超燃发动机内壁摩阻测量传感器研究

推进技术 ›› 2016, Vol. 37 ›› Issue (6): 1175-1181.

超燃发动机内壁摩阻测量传感器研究

隆永胜,王辉,张涛,李绪国,袁竭,胡振震

中国空气动力研究与发展中心，四川绵阳 621000,中国空气动力研究与发展中心，四川绵阳 621000,中国空气动力研究与发展中心，四川绵阳 621000,中国空气动力研究与发展中心，四川绵阳 621000,中国空气动力研究与发展中心，四川绵阳 621000,中国空气动力研究与发展中心，四川绵阳 621000

发布日期:2021-08-15
作者简介:隆永胜，男，硕士，研究员，研究领域为电弧加热器研制及其试验技术。

Research of Skin Friction Gage for Inner Wall of Scramjet

China Aerodynamics Research and Development Center，Mianyang 621000，China,China Aerodynamics Research and Development Center，Mianyang 621000，China,China Aerodynamics Research and Development Center，Mianyang 621000，China,China Aerodynamics Research and Development Center，Mianyang 621000，China,China Aerodynamics Research and Development Center，Mianyang 621000，China and China Aerodynamics Research and Development Center，Mianyang 621000，China

Published:2021-08-15

摘要/Abstract

摘要： 根据超燃发动机燃烧室的热环境参数进行传感器冷却换热及应变计算，研制了一种用于燃烧室高温环境直接测量摩阻的传感器，解决了传感器的高温隔热、冷却和灵敏度等问题，并进行了标定和校核。通过CARDC电弧加热器开展了初步的测试试验和数值模拟，结果表明，数值模拟和测试的摩阻相差达20%，雷诺比拟因子与文献中0.7～1.3符合较好。

关键词: 超燃发动机；高温；摩阻

Abstract: Heat transfer and strain of sensors were calculated based on the thermal environment parameters of scramjet combustion chamber. A sensor was developed for directly measuring friction of the combustion chamber in a high-temperature environment. High-temperature insulation，cooling and sensitivity of the sensor were solved. Meanwhile it was calibrated and verified. Simulation and preliminary tests by CARDC arc heater show that the difference of friction between simulation and test was up to 20%，Reynolds analogy factor of 0.7 to 1.3 was in good agreement with that of literatures.

Key words: Scramjet；High temperature；Skin friction

隆永胜,王辉,张涛,李绪国,袁竭,胡振震. 超燃发动机内壁摩阻测量传感器研究[J]. 推进技术, 2016, 37(6): 1175-1181.

LONG Yong-sheng,WANG Hui,ZHANG Tao,LI Xu-guo,YUAN Jie,HU Zhen-zhen. Research of Skin Friction Gage for Inner Wall of Scramjet[J]. Journal of Propulsion Technology, 2016, 37(6): 1175-1181.

参考文献

[1] 乐嘉陵. 吸气式高超声速技术研究进展[J]. 推进技术, 2010, 31(6): 641-649. (LE Jia-ling. Progress in Air-Breathing Hypersonic Technology[J]. Journal of Propulsion Technology, 2010, 31(6): 641-649.)
[2] 骆晓臣, 张堃元. 侧压式进气道内部阻力分析[J]. 推进技术, 2007, 28(2): 273-277. (LUO Xiao-chen, ZHANG Kun-yuan. Parametric Analysis of Internal Drag in Sidewall Compression Inlet[J]. Journal of Propulsion Technology, 2007, 28(2): 273-277.)
[3] Schetz J A, Billig F S. Combustor Wall Boundary Layer Analysis[R]. AIAA 81-0267.
[4] Heiser W H, Pratt D T. Hypersonic Air Breathing Propulsion[M]. Washington DC: AIAA Education Series, 1994: 429-434.
[5] Hazelton D M, Rodney D W Bowersox. Skin Friction Correlations for High Enthalpy Flows[R]. AIAA 98-1636.
[6] Nitsche W, Haberland C, Thunker R. Comparative Investigations on Friction Drag Measuring Techniques in Experimental Aerodynamics[R]. ICAS 84-2.4.1.
[7] Pulliam W J. Development of Fiber Optic Aerodynamic Sensors for High Reynolds Number Supersonic Flows[D]. Virgina: Virgina Polytechnic Institute and State University, 2000.
[8] Bland S M, Sang A K. Improved Direct Measurement Fiber-Optic Skin Friction Gauge for Flight Test and Laboratory Applications[R]. AIAA 2006-3836.
[9] Earl R K, Edward J H. Van Driest Generalization Applied to Turbulent Skin Friction and Velocity Profiles Measured on the Wall of a Mach 7.4 Wind Tunnel[J]. AIAA Journal, 1973, (11): 1784～1785.
[10] Dhawan S. Direct Measurements of Skin Friction[R]. NASA-1121, 1953.
[11] Coles D. Measurements in the Boundary Layer on a Smooth Flat Plate in Supersonic Flow[R]. JPL, 20-70, 1953.
[12] Joseph A, Schetz J. Direct Measurement of Skin Friction in Complex Flows[R]. AIAA 2010-44.
[13] Chadwick K, Schetz J. Direct Measurement of Skin Friction in High Enthalpy High Speed Flows[R]. AIAA 92-5036.
[14] Theodore B S. Development and Ground Testing of Direct Measuring Skin Friction Gages for High Enthalpy Supersonic Flight Tests[R]. AIAA 2002-3134.
[15] Tsuru T, Tomioka S. Skin-Friction Measurements in Supersonic Combustion Flows of a Scramjet Combustor[R]. AIAA 2008-4578.
[16] 吕治国, 李国君, 赵荣娟. 激波风洞高超声速摩阻直接测量技术研究[J]. 实验流体力学, 2013, 27(6): 81-85.
[17] 马洪强, 高贺, 毕志献. 高超声速飞行器相关的摩擦阻力直接测量技术[J]. 实验流体力学, 2011, 25(4): 83-88.
[18] 帕坦卡S V. 传热与流体流动的数值计算[M]. 张政译. 北京:科学出版社, 1989.
[19] Wooden P, Hull G. Correlation of Measured and Theoretical Heat Transfer and Skin Friction at HypersonicSpeeds, Including Reynolds Analogy[R]. AIAA 90-5244.
[20] 陈懋章. 粘性流体力学基础[M]. 北京:高等教育出版社, 2002.
[21] Goyne C P, Stalker R J, Paull A. Shock Tunnel Skin-Friction Measurementin a Supersonic Combustor [J]. Journal of Propulsion and Power, 1999, 15(5): 699-705.
[22] David M H, Rodney D W. Heat Transfer and Skin Friction in a Mach 6 Inlet Flow[R]. AIAA 99-4890. 　　　　　　　　　　　　　*　收稿日期:2015-02-20；修订日期:2015-04-16。作者简介:隆永胜,男,硕士,研究员,研究领域为电弧加热器研制及其试验技术。E-mail: lyscardc@163.com(编辑:朱立影)