Volume 30 Issue 2
Feb.  2015
Turn off MathJax
Article Contents
Article Navigation >  Journal of Aerospace Power  > 2015  >  30(2): 349-355
YANG Qing-tao, BAI Han-chen, LIU Ji-chun. Heat conduction loss correction of thin-skin calorimeter on back surface for state-variable measurement[J]. Journal of Aerospace Power, 2015, 30(2): 349-355. doi: 10.13224/j.cnki.jasp.2015.02.012
Citation: YANG Qing-tao, BAI Han-chen, LIU Ji-chun. Heat conduction loss correction of thin-skin calorimeter on back surface for state-variable measurement[J]. Journal of Aerospace Power, 2015, 30(2): 349-355. doi: 10.13224/j.cnki.jasp.2015.02.012
shu

Heat conduction loss correction of thin-skin calorimeter on back surface for state-variable measurement

doi: 10.13224/j.cnki.jasp.2015.02.012

  • 1. Science and Technology on Scramjet Laboratory, Hypervelocity Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China;

  • 2. Hypervelocity Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China

  • Received Date: 2013-10-11
  • Publish Date: 2015-02-28
    Abstract
  • A heat conduction loss correction method of thin-skin calorimeter under state-variable conditions based on energy balance principle was presented to meet the requirements for scramjet pulse combustion tests. Then thin-skin calorimeter was numerically simulated and verified in a test, and the measurement results with/without correction were compared and analyzed. Finite element analysis showes that the method can compensate the heat conduction loss on the back surface, and the measurement errors of the heat flux with correction are not greater than 4%, while those without correction are not less than 20% for the numerial examples. Thin-skin calorimeter and coaxial thermocouple were used in scramjet pulse combustion test to measure the surface heat fluxes at the same axial positions of the axsymmetric model. In cold-state test, the relative deviation between the heat flux results is -11.2% without correction using thin-skin calorimeter and using coaxial thermocouple, and is 3.3% with correction. Hot-state test results indicate that oscillation combustion occurs during the test, and the thin-skin calorimeter used in the test can not reflect change of the combustion states because the response time of the thin-skin calorimeter is about 0.02s, which is close to the oscillation period (about 0.03s).

     

    • FullText(HTML)
  • loading
    • References(18)
  • [1]
    乐嘉陵.吸气式高超声速技术研究进展[J].西南科技大学学报,2011,26(4):1-14. LE Jialing.Progress in air-breathing hypersonic technology[J].Journal of Southwest University of Science and Technology,2011,26(4):1-14.(in Chinese)
    [2]
    王自勇,牛文,李文杰.2012年美国高超声速项目进展及趋势分析[J].战术导弹技术,2013(1):6-13. WANG Ziyong,NIU Wen,LI Wenjie.Analysis of the development of hypersonic programs of the USA in 2012[J].Tactical Missile Technology,2013(1):6-13.(in Chinese)
    [3]
    Ladeinde F.A critical review of scramjet combustion simulation[R].Orlando,Florida:47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition,2009.
    [4]
    乐嘉陵,刘伟雄,贺伟,等.脉冲燃烧风洞及其在火箭和超燃发动机研究中的应用[J].实验流体力学,2005,19(1):1-10. LE Jialing,LIU Weixiong,HE Wei,et al.Impulse combustion wind tunnel and its application in rocket and scramjet research[J].Journal of Experiments in Fluid Mechanics,2005,19(1):1-10.(in Chinese)
    [5]
    魏鑫,孙冰,郑力铭,等.超燃冲压发动机进气道表面热结构设计与分析[J].航空动力学报,2008,23(11):1961-1965. WEI Xin,SUN Bing,ZHENG Liming,et al.Design and analysis of thermal structure of inlet of scramjet[J].Journal of Aerospace Power,2008,23(11):1961-1965.(in Chinese)
    [6]
    蒋劲,张若凌,乐嘉陵.再生冷却超燃冲压发动机整机稳态热分析[J].航空动力学报,2009,24(12):2649-2654. JIANG Jin,ZHANG Ruoling,LE Jialing.Steady thermal analysis of regeneratively cooled scramjet[J].Journal of Aerospace Power,2009,24(12):2649-2654.(in Chinese)
    [7]
    孙冰,郑力铭.超燃冲压发动机支板热环境及热防护方案[J].航空动力学报,2006,21(2):336-341. SUN Bing,ZHENG Liming.Research of scramjet strut thermal environment and thermal protection scheme[J].Journal of Aerospace Power,2006,21(2):336-341.(in Chinese)
    [8]
    American Society for Testing and Materials.ASTM E459-97,standard test method for measuring heat transfer rate using a thin-skin calorimeter[S].West Conshohocken,PA:ASTM International,1997.
    [9]
    刘初平.气动热与热防护试验热流测量[M].北京:国防工业出版社,2013.
    [10]
    Mehta R C,Jayachandran T,Sastri V M K,et al.Finite element analysis of conductive and radiative heating of a thin skin calorimeter[J].Wärme-und Stofffübertragung,1988(22):227-230.
    [11]
    Kidd C T.Thin-skin technique heat-transfer measurement errors due to heat conduction into thermocouple wires[J].ISA Transactions,1985,24(2):97-99.
    [12]
    Keltner N R,Beck J V.Surface temperature measurement errors[J].Journal of Heat Transfer,1983,105(5):312-318.
    [13]
    Lewis D R,Norris J D.Techniques for thin-skin heat-transfer measurements for surface roughness at AEDC tunnel 9[R].Seattle,Washington:26th AIAA Aerodynamic Measurement Technnology and Ground Testing Conference,2008.
    [14]
    Shultz D L,Jones T V.Heat-transfer measurements in short-duration hypersonic facilities[R].AGARD-AG-165,1973.
    [15]
    杨庆涛,白菡尘,杨娟.薄壁量热计后壁面导热损失的影响及修正[R].海南 三亚:第四届高超声速科技学术会议,2011.
    [16]
    胡芃,陈则韶.量热技术和热物性测定[M].2版.合肥:中国科技大学出版社,2009.
    [17]
    Incropera F P,De Witt D P,Bergman T L,et al.传热和传质基本原理[M].6版.葛新石,叶宏译.北京:化学工业出版社,2009.
    [18]
    张志成,潘梅林,刘初平,等.高超声速气动热与热防护[M].北京:国防工业出版社,2003.
    • Relative Articles
    • Supplements(0)
    • Cited By
  • 加载中

Catalog

    通讯作者: 陈斌, bchen63@163.com
    • 1. 

      沈阳化工大学材料科学与工程学院 沈阳 110142

    1. 本站搜索
    2. 百度学术搜索
    3. 万方数据库搜索
    4. CNKI搜索
    Get Citation
    PDF(990.0KB)
    XML

    Article Metrics

    Article views (1353) PDF downloads(965) Cited by()
    Proportional views
    Related

    Copyright © 《Journal of Aerospace Power》 All Rights Reserved.

    Supported by: Beijing Renhe Information Technology Co., Ltd.  

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return