Influence of thermal and mechanical effects from NS-DBD actuation on water collection efficiency distribution on airfoil surface
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摘要:
建立了纳秒脉冲表面介质阻挡放电（NS-DBD）激励条件下空气-过冷水滴两相流动的计算模型，采用计算流体力学的方法对NS-DBD激励条件下翼型的水滴撞击特性进行了数值模拟，研究了来流迎角、液态水含量、水滴平均直径、激励强度对翼型表面水收集系数的影响。最后，结合短脉冲等离子体放电过程中产生的气动力效应和热效应，分析了热力效应对翼型表面水收集系数的影响。研究发现，NS-DBD短脉冲等离子体放电产生的热力耦合效应可以降低水收集系数峰值，但不改变水滴撞击极限，最佳效果在激励后10～15 μs。激励强度越大，水收集系数降低就越明显，但回升也越慢，水滴平均直径越大激励的影响越弱。激励产生的力效应和热效应在翼型表面形成一层波浪形高温气膜，降低了翼型表面的水收集系数分布。
Abstract:The computational model for two-phase flow including air and supercooled water droplet was established under nanosecond pulse dielectric barrier discharge （NS-DBD） actuation. The compu-tational fluid dynamics method was adopted to simulate the water impingement characteristics of airfoil under NS-DBD actuation. The influences of angle of attack, liquid water content, mean volume diameter and intensity of actuation on the water collection coefficient were studied. Finally, the aerodynamic effect and thermal effect during the process of plasma discharge were coupled to analyze the anti-icing mechanism of plasma actuation. It showed that, the thermal and mechanic effects coupled resulting from the NS-DBD plasma discharge can reduce the peak value of water collection coefficient, but can’t change the water impingement limit of airfoil. The best effect of actuation appeared at the time of 10—15 μs. The higher the strength of actuation increased, the lower the water collection coefficient decreased and the slower it rose again. The actuation had a weaker influence on the larger mean volume diameter. The mechanics and thermal effect from plasma actuation can generate a layer of wavy high temperature air film on the surface of airfoil to decrease the water collection coefficient distribution.
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图 1 翼型近壁网格控制体的质量和动量守恒示意图
Figure 1. Schematic diagram of mass and momentum conservation of mesh control body near airfoil wall
图 4 NACA0012翼型表面水收集系数分布比较
Figure 4. Comparison of water collection coefficient distribution on the surface of NACA0012 airfoil
图 5 α=0°时翼型表面水收集系数分布随激励时间的变化
Figure 5. Variation of water collection coefficient distribution on the airfoil surface with respect to actuation time at α=0°
图 6 α=6°时翼型表面水收集系数分布随激励关闭后时间的变化
Figure 6. Variation of water collection coefficient distribution on the airfoil surface with respect to actuation time at α=6°
图 7 α=6°时激励关闭后不同时刻翼型表面水收集系数与激励前的差值
Figure 7. Difference of water collection coefficient on the airfoil surface between different actuation times and before actuation at α=6°
图 8 不同液态水含量下激励前后翼型表面水收集系数峰值的百分比差值（Dmv=20 μm，α=0°）
Figure 8. Percentage difference of water collection coefficient peak on the airfoil surface before and after actuation under different liquid water contents （Dmv=20 μm, α=0°）
图 9 不同水滴平均直径时激励前后翼型表面水收集系数峰值的百分比差值（ρlwc=0.5 g/m3，Dmv=10，20 μm）
Figure 9. Percentage difference of water collection coefficient peak on the airfoil surface before and after actuation for different mean volume diameter of water droplets （ρlwc=0.5 g/m3, Dmv=10, 20 μm）
图 10 不同激励强度翼型表面水收集系数峰值的时间历程（ρlwc=0.5 g/m3，Dmv=20 μm，α=0°）
Figure 10. Time history of water collection coefficient peak on the airfoil surface with different actuation intensities（ρlwc=0.5 g/m3, Dmv=20 μm, α=0°）
图 11 不同激励强度激励前后翼型表面水收集系数峰值的最大变化量（ρlwc=0.5 g/m3，Dmv=20 μm，α=0°）
Figure 11. Variation of water collection coefficient peak on the airfoil surface before and after actuation for different actuation intensities （ρlwc=0.5 g/m3, Dmv=20 μm, α=0°）
图 12 激励关闭后不同时刻的翼型流场中压力冲击波（ρlwc=0.5 g/m3，Dmv=20 μm，α=0°，Q=8.5 mJ/cm）
Figure 12. Pressure shock waves in flow field around the airfoil at different actuation time （ρlwc=0.5 g/m3, Dmv=20 μm, α=0°, Q=8.5 mJ/cm）
图 13 激励关闭后不同时刻的翼型表面压力系数分布
Figure 13. Distribution of pressure coefficient of airfoil surface at different actuation time
图 14 翼型表面压力系数最大值随激励关闭后时间的变化
Figure 14. Variation of the maximum pressure coefficient of the airfoil surface with actuation time
图 15 NS-DBD激励初期的翼型前缘热源和局部温度分布（t=1 μs）
Figure 15. Heat source and local temperature distribution of leading edge of the airfoil during the initial stage of NS-DBD actuation （t=1 μs）
图 16 激励关闭后不同时刻的翼型前缘附近温度场云图（t=10，30，50，70，90 μs）
Figure 16. Temperature field contour near leading edge of the airfoil at different actuation times （t=10, 30, 50, 70, 90 μs）
图 17 激励关闭后不同时刻的x向翼型表面温度分布比较（ρlwc=0.5 g/m3，Dmv=20 μm，α=0°）
Figure 17. Comparison of temperature distribution on the x-direction airfoil surface at different actuation times （ρlwc=0.5 g/m3，Dmv=20 μm，α=0°）
图 18 激励关闭后不同时刻的y向翼型表面温度分布比较（ρlwc=0.5 g/m3，Dmv=20 μm，α=0°）
Figure 18. Comparison of temperature distribution on the y-direction airfoil surface at different actuation times （ρlwc=0.5 g/m3，Dmv=20 μm，α=0°）
图 19 激励关闭后不同时刻的翼型前缘附近密度场云图（t=10，30，50，70，90 μs）
Figure 19. Density field contour near leading edge of the airfoil at different actuation times （t=10，30，50，70，90 μs）
图 20 多个周期激励后翼型的温度场云图（f=
6000 Hz，t=25.96/6000 s）Figure 20. Temperature field contour of airfoil after long-term actuation （f=
6000 Hz，t=25.96/6000 s）表 1 20 μm平均水滴直径的Langmuir E分布
Table 1. Langmuir E distribution of mean volume diameter of droplet at 20 μm
水滴直径/μm 体积分数/% 54.2 5 40.0 10 29.6 20 20.0 30 13.0 20 8.8 10 4.6 5 
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表 2 验证计算的工况
Table 2. Validation computation conditions
参数 数值 翼型弦长c/m 1.0 来流速度V∞/（m/s） 138.88 来流静压p∞/105 Pa 1.0 来流静温T∞/K 300 机翼迎角α/（°） 5 水滴平均直径Dmv/μm 16 云层液态水含量ρlwc/（g/m3） 1.0
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表 3 来流迎角影响的计算工况
Table 3. Computational conditions for the influence of angle of attack of incoming flow
参数 数值 翼型弦长c/m 0.35306 来流速度V∞/（m/s） 95.22 来流静压p∞/105 Pa 1.0 来流静温T∞/K 262.85 机翼迎角α/（°） 0，6 水滴平均直径Dmv/μm 20 云层液态水含量ρlwc/（g/m3） 0.5
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表 4 液态水含量影响的计算工况
Table 4. Computational conditions for the influence of liquid water content
参数 数值 翼型弦长c/m 0.35306 来流速度V∞/（m/s） 95.22 来流静压p∞/105 Pa 1.0 来流静温T∞/K 262.85 机翼迎角α/（°） 0 水滴平均直径Dmv/μm 20 云层液态水含量ρlwc/（g/m3） 0.2，0.5
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表 5 水滴平均直径影响的计算工况
Table 5. Computational conditions for the influence of mean volume diameter of water droplets
参数 数值 翼型弦长c/m 0.35306 来流速度V∞/（m/s） 95.22 来流静压p∞/105 Pa 1.0 来流静温T∞/K 262.85 机翼迎角α/（°） 0 水滴平均直径Dmv/μm 10，20 云层液态水含量ρlwc/（g/m3） 0.5
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表 6 激励强度影响的计算工况
Table 6. Computational conditions for the influence of actuation intensity
ρlwc/（g/m3） Dmv/μm α/（°） Q/（mJ/cm） 0.5 20 0 4.25，8.5，17
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