ZrB_2-SiC前缘构件气动加热及热应力的数值模拟分析  

Numerical Simulation on Aerodynamic Heating and Thermal Stress of ZrB_2-SiC Leading Edge

作　　者：蔺晓轩[1,2] 武海棠[1,2] 魏玺[1] 沈志洵[1,2] 张伟刚[1] 

机构地区：[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,北京100190 [2]中国科学院研究生院,北京100049

出　　处：《过程工程学报》2010年第3期417-423,共7页The Chinese Journal of Process Engineering

基　　金：中国科学院知识创新工程重要方向基金资助项目(编号:YYYJ-0808-2)

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2375K、总压4.41MPa、结构前缘半径为0.125mm时,5s时驻点温度达1870K,内部最大热应力达1240MPa,这将导致服役过程中材料失效.电弧风洞实验结果表明,5s时驻点温度达2175K,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.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.

关 键 词：ZRB2-SIC 数值模拟 前缘 气动加热 热应力 

分 类 号：TB332[一般工业技术—材料科学与工程]