極限マルチフィジクス環境における液体ロケットエンジンの破損メカニズムの解明(燃焼室スロートの残留変形)  [in Japanese] Failure Mechanism of Combustion Chamber of Liquid Rocket Engine under Severe Multi-Physics Conditions (Residual Deformation of Chamber Throat)  [in Japanese]

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Author(s)

Abstract

In developing liquid rocket engine, life time of combustion chamber is an important design issue. However, it is very difficult to quantitatively predict the life time because complicated multi-physics phenomena occur under severe conditions in the combustion chamber. The LE-X engine is under study in JAXA as the next booster engine. In its research and development, shorter development time, lower cost and higher reliability are sought by using front-loading design approaches. Therefore, it is indispensable to evaluate the life time of the combustion chamber precisely in the early phase of development. In order to improve accuracy in the life prediction, we focus on the interaction between thermo-fluid behaviors and structural responses, and have developed a new analysis procedure, that is, high-fidelity multi-physics coupled simulation. By applying this procedure, we have investigated the mechanisms and the dominant factors of residual deformation occurred in the throat, which was experienced under development of the upper stage engine. It has been revealed that the throat's residual deformation strongly depends on cooling capability in the shutdown process, which is affected by the transient flows of both combustion gas and coolant.

Journal

  • TRANSACTIONS OF THE JAPAN SOCIETY OF MECHANICAL ENGINEERS Series A

    TRANSACTIONS OF THE JAPAN SOCIETY OF MECHANICAL ENGINEERS Series A 78(795), 1534-1546, 2012

    The Japan Society of Mechanical Engineers

Codes

  • NII Article ID (NAID)
    130002573054
  • Text Lang
    JPN
  • ISSN
    0387-5008
  • Data Source
    J-STAGE 
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