多场耦合效应对高超声速进气道入口参数影响

Effects of Fluid-Thermal-Structural Coupling on Inlet Parameters of Hypersonic Intake

为了研究多场耦合效应对高超声速进气道入口参数的影响,采用自主开发的热环境/热响应耦合计算分析平台FL-CAPTER,对吸气式高超声速进气道前体进行了数值仿真研究。介绍了采用的多物理场耦合分析策略及不同物理场求解方法,通过圆管和两级压缩楔外形,初步验证了多场耦合分析方法的可靠性。以此为基础,研究了进气道前体在长时间巡航飞行条件下的结构温升情况和宏观变形量,分析了进气道结构变形对入口参数的影响。结果表明:进气道前体迎风区域和背风区域不均匀的温度分布引起热应力变化,进气道前体压缩面在多场耦合效应作用下上翘约20mm,考虑变形影响后,进气道偏离设计状态,激波边界层干扰效应增强,喉道附近的分离区域有所增大,进气道入口的质量流量增加约4.2%,喉道平均马赫数降低,静压升高,总压恢复系数降低。

A numerical investigation based on the in-house FL-CAPTER software is performed to study the effects of the fluid-thermal-structural coupling on the inlet parameters of the hypersonic intake. The coupling strategy and the numerical methods for flow,structure temperature,stress and deformation are introduced firstly.Then,a tube and a compression ramp model are adopted to preliminarily validate the software. On this basis,the fluid-thermal-structural coupling calculation of an inlet model under long cruise condition is conducted and the influence of the coupling induced deformation on the inlet parameters is analyzed. The results show that the leading edge of the first ramp is deformed upward for about 20 mm due to the non-uniformed temperature distribution and the deformation will cause the inlet to deviate from the design state. Additionally,after taking the structural deformation into account,the shock boundary layer interaction effect is enhanced,the separation area near the throat is enlarged,the inlet mass flow rate increases by about 4.2%,the average Mach number decreases,the static pressure increases and the total pressure recovery coefficient is reduced.