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环形燃烧室周向点火机理基础研究进展

王高峰 夏一帆 叶沉然 胡科琪 令狐昌鸿

王高峰, 夏一帆, 叶沉然, 等. 环形燃烧室周向点火机理基础研究进展[J]. 实验流体力学, 2019, 33(1): 14-28. doi: 10.11729/syltlx20180090
引用本文: 王高峰, 夏一帆, 叶沉然, 等. 环形燃烧室周向点火机理基础研究进展[J]. 实验流体力学, 2019, 33(1): 14-28. doi: 10.11729/syltlx20180090
Wang Gaofeng, Xia Yifan, Ye Chenran, et al. Progress on light-round ignition dynamics in annular combustor[J]. Journal of Experiments in Fluid Mechanics, 2019, 33(1): 14-28. doi: 10.11729/syltlx20180090
Citation: Wang Gaofeng, Xia Yifan, Ye Chenran, et al. Progress on light-round ignition dynamics in annular combustor[J]. Journal of Experiments in Fluid Mechanics, 2019, 33(1): 14-28. doi: 10.11729/syltlx20180090

环形燃烧室周向点火机理基础研究进展

doi: 10.11729/syltlx20180090
基金项目: 

燃烧室/涡轮耦合计算及其在热斑机理研究中的应用项目 91541108

详细信息
    作者简介:

    王高峰(1979-), 男, 副教授, 博士.研究方向:燃烧室和涡轮耦合作用.通信地址:浙江省杭州区西湖区浙大路38号浙江大学航空航天学院 310000).E-mail:gfwang@zju.edu.cn

    通讯作者:

    叶沉然, E-mail:yechenran@zju.edu.cn

  • 中图分类号: V231.2;TK16

Progress on light-round ignition dynamics in annular combustor

  • 摘要: 先进航空发动机普遍采用环形燃烧室结构,其周向点火联焰机理对发动机点火可靠性具有重要研究价值。由于实验室尺度模型实验成本低、测量精度高,已经逐渐成为实验研究环形燃烧室点火机理的重要途径。本文介绍了国内外几种典型的实验室尺度环形燃烧室模型及其相关研究,包括法国巴黎中央理工大学EM2C实验室的MICCA燃烧室模型;剑桥大学的预混/非预混环形燃烧室模型;慕尼黑工业大学的缩比燃气轮机环形燃烧室模型;浙江大学的环形燃烧室和涡轮耦合的TurboCombo模型。环形燃烧室周向点火过程一般分为3个阶段:(1)初始火核的形成;(2)火核扩张发展,在点火针附近喷嘴处形成单个稳定的旋流火焰;(3)火焰沿周向传播,依次点燃全部喷嘴后稳定燃烧。影响周向点火联焰过程的因素众多,机理复杂,已有的实验和数值计算对当量比、点火模式、热功率、流速、喷嘴间距等因素影响下的点火、熄火、火焰传播模式、周向点火时间等特征规律进行了丰富的研究。近年来,在环形燃烧室模型上也逐渐开展了气液两相喷雾燃烧的相关研究。同时,高时空分辨率的先进激光诊断方法的引入也将进一步推动点火机理的更深入研究。
  • 图  1  多头部直线排列燃烧室模型概念

    Figure  1.  Evolvement of the linearly arranged multiple burners

    图  2  法国鲁昂大学CORIA实验室直线布置多头部实验装置[10-11]

    Figure  2.  The experimental multi-burner setup with linearly arranged multiple injectors installed in Lab CORIA, Universite de Rouen[10-11]

    图  3  英国剑桥大学直线布置多头部实验装置[12](单位: mm)

    Figure  3.  The experimental multi-burner setup with linearly arranged multiple injectors installed in University of Cambridge[12](unit: mm)

    图  4  日本宇宙航空研究开发机构3头部实验装置[9]

    Figure  4.  Multi sector unit (3 sectors) in JAXA[9]

    图  5  多头部扇区燃烧实验装置

    Figure  5.  The experimental multi-burner setups with fan-shaped

    图  6  MICCA环形燃烧室模型示意图[13](单位: mm)

    Figure  6.  Schematic diagram of the experimental setup of MICCA[13] (unit: mm)

    图  7  剑桥大学环形燃烧室模型示意图

    Figure  7.  Schematic diagram of the experimental setup in University of Cambridge

    图  8  慕尼黑工业大学环形燃烧室模型[23]

    Figure  8.  Annular combustor model in Technische Universität München[23]

    图  9  浙江大学TurboCombo环形燃烧室模型[26-27]

    Figure  9.  Schematic of the TurboCombo annular combustor model in Zhejiang University[26-27]

    图  10  环形燃烧室周向点火过程的3个阶段[13]

    Figure  10.  Three phases of the light-round sequence in annular combustor[13]

    图  11  环形燃烧室周向点火过程时序图(φ=0.76, Ub=24.5 m/s)[13]

    Figure  11.  Images of light intensity emitted by the flame during ignition of the annular chamber (φ=0.76, Ub=24.5 m/s) [13]

    图  12  周向点火过程亮度积分图(φ=0.76, Ub=24.5 m/s)[13]

    Figure  12.  Integrated light intensity recorded by the camera during ignition (φ=0.76, Ub=24.5 m/s)[13]

    图  13  周向点火过程的5个阶段[16] (左:实验; 中:F-TACLES模型计算结果; 右: TFLES模型计算结果)

    Figure  13.  Five instants of an ignition sequence[16] (left: experimental images, middle: F-TACLES simulations and right: TFLES simulations)

    图  14  喷嘴间火焰传播过程OH*发光侧视图(φ=0.70, Ub=10 m/s)[20]

    Figure  14.  Side visualization of evolution of a successful burner-to-burner flame propagation (φ=0.70, Ub=10 m/s)[20]

    图  15  周向火焰传播过程时序图(φ=0.70, P=15.5kW)[26]

    Figure  15.  Images of the light-round sequence (φ=0.70, P=15.5kW)[26]

    图  16  不同点火位置示意图[18]

    Figure  16.  Different spark positions[18]

    图  17  (a) 点火概率 (b) 可燃因子 (c) 归一化的湍流脉动速度 (d) 归一化的轴向速度(φ=0.35, Ub=10 m/s)[12]

    Figure  17.  Measurements: (a) probability of ignition (b) flammability factor (c) normalized fluctuation of the turbulent velocity (d) normalized axial velocity (φ=0.35, Ub=10 m/s)[12]

    图  18  点火极限与可燃极限[19]

    Figure  18.  Stability and ignition limits for the 12-burners (a), 15-burners (b) and 18-burners (c) configurations. The one-burner and light-round ignition limits for three configurations are summarized in (d) and (e)[19]

    图  19  剑桥大学环形燃烧室示意图(俯视)[19]

    Figure  19.  Overhead schematic of the annular combustor in University of Cambridge[19]

    图  20  剑桥大学环形燃烧室模型的周向火焰传播过程(俯视, φ=0.40)[19]

    Figure  20.  Top view of burner-to-burner ignition sequence in the annular combustor in University of Cambridge (φ=0.40)[19]

    图  21  剑桥大学环形燃烧室模型头部干涉OH*基自发光平均场[41] (a)头部间距是2.33倍喷嘴直径; (b)头部间距是1.56倍喷嘴直径

    Figure  21.  Extent of flame interaction in an annular combustor mea-sured via time-average OH* chemiluminescence from an overhead view with two nozzles pacings: (a) 2.33 and (b) 1.56 times the nozzle diameter[41]

    图  22  浙江大学斜喷环流环形燃烧室的周向点火过程[24](φ=0.75, P=18.6kW)

    Figure  22.  Light-round ignition sequences in the oblique-injecting annular combustor in Zhejiang University (φ=0.75, P=18.6kW) [24]

    图  23  喷嘴间距对火焰传播时间的影响[10]

    Figure  23.  Spacing effect of injectors on flame propagation time[10]

    图  24  喷嘴间距对火焰在相邻喷嘴间传播所用时间的影响[11](实验与LES结果)

    Figure  24.  Experiments versus LES: spacing effect on the first injector/injector propagation time[11]

    图  25  不同条件下周向火焰传播进程随时间发展规律[20]

    Figure  25.  Fraction of annular combustor area ignited vs. time. For each flame, four separate ignition events (fine dotted lines) and their average (thick solid lines) are shown[20]

    图  26  火焰面融合所需时间在冷态与预热情况下随流速的变化[15]

    Figure  26.  Flame fronts merging time as a function of the bulk velocity Ub in cold and preheated conditions[15]

    图  27  三种不同燃料的周向点火时间[17]

    Figure  27.  Light-round delay τl when: (a) the bulk velocity Ub, (b) the equivalence ratio φ kept constant for multiple fuels[17]

    图  28  实验和基于G方程数值模拟得到的周向点火时间[13]

    Figure  28.  Total propagation time deduced from experimental results (red) and from simulations based on the G-equation (black) [13]

    图  29  点火模式对周向点火时间的影响[26]

    Figure  29.  Influence of ignition mode on the light-round time[26]

    图  30  不同喷嘴结构下周向点火时间t的变化规律(FFSL模式)[28]

    Figure  30.  Time delay t for different injection types (FFSL mode)[28]

    图  31  不同喷嘴结构下周向点火时间t的变化规律(SFFL模式)[24]

    Figure  31.  Time delay t for different injection types (SFFL mode)[24]

    图  32  不同位置点火器示意图(E:红; I:绿; C:蓝)及对应的火焰面融合时间[13]

    Figure  32.  Schematic top view of the experiment, showing the different igniters locations: E: external (red), I: internal (green), C: central (blue) and its corresponding propagation time[13]

    图  33  TurboCombo实验平台上周向点火过程火焰形态[27]

    Figure  33.  Flame visualization in TurboCombo during light-round sequence[27]

    图  34  涡轮导叶对周向点火时间的影响[27]

    Figure  34.  The influence of the turbine guide vanes to the light-round time[27]

    图  35  火焰积分亮度随时间变化曲线的重复性(φ=0.70, P=15.5kW)[26]

    Figure  35.  The repeatability of temporal evolution of integrated light intensity (φ=0.70, P=15.5kW)[26]

    表  1  主流一定, 各燃料在当量比、功率增大时的周向点火时间[17]

    Table  1.   Mean light-round time delay τl for increasing equivalence ratio and power when bulk velocity is kept constant[17]

    φ=0.92P=82kW φ=1.00P=89kW
    Propane (gaseous) 23.5ms 21.0ms
    n-Heptane (liquid) 29ms (+23%) 25ms (+19%)
    Dodecane (liquid) 35.5ms (+51%) 32.0ms (+52%)
    下载: 导出CSV
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  • 收稿日期:  2018-06-05
  • 修回日期:  2018-09-26
  • 刊出日期:  2019-02-25

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    2021年8月13日