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旋翼翼型动态风洞试验技术研究

张卫国 李国强 李栋 车兵辉 顾艺 吴霖鑫

张卫国, 李国强, 李栋, 等. 旋翼翼型动态风洞试验技术研究[J]. 实验流体力学, 2023, 37(2): 78-93 doi: 10.11729/syltlx20210147
引用本文: 张卫国, 李国强, 李栋, 等. 旋翼翼型动态风洞试验技术研究[J]. 实验流体力学, 2023, 37(2): 78-93 doi: 10.11729/syltlx20210147
ZHANG W G, LI G Q, LI D, et al. Research on dynamic wind tunnel test technology of rotor airfoil[J]. Journal of Experiments in Fluid Mechanics, 2023, 37(2): 78-93 doi: 10.11729/syltlx20210147
Citation: ZHANG W G, LI G Q, LI D, et al. Research on dynamic wind tunnel test technology of rotor airfoil[J]. Journal of Experiments in Fluid Mechanics, 2023, 37(2): 78-93 doi: 10.11729/syltlx20210147

旋翼翼型动态风洞试验技术研究

doi: 10.11729/syltlx20210147
基金项目: 预研专用技术项目(30103010304);预研共用技术项目(50906030601);预研综合研究项目(JK20211A020092)
详细信息
    作者简介:

    张卫国:(1975—),男,山东兖州人,博士,研究员。 研究方向:直升机空气动力学。通信地址:四川省绵阳市涪城区二环路南段6号(621000)。 E-mail:zwglxy@163.com

    通讯作者:

    E-mail:CARDCL@126.com

  • 中图分类号: V211.52;V211.752

Research on dynamic wind tunnel test technology of rotor airfoil

  • 摘要: 旋翼翼型的设计优化及性能确定亟须建立并发展翼型动态风洞试验技术。通过动力学仿真与结构优化设计,基于FL–11低速风洞研制出旋翼翼型两自由度动态试验装置,可实现俯仰/沉浮单自由或两自由度耦合运动,最高振荡频率达到5 Hz;基于FL–20连续式跨声速风洞研制出旋翼翼型高频高速动态试验装置,最高振荡频率达到17 Hz,试验最高雷诺数为5 × 106,模拟参数包线满足真实直升机参数要求;基于FL–14低速风洞研制出大尺度旋翼翼型动态试验装置,翼型模型弦长为800 mm,试验最高雷诺数达到4 × 106。完善了旋翼翼型动态试验精准测试相关技术,并开展了验证性试验,试验数据规律合理、量值可靠,表明试验系统及相关测试技术具有较高的可靠性,可为旋翼翼型动态气动特性试验评估提供重要的设备平台和技术支撑。
  • 图  1  低速风洞两自由度动态试验装置

    Figure  1.  Dynamic test device of two degree of freedom in low speed wind tunnel

    图  2  装置第一阶模态振型

    Figure  2.  Frequency modes of first order for the device

    图  3  低速风洞动态试验装置控制系统结构

    Figure  3.  Control system structure of low speed wind tunnel dynamic test device

    图  4  旋翼翼型高频高速动态试验装置

    Figure  4.  High frequency and high speed rotor airfoil dynamic test device

    图  5  大尺度旋翼翼型动态试验装置示意图

    Figure  5.  Schematic diagram of dynamic test device for large scale airfoil model

    图  6  动力学仿真结果

    Figure  6.  Dynamic simulation results

    图  7  FL–14低速风洞旋翼翼型动态试验张线抑振

    Figure  7.  Vibration suppression of rotor airfoil dynamic test in FL–14 low-speed wind tunnel

    图  8  翼型模型结构图

    Figure  8.  Structural diagram of airfoil model

    图  9  翼型网格划分图

    Figure  9.  Grid division of airfoil

    图  10  旋翼翼型动态风洞试验传感器安装布置示意图

    Figure  10.  Installation layout of sensors for dynamic wind tunnel test of rotor airfoil

    图  11  翼型模型测压孔分布图

    Figure  11.  Pressure tap distribution of airfoil model

    图  12  高速风洞动态天平与翼型连接方式

    Figure  12.  Connection between dynamic balance and airfoil in high speed wind tunnel

    图  13  低速风洞翼型动态试验天平安装连接图

    Figure  13.  Installation and connection diagram of airfoil dynamic test balance in low speed wind tunnel

    图  14  同步采集原理

    Figure  14.  Principle of synchronous acquisition

    图  15  数据采集系统结构

    Figure  15.  Structure of data acquisition system

    图  16  OptotrakTM系统典型构成图

    Figure  16.  Typical composition of OptotrakTM system

    图  17  旋翼翼型动态振荡位移变形测量试验照片

    Figure  17.  Test photo of oscillation displacement and deformation measurement for rotor airfoil

    图  18  耦合振荡试验频率影响结果对比

    Figure  18.  Comparison of frequency influence results of coupled oscillation test

    图  19  旋翼翼型静态/动态风洞试验测力结果和测压结果对比

    Figure  19.  Comparison of static and dynamic wind tunnel test results of rotor airfoil

    图  20  变振荡频率的翼型气动曲线

    Figure  20.  Aerodynamic curve of airfoil with varying oscillation frequency

    图  21  不同平衡迎角下振荡翼型气动曲线

    Figure  21.  Aerodynamic curves of oscillating airfoil at different balanced angles of attack

    图  22  高频高速动态试验装置运动能力考核试验结果

    Figure  22.  Test results of motion ability assessment of high frequency and high speed dynamic test device

    表  1  国内外主要气动研究机构动态试验模拟能力对比表

    Table  1.   Comparison of dynamic test simulation capabilities of major international aerodynamic research institutes

    风洞名称模型尺度(弦长)/m来流马赫数雷诺数/(105)振荡幅值振荡频率/Hz运动自由度
    美国NASA结冰风洞[37]0.400.40(最大)3710°5.0俯仰
    德国荷兰DNW TWG[12]0.300.30~0.50354°~7°6.6俯仰
    法国ONERA F2[38]0.500.16(常用)1910°5.0俯仰
    俄罗斯TsAGI SVS−2[35]0.180.30~0.602515.0俯仰
    中国南京航空航天大学
    非定常风洞[33]
    0.300.10(最大)710° (俯仰)
    100 mm (沉浮)
    4.0(俯仰)
    2.0(沉浮)
    俯仰/沉浮
    中国西北工业大学 NF−3[39]0.700.20(最大)3215° (俯仰)
    100 mm (沉浮)
    5.0(俯仰)
    3.0(沉浮)
    俯仰/沉浮
    中国西北工业大学 NF−6[31]0.200.301410°8.0俯仰
    中国气动中心 FL−11[40]0.400.20~0.323020° (俯仰)
    150 mm (沉浮)
    6.0(俯仰)
    5.0(沉浮)
    俯仰/沉浮
    中国气动中心 FL−14[29]0.800.25(最大)4030°4.0俯仰
    中国气动中心 FL−20[41-42]0.210.20~0.605010°17.0俯仰
    下载: 导出CSV

    表  2  装置前五阶固有频率

    Table  2.   The first five order inherent frequency

    阶数固有频率/Hz
    118.5
    220.3
    324.9
    448.0
    565.3
    下载: 导出CSV

    表  3  旋翼翼型动态试验装置技术指标

    Table  3.   Technical specifications of rotor airfoil dynamic test device

    风洞测试内容技术指标
    FL−11
    α−180°~180°,精度0.01°,在线连续可调
    h−150~150 mm,精度0.01 mm,在线连续可调
    α1≤30°,精度0.05°,在线连续可调
    h1≤150 mm,精度0.05 mm,在线连续可调
    fpifpl俯仰0.1~6.0 Hz,沉浮0.1~5.0 Hz,
    精度优于0.01 Hz,在线连续可调
    Rec3 × 106
    FL−20
    α13°、5°、8°、10°,精度优于0.1°
    α0−5°、0°、5°、10°,精度优于0.1°
    fpi0.2~17.0 Hz,精度优于0.05 Hz
    Ma0.2~0.6
    Rec5 × 106(压力2 atm)
    FL−14
    α−180°~180°,精度0.01°,在线连续可调
    α1≤30°,精度0.05°,在线连续可调
    fpi0.1~4.0 Hz,精度优于0.01 Hz,在线连续可调
    Rec4 × 106
    下载: 导出CSV

    表  4  翼型模型结构优化结果

    Table  4.   Optimization results of airfoil model structure

    优化目标
    质量/kg受载最大
    等效应力/N
    最大位移
    /mm
    第一阶固有
    频率/Hz
    失效
    指标
    初始值 12.567 252.15 7.46 56.10 0.728
    优化值 8.288 227.16 5.74 63.28 0.319
    变化值 4.279 25.34 1.72 7.18 0.409
    变化率 34.05 9.91 23.06 12.80 56.18
    下载: 导出CSV

    表  5  静态测量精准度结果

    Table  5.   Results of static measurement

    俯仰角度沉浮位移
    名义值/(°)实测值/(°)名义值/mm实测值/mm
    −5 −4.957 −30 −29.946
    5 5.046 −15 −15.054
    10 9.985 15 15.001
    20 20.038 30 29.932
    下载: 导出CSV

    表  6  俯仰–沉浮两自由度耦合振荡动态测量结果

    Table  6.   Dynamic measurement results of pitching and plunging coupled oscillation

    俯仰角度沉浮位移
    名义值/(°)实测值/(°)名义值/mm实测值/mm
    5 4.951
    (无吹风)
    30 30.930
    (无吹风)
    4.964
    (吹风,v=34 m/s)
    31.940
    (吹风,v=34 m/s)
    4.947
    (吹风,v=45 m/s)
    32.882
    (吹风,v=45 m/s)
    下载: 导出CSV
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出版历程
  • 收稿日期:  2021-09-30
  • 修回日期:  2021-12-26
  • 录用日期:  2022-01-13
  • 刊出日期:  2023-04-25

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