旋流杯燃烧室流场的数值与试验研究

本文在任意曲线坐标系下对旋流杯环形燃烧室冷态和两相燃烧全流程流场进行数值研究。采用RNG k-ε湍流模型,EBU-Arrhenius燃烧模型和六通量辐射模型模拟湍流燃烧过程;采用颗粒轨道模型模拟两相流动。为了验证数学模型与计算方法,本文还采用PIV测量燃烧室火焰筒内冷、热态流场,利用温度耙测量燃烧室出口温度径向分布,所得的计算值与试验数据符合较好,表明所用的各数学模型合理、计算方法可行,所得研究结果可为该类燃烧室的优化设计提供有用的依据。     

基于FGM的旋流预混燃烧室超大涡模拟

针对航空发动机燃烧室等复杂工程中的预混燃烧问题发展高精度、高效的数值预测方法,本研究发展了火焰面生成流型(FGM)详细化学反应建表方法结合超大涡模拟方法(VLES),对工程中的GE LM6000预混旋流燃烧室燃烧开展了高精度数值研究,并与实验结果进行了比较。计算结果表明,VLES-FGM方法可以较准确地预测出旋流预混燃烧室内的流场及温度场分布。为了进一步模拟航空发动机真实的燃烧工况,对原始单头部燃烧室使用周期性边界条件来类比全环燃烧室。计算结果表明,VLES-FGM方法计算得到的周期性燃烧室流场回流区相比较固壁边界燃烧室较小,并且固壁边界燃烧室温度场具有明显的颈部结构,燃烧室下游的高温区分布更为均匀。本文计算结果表明基于FGM燃烧模型的自适应湍流模拟方法VLES对于模拟复杂航空发动机相关的旋流预混燃烧具有很大的应用潜力。     

发动机燃烧室数值计算

1引言为了研制或改进发动机燃烧室的设计；了解燃烧室内各气流参数分布对燃烧过程的影响是很有必要的。本文采用数值计算方法模拟涡喷发动机燃烧室内流场和壁温。本文计算的是发动机燃烧室火焰筒流场，所计算的实际几何形状较为复杂，如图1所示，入口处有倾斜壁面，在轴线方向有6排径向孔和6排轴向气膜隙缝槽；火焰筒进口处旋流器叶片安装角为74”，在旋流器内装有一个喷雾角为95”的喷咀。在计算过程中，由于径向小孔不对称，所以计算园周方向为360”园形截面。考虑到火焰筒实际形状，在计算时分前后二段；前段是联管火焰筒部分按三维两相…     

环形燃烧室火焰简及旋流器流场计算

本文采用偏微分方程法生成贴体网格,在任意曲线坐标系下数值研究两种先进燃烧室火焰筒及其旋流器三维紊流流场。由于旋流器的形状复杂,本文采用型线定点法确定网格的边界。在非交错网格系下采用SIMPLE算法和混合差分格式对离散方程进行求解。计算结果表明计算方法合理,这计算程序进一步扩展,可用来预估环形燃烧室反应流流场。     

两种亚网格燃烧模型的对比研究

为详细比较动态增厚火焰模型和火焰锋面密度模型的性能,本文分别采用这两种亚网格燃烧模型对工业燃气轮机PRECCINSTA的模型燃烧室内湍流预混火焰进行了大涡模拟研究。计算结果与实验数据吻合良好,且这两种模型预测得到的速度、温度和主要组分的统计数据也非常接近。然而对于CO的分布两者的预测结果差异明显,文中对此进行了简要分析。研究还表明本文的计算结果与实验数据的吻合度与文献中报道的前期结果相比有所提高。     

湍流燃烧自适应求解技术在低排放燃烧室计算中的应用

基于各向异性非结构网格生成技术, 开发了面向复杂几何和复杂湍流燃烧问题的自适应求解算法, 并进行了程序代码的可靠性验证工作, 展示了各向异性网格自适应算法在降低问题求解规模、提高火焰面和流场计算精度等方面的优势.应用该自适应求解技术准确捕捉到了一维预混层流火焰、二维对冲火焰和三维本生灯湍流火焰的流场信息, 火焰面附近的温度、速度、组分等物理量与实验值吻合很好.对一款富油-快速混合-贫油(rich-burn, quick-mix, lean-burn, RQL)低排放发动机燃烧室进行了计算分析, 发现了燃烧室内的热声不稳定现象.      

基于LES-PDF方法的双旋流模型燃烧室数值模拟

文章使用基于LES-PDF方法的AECSC两相程序,对模型燃烧室GTMC进行了数值模拟,以此验证AECSC程序对燃烧室模拟的可行性和可信度,并对旋流燃烧室的流动和燃烧特性进行分析.首先,分别用商用软件Fluent 18.1和AECSC程序的LES方法对GTMC的冷态工况进行了模拟.与实验结果相比,程序计算的轴向、径向、切向速度峰值的相对误差在大多数统计点上在20%以内,3个方向速度峰值位置的相对误差基本都在10%以内.同时发现,AECSC程序的计算结果在一定程度上比Fluent的计算结果更接近实验值.文章进一步使用AECSC程序对GTMC的热态工况进行了模拟.在计算结果中,整体的时间平均温度在数值和分布上和实验结果很接近,并很好地再现了实验的"V形"火焰和内外低温回流区,但是高温区出现的位置相比实验结果有些靠前.总体来说,热态结果和实验结果比较吻合,尤其在液雾的模拟方面,计算结果和实验结果相比有着很好的一致性.这说明将LES和PDF相结合的方法在模拟湍流燃烧方面有较强的优势,可以成为未来的研究和发展方向.      

环形燃烧室性能计算

本文在任意曲线坐标下对包括扩压器和火焰筒在内的环形燃烧室三维两相反应流进行了数值模拟,燃烧室性能是采用多维经验分析法估算所用的数学模型有k-ε紊流模型,EBU-Arrhenius紊流燃烧室模型,六通量热辐射模型以及颗粒群轨道模型。在非交错网格体系下,气相采用SIMPLE算法和液体采用PSIC算法求解,通过两种工况和三种扩压器进口速度分布计算表明,所得的流场各气流参数分布和燃烧室性能较合理,本文所建立的程序可为燃烧室优化设计和研究提供有用数据。     

燃气轮机燃烧室化学反应器网络模型研究

本文针对CFD燃烧室设计方法在计算时间以及计算的准确度上的不足,发展了一种计算量较小的、能够快速准确地预测燃气轮机燃烧室污染物排放的化学反应器网络模型方法(CRN).该方法首先根据CFD的计算结果对燃烧室进行分区,不同的区域采用不同的化学反应器模型进行模拟,反应器之间的连接关系以及入口参数都根据CFD的结果确定.本文采用这种方法对某个燃烧富氢合成气的重型燃气轮机燃烧室的NO_x排放随燃料加湿量的变化进行了预测,并与现场测量的结果进行了比较.计算结果与现场试验数据吻合得很好,证明这是一种很好的预测燃烧室NO_x排放的方法,与CFD方法相比预测精度有了很大提高,而且在计算时间上小了几个数量级.     

燃气轮机合成气双旋流非预混燃烧室的设计及实验测试

本文针对上海交通大学25 kW燃气轮机性能试验台的合成气燃烧室开展了设计研究,完成了燃烧室样机的加工与实验测试。研究过程中,首先对合成气燃烧室开展了结构设计;采用双旋流结构的燃烧器进行合成气燃烧火焰组织;采用了燃烧室头部贫燃方式(低当量比)设计以保证燃烧室低排放特性;利用双层壁冷却方式进行火焰筒壁面冷却。在燃烧室结构设计的基础上,利用数值方法系统分析了合成气双旋流非预混燃烧室工作特性,完成了合成气非预混母型燃烧室的设计优化。根据优化方案,完成了燃烧室样机的加工、安装,并进行了实验性能测试。实验结果表明实验工况该燃烧室燃烧稳定,NO_x排放小于25 mg/m~3@15%O_2。     

湍流扩散火焰的非稳态火焰面模拟

采用稳态的和非稳态的火焰面模型同时对一个湍流甲烷射流扩散火焰进行了数值模拟,比较了两者对湍流平均火焰结构、活性自由基和污染物(氮氧化物)排放的模拟效果。速度场采用κ-ε模型计算,守恒标量混合物分数的分布通过其概率密度函数(PDF)输运方程的求解得到。稳态的火焰面结构由查询火焰面数据库得到,而非稳态的火焰面结构由火焰面方程和流场方程耦合求解来计算。采用详细的GRI—Mech 3.0机理描述甲烷的氧化和氮氧化物的形成。数值模拟结果和实验数据作了广泛的对比,验证了火焰面模型对湍流扩散燃烧的定量模拟能力。     

钝体驻定湍流扩散火焰的数值研究——燃烧模型比较

分别采用标量联合的概率密度函数方法、稳态火焰面模型、Euler非稳态火焰面模型和基于有限体积/Monte Carlo混合算法的完备PDF模型对钝体驻定的Sydney湍流扩散火焰HM1进行数值模拟,以比较不同燃烧模型的性能,并比较标量联合的概率密度函数方法和Euler非稳态火焰面模型对氮氧化物排放预测的差异.计算结果和实验数据的比较表明,采用概率密度函数方法计算化学反应可以得到更好的结果但计算量较大,而用火焰面模型求解计算量较小,在接近完全燃烧的情形下,其计算结果比较合理.     

Effects of Lewis number,density ratio and gravity on burning velocity and conditional statistics in stagnating turbulent premixed flames

DNS is performed to analyse the effects of Lewis number (Le), density ratio and gravity in stagnating turbulent premixed flames. The results show good agreement with those of Lee and Huh (Combustion and Flame, Vol. 159, 2012, pp. 1576–1591) with respect to the turbulent burning velocity, S_T, in terms of turbulent diffusivity, flamelet thickness, mean curvature and displacement speed at the leading edge. In all four stagnating flames studied, a mean tangential strain rate resulting in a mean flamelet thickness smaller than the unstretched laminar flame thickness leads to an increase in S_T. A flame cusp of positive curvature involves a superadiabatic burned gas temperature due to diffusive–thermal instability for an Le less than unity. Wrinkling tends to be suppressed at a larger density ratio, not enhanced by hydrodynamic instability, in the stagnating flow configuration. Turbulence is produced, resulting in highly anisotropic turbulence with heavier unburned gas accelerating through a flame brush by Rayleigh–Taylor instability. Results are also provided on brush thickness, flame surface density and conditional velocities in burned and unburned gas and on flame surfaces to represent the internal brush structures for all four test flames.     

A three mixture fraction flamelet model for multi-stream laminar pulverized coal combustion

A three mixture fraction flamelet model is proposed for multi-stream laminar pulverized coal combustion. The technique of coordinate transformation is utilized to map the flamelet solutions from a unit pyramid space into a unit cubic space to improve the stability of the simulation. The validity of the three mixture fraction flamelet model was assessed on different configurations, including a laminar counterflow pulverized coal/methane flame and a laminar piloted pulverized coal jet flame. The flamelet predictions were compared to the reference results of the detailed chemistry solutions. For the counterflow flame, it was found that the flame temperature and major species mass fractions are correctly predicted by the three mixture fraction flamelet model. However, discrepancies are observed for combustion-mode-sensitive species such as CO and H₂ in the premixed combustion region. The thermo-chemical quantities in the char surface reaction zone cannot be correctly predicted if the mixing between the char off-gas stream and other streams is neglected. For the piloted jet flame, it was shown that the stable thermo-chemical variables can be correctly predicted at the upper and middle stream locations. However, at the downstream location, discrepancies can be observed in certain regions. Overall, the validity of the three mixture fraction flamelet model for multi-stream pulverized coal combustion is confirmed and its performance in turbulent pulverized coal combustion will be tested in future work.     

A spray flamelet/progress variable approach combined with a transported joint PDF model for turbulent spray flames

A spray flamelet/progress variable approach is developed for use in spray combustion with partly pre-vaporised liquid fuel, where a laminar spray flamelet library accounts for evaporation within the laminar flame structures. For this purpose, the standard spray flamelet formulation for pure evaporating liquid fuel and oxidiser is extended by a chemical reaction progress variable in both the turbulent spray flame model and the laminar spray flame structures, in order to account for the effect of pre-vaporised liquid fuel for instance through use of a pilot flame. This new approach is combined with a transported joint probability density function (PDF) method for the simulation of a turbulent piloted ethanol/air spray flame, and the extension requires the formulation of a joint three-variate PDF depending on the gas phase mixture fraction, the chemical reaction progress variable, and gas enthalpy. The molecular mixing is modelled with the extended interaction-by-exchange-with-the-mean (IEM) model, where source terms account for spray evaporation and heat exchange due to evaporation as well as the chemical reaction rate for the chemical reaction progress variable. This is the first formulation using a spray flamelet model considering both evaporation and partly pre-vaporised liquid fuel within the laminar spray flamelets. Results with this new formulation show good agreement with the experimental data provided by A.R. Masri, Sydney, Australia. The analysis of the Lagrangian statistics of the gas temperature and the OH mass fraction indicates that partially premixed combustion prevails near the nozzle exit of the spray, whereas further downstream, the non-premixed flame is promoted towards the inner rich-side of the spray jet since the pilot flame heats up the premixed inner spray zone. In summary, the simulation with the new formulation considering the reaction progress variable shows good performance, greatly improving the standard formulation, and it provides new insight into the local structure of this complex spray flame.     

Problems of predicting turbulent burning rates

Different approaches to the modelling of turbulent combustion first are reviewed briefly. A unified, stretched flamelet approach then is presented. With Reynolds stress modelling and a generalized probability density function (PDF) of strain rate, it enables a source term, in the form of a probability of burning function, P_b, to be expressed as a function of Markstein numbers and the Karlovitz stretch factor. When P_b is combined with some turbulent flame fractal considerations, an expression is obtained for the turbulent burning velocity. When it is combined with the profile of the unstretched laminar flame volumetric heat release rate plotted against the reaction progress variable and the PDF of the latter, an expression is obtained for the mean volumetric turbulent heat release rate. Through these relationships experimental values of turbulent burning velocity might be used to evaluate P_b and hence the CFD source term, the mean volumetric heat release rate.

Different theoretical expressions for the turbulent burning velocity, including the present one, are compared with experimental measurements. The differences between these are discussed and this is followed by a review of CFD applications of these flamelet concepts to premixed and non-premixed combustion. The various assumptions made in the course of the analyses are scrutinized in the light of recent direct numerical simulations of turbulent flames and the applications to the flames of laser diagnostics. Remaining problem areas include a sufficiently general combination of strain rate and flame curvature PDFs to give a single PDF of flame stretch rate, the nature of flame quenching under positive and negative stretch rates, flame responses to changing stretch rates and the effects of flame instabilities.     

A comparison of different approaches to integrate flamelet tables with presumed-shape PDF in flamelet models for turbulent flames

Flamelet models for turbulent combustion modelling make use of presumed-shape probability density functions (PDFs) for integrating laminar flamelet solutions to obtain an integrated flamelet table that can readily be used for turbulent flame calculations. The existence of non-unique approaches for such an integration has rarely been investigated before. For the first time, this work studies systematically the non-uniqueness of the flamelet table integration approaches. A flamelet model called the flamelet/progress variable model is used in the study, although the issue exists generally in many other flamelet models. Two classes of table integration approaches are investigated, one preserving the laminar flamelet structures during integration and the other not. Three different table integration approaches are examined and compared in detail to provide a thorough understanding of the different approaches. A partially stirred reactor is used as a test case for examining the different approaches. A method based on the transported PDF method is also employed to provide a reference for the assessment of the different flamelet table integration approaches. It is found in general that the flamelet preserving integration approach yields a more reasonable joint PDF of the mixture fraction and the progress variable, and the prediction results are closer to the referenced transported PDF results.     

A flamelet analysis of the burning velocity of premixed turbulent expanding flames

Direct numerical simulation is a very powerful tool to evaluate the validity of new models and theories for turbulent combustion. In this paper, direct numerical simulations of spherically expanding premixed turbulent flames in the corrugated flamelet regime are performed. The flamelet-generated manifold method is used to deal with detailed reaction kinetics. The numerical method is validated for both laminar and turbulent expanding flames. The computational results are analyzed by using an extended flame stretch theory. It is investigated whether this theory is able to describe the influence of flame stretch and curvature on the local burning velocity of the flame. If the full profiles of flame stretch and curvature through the flame front are included in the theory, the local mass burning rate is predicted accurately. The influence of several approximations, which are used in other existing theories, is studied. When flame stretch is assumed to be constant through the flame front or when curvature of the flame front is neglected, the theory fails to predict the local mass burning rate.     

Simulation of transient turbulent methane jet ignition and combustion under engine-relevant conditions using conditional source-term estimation with detailed chemistry

The ignition and combustion processes of transient turbulent methane jets under high-pressure and moderate temperature conditions were simulated using a computationally efficient combustion model. Closure for the mean chemical source-terms was obtained with Conditional Source-term Estimation (CSE) using first conditional moment closure in conjunction with a detailed chemical kinetic mechanism, which was reduced to a Trajectory-Generated Low-Dimensional Manifold (TGLDM). The accuracy of the manifold was first validated against the direct integral method by comparing the predicted reactive scalar profiles in three methane–air reaction systems: a laminar premixed flame, a laminar flamelet and a perfectly stirred reactor. Detailed CFD simulations incorporating the CSE-TGLDM model were able to provide reasonably good predictions of the experimental ignition delay and initial ignition kernel locations of the methane jets reported in the literature with relatively low computational cost. Nitrogen oxides formed in the methane jet flame were found to be underpredicted by the model by as much as a factor of 2. The discrepancy may be attributable to the inability of the simulation to account for the effects of the rarefaction wave in the shock-tube experiments.