Research progress of test technologies for 3 m×2 m icing wind tunnel

Ni Zhangsong; Liu Senyun; Wang Qiao; Wang Zixu; Guo Long

doi:10.11729/syltlx20180115

Volume 33 Issue 6

Dec. 2019

Turn off MathJax

Article Contents

Article Navigation > Journal of Experiments in Fluid Mechanics > 2019 > 33(6): 46-53

Ni Zhangsong, Liu Senyun, Wang Qiao, et al. Research progress of test technologies for 3 m×2 m icing wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2019, 33(6): 46-53. doi: 10.11729/syltlx20180115

Citation:

PDF( 8076 KB)

Research progress of test technologies for 3 m×2 m icing wind tunnel

doi: 10.11729/syltlx20180115

State Key Laboratory of Aerodynamics, China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China

Received Date: 2018-08-28
Rev Recd Date: 2019-09-23
Publish Date: 2019-12-25

Abstract

Abstract

The 3 m×2 m icing wind tunnel was built in 2013. A lot of progresses have been made in the research of the wind tunnel test technologies in recent years. This paper presents the basic situations and test technologies of the 3 m×2 m icing wind tunnel, including overall situation, technical indexes and test capabilities. The status of the conventional icing and anti-icing test technologies in the 3 m×2 m icing wind tunnel, such as the calibration of cloud parameters, the capture of ice characteristics, the anti-icing technology using hot air and the de-icing technology using electrics are described in detail. From the view of engineering application and basic research, the research trend of test technologies in the fields of aircraft engines, helicopters, supercooled large droplets (SLD), and ice crystals are highlighted and analyzed. The development ideas and methods are put forward from the perspective of independent innovation. This paper provides a reference for the research on the construction and test technology development for the icing wind tunnel.
- aircraft icing,
- icing wind tunnel,
- test technology,
- research progress

FullText(HTML)

References(49)

References

[1]	裘燮纲, 韩凤华.飞机防冰系统[M].北京:航空专业教材编审组, 1985.
[2]	朱春玲, 朱程香.飞机结冰及其防护[M].北京:科学出版社, 2016. Zhu C L, Zhu C X. Aircraft icing and its protection[M]. Beijing: Science Press, 2016.
[3]	林贵平, 卜雪琴, 申晓斌, 等.飞机结冰与防冰技术[M].北京:北京航空航天大学出版社, 2016. Lin G P, Bu X Q, Shen X B, et al. Aircraft icing and anti-icing technology[M]. Beijing: Beihang University Press, 2016.
[4]	王宗衍.冰风洞与结冰动力学[J].制冷学报, 1999, 20(4):15-17. http://d.old.wanfangdata.com.cn/Conference/3510382 Wang Z Y. Icing wind tunnel and icing dynamics[J]. Journal of Refrigeration, 1999, 20(4):15-17. http://d.old.wanfangdata.com.cn/Conference/3510382
[5]	战培国.结冰风洞研究综述[J].实验流体力学, 2007, 21(3): 92-96. doi: 10.3969/j.issn.1672-9897.2007.03.019 Zhan P G.A review of research on icing wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2007, 21(3):92-96. doi: 10.3969/j.issn.1672-9897.2007.03.019
[6]	Gonsalez J, Arrington E. Aerodynamic calibration of the NASA Lewis icing research tunnel (1997 tests)[R]. AIAA-98-0633, 1998.
[7]	Gates H M, Knudsen J C. A case for optionally piloted vehicle research and development[R]. AIAA 2007-2760, 2007.
[8]	Liu H L, Fan T Y, Xing Y M, et al. Study for spray experiment and simulation of nozzle on icing wind tunnel[J]. Advanced Materials Research, 2012, 490-495:2573-2577. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=10.4028/www.scientific.net/AMR.490-495.2573
[9]	刘政崇, 彭强, 肖斌, 等. 3m×2m结冰风洞设计总体初步方案[C]//大型飞机关键技术高层论坛暨中国航空学会学术年会论文集. 2007. Liu C Z, Peng Q, Xiao B, et al. 3m×2m icing wind tunnel overall preliminary design scheme[C]//Proc of the BBS and annual conference of Chinese aviation association. 2007.
[10]	熊建军, 倪章松, 李刚, 等. 3m×2m结冰风洞动力系统设计与应用[J].测控技术, 2018, 37(S2):204-208, 215. http://www.cnki.com.cn/Article/CJFDTotal-IKJS2018S2057.htm Xiong J J, Ni Z S, Li G, et al. Design and application of power system for 3m×2m icing wind tunnel[J]. Measurement and Control Technology, 2018, 37(S2):204-208, 215. http://www.cnki.com.cn/Article/CJFDTotal-IKJS2018S2057.htm
[11]	丛成华, 彭强, 汪伏波, 等.基于粒子轨迹的结冰风洞收缩段优化设计数值模拟[J].航空动力学报, 2012, 27(7):1555-1561. http://d.old.wanfangdata.com.cn/Periodical/hkdlxb201207018 Cong C H, Peng Q, Wang F B, et al. Numerical simulation on optimization design of contraction section in icing wind tunnel based on droplet trajectory[J]. Journal of Aerospace Power, 2012, 27(7): 1555-1561. http://d.old.wanfangdata.com.cn/Periodical/hkdlxb201207018
[12]	战培国.国家大型结冰风洞运营管理研究[J].航空科学技术, 2014, 25(8):95-99. doi: 10.3969/j.issn.1007-5453.2014.08.021 Zhan P G. Research on the development stratagem of national large icing wind tunnel[J]. Aeronautical Science and Technology, 2014, 25(8):95-99. doi: 10.3969/j.issn.1007-5453.2014.08.021
[13]	Imperato L, Leone G, Vecchione L. Spray nozzles experiment comparison in laboratory and icing wind tunnel testing[R]. AIAA 2000-0487, 2000.
[14]	Irvine T B, Oldenburg J R, Sheldon D W. The new icing cloud simulation system at NASA Lewis' icing research tunnel[R]. AIAA-98-143, 1998.
[15]	Addy H E Jr, Keith T G Jr. Investigation of the flow in the diffuser section of the NASA Lewis icing research tunnel[R]. AIAA-89-755, 1989.
[16]	Canacci V A, Gonsalez J C. Flow quality measurements in an aerodynamic model of NASA Lewis' icing research tunnel[R]. AIAA-95-2389, 1995.
[17]	Wright W B, Gent R W, Guffond D. DRA/NASA/ONERA collaboration on icing research, Part 2: prediction of airfoil ice accretion[R]. NASA CR-202349, 1997.
[18]	Wright W B, Bidwell C S. Additional improvements to the NASA Lewis ice accretion code LEWICE[R]. AIAA-95-752, 1995.
[19]	Masiulaniec K C, Wright W B. User's manual for the NASA Lewis ice accretion/heat transfer prediction code with electrothermal deicer input[R]. NASA Contractor Report 4530, 1994. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=XnXewb3bJ9iMSHOwY5sjiCtBqG4iyc2vaqX5twvf4+4=
[20]	Baruzzi G, Tran P, Habashi W G, et al. FENSAP-ICE: progress towards a rotorcraft full 3D icing simulation system[R]. AIAA 2003-0024, 2003.
[21]	王梓旭, 沈浩, 郭龙, 等. 3m×2m结冰风洞云雾参数校测方法[J].实验流体力学, 2018, 32(2):61-67. http://d.old.wanfangdata.com.cn/Periodical/ltlxsyycl201802010 Wang Z X, Shen H, Guo L, et al. Cloud calibration method of 3m×2m icing wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2018, 32(2):61-67. http://d.old.wanfangdata.com.cn/Periodical/ltlxsyycl201802010
[22]	SAE Aerospace. Calibration and acceptance of icing wind tunnels: SAE ARP5905[S]. SAE, 2003.
[23]	SAE Aerospace. Icing wind tunnel interfacility comparison tests: SAE ARP5666[S]. SAE, 2012.
[24]	郭龙, 程尧, 王梓旭.结冰风洞试验段云雾粒径测量与控制实验研究[J].实验流体力学, 2018, 32(2):55-60. http://d.old.wanfangdata.com.cn/Periodical/ltlxsyycl201802009 Guo L, Cheng Y, Wang Z X. Experimental study on droplet size measurement and control of icing cloud in icing wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2018, 32(2):55-60. http://d.old.wanfangdata.com.cn/Periodical/ltlxsyycl201802009
[25]	易贤, 桂业伟, 杜雁霞, 等.结冰风洞水滴直径标定方法研究[J].实验流体力学, 2010, 24(5):36-41. doi: 10.3969/j.issn.1672-9897.2010.05.008 Yi X, Gui Y W, Du Y X, et al. Study on calibration method of water droplet diameter in frozen wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2010, 24(5):36-41. doi: 10.3969/j.issn.1672-9897.2010.05.008
[26]	易贤, 朱国林, 王开春, 等.结冰风洞试验水滴直径选取方法[J].航空学报, 2010, 31(5):877-882. http://d.old.wanfangdata.com.cn/Periodical/hkxb201005001 Yi X, Zhu G L, Wang K C, et al. Selection of water droplet diameter in icing wind tunnel test[J]. Acta Aeronautica et Astronautica Sinica, 2010, 31(5):877-882. http://d.old.wanfangdata.com.cn/Periodical/hkxb201005001
[27]	易贤, 王斌, 李伟斌, 等.飞机结冰冰形测量方法研究进展[J].航空学报, 2017, 38(2):13-24. http://d.old.wanfangdata.com.cn/Periodical/hkxb201702002 Yi X, Wang B, Li W B, et al. Research progress on ice shape measurement approaches for aircraft icing[J]. Acta Aeronautica et Astronautica Sinica, 2017, 38(2):13-24. http://d.old.wanfangdata.com.cn/Periodical/hkxb201702002
[28]	李伟斌, 易贤, 杜雁霞, 等.基于变分分割模型的结冰冰形测量方法[J].航空学报, 2017, 38(1):95-102. http://d.old.wanfangdata.com.cn/Periodical/hkxb201701009 Li W B, Yi X, Du Y X, et al. A measurement approach for ice shape based on variational segmentation model[J]. Acta Aeronautica et Astronautica Sinica, 2017, 38(1):95-102. http://d.old.wanfangdata.com.cn/Periodical/hkxb201701009
[29]	Gong X L, Bansmer S. Laser scanning applied for ice shape measurements[J]. Cold Regions Science and Technology, 2015, 115:64-76. doi: 10.1016/j.coldregions.2015.03.010
[30]	Gong X L, Bansmer S. 3-D ice shape measurements using mid-infrared laser scanning[J]. Optics express, 2015, 23(4): 4908-4926. doi: 10.1364/OE.23.004908
[31]	Lee S, Broeren A P, Addy H E, et al. Development of 3D ice accretion measurement method[R]. AIAA 2012-2938, 2012.
[32]	Mercer C R, Vargas M, Oldenburg J R. A preliminary study on ice shape tracing with a laser light sheet[R]. NASA TM-105964, 1993. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=Jm38EmO+6rMeqp94hH06UzDsIEWbkcWVZweV/yV61cY=
[33]	郭之强, 郑梅, 董威, 等.表面凸起对机翼热气防冰腔内换热强化的影响[J].航空学报, 2017, 38(2):81-90. http://d.old.wanfangdata.com.cn/Periodical/hkxb201702008 Guo Z Q, Zheng M, Dong W, et al. Influence of surface convex on heat transfer enhancement of wing hot air anti-icing system. Acta Aeronautica et Astronautica Sinica, 2017, 38(2):81-90. http://d.old.wanfangdata.com.cn/Periodical/hkxb201702008
[34]	Teng X, Dong J K, Chen H W, et al. Experimental investigation of deicing characteristics using hot air as heat source[J]. Applied Thermal Engineering, 2016, 107:681-688. doi: 10.1016/j.applthermaleng.2016.05.162
[35]	Pellissier M P C, Habashi W G, Pueyo A. Optimization via FENSAP-ICE of aircraft hot-air anti-icing systems[J]. Journal of Aircraft, 2012, 48(1):265-276. http://cn.bing.com/academic/profile?id=f87e65f94159e4cee521cec855b8648e&encoded=0&v=paper_preview&mkt=zh-cn
[36]	Papadakis M, Wong S H, Yeong H W, et al. Icing tunnel experiments with a hot air anti-icing system[R]. AIAA 2008-444, 2008.
[37]	肖春华, 桂业伟, 林贵平.飞机电热除冰的研究进展与展望[J].科技导报, 2011, 29(18):69-73. doi: 10.3981/j.issn.1000-7857.2011.18.011 Xiao C H, Gui Y W, Lin G P. A review of studies of aircraft electrothermal de-icing[J]. Science & Technology Review, 2011, 29(18):69-73. doi: 10.3981/j.issn.1000-7857.2011.18.011
[38]	Pourbagian M, Habashi W G. Aero-thermal optimization of in-flight electro-thermal ice protection systems in transient de-icing mode[J]. International Journal of Heat and Fluid Flow, 2015, 54(3):167-182. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=c0b27abc1a8d9a761c3c4cb634e1446f
[39]	杨倩, 常士楠, 袁修干.发动机进气道水滴撞击特性分析[J].北京航空航天大学学报, 2002, 28(3):362-365. doi: 10.3969/j.issn.1001-5965.2002.03.031 Yang Q, Chang S N, Yuan X G. Analysis of droplet impact characteristics in engine inlet[J]. Journal of Beijing University of Aeronautics and Astronautics, 2002, 28(3):362-365. doi: 10.3969/j.issn.1001-5965.2002.03.031
[40]	符澄, 彭强, 张海洋, 等.结冰风洞喷嘴雾化特性研究[J].实验流体力学, 2015, 29(2):32-36. http://d.old.wanfangdata.com.cn/Periodical/ltlxsyycl201502006 Fu C, Peng Q, Zhang H Y, et al. The atomization characteristics research for spray nozzle of icing wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2015, 29(2):32-36. http://d.old.wanfangdata.com.cn/Periodical/ltlxsyycl201502006
[41]	Flemming R J. The past twenty years of icing research and development at Sikorsky Aircraft[R]. AIAA-2002-0238, 2002.
[42]	李国知, 曹义华, 钟国.旋翼结冰模型与纵列式直升机平衡特性分析[J].北京航空航天大学学报, 2010, 36(9):1034-1037. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=bjhkhtdxxb201009007 Li G Z, Cao Y H, Zhong G. Rotor icing model and balancing characteristics analysis of tandem helicopter [J]. Journal of Beijing University of Aeronautics and Astronautics, 2010, 36(9):1034-1037. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=bjhkhtdxxb201009007
[43]	Renato(Ron) C. NASA capabilities in aircraft icing[R]. NASA Technical Report GRC-E-DAA-TN40057, 2017.
[44]	Zhang C, Wang F X, Kong W L, et al. The characteristics of SLD icing accretions and aerodynamic effects on high-lift configurations[R]. AIAA 2015-3385, 2015.
[45]	Potapczuk M G, Tsao J C. Further examinations of bimodal SLD ice accretion in the NASA icing research tunnel[R]. AIAA 2018-3182, 2018.
[46]	Oliver M J. Validation ice crystal icing engine test in the propulsion systems laboratory at NASA Glenn Research Center [R]. AIAA-2014-2898, 2014.
[47]	Addy H E Jr, Veres J P. An overview of NASA engine ice-crystal icing research[R]. NASA/TM-2011-21725, 2011.
[48]	Veres J P, Jorgenson P C E, Coennen R. Modeling of commercial turbofan engine with ice crystalingestion; follow-on[R]. AIAA 2014-2899, 2014.
[49]	Flegel A B. Ice crystal icing research at NASA[R]. AIAA 2017-4085, 2017.