簡易檢索 / 詳目顯示

研究生: 陳昭宇
Chen, Chao-Yu
論文名稱: 應用快速反應壓力螢光感測塗料於裝有渦流產生器之穿音速凸角流壓力場量測
The Application of Fast-responding Pressure Sensitive Paints on Transonic Convex Corner Pressure Measurements with Vortex Generator
指導教授: 黃智永
Huang, Chih-Yung
口試委員: 鍾光民
Chung, Kung-Ming
劉耀先
Liu, Yao-Hsien
學位類別: 碩士
Master
系所名稱: 工學院 - 動力機械工程學系
Department of Power Mechanical Engineering
論文出版年: 2021
畢業學年度: 109
語文別: 中文
論文頁數: 128
中文關鍵詞: 壓力螢光感測塗料溫度螢光感測塗料凸角流渦流產生器可壓縮流震波誘導分離
外文關鍵詞: Pressure sensitive paint, Temperature sensitive paint, Corner flow, Vortex generator, Compressible flow, Shock-induced boundary layer separation
相關次數: 點閱:3下載:0
分享至:
查詢本校圖書館目錄 查詢臺灣博碩士論文知識加值系統 勘誤回報
  • 本研究旨在應用壓力螢光感測塗料(Pressure sensitive paint; PSP)於穿音速流場中凸角流(transonic convex corner flow)全域性壓力量測,並將凸角上游裝有渦流產生器(vortex generator)的壓力量測結果做比對。實驗結果顯示,加裝高度為0.2個邊界層高度的渦流產生器可以延遲邊界層分離發生,而加裝高度為1.0個邊界層高度的渦流產生器會造成寄生阻力(parasitic drag)。
    研究中所使用的壓力螢光感測塗料為摻入中空顆粒的PSP(Mesoporous PSP, MP-PSP),是具有高壓力靈敏度且反應快速的PSP。但由於PSP在壓力量測上會受到溫度影響而生誤差,因此根據相關文獻,自行開發溫度螢光感測塗料(Temperature sensitive paint, TSP)藉由量測凸角流模型全域性溫度分布,以修正PSP所獲得的壓力數據。在PSP動態反應時間量測的部分,本研究會以震波管量測PSP在短暫時間內,對於壓力躍升的反應時間。實驗結果證明PSP反應時間為次毫秒等級,足以應用於幾秒穩態時間的壓力量測。最後,溫度修正後的壓力量測結果與Kulite transducer做比對。研究結果顯示,PSP在凸角流模型幾何中心的壓力量測結果與Kulite transducer的結果吻合。藉由PSP的全域性壓力量測結果,可將Kulite transducer所無法觀測的壓力場現象,例如:渦流行經軌跡造成的低壓帶,以及渦流產生器內側upwash以及外側downwash區域等以全域性壓力分布顯示出來。凸顯PSP在定性、定量以及高空間解析度的壓力場量測優勢。


    This study aims to investigate the global pressure distribution of transonic convex corner model by Pressure Sensitive Paint, PSP. The results are compared to the cases with different heights of vortex generator. The results demonstrated that vortex generator with 0.2 height of turbulence boundary layer thickness is the better type to delay the occurrence of separation. On the other hand, the vortex generator with 1.0 height of turbulence boundary layer thickness can cause parasitic drag.
    PSP used in this research is mesoporous PSP, MP-PSP, which contains mesoporous particles and has the characteristic of high pressure sensitivity and short response time. The measurement of PSP can be affected by temperature variation. To resolve this problem, temperature sensitive paint, TSP, is developed and applied to the wind tunnel tests. By measuring the global temperature of a model, errors of PSP pressure data resulted from temperature can be corrected. The dynamic response of PSP to pressure rise has been examined in shock tube experiment. The result demonstrates that response time of MP-PSP is in sub-millisecond, which is applicable for steady state wind tunnel measurement in few seconds. The result of temperature-corrected PSP data shows good agreement with Kulite transducer measurement. Kulite transducer cannot get the global pressure distribution and therefore the 2D pressure distribution can only be well demonstrated by PSP. With PSP, the global pressure distribution can illustrate the low-pressure region caused by trace of pair vortices Also, upwash in the inward region and downwash in the outward region of a vortex generator can be well demonstrated in the result of PSP. This shows the advantage of high spatial resolution of PSP measurement.

    摘要 I Abstract III 致謝 V 目錄 VII 圖目錄 X 表目錄 XVIII 第1章 緒論 1 1.1 研究動機 1 1.2 文獻回顧 2 1.2.1 渦流產生器(Vortex Generator)與凸角流(Corner Flow) 2 1.2.2 壓力螢光感測塗料(Pressure Sensitive Paint; PSP) 21 1.2.3 溫度螢光感測塗料(Temperature Sensitive Paint;TSP) 33 1.3 研究架構 45 第2章 壓力與溫度之光學量測原理 46 2.1 壓力螢光感測塗料 46 2.1.1 光致發光 46 2.1.2 氧氣淬滅 47 2.1.3 壓力螢光感測塗料壓力之量測原理 48 2.2 溫度螢光感測塗料 50 2.2.1 熱淬滅 50 2.2.2 溫度螢光感測塗料之溫度量測原理 51 第3章 實驗架設與方法 52 3.1 壓力/溫度感測螢光塗料製備 52 3.1.1 壓力螢光感測塗料配方選擇 53 3.1.2 溫度感測螢光感測塗料配方選擇 62 3.1.3 模型底漆 68 3.1.4 螢光感測塗料製備與噴塗 69 3.2 震波管動態反應時間量測 71 3.3 風洞實驗 76 3.3.1 穿音速風洞 76 3.3.2 實驗模型架設與風洞設定 78 3.4 PSP溫度修正 82 第4章 實驗結果與討論 87 4.1 風洞實驗量測結果 87 4.1.1 模型位移分析 87 4.1.2 亮度雜訊後處理 89 4.1.3 PSP溫度修正 90 4.1.4 M∞=0.83凸角流全域性溫度分布 93 4.1.5 M∞=0.83凸角流壓力係數分布 100 4.1.6 M∞=0.89凸角流溫度分布 106 4.1.7 M∞=0.89凸角流壓力係數分布 111 4.1.8 實驗不確定性計算 120 第5章 結論與未來工作 122 5.1 結論 122 5.2 未來工作 123 參考文獻 124

    [1] Z. Sun, "Micro Vortex Generators for Boundary Layer Control: Principles and Applications," International Journal of Flow Control, vol. 7, no. 1-2, pp. 67-86, 2015, doi: 10.1260/1756-8250.7.1-2.67.
    [2] J. C. Lin, S. K. Robinson, R. J. McGhee, and W. O. Valarezo, "Separation control on high-lift airfoils via micro-vortex generators," Journal of aircraft, vol. 31, no. 6, pp. 1317-1323, 1994.
    [3] Y. Kuya, K. Takeda, X. Zhang, S. Beeton, and T. Pandaleon, "Flow separation control on a race car wing with vortex generators in ground effect," Journal of fluids engineering, vol. 131, no. 12, 2009.
    [4] J. C. Lin, "Review of research on low-profile vortex generators to control boundary-layer separation," Progress in Aerospace Sciences, vol. 38, no. 4-5, pp. 389-420, 2002.
    [5] E. Baydar, F. K. Lu, and J. W. Slater, "Vortex generators in a two-dimensional external-compression supersonic inlet," Journal of Propulsion and Power, vol. 34, no. 2, pp. 521-538, 2018.
    [6] H. D. Taylor, "The elimination of diffuser separation by vortex generators," Research department report no. r-4012-3, United Aircraft Corporation, East Hartford, Connecticut, vol. 103, 1947.
    [7] A. M. Kuethe, "Effect of streamwise vortices on wake properties associated with sound generation," Journal of Aircraft, vol. 9, no. 10, pp. 715-719, 1972, doi: 10.2514/3.44333.
    [8] D. Rao and T. Kariya, "Boundary-layer submerged vortex generators for separation control-an exploratory study," in 1st National Fluid Dynamics Conference, 1988, p. 3546.
    [9] J. C. Lin, F. G. Howard, and G. V. Selby, "Small submerged vortex generators for turbulent flow separation control," Journal of Spacecraft and Rockets, vol. 27, no. 5, pp. 503-507, 1990, doi: 10.2514/3.26172.
    [10] R. Bur, D. Coponet, and Y. Carpels, "Separation control by vortex generator devices in a transonic channel flow," Shock Waves, vol. 19, no. 6, pp. 521-530, 2009, doi: 10.1007/s00193-009-0234-6.
    [11] H. Holden and H. Babinsky, "Effect of Microvortex Generators On Seperated Normal Shock/ Boundary Layer Interactions," Journal of Aircraft, vol. 44, no. 1, pp. 170-174, 2007, doi: 10.2514/1.22770.
    [12] K.-M. Chung, K.-C. Su, and K.-C. Chang, "The Effect of Vortex Generators on Shock-Induced Boundary Layer Separation in a Transonic Convex-Corner Flow," Aerospace, vol. 8, no. 6, 2021, doi: 10.3390/aerospace8060157.
    [13] S. Wang and S. Ghaemi, "Effect of vane sweep angle on vortex generator wake," Experiments in Fluids, vol. 60, no. 1, 2019, doi: 10.1007/s00348-018-2666-1.
    [14] H.-H. Kim, H.-Y. Kim, J.-S. Han, and J.-H. Han, "A Development and Assessment of Variable-Incidence Angle Vortex Generator at Low Reynolds Number of ~ 5×104," International Journal of Aeronautical and Space Sciences, vol. 19, no. 4, pp. 836-842, 2018, doi: 10.1007/s42405-018-0099-y.
    [15] N. Namura and S. Jeong, "Parametric study of vortex generators on a super critical infinite-wing to alleviate shock-induced separation," Transactions of the Japan Society for Aeronautical and Space Sciences, vol. 56, no. 5, pp. 293-302, 2013.
    [16] K.-M. Chung, "Investigation on Transonic Convex-Corner Flows," Journal of Aircraft, vol. 39, no. 6, pp. 1014-1018, 2002, doi: 10.2514/2.3029.
    [17] G. Ben-Dor, O. Igra, and T. Elperin, Handbook of shock waves, three volume set. Elsevier, 2000.
    [18] H. Holden and H. Babinsky, "Effect of microvortex generators on seperated normal shock/boundary layer interactions," Journal of Aircraft, vol. 44, no. 1, pp. 170-174, 2007.
    [19] H. Babinsky, N. Makinson, and C. Morgan, "Micro-vortex generator flow control for supersonic engine inlets," in 45th AIAA Aerospace Sciences Meeting and Exhibit, 2007, p. 521.
    [20] N. Titchener and H. Babinsky, "Microvortex generators applied to a flowfield containing a normal shock wave and diffuser," AIAA journal, vol. 49, no. 5, pp. 1046-1056, 2011.
    [21] M. Rybalko, H. Babinsky, and E. Loth, "Vortex generators for a normal shock/boundary layer interaction with a downstream diffuser," Journal of Propulsion and Power, vol. 28, no. 1, pp. 71-82, 2012.
    [22] S. Lee, E. Loth, and H. Babinsky, "Normal shock boundary layer control with various vortex generator geometries," Computers & Fluids, vol. 49, no. 1, pp. 233-246, 2011.
    [23] S. Lee and E. Loth, "Impact of ramped vanes on normal shock boundary layer interaction," AIAA journal, vol. 50, no. 10, pp. 2069-2079, 2012.
    [24] T. Herges, E. Kroeker, G. Elliott, and C. Dutton, "Microramp flow control of normal shock/boundary-layer interactions," AIAA journal, vol. 48, no. 11, pp. 2529-2542, 2010.
    [25] T. Herges, G. Elliott, C. Dutton, and Y. Lee, "Micro-vortex generators and recirculating flow control of normal shock stability and position sensitivity," in 48th AIAA aerospace sciences meeting including the new horizons forum and aerospace exposition, 2010, p. 1097.
    [26] J. I. Peterson and R. V. Fitzgerald, "New technique of surface flow visualization based on oxygen quenching of fluorescence," Review of Scientific Instruments, vol. 51, no. 5, pp. 670-671, 1980.
    [27] T. Liu, "Pressure‐and Temperature‐Sensitive Paints," Encyclopedia of Aerospace Engineering, 2010.
    [28] M. Kameda, H. Seki, T. Makoshi, Y. Amao, and K. Nakakita, "A fast-response pressure sensor based on a dye-adsorbed silica nanoparticle film," Sensors and Actuators B: Chemical, vol. 171, pp. 343-349, 2012.
    [29] J. Gregory, K. Asai, M. Kameda, T. Liu, and J. Sullivan, "A review of pressure-sensitive paint for high-speed and unsteady aerodynamics," Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, vol. 222, no. 2, pp. 249-290, 2008.
    [30] Y. Egami, Y. Sato, and S. Konishi, "Development of Polymer/Ceramic Pressure-Sensitive Paint with the same response time as Anodized-Aluminum PSP," in 2018 AIAA Aerospace Sciences Meeting, 2018, p. 1032.
    [31] H. Sakaue, T. Kakisako, and H. Ishikawa, "Characterization and optimization of polymer-ceramic pressure-sensitive paint by controlling polymer content," Sensors, vol. 11, no. 7, pp. 6967-6977, 2011.
    [32] Y. Egami, S. Konishi, Y. Sato, and Y. Matsuda, "Effects of solvents for luminophore on dynamic and static characteristics of sprayable polymer/ceramic pressure-sensitive paint," Sensors and Actuators A: Physical, vol. 286, pp. 188-194, 2019.
    [33] K. Nakakita, M. Kurita, and K. Mitsuo, "Development of the Pressure-Sensitive Paint Measurement for Large Wind Tunnels at Japan Aerospace Exploration Agency," in ICAS, 2004, vol. 3, no. 2, p. 2004.
    [34] D. Peng, F. Gu, Y. Li, and Y. Liu, "A novel sprayable fast-responding pressure-sensitive paint based on mesoporous silicone dioxide particles," Sensors and Actuators A: Physical, vol. 279, pp. 390-398, 2018.
    [35] L. Yang, H. Zare-Behtash, E. Erdem, and K. Kontis, "Application of AA-PSP to hypersonic flows: The double ramp model," Sensors and Actuators B: Chemical, vol. 161, no. 1, pp. 100-107, 2012, doi: 10.1016/j.snb.2011.09.053.
    [36] Y. F. Lin, "The Application of Fast-responding Pressure Sensitive Paints on Transonic Delta Wing Flow Measurement.," Master thesis, Dept. of Power Mechanical Engineering, National Tsing Hua University, 2020.
    [37] T. Liu, B. T. Campbell, S. P. Burns, and J. P. Sullivan, "Temperature-and pressure-sensitive luminescent paints in aerodynamics," Applied Mechanics Reviews, vol. 50, pp. 227-246, 1997.
    [38] S. Ohmi, H. Nagai, K. Asai, and K. Nakakita, "Effect of TSP layer thickness on global heat transfer measurement in hypersonic flow," in 44th AIAA Aerospace Sciences Meeting and Exhibit, 2006, p. 1048.
    [39] Y. Ishiguro, H. Nagai, K. Asai, and K. Nakakita, "Visualization of hypersonic compression corner flows using temperature-and pressure-sensitive paints," in 45th AIAA Aerospace Sciences Meeting and Exhibit, 2007, p. 118.
    [40] H. Ozawa, S. J. Laurence, J. M. Schramm, A. Wagner, and K. Hannemann, "Fast-response temperature-sensitive-paint measurements on a hypersonic transition cone," Experiments in Fluids, vol. 56, no. 1, p. 1853, 2015.
    [41] H. Ozawa, "Experimental study of unsteady aerothermodynamic phenomena on shock-tube wall using fast-response temperature-sensitive paints," Physics of Fluids, vol. 28, no. 4, p. 046103, 2016.
    [42] J. Heine and K. Müller-Buschbaum, "Engineering metal-based luminescence in coordination polymers and metal–organic frameworks," Chemical Society Reviews, vol. 42, no. 24, pp. 9232-9242, 2013.
    [43] H. Sakaue, T. Kakisako, and H. Ishikawa, "Characterization and optimization of polymer-ceramic pressure-sensitive paint by controlling polymer content," Sensors (Basel), vol. 11, no. 7, pp. 6967-77, 2011, doi: 10.3390/s110706967.
    [44] S. R. Nanda, S. Agarwal, V. Kulkarni, and N. Sahoo, "Shock Tube as an Impulsive Application Device," International Journal of Aerospace Engineering, vol. 2017, pp. 1-12, 2017, doi: 10.1155/2017/2010476.
    [45] Z. Hong, G. A. Pang, S. S. Vasu, D. F. Davidson, and R. K. Hanson, "The use of driver inserts to reduce non-ideal pressure variations behind reflected shock waves," Shock Waves, vol. 19, no. 2, pp. 113-123, 2009, doi: 10.1007/s00193-009-0205-y.
    [46] K.-M. Chung, P.-H. Chang, K.-C. Chang, and F. K. Lu, "Investigation of transonic bi-convex corner flows," Aerospace Science and Technology, vol. 39, pp. 22-30, 2014.
    [47] C. Y. Wang, "Image Processing and Temperature Correction of Pressure-Sensitive Paint for Airfoil Surface Pressure Measurement in Low Speed Wind Tunnel," Dept. of Power Mechanical Engineering, National Tsing Hua University, 2019.
    [48] J. W. Gregory, H. Sakaue, T. Liu, and J. P. Sullivan, "Fast pressure-sensitive paint for flow and acoustic diagnostics," Annual Review of Fluid Mechanics, vol. 46, pp. 303-330, 2014.
    [49] P.-H. Chang, "An Experimental Study of Transonic Convex-Corner Flows," Dissertation of Doctor fo Philosophy, Dept. of Aeronautics and Astronautics, National Cheng Kung University, October 2014.
    [50] K. Nakakita, "Simultaneous visualization of transonic buffet on a rocket faring model using unsteady PSP measurement and Schlieren method," in Selected Papers from the 31st International Congress on High-Speed Imaging and Photonics, 2017, vol. 10328: International Society for Optics and Photonics, p. 1032810.
    [51] G. Biswas, H. Chattopadhyay, and A. Sinha, "Augmentation of Heat Transfer by Creation of Streamwise Longitudinal Vortices Using Vortex Generators," Heat Transfer Engineering, vol. 33, no. 4-5, pp. 406-424, 2012, doi: 10.1080/01457632.2012.614150.
    [52] K.-M. Chung, "Aerodynamic characteristics of deflected surfaces in compressible flows," Journal of aircraft, vol. 41, no. 2, pp. 415-418, 2004.
    [53] K.-M. Chung, "Unsteadiness of transonic convex-corner flows," Experiments in Fluids, vol. 37, no. 6, pp. 917-922, 2004, doi: 10.1007/s00348-004-0890-3.
    [54] N. Titchener and H. Babinsky, "A review of the use of vortex generators for mitigating shock-induced separation," Shock Waves, vol. 25, no. 5, pp. 473-494, 2015, doi: 10.1007/s00193-015-0551-x.
    [55] H. Babinsky, "Shock Boundary Layer Interaction Flow Control with Micro Vortex Generators," University of Cambridge, Engineering Department, Trumpington Street, Cambridge, United Kingdom CB2 1PZ, 2011.
    [56] "<Review-of-research-on-low-profile-vortex-generators-to-control-boundary-layer-separation.pdf>."
    [57] A. Bouhadji and M. Braza, "Organised modes and shock–vortex interaction in unsteady viscous transonic flows around an aerofoil," Computers & Fluids, vol. 32, no. 9, pp. 1233-1260, 2003, doi: 10.1016/s0045-7930(02)00100-7.

    QR CODE