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燃气轮机燃烧室内NOx生成影响因素的数值研究 总被引:2,自引:0,他引:2
低NOx燃气轮机燃烧室的燃烧特性受到旋流的强烈影响,旋流特性的分析对燃烧室的设计和优化具有非常重要的作用。本文对燃气轮机燃烧室的旋流燃烧流动,应用商用程序FLUENT进行了数值模拟,并分析了旋流数、压强、湍流度对燃烧室内燃烧特性和NOx生成特性的影响。模拟结果表明,随着压强的增加,NOx排放逐渐增加,随着燃料入口湍流度的增加,NOx排放将减少,而随着旋流数的增加,NOx排放先是增加而后减小,同时,NOx随压强变化呈指数规律变化,但不同的燃烧组织形式对指数值有较大的影响。 相似文献
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采用浮力修正的k-ε湍流模型和涡团耗散(EDC)湍流燃烧模型,对旋流燃烧室内具有不同初始切向动量或旋流数的受浮力作用的甲烷湍流火焰进行了数值模拟,得到三组工况下的气体温度场、组分体积分数场、速度场和湍流脉动特性的分布,并与试验测量数据进行了比较.结果表明:浮力对初始切向动量或旋流数较高的湍流火焰有更强的影响. 相似文献
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燃料质量浓度分布在一定程度上影响混合气体的燃烧效率,能使燃气充分混合的同轴射流、旋片同轴、轴切结合、切向旋流等典型混合模式在航空发动机、燃气轮机及火箭发动机等先进燃烧技术应用中较为常见。因此,设计了甲烷/空气部分预混的燃烧实验装置,较为系统地实验研究了旋流数和轴向流速对混合气体在约束空间燃烧室内燃烧特性的影响。结果表明:对于有中心射流的混合结构,燃气轴向流速较低时产生黄色火焰,增大轴向流速,黄色火焰转为蓝色湍流火焰,且温度分布趋于均匀;纯切向旋流燃烧器的掺混效果较好,受燃气轴向流速的影响小,火焰结构稳定,均为蓝色火焰,温度轴/径向分布均匀且趋势一致,同当量比下燃烧产物中的污染物体积分数最小。 相似文献
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实验研究了一种中心分级燃烧室值班级旋流角变化对燃烧性能的影响。采用了单头部单管式燃烧室,值班级一级旋流器旋流数分别为0. 63、0. 72和0. 93,实验研究了采用不同旋流数时燃烧室的点火、慢车贫油熄火、污染物排放和燃烧效率等燃烧特性。实验结果表明:旋流数变化对燃烧室的点火、慢车贫油熄火、污染物排放及燃烧效率等有很大影响;旋流数及一级旋流器和二级旋流器的旋流数差值增加后燃烧室的点火和慢车贫油熄火特性得到改善。一级旋流器旋流数的增加会导致污染物排放的增加及燃烧效率的下降。 相似文献
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在一台1 MW的热态煤粉燃烧试验炉上进行热态模拟试验,用两台双调风旋流燃烧器对冲燃烧,并且在主燃烧器上方的不同位置还布置了燃尽风装置(OFA)。主燃烧器使用的是变截面的一次风管和碰撞环相结合,在一次风管内,风粉气流在惯性的作用下分离为外浓内淡的环状气流,从而实现了燃烧器喷口处沿直径方向的浓淡分布。通过对陕北神华优质烟煤、山西河津劣质烟煤和山西长治贫煤这三种特性相差较大的煤的燃烧对比实验,得到了燃尽风布置的相对位置变化,一次风率、内二次风率、外二次风率的变化,内二次风、外二次风旋流强度等因素的变化,对NOx的生成和对飞灰含碳量的影响作用,同时也得到了NOx的生成和燃尽率之间的相互关系,以及对燃烧的稳定性、经济性的影响因素,其结果对工程设计和实际应用有着重要的指导意义。 相似文献
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在设计热功率为1 MW的热态模化实验台上,研究了带有燃尽风的径向浓淡双调风旋流燃烧器的运行特点,得到燃尽风布置的相对位置、一次风率、内二次风率、外二次风率以及二次风旋流强度对NOx生成和飞灰含碳量的影响.结果表明:旋流对冲的煤粉浓淡燃烧配合采用燃尽风(OFA)空气分级燃烧技术,对降低NOx的生成和减少飞灰含碳量非常有益;只有合理地设计和布置OFA燃烧器,才能在降低NOx生成量的同时,尽量减少飞灰含碳量;增大一次风率时,NOx的生成量先增加后减少,而飞灰含碳量先减少后增加;增加内、外二次风的旋流强度,NOx的生成量不断提高,而飞灰含碳量则呈现降低趋势. 相似文献
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以液排渣旋风燃烧过程为基础的煤粉低尘燃烧器可在燃烧过程实现捕渣,为工业加热提供低含尘浓度的高温火焰,是工业加热过程实现以煤代油的先进燃烧技术。根据旋流燃烧流动特点,采用能考虑非均向湍流应力的雷诺应力模型,对旋流煤粉低尘燃烧器内气流流动过程场进行数值模拟计算,计算结果与流场实验测试相吻合。研究表明,气流进入燃烧器时的旋转强度(旋流数)对燃烧器内的流动特性有很大影响,在冷态模型条件下,当旋流数在7以上时,环室回流在轴向贯穿燃烧器整个流场,有利于增加煤粉颗粒在燃烧室内的循环次数,提高灰渣捕获率;低于7时,环室回流出现阻断,不再连续,易造成煤粉颗粒直接逸出,对燃烧及灰渣捕获不利。随旋流数增加,燃烧器出口处中心回流率增大,对炉膛高温烟气的抽吸作用增强。 相似文献
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Colorless distributed combustion (CDC) has been shown to provide significant improvement in gas turbine combustor performance. Colorless distributed combustion with swirl is investigated here to develop ultra-low emissions of NO and CO, and significantly improved pattern factor. Experimental investigations have been performed using a cylindrical geometry combustor with swirling air injection and axial hot gas exit stream from the combustor. Air was injected tangentially to impart swirl to the flow inside the combustor. The results obtained from the combustor have demonstrated very low levels of NO (∼3 PPM) and CO (∼70 PPM) emissions at an equivalence ratio of 0.7 and a high heat release intensity of 36 MW/m3-atm under non-premixed combustion. To further simulate gas turbine operating conditions, inlet air to the combustor was preheated to 600 K temperature and the combustor operated at 2 atm pressure. Results showed very low levels of CO (∼10 PPM) but the NO increased somewhat to ∼10 PPM at an equivalence ratio of 0.5 and heat release intensity of 22.5 MW/m3-atm under non-premixed combustion conditions. For premixed combustion, the combustor demonstrated low levels of both NO (5 PPM) and CO (8 PPM) at an equivalence ratio of 0.6 and a heat release intensity of 27 MW/m3-atm. Results are reported at different equivalence ratios on the emission of NO and CO, lean stability limit and OH* chemiluminescence. These results suggest that further performance improvement can be achieved with improved fuel mixture preparation prior to the ignition of fuel at higher operational pressures using swirling combustor design for our quest to develop ultra low emission high intensity combustor for gas turbine application. 相似文献
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A. Datta 《国际能源研究杂志》2000,24(5):373-390
A numerical model of liquid fuel spray combustion is developed to study the effects of inlet flow conditions of primary and dilution air on the performance of a swirl‐stabilized axi‐symmetric combustor. The model is based on two‐phase stochastic separated flow approach. A standard k–ϵ model with logarithmic law of the wall for the near‐wall region is adopted for the solution of the gas phase turbulence. The chemical reaction is taken as a single step, irreversible, global one with the rate determined by the kinetically and diffusionally controlled rates. The liquid spray is divided into a finite number of droplet classes with the size distribution following a probability function. It has been observed that an improved pattern factor and better combustion efficiency can be obtained when both the primary and the dilution air streams enter the combustor with swirl, but in the counter‐rotating directions. However, the combustor pressure loss factor increases for the counter‐rotating flow entries of the primary and the dilution air compared to the co‐rotating air entries or to the swirled primary and non‐swirled dilution air entries. Copyright © 2000 John Wiley & Sons, Ltd. 相似文献