双模式放电中DBD放电参数对甲烷滑动弧火焰光谱及活性粒子的影响分析

对未燃烧的可燃混合气体进行DBD放电,放电后会产生大量的活性粒子,这些活性粒子可以辅助气体燃烧,达到提高燃料燃烧利用率等目的。以DBD激励氩气、甲烷、空气产生的自由基（CH基和OH基）等强化燃烧的关键活性粒子为探索对象,研究DBD放电激励甲烷对滑动弧火焰的影响。为此,采用自主设计的DBD-滑动弧双模式等离子体激励器,利用同轴介质阻挡放电结构对氩气、甲烷、空气混合气进行放电激励,将激励后的氩气、甲烷、空气混合气通入滑动弧端进行点火。固定氩气流量不变,调整空气流量为4.76 L·min-1,并加入甲烷0.5 L·min-1,保证进气通道内氩气与空气-甲烷的气体体积流量比达到Ar∶（CH₄+Air）=1∶30,其中空气、甲烷这两种气体达到了化学燃烧当量比φ=1,氩气、甲烷、甲烷混合气体能实现均匀而稳定的放电并燃烧。DBD段放电电压在15～20 kV范围变化,放电频率在6～10 kHz范围变化,滑动弧段的电压和频率分别保持4 kV与10 kHz恒定,通过改变DBD段放电电压和放电频率,用高速光纤光谱仪检测滑动弧火焰中自由基种类及其光谱强度,分析放电参数激励甲烷对火焰中自由基（CH基和OH基）的影响。结果表明,DBD段放电电压及放电频率的增加可以促进火焰内部的偶联反应发生,可有效提升甲烷滑动弧火焰内部的活性粒子含量,其中OH基团、CH基团在燃烧链式化学反应进程中发挥着较为重要的作用。甲烷经过DBD激励后,随放电电压和频率的增加,火焰中OH基、CH基等主要活性粒子都随之增加。DBD放电后,活性粒子的光谱强度增大,特征谱线比单模式更加明显;甲烷经过DBD激励后,火焰组成发生了变化,滑动弧段出口处甲烷燃烧反应更加充分,火焰温度越高越容易产生OH基。与单模式滑动弧相比,双模式放电可有效促进火焰内部的链式化学反应进程,促进燃料燃烧。     

两电极等离子体合成射流激励器工作特性研究

采用放电测量和高速阴影技术对两电极等离子体合成射流激励器工作特性进行了系统实验研究.实验表明:激励器工作击穿电压和放电峰值电流随激励器所处环境压强的降低和放电频率的增大而减小,激励器腔体内的放电过程为火花电弧放电.典型的等离子体合成射流流场包含有一道前驱激波和一股呈蘑菇状的高速射流.在整个射流发展过程中,前驱激波以当地声速恒速传播,不随激励器条件的改变而变化,波的强度则随着激励器出口直径的减小、腔体体积的增大、环境压强的降低和放电频率的升高而减小.激励器腔体体积和放电频率的增加会降低腔内气体的加热效果,并减小射流速度.激励器出口直径和环境压强对射流速度的影响按规律变化且存在最佳值.本文实各验条件下激励器都产生了明显的前驱激波和高速射流,具有实现高速流场主动流动控制的应用潜能.     

甲烷在空气燃烧的等离子体射流助燃效应的光谱研究

大气压氩等离子体射流是一种非平衡等离子体,能够产生大量的电子、离子、激发态粒子和活性基团,在燃烧过程中这些粒子的参与能够大大降低化学反应的活化能,而等离子体射流的动力学效应影响粒子输运过程,使得等离子体射流具有一定程度的辅助燃烧效果。本实验通过发射光谱测量,分别识别出了在非预混和预混的甲烷燃烧过程参与燃烧的中间物种（OH,CH和C₂）,测量了这些自由基的发射光谱强度随着外部控制变量（放电电压、混合当量比）变化的规律。对于非预混情况,实验发现随着产生等离子体射流放电电压的增大,火焰总体长度变短,火焰面出现褶皱,火焰根部蓝色区域面积不断扩大,在22 kV时,大约占总火焰面积的1/2。对火焰根部的发射光谱测量结果表明,当电压达到16 kV时,发射光谱明显增强,而当电压进一步增大到22 kV时,这些自由基粒子的光谱强度却出现下降,这归因于在等离子体产生的电离风作用下管内气体流速增大,导致燃烧区发生移动远离喷口,使采集到的火焰根部区域变小造成的。另外,研究了在不同的燃料当量比下等离子体射流对预混气体助燃的过程,实验发现燃料当量比为2时,OH(A-X)的光谱发射强度随电压的增大而增强而CH(A-X)和C₂(d)的发射强度在等离子体射流直接作用的情况下减小,反映了在氩等离子体射流参与助燃下燃烧变得更加充分了。实验发现等离子体射流产生大量的自由基以及等离子体电离风对混合过程的影响能够对燃烧过程产生明显影响。     

大气压等离子体射流中振转温度的发射光谱研究

通过发射光谱对大气压氦等离子体射流三个不同位置进行测量, 并采用光谱拟合获得氮气分子振转温度的方法, 研究了放电电压和气体流量以及离喷口的距离对射流的温度和化学活性的影响。发现大气压等离子体射流的气体温度和振动温度均随着放电电压增加而升高, 随着气体流量的增大而降低, 随着离喷口距离的增加而降低并逐步趋于稳定。通过对等离子体射流中振动温度的变化趋势并结合活性成分氧原子光谱强度的变化证实了等离子体射流的活性亦随着气体流量及离喷口距离的增大而降低, 随着放电电压增加而升高的结论。     

低功率电弧放电辅助甲烷燃烧的实验研究

利用低功率电弧放电辅助甲烷燃烧,研究了在不同甲烷/空气比例的情况下,等离子体对甲烷燃烧的影响。采用发射光谱仪进行光谱诊断,比较有/无等离子体辅助甲烷燃烧火焰发射光谱的异同,讨论了等离子体辅助燃烧可能发生的过程和机理。比较有/无等离子体辅助甲烷燃烧火焰温度的变化。利用气相色谱和烟气分析仪对甲烷燃烧产物中的CH₄、CO 和O₂ 进行分析。实验结果表明,加等离子体后,火焰的温度升高,尾气中的可燃性成分减少,氧气含量降低,在很大程度上提高了甲烷的燃烧效率;甲烷/空气的比例越低,燃烧效率的提高越明显;甲烷的富燃燃烧极限从16%调高到21%。     

多相等离子体气动激励流动特性

 等离子体激励器电极组相位不同便产生多相等离子体气动激励,建立了粒子图像测速仪流场参数测试系统,利用粒子图像测速仪技术,研究了非对称布局等离子体气动激励诱导空气流动特性,分析了多相等离子体气动激励对诱导空气流动速度的影响。结果表明：粒子图像测速仪流场测试系统能够准确地反映等离子体气动激励诱导空气流动的流场空间结构,等离子体气动激励诱导空气流动是平行于激励器的近壁面射流,多相等离子体气动激励能够增大等离子体气动激励诱导气流速度,或者使等离子体气动激励影响流场区域增大。粒子图像测速仪系统是深入研究等离子体气动激励的流场结构最佳的方式之一。     

Ar/CH4等离子体射流发射光谱诊断研究

为了更加深入的研究大气压条件下Ar/CH₄等离子体射流的放电机理和其内部电子的状态,通过自主设计的针-环式介质阻挡放电结构,在放电频率10 kHz、一个大气压条件下产生了稳定的Ar/CH₄等离子体射流,并利用发射光谱法对其进行了诊断研究。对大气条件下Ar/CH₄等离子体射流的放电现象及内部活性粒子种类进行诊断分析,重点研究了不同氩气甲烷体积流量比、不同峰值电压对大气压Ar/CH₄等离子体射流电子激发温度、电子密度以及CH基团活性粒子浓度的影响规律。结果表明,大气压条件下Ar/CH₄等离子体射流呈淡蓝色,在射流边缘可观察到丝状毛刺并伴有刺耳的电离声同时发现射流尖端的形态波动较大;通过发射光谱可以发现Ar/CH₄等离子体射流中的主要活性粒子为CH基团,C,CⅡ,CⅢ,CⅣ,ArⅠ和ArⅡ,其中含碳粒子的谱线主要集中在400~600 nm之间,ArⅠ和ArⅡ的谱线分布在680~800 nm之间;可以发现CH基团的浓度随峰值电压的增大而增大,但CH基团浓度随Ar/CH₄体积流量比的增大而减小,同时Ar/CH₄等离子体射流中C原子的浓度随之增加,这表明氩气甲烷体积流量比的增大加速了Ar/CH₄等离子体射流中C-H的断裂,因此可以发现增大峰值电压与氩气甲烷体积流量比均可明显的加快甲烷分子的脱氢效率,但增大氩气甲烷体积流量比的脱氢效果更加明显。通过多谱线斜率法选取4条ArⅠ谱线计算了不同工况下的电子激发温度,求得大气压Ar/CH₄等离子体射流的电子激发温度在6 000~12 000 K之间,且随峰值电压与氩气甲烷体积流量比的增大均呈现上升的趋势;依据Stark展宽机理对Ar/CH₄等离子体射流的电子密度进行了计算,电子密度的数量级可达1017 cm-3,且增大峰值电压与氩气甲烷体积流量比均可有效的提高射流中的电子密度。这些参数的探索对大气压等离子体射流的研讨具有重大意义。     

大气压低温氦等离子体射流的诊断研究

为了加快低温氦气等离子体射流的工程化进程,通过自主设计的同轴式介质阻挡放电等离子体射流发生器,在放电频率10 kHz,一个大气压条件下产生了稳定的氦气等离子体射流。通过分析不同工况下的电压电流波形可以发现单纯增加氦气体积流量只能小幅的增加电流脉冲幅值,而对放电时间、电流脉冲数的影响不大。增加放电峰值电压时电流脉冲幅值会得到较大幅度增加。通过发射光谱法对大气压氦气等离子射流的活性粒子种类、电子激发温度、电子密度进行了诊断。结果表明,大气压氦气等离子体射流中的主要活性粒子为He Ⅰ原子、N₂第二正带系、N+₂的第一负带系、羟基（OH）,H原子的巴尔末线系（H_α和H_β）与O原子,这表明虽然该试验中使用的氦气纯度已达99.99%,但其中仍残留有少量的空气,同时放电时大气中的空气会被卷吸到放电空间发生电离。还可以发现,主要活性粒子的相对光谱强度随氦气体积流量的增加及放电峰值电压的增大均呈现上涨的趋势。选用He Ⅰ原子的四条谱线对不同试验工况下的电子激发温度进行了计算,得到大气压氦气等离子体射流的电子激发温度在3 500~6 300 K之间,电子激发温度随放电峰值电压与氦气体积流量的增大总体上呈现上升的趋势。但由于反向电场的存在,某些峰值电压可能会出现电子激发温度下降的情况;根据Stark展宽原理对大气压氦气等离子体射流的电子密度进行了计算,发现电子密度的数量级可达1015 cm-3,同时增大峰值电压与氦气体积流量均可有效的提高射流中的电子密度。这些参数的研究对氦气等离子体射流在工程实际中的应用具有重要意义。     

甲烷/氧气层流同轴射流扩散火焰OH*自由基的数值研究

OH*自由基是火焰中主要的激发态自由基之一,它所产生的化学发光可用于描述火焰的结构、拉伸率、氧燃当量比和热释放速率等特征信息,因此被广泛应用于火焰燃烧状态的在线诊断。以甲烷/氧气层流同轴射流扩散火焰作为研究对象,采用GRI-Mech 3.0机理结合OH*自由基生成和淬灭反应进行数值计算,对OH*自由基的二维分布特性进行研究,分析不同区域内OH*自由基的生成路径,并探讨不同氧燃当量比例和不同喷嘴出口尺寸对OH*自由基强度和分布特性的影响。模拟结果与实验研究基本吻合,表明计算模型能够准确描述火焰中OH*自由基的二维分布。结果表明：在甲烷/氧气层流同轴射流扩散火焰中,OH*自由基存在两种不同形态的分布区域,分别由反应CH+O₂=OH*+CO和H+O+M=OH*+M生成;随着氧燃当量比提高,OH*自由基的分布区域逐渐向火焰下游扩张,根据其分布形态的变化可以对火焰燃烧状况进行判断;如果OH*自由基仅分布于火焰的上游区域且呈断开形态,则说明火焰处于贫氧燃烧状态。如果OH*分布呈环状形态,则说明火焰处于富氧燃烧状态;相同氧气流量条件下,缩小喷嘴出口的环隙尺寸有助于加强燃料和氧气的化学反应程度,从而使火焰中OH*自由基的摩尔分数显著提高,增强OH*化学发光的辐射强度,提高火焰光谱诊断的准确性。     

激波/边界层干扰对等离子体合成射流的响应特性

利用高速纹影系统和数值模拟方法研究了激波/边界层干扰对逆流喷射的等离子体合成射流的响应特性,并揭示了流动控制机理.实验在来流马赫数Ma=3.1的风洞中进行,测试模型采用钝头体和压缩斜坡的组合模型,等离子体合成射流激励器安装在钝头体头部.纹影系统捕捉了放电频率为f=1 kHz和f=3 kHz的激励对附体激波形态和分离激波运动的控制效果.等离子体合成射流使压缩斜坡激波/边界层干扰区域的起始点向下游移动,分离泡尺寸减小,附体激波强度减弱,发生弯曲,再附点移向上游,与此同时分离激波向附体激波逼近.与f=3 kHz激励相比,f=1 kHz激励的射流流量更大,对激波/边界层干扰的影响范围更广、控制效果更好.通过数值模拟,揭示了射流与来流相互作用对下游流场的作用机理:射流与来流相互作用诱导出大尺度旋涡,大尺度旋涡耗散发展增强了近壁面流场的湍流度;压缩斜坡上游近壁面的流场性质发生变化,进而导致了压缩斜坡激波/边界层干扰区域流动的变化.     

大气压氩气射流等离子体的光谱特性研究

等离子体喷枪是一种重要的等离子体源,已成为近几年低温等离子体研究的一个重要课题。本文利用钨针-钨丝网电极制作了直流喷枪装置,在大气压空气中产生了稳定的等离子体羽,并采用发射光谱的方法,对等离子体羽的等离子体参数进行了研究。在钨针电极与钨丝网电极之间放出耀眼的白光,钨丝网电极出口的气流下游有火苗形状的等离子体羽喷出。在电压保持不变的条件下(13.5 kV),等离子体羽长度随气体流量增加而增大;在气体流量保持不变的条件下(10 L·min-1),羽长度随外加电压的增大而增大。在气体流量一定的条件下,放电电压和放电电流呈反比例关系,即电压随着电流的增大而减小,说明放电属于辉光放电。采集了该喷枪在300～800 nm范围内的放电发射光谱,通过玻尔兹曼方法对放电等离子体电子激发温度进行了测量。结果表明,电子的激发温度随外加电压的增大而降低,随着工作气体流量的减小而升高。利用放电的基本理论对上述现象做了解释。这些研究结果对大气压均匀放电等离子体源的研制和工业应用具有重要意义。     

Temperature measurement of a premixed radially symmetric methane flame jet using the Mach-Zehnder Interferometry

The temperature field of a premixed methane symmetric laminar flame jet is visualized by studying the interferograms of the flame, using the Mach-Zehnder Interferometry. Two kinds of oxidizers are chosen for combustion: industrially pure oxygen and oxygen-enriched air. The flame is chosen to be both lean, and rich. For the lean oxygen-enriched combustion (OEC), the equivalence ratio was held constant at 0.5, and the oxygen enrichment was adjusted to 0.5 and 0.6, and for rich OEC, equivalence ratio is chosen to be 1.2 while the oxygen enrichment was 0.7 and 0.8. For methane/oxygen combustion, the equivalence ratio varied from 0.35 to 0.55 for the lean flame, and 1.3 and 1.7 for the rich flame. Attempt was made to keep the Reynolds number unchanged at 500, for OEC, and 1000, for methane/oxygen flame. In the present study a non-contact method is successfully developed to measure the temperature field of a premixed radially symmetric laminar methane flame jet. The effect of oxygen enrichment and equivalence ratio on temperature field is also investigated and depicted.     

Effect of pressure on the performance of plasma synthetic jet actuator

The effects of the ambient air pressure level on the performance of plasma synthetic jet actuator have been investigated through electrical and optical diagnostics.Pressures from 1 atm down to 0.1 atm were tested with a 10 Hz excitation.The discharge measurement demonstrates that there is a voltage range to make the actuator work reliably.Higher pressure level needs a higher breakdown voltage,and a higher discharge current and energy deposition are produced.But when the actuator works with the maximum breakdown voltage,the fraction of the initial capacitor energy delivered to the arc is almost invariable.This preliminary study also confirms the effectiveness of the plasma synthetic jet at low pressure.Indeed,the maximum velocities of the precursor shock and the plasma jet induced by the actuator with maximum breakdown voltage are independent of the ambient pressure level;reach about 530 and 460 m/s respectively.The mass flux of the plasma jet increases with ambient pressure increasing,but the strength of the precursor shock presents a local maximum at 0.6 atm.     

Numerical study of the effect of turbulence on rate of reactions in the MILD combustion regime

In this paper, the importance of fluctuations in flow field parameters is studied under MILD combustion conditions. In this way, a turbulent non-premixed CH₄+H₂ jet flame issuing into a hot and deficient co-flow air is modeled using the RANS Axisymmetric equations. The modeling is carried out using the EDC model to describe the turbulence-chemistry interaction. The DRM-22 reduced mechanism and the GRI2.11 full mechanism are used to represent the chemical reactions of H₂/methane jet flame. Results illustrate that although the fluctuations in temperature field are small and the reaction zone volume are large in the MILD regime, the fluctuations in temperature and species concentrations are still effective on the flow field. Also, inappropriate dealing with the turbulence effect on chemistry leads to errors in prediction of temperature up to 15% in the present flame. By decreasing of O₂ concentration of hot co-flow air, the effect of fluctuations in flow field parameters on flame characteristics are still significant and its effect on species reaction rates does not decrease. On the other hand, although decreasing of jet inlet Reynolds number at constant inlet turbulence intensity addresses to smaller fluctuations in flow filed, it does not lead to lower the effect of turbulence on species distribution and temperature field under MILD combustion conditions.     

Experimental and kinetic investigations of the effect of H2/CH4/C2H4 addition on the burning properties of practical jet fuel

Laminar flame speeds of premixed jet fuel/air with the addition of hydrogen, methane and ethylene are measured in a constant-volume bomb at an initial temperature of 420 K, initial pressure of 3 atm, equivalence ratios of 0.6–1.5 and gas mass fractions of 0–50%. The experimental results show that the addition of hydrogen and ethylene can significantly improve the laminar flame speed of the liquid jet fuel, while the addition of methane shows a weak inhibitory effect, and these effects are relatively remarkable on the fuel-rich conditions. The laminar flame speed of the dual fuels/air is linearly dependent on the additional gas mass fraction. A kinetic analysis indicates that the gas addition causes both thermodynamic and chemical kinetic effects on the laminar flame speed of the dual fuels/air. The adiabatic temperature increases and decreases with the addition of hydrogen/ethylene and methane, respectively. A sensitivity analysis shows that the reactions concerning to the H, CH₃ and C₂H₃ radicals become significant with the addition of hydrogen, methane and ethylene, respectively, and that the different values of the rate of product (ROP) of these species via the critical reactions lead to a different promotional or inhibitory effect on the fuel-rich and fuel-lean conditions.     

Active plasma grid for on-demand airflow mixing increase

The present paper concerns the electromechanical characterization of an actuator composed of a ceramic plate perforated by 121 holes housing embedded and printed electrodes between which a high voltage is applied. The electrode arrangement is such that the holes where the gas flows are surrounded by surface discharges. Electrical measurements and iCCD images show that the discharge behaves as a typical surface dielectric barrier discharge with streamer and glow regimes during one period of the AC sine voltage. Particle image velocimetry has been used to measure the jet flow produced by the discharge. The plasma discharge is at the origin of a wall jet with mean velocity of about 2.2 m/s, oriented from the active electrode to the grounded one. The capability of this discharge for promoting mixing by reducing the length of the jet core is demonstrated for flow velocities from 20 up to 60 m/s. In all the tested cases, the actuator can improve the mixing downstream of the perforated plate, when periodic perturbations are imposed at the jet column mode (St_D = 0.3).     

等离子体激励器的静特性与高速特性仿真研究

A parametric study of high-frequency plasma jet actuator was carried out, using the experiment- tally measured energy distribution law of arc discharge as an ideal heat source. The influence of the exit angle of the actuator on the flow field was explored. The jet flow field characteristics of the spark discharge actuator under supersonic flow (Ma0=2.0) were investigated. The results show that the energy density of heat flux increases and the jet front and forward shock wave moves faster with the decrease of discharge region, and the smaller the exit angle of the jet is, the stronger the momentum injection ability of the actuator along the flow direction is. The rule still applies under high-speed air flow conditions. Compared to the static condition, the momentum injection capability of the jet is stronger and the influence domain is larger under supersonic flow conditions.