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›› 2010, Vol. 10 ›› Issue (3): 417-423.

• 流动与传递 •    下一篇

ZrB2-SiC前缘构件气动加热及热应力的数值模拟分析

蔺晓轩 武海棠 魏玺 沈志洵 张伟刚   

  1. 中国科学院过程工程研究所多相复杂系统国家重点实验室 中国科学院过程工程研究所多相复杂系统国家重点实验室 中国科学院过程工程研究所多相复杂系统国家重点实验室 中国科学院过程研究所多相反应开放实验室
  • 收稿日期:2010-03-02 修回日期:2010-04-16 出版日期:2010-06-20 发布日期:2010-06-20
  • 通讯作者: 蔺晓轩

Numerical Simulation on Aerodynamic Heating and Thermal Stress of ZrB2-SiC Leading Edge

LIN Xiao-xuan WU Hai-tang WEI Xi SHEN Zhi-xun, ZHANG Wei-gang，   

  1. State Key Laboratory of Multi-Phase Reaction Engineering, Institute of Process Engineering, Chinese Academy of Sciences State Key Laboratory of Multi-Phase Reaction Engineering, Institute of Process Engineering, Chinese Academy of Sciences State Key Laboratory of Multi-Phase Reaction Engineering, Institute of Process Engineering, Chinese Academy of Sciences Key Lab of Multi-phase Reactions, Institute of Process Engineering. Chinese Academy of Sciences
  • Received:2010-03-02 Revised:2010-04-16 Online:2010-06-20 Published:2010-06-20
  • Contact: LIN Xiao-xuan

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被引次数

9

摘要： 分别采用有限差分法和有限单元法对ZrB2-SiC前缘构件高超声速气动加热过程及其内部热应力进行了数值模拟，并以电弧风洞地面模拟实验对计算结果进行了验证. 计算结果表明，飞行马赫数为6、总温2375 K、总压4.41 MPa、结构前缘半径为0.125 mm时，5 s时驻点温度达1870 K，内部最大热应力达1240 MPa，这将导致服役过程中材料失效. 电弧风洞实验结果表明，5 s时驻点温度达2175 K，材料前缘因承受的应力超过其弯曲强度而断裂.计算结果与风洞实验结果吻合较好.

关键词: ZrB2-SiC, 数值模拟, 前缘, 气动加热, 热应力

Abstract: Aerodynamic heating process and thermal stress of ZrB2-SiC leading edge as the component of scramjet engines were numerically investigated by finite-difference and finite-element methods, and the simulation results were verified through thermal structure tests with arc-heated wind tunnels. Simulation results showed that the temperature at stagnation point reached 1870 K in 5 s, and thermal stress of structure was up to 1240 MPa which was beyond the fracture strength of ZrB2-SiC material, when the inflow Mach number was 6, total pressure 4.41 MPa, total temperature 2375 K, with the radius of leading edge at 0.125 mm. The experimental results show that the temperature at stagnation point reached 2175 K in 5 s, and the leading edge cracked in thermal structure tests. Simulation results were in reasonable agreement with the experimental results.

Key words: ZrB2-SiC, numerical simulation, leading edge, aerodynamic heating, thermal stress

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