Accuracy analysis of Eulerian method for droplet impingement characteristics under aircraft icing conditions
-
摘要:
过冷水滴撞击特性计算是飞机结冰冰形预测与防除冰系统性能分析的基础，常用方法为欧拉法与拉格朗日法，2种方法的结果通常是一致的，但在某些部件上会出现差异。通过对欧拉法与拉格朗日法进行比较，分析2种方法结果的异同，进而讨论欧拉法对于飞机结冰中水滴撞击特性计算的准确性。以NACA 0012翼型、冰风洞风道、S形进气道与发动机气膜帽罩为对象，采用欧拉法与拉格朗日法计算获得水滴运动及局部水收集系数。结果表明：当水滴运动未受到上游效应影响时，欧拉法与拉格朗日法的结果一致；当水滴发生偏转后，欧拉法速度的单一性使水滴流线不能相交，而拉格朗日法能捕捉水滴轨迹的交叉，导致2种方法的预测产生差异，且欧拉法结果与水滴不碰撞及聚并的假设存在冲突；水滴在上游部件空气绕流或气流吹袭作用下都会发生偏转，使得欧拉法与拉格朗日法得到的下游表面水收集系数不相符，欧拉法对于S形进气道与发动机气膜帽罩的水滴运动及撞击特性计算存在误差。研究成果对飞机结冰冰形的准确预测及防除冰系统的设计有重要参考价值。
Abstract:The calculation of super-cooled droplet impingement characteristics is the basis for the prediction of ice shape and the performance analysis of anti-icing and de-icing systems under icing conditions. Eulerian and Lagrangian methods are the commonly used ones, and their predictions are usually consistent. However, different results were found between the two methods for some aircraft components. In this paper, Eulerian and Lagrangian methods are compared to analyze the similarities and differences between the two results, and then the accuracy of Eulerian method for the calculation of the droplet impingement characteristics is discussed. Taking a NACA 0012 airfoil, an icing wind tunnel, an S-shape duct, and an engine cone with a hot-air film-heating anti-icing system as the research objects, the water droplet motion, and local water collection efficiency are calculated by Eulerian and Lagrangian methods. The outcomes demonstrate that the Eulerian and Lagrangian approaches produce consistent outcomes when the droplet motion is not influenced by upstream factors. After the water droplet deflections, the water droplet streamlines obtained by Eulerian method cannot intersect, while Lagrangian method can capture the crossing of droplet trajectories, which leads to the difference between the two methods. And the results of Eulerian method conflict with the assumption of no droplets collision or coalescence. The Eulerian method is not accurate for the calculation of water droplet motion and impingement characteristics of the S-shape duct and the engine cone with hot-air film-heating anti-icing system because water droplets will deflect under the influence of the upstream components and the airflow injection, making the collection efficiencies of the downstream surface obtained by Eulerian and Lagrangian methods inconsistent. This work is helpful for the accurate prediction of ice shape and the design of anti-icing and de-icing systems under aircraft icing conditions.
-
图 1 FENSAP-ICE欧拉法获得的NACA 0012翼型液态水含量分布
Figure 1. Contour of liquid water content obtained by FENSAP-ICE Eulerian method for NACA 0012 airfoil
图 3 FENSAP-ICE欧拉法获得的冰风洞风道液态水含量分布与水滴的流线
Figure 3. Droplet streamlines obtained by FENSAP-ICE Eulerian method with distribution of liquid water content for an ice wind tunnel
图 4 拉格朗日法获得的冰风洞风道水滴运动轨迹
Figure 4. Droplet trajectories obtained by Lagrangian method for an ice wind tunnel
图 5 FENSAP-ICE欧拉法获得的S形进气道液态水含量分布
Figure 5. Contour of liquid water content obtained by FENSAP-ICE Eulerian method for an S-shape duct
图 6 拉格朗日法获得的S形进气道水滴运动轨迹
Figure 6. Droplet trajectories obtained by Lagrangian method for an S-shape duct
图 7 FENSAP-ICE欧拉法与拉格朗日法计算的S形进气道内帽罩表面水收集系数比较
Figure 7. Comparison of collection efficiencies obtained by FENSAP-ICE Eulerian and Lagrangian methods for an S-shape duct
图 8 有出流气膜的发动机帽罩空气速度场分布
Figure 8. Contour of air velocity for an engine cone with outflow air film
图 9 FENSAP-ICE欧拉法获得的有出流气膜的发动机帽罩液态水含量分布
Figure 9. Contour of liquid water content obtained by FENSAP-ICE Eulerian method for an engine cone with outflow air film
图 10 拉格朗日法获得的有出流气膜的发动机帽罩水滴运动轨迹
Figure 10. Droplet trajectories obtained by Lagrangian method for an engine cone with outflow air film
图 11 FENSAP-ICE欧拉法与拉格朗日法计算的有出流气膜的发动机帽罩表面水收集系数比较
Figure 11. Comparison of collection efficiencies obtained by FENSAP-ICE Eulerian and Lagrangian methods for an engine cone with outflow air film
图 12 无出流气膜的发动机帽罩空气速度场分布
Figure 12. Contour of air velocity for an engine cone without outflow air film
图 13 FENSAP-ICE欧拉法获得的无出流气膜的发动机帽罩液态水含量分布
Figure 13. Contour of liquid water content obtained by FENSAP-ICE Eulerian method for an engine cone without outflow air film
图 14 拉格朗日法获得的无出流气膜的发动机帽罩水滴运动轨迹
Figure 14. Droplet trajectories obtained by Lagrangian method for an engine cone without outflow air film
-
[1] CAO Y, TAN W, WU Z. Aircraft icing: An ongoing threat to aviation safety[J]. Aerospace Science and Technology, 2018, 75: 353-385. doi: 10.1016/j.ast.2017.12.028 [2] 雷梦龙, 常士楠, 杨波. 基于Myers模型的三维结冰数值仿真[J]. 航空学报, 2018, 39(9): 121952. doi: 10.7527/S1000-6893.2018.21952LEI M L, CHANG S N, YANG B. Three-dimensional numerical simulation of icing using Myers model[J]. Acta Aeronautica et Astronautica Sinca, 2018, 39(9): 121952(in Chinese). doi: 10.7527/S1000-6893.2018.21952 [3] YU J, PENG L, BU X Q, et al. Experimental investigation and correlation development of jet impingement heat transfer with two rows of aligned jet holes on an internal surface of a wing leading edge[J]. Chinese Journal of Aeronautics, 2018, 31(10): 37-47. [4] WANG C, CHANG S, WU H. Lagrangian approach for simulating supercooled large droplets’ impingement effect[J]. Journal of Aircraft, 2015, 52(2): 1-14. [5] WRIGHT W B. User manual for the NASA Glenn ice accretion code LEWICE: Version 2.2. 2: NASA-CR-2002-211793[R]. Washington, D. C. : NASA, 2002. [6] PAPADAKIS M, HUNG K E, VU G T, et al. Experimental investigation of water droplet impingement on airfoils, finite wings, and an S-duct engine inlet: NASA/TM-2002-211700[R]. Washington, D. C. : NASA, 2002. [7] PAPADAKIS M, RACHMAN A, WONG S C, et al. Water droplet impingement on simulated glaze, mixed, and rime ice accretions: NASA/TM-2007-213961[R]. Washington, D. C. : NASA, 2007. [8] PAPADAKIS M, WONG S C, RACHMAN A, et al. Large and small droplet impingement data on airfoils and two simulated ice shapes: NASA/TM-2007-213959[R]. Washington, D. C. : NASA, 2007. [9] BOURGAULT Y, HABASHI W G, DOMPIERRE J, et al. A finite element method study of Eulerian droplets impingement models[J]. International Journal for Numerical Methods in Fluids, 1999, 29(4): 429-449. doi: 10.1002/(SICI)1097-0363(19990228)29:4<429::AID-FLD795>3.0.CO;2-F [10] WIROGO S, SRIRAMBHATLA S. An Eulerian method to calculate the collection efficiency on two and three dimensional bodies: AIAA 2003-1073[R]. Reston: AIAA, 2003. [11] VEILLARD X, HABASHI W G, AUBÉ M S, et al. FENSAP-ICE: Ice accretion in multi-stage jet engines[C]//19th AIAA Computational Fluid Dynamics. Reston: AIAA, 2009: 4158. [12] ALIAGA C N, AUBÉ M S, BARUZZI G S, et al. FENSAP-ICE-Unsteady: Unified in-flight icing simulation methodology for aircraft, rotorcraft, and jet engines[J]. Journal of Aircraft, 2011, 48(1): 119-126. doi: 10.2514/1.C000327 [13] TONG X, LUKE E. Eulerian simulations of icing collection efficiency using a singularity diffusion model[C]//AIAA Aerospace Sciences Meeting & Exhibit. Reston: AIAA, 2005: 1246. [14] 王洪伟, 李先哲, 宋展. 通用飞机结冰适航验证关键技术及工程应用[J]. 航空学报, 2016, 37(1): 335-350.WANG H W, LI X Z, SONG Z. Key airworthiness validation technologies for icing of general aviation aircraft and their engineering application[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(1): 335-350(in Chinese). [15] 陈希, 招启军. 考虑遮蔽区影响的旋翼三维水滴撞击特性计算新方法[J]. 航空学报, 2017, 38(6): 120745.CHEN X, ZHAO Q J. New method for predicting 3-D water droplet impingement on rotor considering influence of shadow zone[J]. Acta Aeronautica et Astronautica Sinca, 2017, 38(6): 120745(in Chinese). [16] XIE L, LI P, CHEN H, et al. Robust and efficient prediction of the collection efficiency in icing accretion simulation for 3D complex geometries using the Lagrangian approach I: An adaptive interpolation method based on the restricted radial basis functions[J]. International Journal of Heat and Mass Transfer, 2020, 150: 119290. doi: 10.1016/j.ijheatmasstransfer.2019.119290 [17] SHEN X B, TAN Y D, YU R D, et al. Effects of upstream component and air injection on water droplet impingement characteristics for downstream surfaces[J]. International Journal of Aerospace Engineering, 2021, 2021: 1-12. [18] CLOETE S, AMINI S, JOHANSEN S T. Performance evaluation of a complete Lagrangian KTGF approach for dilute granular flow modelling[J]. Powder Technology, 2012, 226: 43-52. doi: 10.1016/j.powtec.2012.04.010 [19] CHEN X, WANG J. A comparison of two-fluid model, dense discrete particle model and CFD-DEM method for modeling impinging gas-solid flows[J]. Powder Technology, 2014, 254: 94-102. doi: 10.1016/j.powtec.2013.12.056 [20] FOX R O. A quadrature-based third-order moment method for dilute gas-particle flows[J]. Journal of Computational Physics, 2008, 227(12): 6313-6350. doi: 10.1016/j.jcp.2008.03.014 [21] AL-KHALIL K, HITZIGRATH R, PHILIPPI O, et al. Icing analysis and test of a business jet engine inlet duct: AIAA-2000-1040[R]. Reston: AIAA, 2000. [22] DONG W, ZHU J, ZHENG M, et al. Thermal analysis and testing of nonrotating cone with hot-air anti-icing system[J]. Journal of Propulsion and Power, 2015, 31(3): 1-8. [23] 高艳欣, 周建军, 李云单, 等. 吹气式旋转帽罩防冰特性[J]. 南京航空航天大学学报, 2016, 48(3): 359-365. doi: 10.16356/j.1005-2615.2016.03.010GAO Y X, ZHOU J J, LI Y D, et al. Anti-icing properties of blowing rotating spinner[J]. Journal of Nanjing University of Aeronautics and Astronautics, 2016, 48(3): 359-365(in Chinese). doi: 10.16356/j.1005-2615.2016.03.010 -
下载:
点击查看大图
计量
- 文章访问数: 270
- HTML全文浏览量: 95
- PDF下载量: 40
- 被引次数: 0
