等离子体点火对脉冲爆轰发动机两相爆轰过程影响的研究
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摘要
脉冲爆轰发动机(Pulse Detonation Engine,简称PDE)是一种利用脉冲式爆轰波产生的高温、高压燃气来获得推力的新概念发动机。它具有热循环效率高、结构简单、重量轻、工作范围宽等特点,在未来的航空航天与兵器领域具有广阔的应用前景。等离子体点火具有点火能量大、能量转移效率高、可加速化学反应等特点,能够极大地缩短点火延迟时间和提高点火起爆成功率。本文以等离子体点火的液体燃料脉冲爆轰发动机为研究对象,根据脉冲爆轰发动机流场的特点,建立合理的数学物理模型,应用时空守恒元和求解元方法(简称CE/SE方法)进行数值求解,用Fortran语言编写程序,对脉冲爆轰发动机中等离子体点火和汽油／空气两相燃烧转爆轰过程进行了一维、二维、三维的数值模拟,并在此基础上,进行了相关的脉冲爆轰发动机实验研究。主要内容包括：
(1)建立了脉冲爆轰发动机中考虑等离子体点火的一维两相爆轰的数学物理模型,推导了相应的一维CE/SE方法计算格式,编写了相关计算程序,实现了对脉冲爆轰发动机中等离子体点火和气液两相燃烧转爆轰过程的数值模拟。
(2)建立了等离子体发生器内外流场的二维／轴对称数学物理模型,推导了二维含扩散项CE/SE方法的计算格式以及流场、电磁场参数耦合的雅可比系数矩阵,编写了相关计算程序,通过对耦合的流体力学方程与电磁学方程求解,实现了对等离子体发生器内外流场的数值模拟,获得了等离子体射流的温度、压力、速度等参数的变化规律。
(3)建立了考虑等离子体点火的脉冲爆轰发动机二维／轴对称两相爆轰的数学物理模型,采用CE/SE方法数值求解,编写了相关计算程序,实现了对脉冲爆轰发动机中等离子体点火和气液两相爆轰的二维／轴对称数值模拟,分析了两种等离子体点火位置对脉冲爆轰发动机点火起爆过程的影响。结果表明：点火位置对燃烧转爆轰过程有影响。采用壁面点火方式时,点火位置靠近推力壁可以缩短点火起爆的时间和距离。
(4)建立了脉冲爆轰发动机中考虑组分反应的二维／轴对称两相爆轰控制方程,采用CE/SE方法进行数值求解,编写了相关计算程序,分析了不同的等离子体射流能量和射流时间对点火起爆过程的影响以及考虑组分反应模型和不考虑组分反应模型在描述脉冲爆轰发动机点火起爆过程中的异同。结果表明：在一定范围内增加等离子体射流能量与射流时间可以缩短形成稳定爆轰波的时间和距离。在爆轰波形成之前,考虑组分反应模型能更为细致地反映管内流场变化；在稳定爆轰波形成之后,考虑组分反应模型和不考虑组分反应模型对爆轰波的描述基本相同。
(5)建立了等离子体点火的脉冲爆轰发动机三维数学物理模型,推导了三维CE/SE方法的计算格式,编写了相关计算程序,实现了对考虑点火室结构的脉冲爆轰发动机点火起爆过程的数值模拟,分析了不同进气速度条件下凹槽+单环片、凹槽+双环片点火室结构对点火起爆过程的影响以及三维模型和二维模型在脉冲爆轰发动机内反映流场时的异同。结果表明：在脉冲爆轰发动机中设置点火室可以显著降低点火位置的气流速度,并在点火室内形成大范围的高压区域。在10m/s～200m/s的填充气流速度下,凹槽+双环片点火室的点火起爆时间和距离距略小于凹槽+单环片点火室,随着气流速度的提高,两者间的差距逐渐缩小。随着爆轰管内填充气流速度提高,形成稳定爆轰波的时间和距离均缩短。在点火室区域波传播的三维效应非常明显,在稳定爆轰波形成之后,管内的三维效应不明显。
(6)建立了脉冲爆轰发动机中考虑组分反应的三维两相爆轰控制方程,采用CE/SE方法进行数值求解,编写了相关计算程序,比较了等离子体点火条件下在点火室局部形成的三种燃料/氧化剂配比对点火起爆过程的影响。结果表明：提高点火室局部氧气的质量浓度能在点火后加速化学反应速率,增强燃烧波强度,缩短点火起爆的时间和距离。同时增加点火室局部燃料和氧气的质量浓度则可以在初始阶段形成强度较弱的爆轰波,进一步缩短点火起爆的时间和距离。
(7)进行了以液态汽油/空气为工质、工作频率为10Hz～30Hz的脉冲爆轰发动机实验研究,通过改变点火室局部的燃料/氧化剂配比,得到了等离子体点火和常规火花点火条件下脉冲爆轰发动机的点火延迟时间、燃烧转爆轰时间和工作频率之间的关系。实验结果表明：随着脉冲爆轰发动机工作频率的提高,点火延迟时间逐渐减少。燃烧转爆轰时间基本不受工作频率的影响。等离子体的点火延迟时间小于常规火花点火的点火延迟时间,随着工作频率的提高,点火延迟时间减少的程度下降。在多种工作频率下,等离子体点火的燃烧转爆轰时间均略小于常规火花点火的燃烧转爆轰时间。提高点火室局部氧气质量浓度可以缩短点火延迟时间和燃烧转爆轰时间。
本文在国内首次将等离子体点火技术应用于脉冲爆轰发动机的点火起爆过程,分析了等离子体点火对脉冲爆轰发动机燃烧转爆轰过程的影响,研究了脉冲爆轰发动机中等离子体点火起爆的机理,实现了用等离子体点火起爆技术缩短燃烧转爆轰时间和距离的目的,对提高脉冲爆轰发动机的性能具有重要的理论意义和工程实际价值。
Pulse Detonation Engine (PDE) is an innovative propulsion system that utilizes repetitive detentions to produce thrust and power. It has a broad application prospect in future aerospace and weapon fields with the advantages of high thermal cycle efficiency, hardware simplicity, light weight and wide working scope. Plasma ignition has large ignition energy, high transfer efficiency and can accelerate chemical reaction rate, which can greatly shorten the ignition delay time and improve the success rate of ignition-detonation. The plasma ignition PDE with gasoline/air mixture was researched. The proper mathematical and physical models were built according to the flow characteristics. The governing equations were solved by CE/SE (the method of conservation element and solution element). The processes of plasma ignition and two-phase flow of detonation were simulated by one-dimensional, two-dimensional and three-dimensional numerical method. The main contents are as following.
(1)The One-dimensional two-phase detonation equations of plasma jet ignition were established. One-dimensional CE/SE was induced to simulate the processes of plasma jet ignition and two-phase DDT (Deflagration to Detonation Transition). The corresponding numerical calculation was programmed.
(2)The two-dimensional axial-symmetry mathematical and physical model of the internal and external flow field in plasma generator was established. The computing format of two-dimensional CE/SE with diffusion item was deduced to solve the coupled fluid dynamic equations and Maxwell equations. The variation of temperature, pressure and velocity of plasma jet were obtained.
(3)The two-dimensional/axisymmetric two-phase detonation mathematical and physical model of plasma ignition was established. The processes of plasma ignition and two-phase detonation were numerical simulated by CE/SE. The effects of two different ignition methods on ignition-detonation process were analyzed. The results show that the ignition position has an effect on DDT. When it's near the thrust wall, the time and distance of ignition-detonation can be shortened by radial ignition.
(4)The multicomponent two-dimensional/axisymmetric two-phase detonation equations were solved by CE/SE. The effects of different plasma jet time and jet energy on the ignition-detonation process were analyzed and discussed, and the similarities and differences were analyzed on condition that considering the multicomponent reaction model or not. The results show that increasing the energy and time of plasma jet can shorten the time and distance of forming stable detonation wave within certain scope. Before the detonation wave is formed, the two-phase detonation flow field is more meticulous reacted by considering the multicomponent reaction model, while after that, the discretions of the detonation wave are almost the same by considering the multicomponent reaction model or not.
(5)The three-dimensional mathematical and physical model of the plasma ignition was established. The computing format of three-dimensional CE/SE was deduced. The numerical simulation of ignition-detonation process was carried out by considering the ignition chamber structure. The influences of groove-single ring piece and groove-double ring piece ignition chambers structure on the ignition-detonation process were analyzed in different air inlet velocity. The similarities and differences between two-dimensional model and three-dimensional model were analyzed in reactions of the internal flow field. The results show that using ignition chamber can significantly reduce the airflow velocity in ignition position and form a wide range of high-pressure areas in the ignition chamber. In lOm/s-200m/s filled airflow velocity, the ignition-detonation time and distance of groove-double loop piece ignition chamber are shorter than that of groove-single ring piece ignition chamber. As air inlet velocity increases, the difference between them gradually reduces. The time and distance of developing steady detonation wave are shortened by increasing air inlet velocity. The three-dimensional effect of wave propagation in ignition chamber is very obvious, while the result is just the opposite after the steady detonation wave is formed.
(6)The multicomponent three-dimensional two-phase detonation equations were solved by CE/SE. The effects of three kinds of fuel/oxidant mass ratio on the ignition-detonation process which formed in the ignition local areas during plasma ignition were analyzed and compared. The results show that increasing the quality concentration of local oxygen in ignition areas can accelerate chemical reaction rate, enhance the combustion wave intensity and shorten the time and distance of ignition-detonation process. Meanwhile increasing the local fuel and oxygen concentration in ignition areas can form weak detonation wave at the beginning, which further shorten the time and distance of ignition-detonation process.
(7)The air breathing PDE which used gasoline/air was experimental researched under 10Hz-30Hz. By changing the fuel/oxidant mass ratio in the ignition local areas, the relationships among ignition delay time, DDT time and working frequency were obtained in plasma ignition and conventional spark ignition. The results show that the ignition delay time decreases when the working frequency increases. The DDT time is mainly free from the impact of working frequency. The ignition delay time of plasma ignition is less than that of conventional spark ignition, while the percentage of the reduced ignition delay time declines as the working frequency increases. The DDT time is slightly shorter than that of conventional spark ignition in all working frequency. Increasing the oxygen quality concentration can shorten the ignition delay time and DDT time.
In this thesis, the plasma ignition was first used in ignition-detonation progress of PDE in domestic.The effect of plasma ignition on ignition-detonation process was analyzed, the mechanism of plasma ignition was researched, the purpose to shorten the time and distance of combustion to detonation was achieved, all of which have great theoretical and practical value of improving the performance of PDE.
(1)建立了脉冲爆轰发动机中考虑等离子体点火的一维两相爆轰的数学物理模型,推导了相应的一维CE/SE方法计算格式,编写了相关计算程序,实现了对脉冲爆轰发动机中等离子体点火和气液两相燃烧转爆轰过程的数值模拟。
(2)建立了等离子体发生器内外流场的二维／轴对称数学物理模型,推导了二维含扩散项CE/SE方法的计算格式以及流场、电磁场参数耦合的雅可比系数矩阵,编写了相关计算程序,通过对耦合的流体力学方程与电磁学方程求解,实现了对等离子体发生器内外流场的数值模拟,获得了等离子体射流的温度、压力、速度等参数的变化规律。
(3)建立了考虑等离子体点火的脉冲爆轰发动机二维／轴对称两相爆轰的数学物理模型,采用CE/SE方法数值求解,编写了相关计算程序,实现了对脉冲爆轰发动机中等离子体点火和气液两相爆轰的二维／轴对称数值模拟,分析了两种等离子体点火位置对脉冲爆轰发动机点火起爆过程的影响。结果表明：点火位置对燃烧转爆轰过程有影响。采用壁面点火方式时,点火位置靠近推力壁可以缩短点火起爆的时间和距离。
(4)建立了脉冲爆轰发动机中考虑组分反应的二维／轴对称两相爆轰控制方程,采用CE/SE方法进行数值求解,编写了相关计算程序,分析了不同的等离子体射流能量和射流时间对点火起爆过程的影响以及考虑组分反应模型和不考虑组分反应模型在描述脉冲爆轰发动机点火起爆过程中的异同。结果表明：在一定范围内增加等离子体射流能量与射流时间可以缩短形成稳定爆轰波的时间和距离。在爆轰波形成之前,考虑组分反应模型能更为细致地反映管内流场变化；在稳定爆轰波形成之后,考虑组分反应模型和不考虑组分反应模型对爆轰波的描述基本相同。
(5)建立了等离子体点火的脉冲爆轰发动机三维数学物理模型,推导了三维CE/SE方法的计算格式,编写了相关计算程序,实现了对考虑点火室结构的脉冲爆轰发动机点火起爆过程的数值模拟,分析了不同进气速度条件下凹槽+单环片、凹槽+双环片点火室结构对点火起爆过程的影响以及三维模型和二维模型在脉冲爆轰发动机内反映流场时的异同。结果表明：在脉冲爆轰发动机中设置点火室可以显著降低点火位置的气流速度,并在点火室内形成大范围的高压区域。在10m/s～200m/s的填充气流速度下,凹槽+双环片点火室的点火起爆时间和距离距略小于凹槽+单环片点火室,随着气流速度的提高,两者间的差距逐渐缩小。随着爆轰管内填充气流速度提高,形成稳定爆轰波的时间和距离均缩短。在点火室区域波传播的三维效应非常明显,在稳定爆轰波形成之后,管内的三维效应不明显。
(6)建立了脉冲爆轰发动机中考虑组分反应的三维两相爆轰控制方程,采用CE/SE方法进行数值求解,编写了相关计算程序,比较了等离子体点火条件下在点火室局部形成的三种燃料/氧化剂配比对点火起爆过程的影响。结果表明：提高点火室局部氧气的质量浓度能在点火后加速化学反应速率,增强燃烧波强度,缩短点火起爆的时间和距离。同时增加点火室局部燃料和氧气的质量浓度则可以在初始阶段形成强度较弱的爆轰波,进一步缩短点火起爆的时间和距离。
(7)进行了以液态汽油/空气为工质、工作频率为10Hz～30Hz的脉冲爆轰发动机实验研究,通过改变点火室局部的燃料/氧化剂配比,得到了等离子体点火和常规火花点火条件下脉冲爆轰发动机的点火延迟时间、燃烧转爆轰时间和工作频率之间的关系。实验结果表明：随着脉冲爆轰发动机工作频率的提高,点火延迟时间逐渐减少。燃烧转爆轰时间基本不受工作频率的影响。等离子体的点火延迟时间小于常规火花点火的点火延迟时间,随着工作频率的提高,点火延迟时间减少的程度下降。在多种工作频率下,等离子体点火的燃烧转爆轰时间均略小于常规火花点火的燃烧转爆轰时间。提高点火室局部氧气质量浓度可以缩短点火延迟时间和燃烧转爆轰时间。
本文在国内首次将等离子体点火技术应用于脉冲爆轰发动机的点火起爆过程,分析了等离子体点火对脉冲爆轰发动机燃烧转爆轰过程的影响,研究了脉冲爆轰发动机中等离子体点火起爆的机理,实现了用等离子体点火起爆技术缩短燃烧转爆轰时间和距离的目的,对提高脉冲爆轰发动机的性能具有重要的理论意义和工程实际价值。
Pulse Detonation Engine (PDE) is an innovative propulsion system that utilizes repetitive detentions to produce thrust and power. It has a broad application prospect in future aerospace and weapon fields with the advantages of high thermal cycle efficiency, hardware simplicity, light weight and wide working scope. Plasma ignition has large ignition energy, high transfer efficiency and can accelerate chemical reaction rate, which can greatly shorten the ignition delay time and improve the success rate of ignition-detonation. The plasma ignition PDE with gasoline/air mixture was researched. The proper mathematical and physical models were built according to the flow characteristics. The governing equations were solved by CE/SE (the method of conservation element and solution element). The processes of plasma ignition and two-phase flow of detonation were simulated by one-dimensional, two-dimensional and three-dimensional numerical method. The main contents are as following.
(1)The One-dimensional two-phase detonation equations of plasma jet ignition were established. One-dimensional CE/SE was induced to simulate the processes of plasma jet ignition and two-phase DDT (Deflagration to Detonation Transition). The corresponding numerical calculation was programmed.
(2)The two-dimensional axial-symmetry mathematical and physical model of the internal and external flow field in plasma generator was established. The computing format of two-dimensional CE/SE with diffusion item was deduced to solve the coupled fluid dynamic equations and Maxwell equations. The variation of temperature, pressure and velocity of plasma jet were obtained.
(3)The two-dimensional/axisymmetric two-phase detonation mathematical and physical model of plasma ignition was established. The processes of plasma ignition and two-phase detonation were numerical simulated by CE/SE. The effects of two different ignition methods on ignition-detonation process were analyzed. The results show that the ignition position has an effect on DDT. When it's near the thrust wall, the time and distance of ignition-detonation can be shortened by radial ignition.
(4)The multicomponent two-dimensional/axisymmetric two-phase detonation equations were solved by CE/SE. The effects of different plasma jet time and jet energy on the ignition-detonation process were analyzed and discussed, and the similarities and differences were analyzed on condition that considering the multicomponent reaction model or not. The results show that increasing the energy and time of plasma jet can shorten the time and distance of forming stable detonation wave within certain scope. Before the detonation wave is formed, the two-phase detonation flow field is more meticulous reacted by considering the multicomponent reaction model, while after that, the discretions of the detonation wave are almost the same by considering the multicomponent reaction model or not.
(5)The three-dimensional mathematical and physical model of the plasma ignition was established. The computing format of three-dimensional CE/SE was deduced. The numerical simulation of ignition-detonation process was carried out by considering the ignition chamber structure. The influences of groove-single ring piece and groove-double ring piece ignition chambers structure on the ignition-detonation process were analyzed in different air inlet velocity. The similarities and differences between two-dimensional model and three-dimensional model were analyzed in reactions of the internal flow field. The results show that using ignition chamber can significantly reduce the airflow velocity in ignition position and form a wide range of high-pressure areas in the ignition chamber. In lOm/s-200m/s filled airflow velocity, the ignition-detonation time and distance of groove-double loop piece ignition chamber are shorter than that of groove-single ring piece ignition chamber. As air inlet velocity increases, the difference between them gradually reduces. The time and distance of developing steady detonation wave are shortened by increasing air inlet velocity. The three-dimensional effect of wave propagation in ignition chamber is very obvious, while the result is just the opposite after the steady detonation wave is formed.
(6)The multicomponent three-dimensional two-phase detonation equations were solved by CE/SE. The effects of three kinds of fuel/oxidant mass ratio on the ignition-detonation process which formed in the ignition local areas during plasma ignition were analyzed and compared. The results show that increasing the quality concentration of local oxygen in ignition areas can accelerate chemical reaction rate, enhance the combustion wave intensity and shorten the time and distance of ignition-detonation process. Meanwhile increasing the local fuel and oxygen concentration in ignition areas can form weak detonation wave at the beginning, which further shorten the time and distance of ignition-detonation process.
(7)The air breathing PDE which used gasoline/air was experimental researched under 10Hz-30Hz. By changing the fuel/oxidant mass ratio in the ignition local areas, the relationships among ignition delay time, DDT time and working frequency were obtained in plasma ignition and conventional spark ignition. The results show that the ignition delay time decreases when the working frequency increases. The DDT time is mainly free from the impact of working frequency. The ignition delay time of plasma ignition is less than that of conventional spark ignition, while the percentage of the reduced ignition delay time declines as the working frequency increases. The DDT time is slightly shorter than that of conventional spark ignition in all working frequency. Increasing the oxygen quality concentration can shorten the ignition delay time and DDT time.
In this thesis, the plasma ignition was first used in ignition-detonation progress of PDE in domestic.The effect of plasma ignition on ignition-detonation process was analyzed, the mechanism of plasma ignition was researched, the purpose to shorten the time and distance of combustion to detonation was achieved, all of which have great theoretical and practical value of improving the performance of PDE.
引文
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