Volume 23 Issue 5
May  2008
Turn off MathJax
Article Contents
WANG Xiao-wei, JIN Ping, SUN Bing. Study on regeneratively-cooled technology of full-flow stage combustion thrust chamber[J]. Journal of Aerospace Power, 2008, 23(5): 909-915.
Citation: WANG Xiao-wei, JIN Ping, SUN Bing. Study on regeneratively-cooled technology of full-flow stage combustion thrust chamber[J]. Journal of Aerospace Power, 2008, 23(5): 909-915.

Study on regeneratively-cooled technology of full-flow stage combustion thrust chamber

  • Received Date: 2007-05-29
  • Rev Recd Date: 2007-10-01
  • Publish Date: 2008-05-28
  • The full-flow stage combustion(FFSC) cycle engine may be applied in the next generation reusable launch vehicle.In order to meet the enhanced life of FFSCchamber,this paper employed some new technologies developed recently to the regeneratively-cooled thrust chamber for its design work.These technologies include formed platelet technology,high-aspect-ratio cooling passages and elastic cooling structure.While cooling models were established in consideration of the character of FFSCchamber,the modeling of applying these technologies to FFSCchamber was conducted.The results show that these methods can drastically reduce the temperature,the strain of hot-gas-side wall and the coolant pressure drop,and a regeneratively-cooled structure of the FFSCthrust chamber had been preliminarily designed.

     

  • loading
  • [1]
    Popp M,Schmidt G.Rocket engine combustion chamber design concepts for enhanced life[R].AIAA-96-3303,1996.
    [2]
    Giover R C,Kelley B A,Tischer A E.Studies and analyses of the space shuttle main engine[R].Marshall Space Flight Center,AL 35812.NASW-3737:SSME Failure Data Review Dianostic Survey and SSME Diagnostion Evaluation.SCD-SSME-TR-36-1.
    [3]
    Mathew J J,Nichols J T,Boyce W D,et al.Integrated powerhead demonstration:Full flow cycle development[R].Air Force Research Lab 4 Draco Edwards AFB,Aerojct PO Box 13222 Sacramento,William F.Sack,Boeing Defence & Space Group 6633 Canoga Ave Canoga Park,AFRL-PR-ED-TP-1998-003.
    [4]
    Davis J A,Campbell R L.Advantages of a full-flow staged combustion cycle engine system[R].Tokyo Japan:AIAA97-3318,July 6-9,1997.
    [5]
    Immich H,Kretschmer J,Preclik D.Thrust chamber technology developments for future launch vehicle liquid rocket engines[R].AIAA-2001-3544,2001.
    [6]
    Carlile J.An experimental investigation of high-aspect-Ratio cooling passages[R].AIAA-92-3154,1992.
    [7]
    Burkhardt W M,Hayes W A.Formed platelets for low cost regenreatively cooled rocket combuation chambers[R].AIAA-92-3526,1992.
    [8]
    Burkhardt W M,Tokin S W,Mueggenburg H H.Formed plateletliner concept for regeneratively cooled chambers[R].AIAA 90-2117.
    [9]
    Elam S K.Subscale hot-fire testing of a formed platelet liner[R].AIAA-93-1827,1993.
    [10]
    韩振兴,林文,张远君,等.液体火箭发动机铣槽推力室三维壁温分布计算[J].航空动力学报,1996,11(2):145-148.HAN Zhenxing,LIN Wen,ZHANG Yuaniun,et al.Calculation of the wall temperature for 3-D channels of a liquid rocket[J].Journal of Aerospace Power,1996,11(2):145-148.
    [11]
    Frohlich A,Popp M,Schmidt G,et al.Heat transfer characteristics of H2/O2-combustion chambers[R].AIAA-93-1826,1993.
    [12]
    刘国球.液体火箭发动机原理[M].北京:宇航出版社,1993:303-352.
    [13]
    华绍增,杨学宁.实用流体阻力手册[M].北京:国防工业出版社,1985.
    [14]
    Hua Shaozeng.Practical manual of the liquid on of high aspect ratio cooling channel designs for a rocket combustion chamber[R].AIAA-97-2913,1997.
  • 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

    Article Metrics

    Article views (2085) PDF downloads(557) Cited by()
    Proportional views
    Related

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return