fitted grids generation are applied to generate grids in the combustion chamber. The calculation is conducted with MacCormack's two steps of predicted-correction scheme. The stability condition and artifical viscosity are presented. The difference scheme for the two movement boundaries of piston and projectile are deduced, which ensure the physical conservation at these boundaries. The analytic method is used for calculating the liquid phase. The numerical method of source terms is analyzed and the calculating equations are presented in detail.
A high-speed liquid sheet spray model is presented for the annular jets in RLPG based on the linear stability analysis and surface wave breakup theory. In addition to the jets atomization, the drops breakup (secondary breakup) is considered. According to the above spray model, the spray structure and spray characteristic parameters are calculated and the influence of main spray factor on the spray characteristic parameters is studied simultaneously. The result indicates that the interior cavity of the annular jet keeps constriction, and gather like column ones finally while the annular jet moving down the injector orifice. There are mostly large droplets at the head of the spray field. The mean droplet diameter decreases with increase of time at a given cross section. The mean diameter decreases with increase of axial distance firstly, and increases later. It is distributed in valley form. The atomization effect can be improved by increasing injection pressure or decreasing the injector orifice size. The spray model is an important part of the interior ballistic multiphase multidimensional model of RLPG and will be used for the interior ballistic simulation.
The experimental research of RLPG spray combustion process is carried out and the signal of pressure oscillations in combustion chamber is obtained. The signal process method of wavelet analysis is applied to analyze the experimental data. To better understand and reduce pressure oscillations, a multiphase multidimentional model named SACFIG has been written for the spray combution process in the chamber. The annular jet spray model has been used for the two-dimentional code. The hot spray structure and time-space distributions of main physical parameters under two-dimentional condition are gained. The high-frequency combustion instability is generated in the combustion chamber. The dominant mode of computational pressure oscillation is the second radial mode which coincides with the experiment data well. The mechanisms of the pressure oscillations are studied by two aspects: acoustic process in the chamber and combustion instability. The suppression measures of pressure oscillations are discussed finally.
引文
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