连续式跨声速风洞流场湍流度测试实验研究

朱博, 陈吉明, 吴巍, 裴海涛

朱博,陈吉明,吴巍,等. 连续式跨声速风洞流场湍流度测试实验研究[J]. 实验流体力学,2022,36(X):1-9. DOI: 10.11729/syltlx20220034
引用本文: 朱博,陈吉明,吴巍,等. 连续式跨声速风洞流场湍流度测试实验研究[J]. 实验流体力学,2022,36(X):1-9. DOI: 10.11729/syltlx20220034
ZHU B,CHEN J M,WU W,et al. Experimental investigation of turbulence intensity measurement in continuous transonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2022,36(X):1-9.. DOI: 10.11729/syltlx20220034
Citation: ZHU B,CHEN J M,WU W,et al. Experimental investigation of turbulence intensity measurement in continuous transonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2022,36(X):1-9.. DOI: 10.11729/syltlx20220034

连续式跨声速风洞流场湍流度测试实验研究

详细信息
    作者简介:

    朱博: (1973—),男,广西百色人,硕士研究生,高级工程师。研究方向:风洞流场测试与分析技术,热线技术,测控技术。通信地址:四川省绵阳市二环路南段6号12信箱1分箱 (621000)。E-mail:bobjou@139.com

    通讯作者:

    朱博: E-mail:bobjou@139.com

  • 中图分类号: V211.7;O357.5

Experimental investigation of turbulence intensity measurement in continuous transonic wind tunnel

  • 摘要: 使用恒温式热线风速仪(CTA)完成了0.6m连续式跨声速风洞换热器入口至试验段流场湍流度测量;采用二维热线探头旋转方法,完成了换热器入口至稳定段出口的低速流场三维湍流度分布测试;采用一维探头连续变热线过热比方法,完成了试验段跨声速流场湍流度测试,测试流场速度最高马赫数为1.5。研究结果表明:换热器段和稳定段是重要的降湍部段,均可降低湍流度90%以上;稳定段阻尼网从3层增加至5层,可降低稳定段湍流度50%,可降低试验段湍流度17%;采用CTA连续变热线过热比方法可以获得试验段可压流场的扰动图(反映了试验段流场的扰动特征)和湍流度值,马赫数为0.4的流场扰动图呈一阶线性特征,马赫数为0.7的流场扰动图呈现双曲线特征。实验结果可为连续式跨声速风洞流场湍流度评估和优化提供依据。
    Abstract: The constant temperature anemometer is used for turbulence intensity measurement from the entrance of the heat exchanger to the test section in a 0.6 m continuous transonic wind tunnel. Two dimensional hot wire probes were rotated to measure the three dimensional turbulence intensity in the flow field from the entrance of the heat exchanger to the exit of the setting chamber. One dimension hot wire probes were used for turbulence intensity measurement in transonic flow of test section, with the method of continuous varying hot wires over heating ratio, where the maximum testing flow velocity was Ma1.5. Test results show that, the heat exchanger and the setting chamber paly important roles in damping turbulence intensity, each of which could reduce the turbulence intensity by more than 90%; when the screens in the setting chamber are added from 3 to 5 layers, the turbulence intensity of setting chamber could be decreased by 50%, and could be decreased by 17% in the test section; using the continuous varying hot wires over heating ratio method, the fluctuation diagrams and turbulence intensity are acquired in the test section. The fluctuation curve is of the straight line type at Mach number 0.4, and the fluctuation curve is of the hyperbola type at Mach number 0.7, which present the fluctuation characteristics in the flow field. Experiment results are useful for flow turbulence evaluation and optimization in the continuous transonic wind tunnel.
  • 风洞标模最初是检验风洞试验数据长期稳定性指标(如气流偏角、数据重复性、数据不确定度等)的重要工具[1, 2]。随着CFD(Computational Fluid Dynamics)技术不断发展,标模更多被用于验证先进的CFD算法[3-8]。NASA(National Aeronautics and Space Administration)先后研发了DLR-F4[3]、DLR-F6[9]、CRM[10]等标模, 并在风洞中进行试验,利用试验数据验证CFD算法在阻力预测中的实用性。DNW(德-荷风洞机构)与中国航空研究院利用CAE-AVM数模研究高马赫数下机翼变形时CFD算法的预测性能[11]。这些模型本身之间的数据相关性不强,同一模型在不同风洞间的数据比对结果相差较大[12]

    为提升试验数据质量,探究不同风洞之间试验数据的相关性,进一步开展CFD验证与确认工作,中国空气动力研究与发展中心(CARDC)建立了大展弦比运输机高低速统一标模体系[13]。CARDC低速空气动力研究所依据发布数模,先后研制了用于FL-13风洞,缩比为1 :6.4的CHN-T1标模[14];用于FL-17风洞(5.5m×4.0m声学风洞),缩比为1 :8.5的标模;用于FL-12风洞,缩比为1 :11.5的标模以及用于FL-11风洞(1.8m×1.4m风洞),缩比为1 :32的标模。这组标模既可用来检验各自风洞试验数据质量,也可用来验证不同风洞之间试验数据的相关性,同时CHN-T1标模也可为CFD验证与确认提供基准。为获得准确的试验数据,利用CHN-T1标模先后在FL-13风洞和DNW-LLF风洞进行了相关试验。

    FL-13风洞是一座直流式、闭口、串列双试验段的大型低速风洞,轮廓图见图 1。第一试验段宽12m、高16m、长25m,第二试验段宽8m、高6m、长15m。每个试验段顶壁开有9.0m×6.0m的顶门,便于模型及试验装置进出,其下洞壁均配有直径Φ6m的转盘,可在0°~360°范围内任意转动。风洞由3台品字型布局的电机提供动力源,电机总功率7.8MW。

    图  1  FL-13风洞轮廓图
    Fig.  1  Sketch of FL-13 wind tunnel

    FL-13风洞试验在第二试验段进行,该试验段有效截面积47.4m2,常用试验风速20~80m/s,最高雷诺数4.5×106

    DNW-LLF风洞是一座单回流、具有2个可更换闭口试验段的大型低速风洞,轮廓图见图 2。每个可更换部段均包括收缩段、试验段和扩散段。整个可更换部段长45m。最大试验段横截面为9.5m×9.5m,较小试验段横截面为8.0m×6.0m或6.0m×6.0m,对应试验段分别称为9.5×9.5试验段、8.0×6.0试验段和6.0×6.0试验段。DNW-LLF风洞也可按开口模式运行,此时风洞配置8.0×6.0收缩段和9.5×9.5扩散段。风洞动力由1台14MW的电机驱动恒定桨角的风扇获得。风洞风速通过风扇转速变化调节,风扇最大转速225r/min。

    图  2  DNW-LLF风洞轮廓图
    Fig.  2  Sketch of DNW-LLF wind tunnel

    试验在8.0×6.0试验段进行,该试验段长20m,空风洞最高风速116m/s,最高雷诺数5.3×106

    CHN-T1标模为下单翼、低平尾常规布局,机翼翼型为超临界翼型,机身代表宽体客机外形。CHN-T1设计巡航马赫数Ma=0.78,对应设计升力系数CL=0.5。CHN-T1外形尺寸见图 3, 图中单位为mm。CHN-T1展弦比为9.355,机翼中线后掠角23.2°,机翼参考面积2.328m2,展长4.667m,平均气动弦长0.582m。模型力矩参考中心位于机身中线上、机头后方1.986m处。同时,模型预留了短舱接口。

    图  3  CHN-T1标模外形尺寸
    Fig.  3  Layout and dimension of CHN-T1 calibration model

    在模型机翼上下表面前缘、机头前缘、垂尾前缘、平尾上下表面前缘粘贴了锯齿形转捩带以实现附面层固定转捩。机翼转捩带厚度0.25mm,粘贴于距前缘5%弦长处;平尾、垂尾和机头转捩带厚度0.40mm,平尾、垂尾转捩带粘贴于距前缘8%弦长处,机头转捩带粘贴于距离机头70mm处。

    CHN-T1标模在FL-13风洞进行了为期2周的测力和流动显示试验,测力所用天平为CARDC研制的TG-1801A天平[15],所用支撑为特大迎角支撑系统+斜腹撑(见图 4)。试验风速40、50、60和70m/s,以平均气动弦长为参考长度的雷诺数分别为1.4×106、1.8×106、2.1×106和2.5×106。低雷诺数用于对比小风洞试验结果,高雷诺数用于同高速风洞试验数据对比及提供CFD验证与确认基准。文中的对比试验数据均在Re=2.5×106给出。试验数据进行了洞壁干扰修正和支架干扰修正。支架干扰修正中支架量通过图 5中“背撑+假腹撑-背撑”(即④-②)获得。试验过程中模型迎角变化范围为-4°~22°,侧滑角变化范围为-18°~18°。

    图  4  FL-13风洞标模试验
    Fig.  4  CHN-T1 test in FL-13 wind tunnel
    图  5  支架干扰修正
    Fig.  5  Support interference correction

    CHN-T1标模在DNW-LLF风洞进行了为期3周的测力、测力矩试验,测力所用天平为DNW的W616天平[16],所用支撑为尾撑系统+斜腹撑(见图 6)。试验风速为40、50、60、70、80及90m/s,以平均气动弦长为参考长度的雷诺数分别为1.4×106、1.8×106、2.1×106、2.5×106、2.9×106及3.2×106。对比试验数据均在Re=2.5×106给出。试验数据进行了洞壁干扰修正和支架干扰修正。支架干扰修正中支架量通过图 5中“腹撑+假背撑-背撑”(即③-②)获得[17]。试验过程中模型迎角变化范围为-8°~24°,侧滑角变化范围为-18°~18°。

    图  6  DNW-LLF风洞标模试验
    Fig.  6  CHN-T1 test in DNW-LLF wind tunnel

    图 7~10表 1给出了CHN-T1标模在不同风洞中阻力和升力的重复性结果。FL-13风洞中重复性试验进行了7次,DNW-LLF风洞中重复性试验进行了6次。

    图  7  FL-13风洞阻力重复性试验结果
    Fig.  7  FL-13 wind tunnel drag repeatability
    图  8  FL-13风洞升力重复性试验结果
    Fig.  8  FL-13 wind tunnel lift force repeatability
    图  9  DNW-LLF风洞阻力重复性试验结果
    Fig.  9  DNW-LLF wind tunnel drag repeatability
    图  10  DNW-LLF风洞升力重复性试验结果
    Fig.  10  DNW-LLF wind tunnel lift force repeatability
    表  1  重复性试验精度
    Table  1  Test repeatability precision
    σCL σCD σCma
    DNW-LLF风洞 0.00078 0.00008 0.0002
    FL-13风洞 0.0022 0.00009 0.0003
    国军标优秀指标 0.0010 0.00020 0.0003
    国军标合格指标 0.0040 0.00050 0.0012
    下载: 导出CSV 
    | 显示表格

    图 7~10(a)均为单次试验测量值与多次重复性试验平均值的偏差,图 7~10(b)给出每次重复性试验测量值。图 7~10(a)中横实线为国军标重复性精度优秀指标2倍或3倍值。从图中可以看出,除FL-13升力重复性试验超出3倍值外,其余均为2倍值。此外,绝大多数偏差值落在2ΔCD和2ΔCL以内,其中ΔCD=0.0002、ΔCL=0.001;FL-13风洞升力偏差值多数落在3ΔCL以内。多数重复性试验结果满足国军标优秀指标要求。

    表 2图 11给出了CHN-T1标模在FL-13风洞和DNW-LLF风洞试验中的气动特性数据对比结果。可以看出,标模在两座风洞中的升力线斜率基本一致,俯仰静稳定裕度差异很小,可忽略不计,设计升力系数点附近(Ma=0.78, CL=0.5)的阻力系数相差在4阻力单位内(0.0004)。两风洞标模数值相差较大的是零升俯仰力矩系数,初步分析表明该差异与两风洞支架干扰扣除方案不同有关。

    表  2  CHN-T1气动特性
    Table  2  CHN-T1 aerodynamic characteristics
    C CDmin Kmax CmaCL Cma0
    DNW-LLF风洞 0.09236 0.0203 18.4 -0.2598 0.155
    FL-13风洞 0.09228 0.0204 18.4 -0.2624 0.122
    下载: 导出CSV 
    | 显示表格
    图  11  两风洞CHN-T1标模气动特性对比结果
    Fig.  11  CHN-T1 calibration model aerodynamic characteristics comparison between two wind tunnels

    图 12给出了FL-13风洞中CHN-T1标模气动特性曲线随雷诺数(试验风速)的变化情况。试验结果表明,随雷诺数增加,标模升力线斜率略有增加;设计升力点附近升力系数有所增大,阻力系数减小;俯仰力矩曲线基本无变化,俯仰静稳定裕度基本一致,符合预期。雷诺数大于1.8×106后,CHN-T1标模临界迎角及最大升力系数变化不大。

    图  12  FL-13风洞中雷诺数对CHN-T1标模气动特性影响
    Fig.  12  Reynolds number effect on CHN-T1 calibration model in FL-13 wind tunnel

    图 13给出了DNW-LLF风洞中CHN-T1标模气动特性随雷诺数的变化情况。试验结果表明,随着雷诺数增加,标模升力线斜率略有增加;设计升力点附近升力系数有所增大,阻力系数减小;俯仰静稳定裕度基本一致,设计升力点附近俯仰力矩系数有所增加,符合预期。雷诺数大于1.8×106后,CHN-T1标模临界迎角及最大升力系数变化不大。Re=3.2×106时,最大升力系数出现明显减小,这可能与CHN-T1标模失速附近迎角间隔较大、模型振动及马赫数有关。雷诺数大于2.5×106后,设计升力点附近阻力系数不再随雷诺数增加而增大。

    图  13  DNW-LLF风洞中雷诺数对CHN-T1标模气动特性影响
    Fig.  13  Reynolds number effect on CHN-T1 calibration model in DNW-LLF wind tunnel

    CHN-T1标模为CARDC高低速统一大展弦比运输机标模体系中的首个标模,标模设计加工完成后,分别在FL-13风洞和DNW-LLF风洞进行了试验。试验结果表明,重复性试验精度基本满足国军标优秀指标要求;对比试验结果表明标模在不同风洞中获得的特征气动参数相差很小,设计升力点附近阻力系数相差仅4个阻力单位;雷诺数对标模气动特性影响符合预期。所获得数据可作为标模体系中其他标模以及CFD验证与评估的基准。

  • 图  1   热线探头测点分布

    Fig.  1   Hot wire probes setting for measurement

    图  2   稳定段出口测点

    Fig.  2   Measuring point in the exit of setting chamber

    图  3   试验段测点

    Fig.  3   Measuring point in test section

    图  4   吹断的探头热丝

    Fig.  4   Hot wire of probe broken by flow

    图  5   换热器入口湍流度分布

    Fig.  5   Turbulence intensity distribution at the entrance of heat exchanger

    图  6   换热器出口湍流度分布

    Fig.  6   Turbulence intensity distribution in the exit of heat exchanger

    图  7   四拐入口湍流度分布

    Fig.  7   Turbulence intensity distribution in the entrance of the 4th corner

    图  8   稳定段入口湍流度分布

    Fig.  8   Turbulence intensity distribution at the entrance of setting chamber

    图  9   3层阻尼网稳定段出口湍流度分布

    Fig.  9   Turbulence intensity distribution at the exit of setting chamber with 3 screens

    图  10   三层阻尼网与五层阻尼网的稳定段出口湍流度比较

    Fig.  10   Comparison of setting chamber exit turbulence intensity between 3 screens and 5 screens

    图  11   风洞回路流向湍流度分布

    Fig.  11   Comparison of turbulence intensity between 3 screens and 5 screens

    图  12   Ma0.4三层阻尼网试验段流场扰动图

    Fig.  12   Ma0.4 flow fluctuation diagram in 3 screens test section

    图  13   Ma0.7三层阻尼网试验段流场扰动图

    Fig.  13   Ma0.7 flow fluctuation diagram in 3 screens test section

    图  14   Ma0.4三层阻尼网试验段热线脉动电压幅值谱

    Fig.  14   Ma0.4 frequency spectrum of hot wire voltage fluctuation amplitude in 3 screens test section

    图  15   Ma0.4五层阻尼网试验段流场扰动图

    Fig.  15   Ma0.4 flow fluctuation diagram in 5 screens test section

    图  16   Ma0.7五层阻尼网试验段流场扰动图

    Fig.  16   Ma0.7 flow fluctuation diagram in 5 screens test section

    图  17   三层阻尼网和五层阻尼网试验段流场湍流度比较

    Fig.  17   Turbulence level comparison between 3 screens and 5 screens in test section

    表  1   不同阻尼网层数试验段湍流度测量结果

    Table  1   Turbulence level result for different screen layers in test section

    阻尼网马赫数湍流度
    <u>, %
    拟合优度不确定度/
    %
    三层0.40.0700.9870.0012
    三层0.70.0540.9810.0003
    五层0.40.0560.9820.0014
    五层0.70.0470.9690.0013
    下载: 导出CSV
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  • 收稿日期:  2022-04-19
  • 修回日期:  2022-06-16
  • 录用日期:  2022-07-12
  • 网络出版日期:  2023-07-03

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