用改进的离散坐标法计算炉内三维辐射传热

采用离散坐标法进行炉内三维辐射传热的计算,首先在正方体炉膛内验证了该法的精确性,计算结果与区域法进行比较,表明离散坐标法算法可靠,计算工作量小,适合于炉内辐射传热的计算。然后针对长方体炉膛计算了吸收－发射－散射介质的传热问题,表明传统的离散坐标法不适合计算具有复杂相函数曲线的辐射传热问题,因此采用改进的离散坐标法,并得到了合理的结果。最后,对于煤粉燃烧炉膛将辐射传热问题和炉内流动、燃烧过程耦合起来进行计算,表明离散坐标法是一种很有工程应用价值的炉内辐射传热计算方法。     

高温空气燃烧的模型比较数值研究

为验证适用于高温空气燃烧过程的燃烧模型,应用EBU模型、E-A模型、PDF模型三种燃烧模型模拟了一个2m×2m×6.25m的高温空气燃烧室的燃烧过程,并根据国际火焰协会的实验数据对模拟结果进行了验证与比较。湍流输运模型和辐射传热模型分别采用了Reynolds应力模型(RSM)湍流模型和离散坐标(DO)辐射传热模型。结果表明,在预测燃烧室温度、燃料组分体积分数和出口NO体积分数上,EBU模型预测值比E-A模型和PDF模型更符合实验测量值。EBU模型是三种模型中最适合模拟高温空气燃烧的燃烧模型。     

用离散坐标法求解矩形炉内三维辐射换热

叙述了有介质参与的三维空腔内辐射换热的离散坐标解法，并编制程序对三维矩形炉膛内辐射换热进行了数值模拟，计算结果与区域法吻合，是炉内辐射传热数值模拟的一种较好方法。最后展望并指出求解辐射传递方程的离散坐标法在非正交坐标系下应用的重要性。     

燃烧器燃烧流场与污染物排放的数值模拟

针对一种新型燃烧器,利用FLUENT软件,对其内部三维燃烧流场进行了数值模拟.计算采用RNGk-ε双方程湍流模型、PDF燃烧模型以及离散坐标辐射传热模型,液体燃料采用颗粒群轨道模型,模拟了不同过量空气系数和不同负荷工况下的燃烧流场,并对NOx排放进行了预测.根据所得到的模拟结果分析了影响燃烧的因素,为此新型燃烧器的研制提供了理论指导.     

三维离散传播辐射模型的理论及数值分析

本文比较详细地阐述了三维离散传播热辐射模型的理论，并且编制了相应的数值模拟程序，运用该程序对三维立方腔体中的两种辐射传热问题进行了数值模拟，所得模拟结果与精确解吻合较好，这表明三维离散传播热辐射模型是目前解决辐射问题中热流量和温度分布的一种较好的方法。     

75t／h燃气锅炉炉内传热数学模型与数值模拟计算的研究

文章计算辐射传热以区域假想面模型为基础,把炉膛沿烟气流动方向分区,以炉膛内最为复杂的燃烧器区域的燃烧与辐射传热过程为研究对象,建立炉内能量平衡方程,并求解出炉内燃烧的一维温度场,以及水冷壁的吸热量和热流密度.计算结果与三维模型的实测数据非常一致.由于模型采用了一维简化处理,收敛结果较快,可以快速得到电站需要的数值.     

辐射离散传播法在三维圆柱腔体辐射传热计算中的应用

运用空间解析几何理论与数值计算相结合的方法，实现了辐射离散传播法（OTM）在三维圆柱腔体内辐射传热计算的应用。采用坐标转换建立了辐射射线方程，通过直接求解所有发射点上各立体角内的辐射射线与各辐射单元体的交点，确定射线经过的路径及各交点与发射点的距离，然后按距离远近对交点进行排序，得到适合DTM法求解辐射能量传递方程的交点顺序。运用该方法对圆柱腔体内辐射换热进行三维计算，得到与精确解基本相符的结果；将DTM法运用于煤粉燃烧火焰辐射换热的计算，得到的温度场与实验结果基本一致，表面辐射热流密度分布合理，由此表明本文设计的方法是可行的。     

均热炉低热值燃料富氧燃烧过程模拟研究

文中采用CFD商用软件对低热值燃料采用富氧燃烧技术后的炉内传热特性进行了模拟分析并简要探讨其节能减排特性,在数值模拟中,考虑流体流动、辐射、燃烧等,获得了炉内典型位置的温度及速度的分布规律。传热特性方面,使用低热值燃料时,随着氧气浓度的增加物料表面的平均对流换热系数减小,但炉内气体的辐射率随着氧浓度的增加而增加,总的热流密度和辐射热流密度随氧气浓度的增加而增加。最终得到结论,低热值燃料在使用富氧燃烧条件下完全可以达到很好的使用性能。     

微型发动机的燃烧模型和数值模拟

提出了微型发动机燃烧过程的数学模型，并对采用氢气为燃料的微型涡轮机中环形燃烧室内的燃烧，建立了阿累尼乌斯有限反应速率模型，在考虑对流和辐射传热损失的条件下，采用CFD软件包FLUENT进行了数值模拟。根据所得到的模拟结果分析了影响燃烧的主要因素：结构、燃料、质量流率、H2与空气比和壁面材料，提出了克服尺寸减小对燃烧带来的困难的途径。     

不同辐射模型对太阳能烟囱数值模拟影响研究

以太阳能烟囱发电（SCPP）系统为研究对象,比较定热流密度、离散纵坐标（DO）辐射模型、表面对表面（S2S）辐射模型对SCPP温度、速度等性能模拟结果,将3种模型模拟结果与试验数据对比,选择更合适的辐射模型应用于SCPP数值模拟。结果表明,S2S辐射模型集热棚出口流体最大速度比定热流密度和DO辐射模型分别高0.13、0.36 m/s;S2S辐射模型沿烟囱入口流体最大湍流黏度比定热流密度和DO辐射模型分别高16.87%、8.44%;定热流密度、DO辐射模型、S2S辐射模型沿集热棚半径流体温度与试验结果的误差分别为3.09%、0.98%、10.14%。DO辐射模型更适合SCPP系统的数值模拟计算。     

燃气轮机双燃料燃烧室温度场优化研究

为了优化双燃料燃烧室温度场分布,针对某型逆流环管双燃料燃烧室,设计了3种不同的火焰筒配气结构。利用ANSYS FLUENT软件,选用Realizable k-epsilon湍流模型及Finate Rate Chemistry and Eddy-disspation燃烧模型对燃烧室额定工况下的温度场及速度场进行了数值模拟。研究表明:对比液体燃料,由于气体燃料扩散较快,燃烧室在使用气体燃料时高温区分布周向收缩并沿火焰筒轴向后移。对于本型燃烧室,适当增大主燃孔孔径并在火焰筒轴向方向偏后布置,可以有效解决双燃料燃烧室使用气体燃料时高温区后移的问题,对气/液两种燃料条件下的温度场组织更为有利。     

甲烷预混多喷嘴阵列燃烧器热声振荡模态实验研究

为研究燃气轮机模型燃烧室的非预混燃烧流场,采用大涡模拟方法分别结合火焰面生成流形模型（FGM）和部分预混稳态火焰面模型（PSFM）对甲烷/空气同轴射流非预混燃烧室开展了数值模拟研究,并与试验结果进行对比。结果表明：FGM所预测的速度分布、混合分数分布、燃烧产物及CO分布与试验结果更符合;两种模型均能捕捉到燃烧室中的火焰抬举现象;燃烧过程中的火焰结构较为复杂,同时存在预混燃烧区域和扩散燃烧区域,扩散燃烧主要分布在化学恰当比等值线附近,预混燃烧区域主要分布在贫油区。     

Prandtl/Schmidt number effect on temperature distribution in a generic combustor

As a benchmarking of turbulence scalar transfer modeling, the effect of Prandtl/Schmidt number on the temperature field of a diffusion flame model combustor has been investigated. Some of the numerical results, obtained from the eddy dissipation combustion model with the turbulent Prandtl/Schmidt number varying from 0.25 to 0.85, are presented and compared with a comprehensive experimental database. It is found that the turbulent Prandtl/Schmidt number has significant effect on the predicted temperature field in the combustion chamber. This is also true for the temperature profile along the combustor wall. In contrast, its effect on the velocity field is insignificant in the range considered. With the optimized turbulent Prandtl/Schmidt number, both velocity and temperature fields can be reasonably and quantitatively predicted. For the present configuration and operating conditions, the optimal Prandtl/Schmidt number is 0.5, and lower than the typical used value of ～0.7. This study suggests that the current method for scalar transfer modeling in turbulent reacting flows should be improved and new approaches should be developed.     

Comparison and extension of methods for acoustic identification of burners

The prediction and the control of combustion instabilities require the identification of the combustion chamber response. This identification is usually performed by forcing the combustor (for example, modulating its inlet velocity) and measuring its response. Two methods may be found in the literature to analyze this response: identification of transfer matrices (ITM) and flame transfer functions (FTF). In ITM approaches, the burner is considered as a “black box” and a two-port formulation (based on acoustic pressure and velocity perturbations) is used to construct a transfer matrix linking acoustic fluctuations on both sides of the burner. A drawback of this method is that in experiments, the measurement of unsteady pressure and velocity in burnt gases can be difficult. In FTF approaches, pressure measurements are replaced by a global heat release measurement (usually based on optical methods). The heat release fluctuations are then related to the flow velocity modulations at a reference point (usually the combustor inlet) through a transfer function. This paper uses a compressible numerical simulation of a forced laminar Bunsen flame to analyze FTF and ITM methods. Results show that FTF approaches lead to an ill-defined problem as soon as the reference point is not close enough to the chamber. This “compactness” limit is quantified here in terms of distance between the reference point and the local chamber. The source of the problem is that FTF approaches correlate heat release fluctuations to velocity oscillations only: extended FTF models are then proposed using the local unsteady pressure as well as the velocity upstream of the flame to predict the heat release oscillations. These models are tested numerically and provide consistent values when the reference point location changes or when upstream and downstream conditions are varied. These results lead to simple recommendations for system identification.     

Flame stability and emission characteristics of propane-fueled flat-flame miniature combustor for ultra-micro gas turbines

An engineering model of a propane-fueled miniature combustor was developed for ultra-micro gas turbines. The combustion chamber had a diameter of 20 mm, height of 4 mm, and volume of 1.26 cm³. The flat-flame burning method was applied for lean-premixed propane–air combustion. To create the stagnation flow field for a specific flat-flame formation, a flat plate was set over the porous plate in the combustion chamber. A burning experiment was performed to evaluate the combustion characteristics. The flame stability limit was sufficiently wide to include the design operation conditions of an equivalence ratio of 0.55 and air mass flow rate of 0.15 g/s, and the dominant factors affecting the limit were clarified as the heat loss and velocity balance between the burning velocity and the premixture flow velocity at the porous plate. CO, total hydrocarbons (THC), and NO_x emission characteristics were established based on the burned gas temperatures in the combustion chamber and the temperature distribution in the combustor. At an air mass flow rate of less than 0.10 g/s, CO and THC emissions were more than 1000 ppm due to large heat loss. As the air mass flow rate increased, the heat loss decreased, but CO emissions remained large due to the short residence time in the combustion chamber. NO_x emission depended mainly on the burned gas temperature in the combustion chamber as well as on the residence time. To reduce emissions despite the short residence time, a platinum mesh was placed after the combustion chamber, which drastically decreased the CO emissions. The combustor performance was compared with that of other miniature combustors, and the results verified that the present combustor has suitable combustion characteristics for a UMGT, although the overall combustor size and heat loss need to be reduced.     

Experimental Studies on Swirling Gas—Particle Flows in a Spouting —Cyclone Combustor

The gas and particle time-averaged velocity rand RMS fluctuation velocity of swirling gas-particle flows in a spouting-cyclone combustor were measured by a hot-ball probe and a conventional LDV system. The results show large velocity slip between the two phases both in tangential and axial directions and high nonisotropic turbulence of the two phases were also observed which is favorable to coal combustion. The particle RMS fluctuation velocity is higher than the gas RMS fluctuation velocity only in some regions of the flow field.     

Predictions of Flow and Heat Transfer in Low Emission Combustors

Flow and heat transfer predictions in modern low emission combustors are critical to maintaining the liner wall at reasonable temperatures. This study is the first to focus on a critical issue for combustor design. The objective of this paper is to understand the effect of different swirl angle for a dry low emission (DLE) combustor on flow and heat transfer distributions. This paper provides the effect of fuel nozzle swirl angle on velocity distributions, temperature, and surface heat transfer coefficients. A simple test model is investigated with flow through fuel nozzles without reactive flow. The fuel nozzle angle is varied to obtain different swirl conditions inside the combustor. The effect of flow Reynolds number and swirl number are investigated using FLUENT. Different RANS-based turbulence models are tested to determine the ability of these models to predict the swirling flow. For comparison, different turbulence models such as standard k ? ε, realizable k ? ε, and shear stress transport (SST) k?ω turbulence model were studied for non-reactive flow conditions. The results show that, for a high degree swirl flow, the SST k?ω model can provide more reasonable predictions for recirculation and high velocity gradients. With increasing swirl angle, the average surface heat transfer coefficient increases while the average static temperature will decrease. Preliminary analysis shows that the k?ω model is the best model for predicting swirling flows. Also critical is the effect of the swirling flows on the liner wall heat transfer. The strength and magnitude of the swirl determines the local heat transfer maxima location. This location needs to be cooled more effectively by various cooling schemes.     

A study on lean blowout of multi-vortexes-dome model combustor

The lean blowout experiments of the combustion stability device A (multi-vortexes-dome model combustor) have been carried out at atmospheric pressure. Compared with the device B (single-vortex-dome model combustor), the experimental results show that the device A has a superior lean blowout performance when the combustor reference velocity is within the range from 3.50m/s to 5.59m/s ( while the liner reference velocity is between 3.84 and 6.13m/s), and this superiority will remain stable after the inlet air flow rate reaches a certain value. In order to analyze the phenomena and experimental results, the numerical simulation method is used, and the strain rate and the cold reflux impact are employed to further explain the reason that causes the difference between the two devices’ lean blowout characteristics.     

Parameter variations and the effects of hydrogen: An experimental investigation in a lean premixed low swirl combustor

With a global focus on the reduction of fossil fuel consumption and harmful pollutant emissions, new technologies have been raised offering reduced emissions with the combustion of alternative and renewable fuels. Low swirl combustion and the addition of highly reactive fuels into the fuel stream are two methods that have been shown to meet these challenges. In the present study, the thermo-acoustic behavior of a lean premixed low swirl combustor is examined by the variation of several parameters: the equivalence ratio, bulk velocity, chamber pressure, and the addition of hydrogen into the fuel mixture. It is reported that the natural modes of the chamber employed shift upwards for both fuel mixtures examined when increasing the equivalence ratio. As additional heat is dumped into the chamber, the increase in acoustic energy is being pumped through these natural modes. An increase in the bulk velocity is found to have opposite effects on these dominant acoustic modes for the two mixtures investigated. The methane mixture shows negative shifts in frequency when increasing the bulk velocity, whereas the hydrogen-methane mixture displays upward-shifting frequencies. Elevating the chamber pressure results in an increase in the acoustic modes for both mixtures, although the trend is more consistently linear for the hydrogen-methane flames.