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.
-
图 5 换热器入口湍流度分布
Figure 5. Turbulence intensity distribution at the entrance of heat exchanger
图 6 换热器出口湍流度分布
Figure 6. Turbulence intensity distribution in the exit of heat exchanger
图 7 四拐入口湍流度分布
Figure 7. Turbulence intensity distribution in the entrance of the 4th corner
图 8 稳定段入口湍流度分布
Figure 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
Figure 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
Figure 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
Figure 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
Figure 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
Figure 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
Figure 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
Figure 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
Figure 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
Figure 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 0.4 0.070 0.987 0.0012 三层 0.7 0.054 0.981 0.0003 五层 0.4 0.056 0.982 0.0014 五层 0.7 0.047 0.969 0.0013 
下载: 导出CSV
-
[1] 郝礼书,乔志德,武洁,等. NF-6风洞AV90-2轴流压缩机喘振曲线测试研究[J]. 西北工业大学学报,2009,27(4):477-480. doi: 10.3969/j.issn.1000-2758.2009.04.009HAO L S,QIAO Z D,WU J,et al. Critically investigating anti-surge monitor and control system of AV90-2 axial compressor in NWPU NF-6 wind tunnel[J]. Journal of Northwestern Polytechnical University,2009,27(4):477-480. doi: 10.3969/j.issn.1000-2758.2009.04.009 [2] 廖达雄,陈吉明,彭强,等. 连续式跨声速风洞设计关键技术[J]. 实验流体力学,2011,25(4):74-78. doi: 10.3969/j.issn.1672-9897.2011.04.014LIAO D X,CHEN J M,PENG Q,et al. Key design techniques of the low noise continuous transonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics,2011,25(4):74-78. doi: 10.3969/j.issn.1672-9897.2011.04.014 [3] 陈吉明,吴盛豪,陈振华,等. 连续式跨声速风洞回路吸声降噪技术试验研究[J]. 西北工业大学学报,2020,38(4):855-861. doi: 10.3969/j.issn.1000-2758.2020.04.021CHEN J M,WU S H,CHEN Z H,et al. Experimental research on noise reduction for continuous transonic wind tunnel loop[J]. Journal of Northwestern Polytechnical University,2020,38(4):855-861. doi: 10.3969/j.issn.1000-2758.2020.04.021 [4] 毕卫涛,唐帆,胡永煌,等. 基于结构系综理论发展可靠工程转捩模型的一种新思路[J]. 空气动力学学报,2020,38(6):1136-1148. doi: 10.7638/kqdlxxb-2020.0123BI W T,TANG F,HU Y H,et al. New perspective for developing reliable engineering transition model based on the structural ensemble dynamics theory[J]. Acta Aerodynamica Sinica,2020,38(6):1136-1148. doi: 10.7638/kqdlxxb-2020.0123 [5] 高超,王娜,袁先士,等. NF-6增压连续式高速风洞压缩机喘振边界的确定[J]. 实验流体力学,2013,27(5):61-66. doi: 10.3969/j.issn.1672-9897.2013.05.011GAO C,WANG N,YUAN X S,et al. Determination of the axial-flow compressor surge boundary in NF-6 pressurized continuously-operating high-speed wind tunnel[J]. Journal of Experiments in Fluid Mechanics,2013,27(5):61-66. doi: 10.3969/j.issn.1672-9897.2013.05.011 [6] 陈旦,杨孝松,李刚,等. 连续式风洞总压和调节阀相关性研究及其应用[J]. 西北工业大学学报,2020,38(2):325-332. doi: 10.3969/j.issn.1000-2758.2020.02.013CHEN D,YANG X S,LI G,et al. Relativity research of total pressure and regulating valve in continuous wind tunnel and its application[J]. Journal of Northwestern Polytechnical University,2020,38(2):325-332. doi: 10.3969/j.issn.1000-2758.2020.02.013 [7] 赵波,符澄,裴海涛,等. 椭圆翅片管对风洞气流湍流特性影响研究[J]. 西北工业大学学报,2020,38(2):303-308. doi: 10.3969/j.issn.1000-2758.2020.02.010ZHAO B,FU C,PEI H T,et al. Study on the effect of oval tubes on airflow turbulence characteristics in wind tunnel[J]. Journal of Northwestern Polytechnical University,2020,38(2):303-308. doi: 10.3969/j.issn.1000-2758.2020.02.010 [8] 朱博,汤更生. 声学风洞流场低湍流度及频谱测量研究[J]. 实验流体力学,2015,29(4):58-64. doi: 10.11729/syltlx20140118ZHU B,TANG G S. Low turbulence intensity and spectrum measurement research in aeroacoustic wind tunnel[J]. Journal of Experiments in Fluid Mechanics,2015,29(4):58-64. doi: 10.11729/syltlx20140118 [9] 杜钰锋,林俊,王勋年,等. 变热线过热比可压缩流湍流度测量方法优化[J]. 航空学报,2019,40(12):123067. doi: 10.7527/S10006-893.2019.23067DU Y F,LIN J,WANG X N,et al. Measurement technique optimization of turbulence level in compressible fluid by changing overheat ratio of hot wire anemometer[J]. Acta Aeronautica et Astronautica Sinica,2019,40(12):123067. doi: 10.7527/S10006-893.2019.23067 [10] 何克敏,白存儒,郭渠渝,屠兴. 较低湍流度范围湍流度对风洞实验结果的影响[J]. 流体力学实验与测量,1997,11(3):11-17.HE K M,BAI C R,GUO Q Y,et al. The effect of turbulence on wind tunnel results in the range of low turbulence[J]. Experiments and Measurements in Fluid Mechanics,1997,11(3):11-17. [11] 李峰,白存儒,周伟,等. 湍流度对飞行器模型大迎角气动特性影响的初步研究[J]. 实验流体力学,2006,20(3):45-47,52. doi: 10.3969/j.issn.1672-9897.2006.03.009LI F,BAI C R,ZHOU W,et al. Primal research of the effect of flow turbulence on aerodynamic characteristics of a aircraft model at high angles of attack[J]. Journal of Experiments in Fluid Mechanics,2006,20(3):45-47,52. doi: 10.3969/j.issn.1672-9897.2006.03.009 [12] KOVASZNAY L S G. The hot-wire anemometer in supersonic flow[J]. Journal of the Aeronautical Sciences,1950,17(9):565-572. doi: 10.2514/8.1725 [13] STAINBACK P, JOHNSON C, BASNETT C. Preliminary measurements of velocity, density and total temperature fluctuations in compressible subsonic flow[C]//Proc of the 21st Aerospace Sciences Meeting. 1983: 384. doi: 10.2514/6.1983-384 [14] CHOU A, LEIDY A, KING R A, et al. Measurements of freestream fluctuations in the NASA langley 20-inch Mach 6 tunnel[C]//Proc of the 2018 Fluid Dynamics Conference. 2018. doi: 10.2514/6.2018-3073 [15] KING R A,ANDINO M Y,MELTON L,et al. Flow disturbance measurements in the national transonic facility[J]. AIAA Journal,2013,52(1):116-130. doi: 10.2514/1.J052429 [16] BAUINGER S, BEHRE S, LENGANI D, et al. On turbulence measurements and analyses in a two-stage two-spool turbine rig[J]. Journal of Turbomachinery, 2017, 139(7). doi: 10.1115/1.4035508 [17] ANDREWS G, POGGIE J. Effects of freestream acoustic disturbances on hypersonic boundary layer stability[C]//Proc of the AIAA AVIATION 2020 FORUM, VIRTUAL EVENT. Reston, Virginia: AIAA, 2020: 2995. doi: 10.2514/6.2020-2995 [18] 马护生,时培杰,李学臣,等. 可压缩流体热线探针校准方法研究[J]. 空气动力学学报,2019,37(1):55-60. doi: 10.7638/kqdlxxb-2016.0093MA H S,SHI P J,LI X C,et al. Investigation of calibration method for hot-wire probe in compressible flow[J]. Acta Aerodynamica Sinica,2019,37(1):55-60. doi: 10.7638/kqdlxxb-2016.0093 [19] 袁湘江,沙心国,时晓天,等. 高超声速流动中噪声与湍流度的关系[J]. 航空学报,2020,41(11):123791. doi: 10.7527/S10006893.2020.23791YUAN X J,SHA X G,SHI X T,et al. Noise-turbulence relationship in hypersonic flow[J]. Acta Aeronautica et Astronautica Sinica,2020,41(11):123791. doi: 10.7527/S10006893.2020.23791 [20] 朱博,刘琴,屈晓力,等. 阵风发生装置流场测量与分析[J]. 实验流体力学,2013,27(6):76-80. doi: 10.3969/j.issn.1672-9897.2013.06.014ZHU B,LIU Q,QU X L,et al. Measurement and analysis of a gust generator flow field in wind tunnel[J]. Journal of Experiments in Fluid Mechanics,2013,27(6):76-80. doi: 10.3969/j.issn.1672-9897.2013.06.014 -
点击查看大图
计量
- 文章访问数: 120
- HTML全文浏览量: 99
- PDF下载量: 13
- 被引次数: 0
