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3 m×2 m结冰风洞试验技术研究进展

倪章松 刘森云 王桥 王梓旭 郭龙

倪章松, 刘森云, 王桥, 等. 3 m×2 m结冰风洞试验技术研究进展[J]. 实验流体力学, 2019, 33(6): 46-53. doi: 10.11729/syltlx20180115
引用本文: 倪章松, 刘森云, 王桥, 等. 3 m×2 m结冰风洞试验技术研究进展[J]. 实验流体力学, 2019, 33(6): 46-53. doi: 10.11729/syltlx20180115
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: 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

3 m×2 m结冰风洞试验技术研究进展

doi: 10.11729/syltlx20180115
基金项目: 

飞机结冰致灾与防护关键基础问题研究项目 2015CB755800

空气动力学国家重点实验室研究基金资助项目 SKLA2019020401

详细信息
    作者简介:

    倪章松(1973-), 男, 安徽太湖人, 高级工程师。研究方向:飞行器结冰与防除冰技术。通信地址:四川省成都市青羊区二环路西二段75号(610072)。E-mail:13890111882@163.com

    通讯作者:

    刘森云, E-mail: cardclsy@163.com

  • 中图分类号: V211.7

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

  • 摘要: 3 m×2 m结冰风洞于2013年建成,近年来该风洞的试验技术研究取得了一系列的进展。首先对风洞概况和相关试验技术进行了介绍,包括总体情况、性能指标、试验能力等,重点阐述了该结冰风洞已形成的云雾场参数校测、冰形特征捕获、热气防冰和电热除冰等试验技术。其次,对发动机、直升机结冰与防除冰、过冷大水滴和冰晶雨雾模拟等结冰风洞试验技术新的发展方向进行了分析和探讨,提出了发展思路。可为结冰风洞建设与试验技术的研究提供参考。
  • 图  1  3 m×2 m结冰风洞布局图

    Figure  1.  Sketch of the layout of 3 m×2 m IWT

    图  2  霜冰与明冰试验结果对比

    Figure  2.  Comparison of test results for rime ice and glass ice

    图  3  均匀度格栅结冰

    Figure  3.  Icing on grid

    图  4  用于MVD校测的PDI-FPDR仪器

    Figure  4.  PDI-FPDR instrumentation for MVD calibration

    图  5  风洞中的冰刀装置[24]

    Figure  5.  Icing blade device in wind tunnel[24]

    图  6  不同风速下的结冰质量[26]

    Figure  6.  Mass of ice at different flow speeds[26]

    图  7  传统热刀法冰形测量技术

    Figure  7.  Ice shape measurement method using hot knife

    图  8  激光扫描冰形非接触式测量技术

    Figure  8.  Ice shape non-contact measurement technology using laser scanning

    图  9  热气供气系统

    Figure  9.  Hot-air supply system

    图  10  发动机结冰与防除冰研究关系图

    Figure  10.  Research map of icing and de-icing techniques on aircraft engine

    图  11  发动机进气模拟系统

    Figure  11.  Engine intake simulation system

    图  12  SLD和冰晶大气特征示意[43]

    Figure  12.  Features of SLD and ice crystal atmosphere characteristics[43]

    图  13  发动机冰晶结冰研究内容

    Figure  13.  Research content of crystal-icing test technologies for aircraft engine

    表  1  结冰风洞主要设计参数[21]

    Table  1.   Main indexes of 3 m×2 m icing wind tunnel[21]

    主试验段 次试验段 高速试验段
    长×宽×高/(m×m×m) 3.0×2.0×6.5 4.8×3.2×9.0 2.0×1.5×4.5
    风速/(m·s-1) 21 ~210 8~78 26~256
    温度 范围:常温~-40 ℃速率:从20 ℃降到-20 ℃时, 时间不超过40 min不均匀性:≤1 ℃控制精度:±0.5 ℃
    湿度 范围:70%~100%(-15~-20 ℃); 100%(-20~-40 ℃)精度:±5%
    高度 结冰试验:0~7000 m高空低雷诺数试验:0~20 000 m
    云雾参数 液态水含量(LWC):0.2~3 g/m3平均水滴直径(MVD):10~300 μm雾化均匀区:60%试验段截面积
    下载: 导出CSV

    表  2  冰晶模拟技术指标

    Table  2.   Crystal-icing simulation technical indexes

    参数 最小值 最大值
    高度/km 1.2 15.0
    进气总温 -60 ℉(-51 ℃) 50 ℉(10 ℃)
    马赫数 0.15 0.80
    进气流量/(kg·s-1) 4.5 150.0
    LWC/(g·m-3) 0.5 8.0
    MVD/μm 15 >100(非全冻结)
    结冰时间/min 45(连续)
    下载: 导出CSV
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出版历程
  • 收稿日期:  2018-08-28
  • 修回日期:  2019-09-23
  • 刊出日期:  2019-12-25

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