真实气体效应下高超声速进气道多场耦合仿真  

Multi-physical Field Coupling Simulation of Hypersonic Inlet Considering Real Gas Effect

作　　者：王鑫 袁化成[1] 刘甫州 张锦昇 WANG Xin;YUAN Huacheng;LIU Fuzhou;ZHANG Jinsheng(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《机械制造与自动化》2023年第4期115-119,共5页Machine Building & Automation

基　　金：航空基金项目(20200012052001)。

摘　　要：吸气式高超声速飞行器速域的不断拓展,使进气道部件在强烈的气动载荷以及热载荷作用下与外部流场耦合效应明显,同时高温流动中的真实气体效应会进一步加剧进气道内多场耦合关系的复杂性。通过在多场耦合仿真中考虑真实气体效应影响,针对壁面共轭耦合传热下高超声速进气道气动性能以及结构温度场的非定常变化进行数值模拟。研究发现:受壁温升高的影响,300 s时刻进气道出口气流温度相比初始时刻上升13.30%,压力升高13.53%,总压恢复系数下降2%,而流量系数几乎不发生变化。50 s时刻,唇缘和前缘处壁温达到2350 K,内通道最高壁温为1200 K,而在300 s时刻内通道最高壁温也接近1900 K。因此在兼顾内通道防热设计的同时,要着重考量前缘及唇缘热防护设计的可靠性。With the increase of the flight speed of the air-breathing hypersonic vehicle,the coupling effect between the inlet and the external flow field is obvious under the strong aerodynamic load and thermal load.Meanwhile,the real gas effect in high temperature flow will further aggravate the complexity of the multi-physicalfield coupling relationship in the inlet.Based on the multi-physical field coupling simulation method considering the real gas effect,carries out the numerical simulation of the unsteady changes of the aerodynamic performance and structural temperature field of the hypersonic inlet under the wall conjugate coupled heat transfer.It is found that under the influence of the increase of wall temperature,the inlet outlet temperature at 300 s increases by 13.30%compared with the initial time,the pressure increases by 13.53%,and the total pressure recovery coefficient decreases by 2%,while the flow coefficient hardly changes.At 50 s,the wall temperature at the cowl-lip and leading-edge reaches 2350 K,the maximum wall temperature of the inner channel is 1200 K,and the highest wall temperature of internal contraction tunnel is close to 1900 K at 300 s.Therefore,while taking into account the thermal protection design of internal contraction tunnel,the reliability of the design of the leading edge and lip should be taken into special consideration.

关 键 词：高超声速进气道 真实气体效应 共轭传热 多场耦合仿真 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]