发动机短舱过冷大水滴结冰数值模拟
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摘要
发动机短舱结冰会对飞机飞行安全造成重大影响。过冷大水滴在撞击物面前存在变形、破碎,撞击时可能出现飞溅、反弹等物理现象,与过冷小水滴存在差异。为更好地模拟过冷大水滴条件下发动机短舱结冰情况,建立了考虑水滴破碎、飞溅、反弹等影响的过冷大水滴运动模型,对某型发动机短舱进行了结冰数值模拟,并研究了边界条件、水滴直径等对结冰外形的影响。计算结果表明,水滴直径越大,局部水收集系数越大,水滴上下撞击极限越大,结冰越厚。短舱风扇处不同边界条件设置对过冷大水滴结冰结果存在影响,边界条件为压力出口和流量出口时计算结果吻合度较高。
Engine nacelle icing would do major impact on aircraft flight safety. Supercooled large droplets( SLD) may deform and break before impacting on the wall,and physical phenomena such as splashing and rebound may occur during the process of impact,which is different from the supercooled small droplets. In order to simulate nacelle icing more precisely under SLD conditions,this paper established a model of supercooled large droplets considering the effects of droplet breaking,splashing,rebound,etc.,and a certain type of engine nacelle' s icing was simulated numerically while the influence of boundary conditions and droplet diameter on the shape of ice was studied. The results showed that the larger diameter of the droplet,the larger local water collection coefficient,the greater upper and lower impact limit,and the thicker ice. Different boundary conditions at the fan of the nacelle have influence on the icing results. The results are in good agreement when the outlet conditions are set as pressure outlet and mass outlet.
Engine nacelle icing would do major impact on aircraft flight safety. Supercooled large droplets( SLD) may deform and break before impacting on the wall,and physical phenomena such as splashing and rebound may occur during the process of impact,which is different from the supercooled small droplets. In order to simulate nacelle icing more precisely under SLD conditions,this paper established a model of supercooled large droplets considering the effects of droplet breaking,splashing,rebound,etc.,and a certain type of engine nacelle' s icing was simulated numerically while the influence of boundary conditions and droplet diameter on the shape of ice was studied. The results showed that the larger diameter of the droplet,the larger local water collection coefficient,the greater upper and lower impact limit,and the thicker ice. Different boundary conditions at the fan of the nacelle have influence on the icing results. The results are in good agreement when the outlet conditions are set as pressure outlet and mass outlet.
引文
[1]孙志国.飞机结冰数值计算与冰风洞部件设计研究[D].南京:南京航空航天大学,2012.
[2]申晓斌,林贵平,卜雪琴,等.发动机进气道短舱前缘结冰三维模拟研究[J].航空学报,2013,34(3):517-524.
[3] Mundo C,Sommerfeld M,Tropea C. Droplet-wall Collisions:Experimental Studies of the Deformation and Breakup Process[J]. International Journal of Multiphase Flow,1995,21(2):151-173.
[4] Villedieu P H,Trontin P,Guffond D,et al. SLD Lagrangian Modeling and Capability Assessment in the Frame of ONERA3D Icing Suite[R]. AIAA-2012-3132,2012.
[5]付斌.机翼结冰数值计算与结冰模型研究[D].南京:南京航空航天大学,2011.
[6] Bourgault Y,Habashi W,Dompierre J,et al. An Eulerian Approach to Supercooled Droplets Impingement Calculations[C]. Montreal,Canada:Aerospace Sciences Meeting and Exhibit,2013.
[7] Shimura M,Yamamoto M. Comparative Investigation on Effect of Droplet Deformation Models on SLD Icing[C]. Tokyo:SAE2015 International Conference on Icing of Aircraft,Engines,and Structures,2015.
[8] Tan C,Papadakis M. Droplet Breakup,Splashing and Re-Impingement on an Iced Airfoil[C]. Reston:AIAA Theoretical Fluid Mechanics Meeting,2013.
[9]吴佩佩,朱春玲,刘文平,等.过冷大水滴条件下机翼结冰数值仿真[J].计算机仿真,2014,31(9):51-55.
[10]孙志国,朱程香,付斌,等.二维翼型结冰数值计算[J].航空动力学报,2010,25(7):1485-1490.
[11]冯丽娟,秦娜,易贤.民用航空发动机进气道防冰功率的计算方法研究[J].航空计算技术,2017,47(4):14-17.
[2]申晓斌,林贵平,卜雪琴,等.发动机进气道短舱前缘结冰三维模拟研究[J].航空学报,2013,34(3):517-524.
[3] Mundo C,Sommerfeld M,Tropea C. Droplet-wall Collisions:Experimental Studies of the Deformation and Breakup Process[J]. International Journal of Multiphase Flow,1995,21(2):151-173.
[4] Villedieu P H,Trontin P,Guffond D,et al. SLD Lagrangian Modeling and Capability Assessment in the Frame of ONERA3D Icing Suite[R]. AIAA-2012-3132,2012.
[5]付斌.机翼结冰数值计算与结冰模型研究[D].南京:南京航空航天大学,2011.
[6] Bourgault Y,Habashi W,Dompierre J,et al. An Eulerian Approach to Supercooled Droplets Impingement Calculations[C]. Montreal,Canada:Aerospace Sciences Meeting and Exhibit,2013.
[7] Shimura M,Yamamoto M. Comparative Investigation on Effect of Droplet Deformation Models on SLD Icing[C]. Tokyo:SAE2015 International Conference on Icing of Aircraft,Engines,and Structures,2015.
[8] Tan C,Papadakis M. Droplet Breakup,Splashing and Re-Impingement on an Iced Airfoil[C]. Reston:AIAA Theoretical Fluid Mechanics Meeting,2013.
[9]吴佩佩,朱春玲,刘文平,等.过冷大水滴条件下机翼结冰数值仿真[J].计算机仿真,2014,31(9):51-55.
[10]孙志国,朱程香,付斌,等.二维翼型结冰数值计算[J].航空动力学报,2010,25(7):1485-1490.
[11]冯丽娟,秦娜,易贤.民用航空发动机进气道防冰功率的计算方法研究[J].航空计算技术,2017,47(4):14-17.