压电陶瓷激励影响燃气燃烧器性能的实验研究

应用热线风速仪和TESTO360烟气分析仪分别对压电陶瓷激励下燃气燃烧器冷、热态情况进行了测量,主要考察了压电陶瓷激励频率、幅值对掺混区域速度场、燃烧器出口NOx生成量和温度分布的影响。实验结果表明,各种频率的压电陶瓷激励对助燃风流动及其与天然气的掺混都有一定效果,但千赫兹量级的激励频率的激励效果更为明显一些,且激励造成的时均速度变化程度要弱于湍流度变化。压电陶瓷激励下,燃烧器NOx生成量和燃烧温度均有所提高,表明燃烧更趋完全。     

合成射流控制策略对垂直轴风力机性能影响研究

设计一种斜出口合成射流激励器并将其应用于垂直轴风力机控制其动态失速,建立不同射流孔数量的叶片并采用5种不同合成射流激励器控制策略,通过FLUENT15.0并采用Realizable k-ε湍流模型分析射流孔数量与控制策略对垂直轴风力机气动性能的影响,进一步研究垂直轴风力机涡量场结构。结果表明:当采用上开口抛物线控制策略、射流吹气系数为0.035,射流孔数量为2时,风能利用系数与平均力矩系数均提升15.2%,随着射流孔数量增多,气动性能降低;采用传统合成射流控制策略的垂直轴风力机承受近乎2倍的载荷波动,改进的控制策略可减小叶片在小攻角时的载荷波动,从而相对提升垂直轴风力机的运行稳定性;另外,合成射流技术可抑制叶片吸力面大涡的生成与发展并使叶片强尾涡削弱成多个小尾涡,减小多个叶片间的流动干扰并降低转轴尾涡强度,从而改善全局流场结构。     

旋流对同轴富氧扩散燃烧NOx排放的影响

对30%～40%的氧浓度下甲烷富氧空气同轴扩散燃烧的火焰形态、可见火焰高度、燃烧特性以及NOx排放进行了实验测量,研究了旋流数对NOx排放控制的影响.结果显示,随着旋流数的增加,火焰高度略有升高,火焰发光由白色逐渐变为橙黄色;最高火焰温度逐渐降低,温度分布也变得平坦;NOx排放指数随旋流数的增加而降低,氧浓度越高,其下降幅度越大.保持其他条件不变,增加氧化剂流速可以增强旋流对燃烧特性及NOx排放的影响.     

射流对高温空气燃烧过程中NO_x生成的影响

总结了燃料燃烧过程中NOx的生成机理和各种影响因素,并结合高温空气燃烧（High Temperature Air Combustion-HiTAC）的特点和射流的基本原理,研究了燃料和空气射流的卷吸作用对该燃烧方式NOx生成量的影响。为选择合理的设计与运行参数,实现该燃烧方式的超低NOx排放和高效节能,也为更好地在我国推广和应用这一先进技术提供理论基础。     

激波风洞中超声速燃烧现象的初步实验研究

激波风洞可以提供超声速燃烧现象研究需要的高速和高温实验模拟条件,而且在实验时间上优于膨胀管和重活塞风洞,但是由于其技术难度,很少用于超声速燃烧现象研究。文章介绍了启用激波风洞进行燃烧研究所作的改造和得到的初步实验结果。实验除测量常规流场参数和模型表面的动态参数外,主要使用二维实验模型,利用高温气体的自发光和燃烧伴随的发光现象,采用高速摄影技术来观测燃烧现象,记录到高焓流场中叠加燃料喷射和燃烧的流场,观察到自由边界条件下扩控制的超声速燃烧现象。结果表明激波风洞用于超声速燃烧研究的一些必要的技术问题已基本解决。     

中心大速差射流降低NOx排放量的实验研究

在实验室的卧式煤粉炉中，对中心大速差射流是否能降低ＮＯｘ排放量进行了实验研究。实验表明：中心大速差射流不仅能明显降低ＮＯＸ排放量，而且可使煤粉提前着火，从而提高了煤粉燃烧的稳定性。该方法若用于煤粉锅炉的最上一层的燃烧器，则可望在降低ＮＯＸ排放量的同时不影响锅炉的燃烧效率。     

甲烷受控扩散火焰合成碳纳米管的实验研究

燃烧火焰法是合成碳纳米管的新方法,具有设备简单、容易实现等优点。以硝酸镍为催化剂,在甲烷-空气受控扩散火焰中合成了多壁碳纳米管,燃烧产物中还发现了碳纳米颗粒、碳纳米纤维和碳黑。实验结果表明,随着采样高度的增加,所合成的无定形多壁碳纳米管和富勒烯状碳纳米颗粒逐渐转变为石墨化程度较高的竹节形多壁碳纳米管和洋葱状碳纳米颗粒。分析表明,火焰温度、甲烷裂解产物以及催化剂种类等因素影响碳纳米管的形态和结构。     

常温空气非对称射流MILD燃烧特性实验研究

比较了不同的燃烧器结构后设计了非对称射流燃烧器,并通过实验研究了非对称射流燃烧器的射流速度、喷嘴角度对常温空气MILD燃烧的影响。结果表明:丙烷流量在0.4~0.8m3/h、空气流量在11~22m3/h都可以达到MILD燃烧状态;增大射流速度,减小喷嘴角度可以使温度峰值降低,温度分布更均匀,MILD燃烧更稳定,效果更好,NOx排放量大大减小,达到了"近零排放"。     

燃烧产生NOx的控制研究

氮氧化物是煤转化过程中产生的主要有害气体之一,其排放问题已经受到了环保部门和科研工作者的关注和重视。这里主要介绍NOX的产生机理和国内外控制措施。     

Experimental investigation of dynamic and emission characteristics of a DLE gas turbine combustor

The DLE (dry low emission) technology has already been used on industrial gas turbine combustor and the NO X emission can be limited to 25 ppmv (@15% O 2 ), but one of the destructive effects is combustion instability. In this paper, the dynamic and emission characteristics of a DLE gas turbine combustor have been researched in the authors’ laboratory, and the results show that the key source of combustion instability is the non-uniformity of fuel in the flame zone. Two main fuel supply methods have been used to form different fuel distribution types; it is shown that in the perfectly premixed case the emission level is low and combustion process is stable. The PPF also has an obvious effect on the combustor’s emission and dynamic characteristics.     

Experimental investigation of producer gas burner for thermal application

This paper deals with the performance evaluation of a premixed-type burner with producer gas, in terms of emission, axial and radial flame temperature. In this study, a burner of 150 kWth capacity was tested on an open core downdraft-type gasifier. The developed burner is a concentric tube-type where the air is supplied through a central tube, which is surrounded by another one. The burner consists of a swirl vane for mixing the air and producer gas, mixing tube and bluff body for flame stabilization. Swirl angle and bluff body diameter were kept constant throughout the study. The burner was evaluated with an open core downdraft-type gasifier. The temperature evaluation and emission testing was done for three flow rates and air–fuel ratio. The study shows low NO _x and CO emission at 125 Nm³ h^?1 when compared with that of 75 and 100 Nm³ h^?1. Maximum flame temperature (753 °C) was recorded at 10 cm axial and 10 mm radial distance.     

Numerical simulation of high-power synthetic jet actuator flowfield and its influence on mixing control

Detailed two-dimensional unsteady numerical simulation is carried out to investigate a high-power synthetic jet actuator flow field and its design characteristic. Simultaneously, mixing control mechanism of coaxial jets with actuators is also studied. Firstly, excitation frequency （rotating speed）, piston displacement and its exit slot width have effect on the controlling ability and controlling efficiency of actuator. With the invariable model and con- cerned parameters, the actuator becomes more desirable as the rotating speed increases. Average velocity and maximal velocity at the actuator exit section increase as the piston displacement enlarges or the exit slot width decreases. But the actuator does not always exhibit good performance with the narrower exit. Secondly, the synthetic jets also have the ＂push＂ effect on the coaxial jets, which results in the fluctuation of vorticity and temperature distribution of mixing flowfield. Finally, the employment of synthetic jet actuator can achieve mixing enhancement significantly.     

优化燃烧降低锅炉NO_X排放的试验分析

采用燃烧优化技术进行了降低某厂300MW机组1号锅炉NOx排放的试验,在提高锅炉运行经济性的同时,大大降低了锅炉NOx的排放浓度。分析了该炉热效率和NOx排放浓度与锅炉运行参数的关系,确定了锅炉低NOx运行方式,可用于指导锅炉的高效低NOx的运行。     

Numerical investigation of spray combustion in jet mixing type combustor for low NOx emission

The present paper describes a numerical investigation of spray combustion in a jet mixing type combustor. In this combustor, kerosene spray was injected with a pressure atomizer, and high speed combustion air was introduced towards the spray flow through some inlet air nozzles to improve mixing of the spray and the air. In the numerical simulation, the conservative equations of mass, momentum and energy in the turbulent flow field were solved in conjunction with the k–ε two equation turbulence model. The effects of the diameter and the number of air inlet nozzles on the combustion behavior and NO emission were numerically investigated. When the diameter of the inlet air nozzle decreased from 8 to 4 mm, the calculated NO mole fraction in the exhaust gas was drastically decreased by about 80%. An increase in the inlet velocity resulted in improvement of the mixing of the spray and the air, and hence, the high temperature region where thermal NO was formed became narrow. As a result, the exhaust NO mole fraction decreased. Furthermore, a decrease in exhaust NO mole fraction was explained by a decrease in the residence time in the high temperature region above 1800 K.     

NO emission from non-premixed MILD combustion of biogas-syngas mixtures in opposed jet configuration

In this paper NO emission from MILD combustion of the mixture biogas-syngas is deeply elucidated, five NO routes were considered, specifically: thermal, prompt, NNH, N₂O and reburning. Several operating conditions are studied namely: fuel mixture composition, oxygen concentration in the oxidizer and injection velocity or strain rate. Biogas is modeled by a mixture of methane and carbon dioxide; while, syngas is considered to be composed by hydrogen and carbon monoxide, this gives a fuel mixture of CH₄/CO₂/H₂/CO. Volume of methane and hydrogen are varied alternatively from 0 to 50% in fuel mixture. Oxidizer is composed by O₂/N₂ mixture where oxygen volume is increased from 4 to 21%. Finally, injection strain rate is varied from apparition to vanishment of combustion. Atmospheric pressure is considered with constant fuel and oxidizer injection temperatures of 300 K and 1200 K respectively. Chemical kinetics of such complicated system is handled by a composed mechanism from the USC C₁–C₄ and the Gri 2.11 N-sub mechanism. It is found that under MILD regime, temperature intervals and levels are enhanced by hydrogen compared to methane. Furthermore, temperature levels keep relatively low which guarantees MILD regime. Contrariwise, when oxygen increases in oxidizer, temperature grows up rapidly and the MILD regime disappears. However, if strain rate augments, temperature shows a steep increase then reduces monotonically. It is observed that for low methane volume in the fuel mixture, NNH route dominates NO production. Whereas, when CH₄ increases, the prompt route is enhanced and exceeds NNH one at a methane volume of 12%. When hydrogen increases, prompt and NNH routes are enhanced with a domination of the prompt route until 44% of hydrogen volume. Oxygen increasing in the oxidizer improves thermal mechanism which surpasses prompt one at 17% of oxygen volume and governs NO production. Globally, the third most important route in NO production is the reburning one which is enhanced by all parameters except strain rate.     

Numerical investigation on effectiveness of flow separation control in two-dimensional high-load compressor cascade by synthetic jet

The effectiveness of flow separation control in two-dimensional high load cascade by synthetic jet is investigated through numerical simulation of the effect of excitation frequency and amplitude together with the adaptability of synthetic jet to off-design conditions. Test results indicate that synthetic jet can be used to effectively control the large-scale two-dimensional flow separation in compressor cascade. Preferable results can be obtained when excitation frequency is close to or times of the characteristic frequency of original flow field. Excitation amplitude has a more important effect on the effectiveness of flow separation control, and the increase in excitation amplitude can bring about a dramatic decrease in the loss of total pressure. Synthetic jet has also a very good adaptability to off-design conditions. It can therefore be concluded that the incidence sensitivity of compressor cascade can be effectively reduced by synthetic jet.     

Experimental investigation of the morphology and stability of diffusion and edge flames in an opposed jet burner

The stability of methane/air and hydrogen/air flames in an axisymmetric counterflow burner was investigated experimentally for different burner geometries, degrees of fuel dilution, and combinations of flow velocities. Both planar diffusion flames and edge flames were observed, and the transitions between these flame types were studied. The experimental results confirmed previously published numerical predictions on diluted hydrogen/air flames: the existence of two distinct stable flame types; the possibility of switching between the two flame types by perturbing the flames, e.g., by suitably changing a flow velocity; and the strong hysteresis for the transition from one flame type to the other. Flame stability diagrams were compiled which delineate the range of fuel and air flow velocities for which the planar diffusion flame and the toroidal edge flame are stable. The lower boundary curve for the edge flame stability exhibits a characteristic minimum at a well-defined value of the fuel velocity. For fuel velocities lower than this value, the transition between the edge and the diffusion structure is reversible, and the flames exhibit bistable behavior. For higher fuel velocities, the decrease of air velocity leads to the extinction of the edge flame. An investigation of both the cold and the reactive flow field identified bistable behavior for the flow field as well. Except for very low flow rates, the stagnation plane stabilizes in two positions, close to either of the two nozzles. Detailed numerical simulations of hydrogen flames capture the essentials of this behavior. The observed flame extinction results from the interaction of the flame dynamics with the dynamics of the flow field.     

Experimental investigation of cooling of heated circular disc using inclined circular jet

An experimental study is performed to examine the heat transfer characteristics of impinging circular jet onto a heated circular disc. The disc is heated under constant heat flux and it has an inclination angle with impinging jet in the range of 90° ≤ φ ≤ 150°. The air is supplied using a radial fan. The fluid flows through a designed tunnel. Experiments were performed under different Reynolds number, 2800, 9000, and 36,000, and different values of inclination angle of the disk and jet-to-plate distance to jet diameter ratio H/D_h as 5, 10, and 15. The results of experiments showed that the most effective parameter is the inclination angle between jet and heater. Both locations of stagnation point and heat transfer are affected from this parameter.     

天然气柔和燃烧锅炉结构参数影响模拟研究

在天然气锅炉中引入柔和燃烧技术将大大降低NOx排放,高速未燃气卷吸高温烟气回流并与之快速掺混再燃烧是柔和燃烧的重要特征,因此,开展天然气锅炉关键结构参数优化设计以组织流场形成柔和燃烧所需的高温低氧反应气氛非常必要。基于天然气锅炉的工况特征,设计了热负荷15kW的模型燃烧室,采用数值模拟手段详细研究了燃烧室高度、喷嘴孔径、喷嘴相对位置及烟气出口尺寸对燃烧室流场、组分场及关键参数——烟气回流比的影响规律,并最终确定了燃烧室结构优选方案,对天然气锅炉柔和燃烧机设计提供理论基础数据。