Numerical simulation of gliding arc ignition characteristics in aeroengine combustor
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摘要:
为深入了解航空发动机燃烧室中的滑动弧等离子体点火特性，基于自有CFD平台GTCC发展了滑动弧激励的数值建模与仿真方法，在单旋流模型燃烧室上测试了该方法的有效可行性。针对轴向双旋流燃烧室开展了6 km高空来流条件下滑动弧点火数值模拟，结果表明施加定轨道旋转滑动弧显著增强了燃油雾化及点火性能，在油气比为0.015、电弧半径为1.5 mm、旋转速度为100（°）/ms的条件下，旋流器出口形成了周期性振荡的值班火焰，流场整体逼近临界着火状态，并在电弧半径增加至2.0 mm后点火成功。进一步模拟了油气比降低至0.01的滑动弧点火过程，电弧半径2.0 mm增加到2.5 mm后，旋流器出口平均气态煤油比例由8.11%增加到22.70%，成功促进值班火焰突破燃烧室临界点火极限。与常规火花塞点火试验的点火极限油气比
0.0163 相比，采用滑动弧激励的数值模拟结果表明可将该型燃烧室点火边界拓宽38.65%。Abstract:To gain an improved understanding of the ignition characteristics in real aeroengine combustor with gliding arc, a modeling and numerical simulation method of the gliding arc was developed on the CFD platform GTCC and tested on a model combustor with single stage swirler. Numerical simulation of the ignition by gliding arc in real combustor with two-stage axial swirler was carried out under 6 km high-altitude inflow condition. Simulation results showed that the gliding arc on fixed track can significantly enhance the performance of fuel pulverization and ignition, induce periodically anchored flame around the swirler outlet with the fuel-air-ratio, arc radius and rotating speed equal to 0.015, 1.5 mm and 100（°）/ms, respectively. The overall flow field approached the critical status of catching fire and eventually ignited with the arc radius increasing to 2.0 mm. Afterwards, fuel-air-ratio was reduced to 0.01 and the ignition processes with arc radius of 2.0 mm and 2.5 mm were simulated. Mean gaseous kerosene proportion on the outlet of swirler increased from 8.11% to 22.70% with stronger actuation, which successfully impelled the anchored flame to break through the critical ignition limit. Compared with the fuel-air-ratio limit
0.0163 with normal spark plug, simulation results showed that the ignition boundary can be expanded up to 38.65% by the gliding arc.-
Key words:
- aeroengine /
- combustor /
- gliding arc /
- ignition /
- numerical simulation
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图 4 滑动弧激励下旋流器出口值班火焰
Figure 4. Anchored flame adjacent to the swirler outlet with the gliding arc actuation
图 6 轴向双旋流燃烧室高保真网格
Figure 6. High-fidelity mesh of combustor with axial two-stage swirler
图 14 z=0 m截面上瞬时混合分数分布（等值线：Z=0.063）
Figure 14. Distribution of instantaneous mixture fraction on profile z=0 m （isoline: Z=0.063）
图 15 x=0 m截面上瞬时混合分数分布（等值线：Z=0.063）
Figure 15. Distribution of instantaneous mixture fraction on profile x=0 m （isoline: Z=0.063）
图 16 x=0.02 m截面上瞬时混合分数分布（等值线：Z=0.063）
Figure 16. Distribution of instantaneous mixture fraction on profile x=0.02 m （isoline: Z=0.063）
图 18 流向等x截面上时间平均气态煤油流量分布
Figure 18. Time-averaged mass flow rate of gaseous kerosene along x-profiles
图 20 流向等x截面上时间平均温度分布（截面半径为25 mm）
Figure 20. Time-averaged temperature along x-profiles （radius of 25 mm）
图 21 z=0 m中心截面上时间平均当量比ϕ分布（等值线：ϕ=1）
Figure 21. Distribution of time-averaged equivalence ratio ϕ on central profile z=0 m （isoline: ϕ=1）
图 22 x=0 m截面上时间平均当量比ϕ分布（等值线：ϕ=1）
Figure 22. Distribution of time-averaged equivalence ratio ϕ on profile x=0 m （isoline: ϕ=1）
表 1 来流条件
Table 1. Flow condition
参数 计算状态1 计算状态2 来流温度/K 249 249 进口压力/kPa 47.2 47.2 空气流量/（g/s） 31 31 油气比 0.015 0.010 余气系数 4.47 6.70 
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表 2 流向等x截面上瞬时气态煤油流量
Table 2. Instantaneous mass flow rate of gaseous kerosene on x-profiles
r/mm x/m $\dot m_{\mathrm{f}} $/（g/s） 占比/% 2.0 0 0.046 14.84 2.0 0.02 0.219 70.65 2.5 0 0.138 44.52 2.5 0.02 0.246 79.35
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