Lean blowout model for concentric staged low emission combustor
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摘要:
为了准确掌握中心分级燃烧室火焰稳定边界的影响因素，建立中心分级燃烧室贫油熄火边界预测模型，对中心分级燃烧室的熄火过程进行了试验与理论研究。研究获取了燃烧室结构、雾化和工况参数对燃烧室贫油熄火边界的影响规律，建立并验证了中心分级燃烧室熄火半经验预测模型。结果表明：相比反向涡流器，同向涡流器下游具有更大的回流区、更低的回流速度和更长的停留时间，从而减弱了主燃级与值班级之间的湍流交换，导致同向旋流火焰的贫油熄火性能明显优于反向旋流火焰的熄火性能。中心分级燃烧室熄火边界预测模型对单头部和全环燃烧室熄火性能预测的最大误差为20%，满足燃烧室工程设计需要。
Abstract:With an aim to develop a prediction model and obtain the key factors influencing the lean blowout limits in concentric staged combustors, experimental and theoretical investigations were conducted based on the flame blowout process inside a gas turbine combustor. The influences on the lean blowout limits of combustor geometry, atomization and conditions were investigated, and a method to optimize the flame stability performance was also proposed. An improved prediction model of the lean blowout limits was developed and validated. It was found that the co-swirl led to the larger recirculation zone, lower recirculated velocity and longer resistance time compared with counter-swirl, resulting in weak turbulent exchange between pilot and main flame. Consequently, the lean blowout performance of co-swirl flame was better than the counter-swirl flame. The maximum error of 20% was validated by comparing the annular and single dome combustor experimental data with the lean blowout model, which can be used in the stage of primary design of combustors.
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Key words:
- concentric staged /
- low emission /
- combustor /
- lean blowout /
- turbulent exchange
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图 3 TSS燃烧室流场及OH基浓度仿真结果
Figure 3. Simulated velocity field and OH chemiluminescence of TSS combustor
图 4 火焰熄火与复燃时序图 （TOS2、TOC1）
Figure 4. Image of flame extinction and reignition sequence （TOS2, TOC1）
图 5 TSS燃烧室火焰发光强度随时间变化（TOS2、TOC1）
Figure 5. Evolution of flame luminous intensity over time in TSS combustor （TOS2, TOC1）
图 6 TSS燃烧室中心截面轴向速度分布
Figure 6. Axial velocity profile of at central plane of TSS combustor
图 7 TSS燃烧室不同轴向位置的速度分布
Figure 7. Axial velocity distribution of TSS combustor at differentaxial positions
图 8 同向与反向涡流器对火焰恢复时间的影响
Figure 8. Influence of co-swirler and counter-swirler on flame recovery time
图 9 同向与反向涡流器对贫油熄火边界的影响
Figure 9. Influence of co-swirler and counter-swirler on lean blowout limit
图 10 中心分级燃烧室贫油熄火物理模型
Figure 10. Pphysical model of lean blowout process in the concentric staged combustor
图 11 单头部TSS燃烧室熄火油气比预测值与试验值对比
Figure 11. Comparison of predicted and measured values of qLBO from single dome TSS combustor
图 12 全环TSS燃烧室熄火油气比预测值与试验值对比
Figure 12. Comparison of predicted and measured values of qLBO from annular TSS combustor
表 1 值班级喷嘴试验方案
Table 1. Experimental schemes for pilot atomizer
喷嘴方案 副油路喷口
直径/mm副油路流量
系数CdNA 0.4 0.4 NB 0.6 0.3 
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表 2 值班级涡流器试验方案
Table 2. Experimental schemes for pilot swirler
涡流器
方案旋流数 旋向 一级涡流器 二级涡流器 一级涡流器 二级涡流器 SA 1.2 1.1 顺时针 顺时针 SB 1.2 1.1 顺时针 逆时针
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表 3 火焰稳定边界试验方案
Table 3. Experimental schemes for flame stability boundary
编号 值班级涡流器 值班级喷嘴 TOS1 SA NA TOS2 SA NB TOS3 SB NB TOS4 SB NB
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表 4 火焰稳定边界测试工况
Table 4. Test operating conditions of flame stability boundary
TOC编号 Δp/% ${\tau _{{\rm{res}}} }$/ms ${U}_{\text{r} }{}_{⃗}$/ （m/s） TOC1 1 29 4.2 TOC2 2 20 5.9 TOC3 3 17 7.4 TOC4 4 14 8.6 TOC5 5 12 9.7
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