Research on Aerothermoelasticity for Hypersonic Inlet with Complex Internal Flow
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摘要:
高超声速进气道在复杂波系的气动载荷和气动热作用下非常容易诱发热气动弹性问题，深入理解复杂内流下热气动弹性机理对未来高超声速进气道的精细化设计具有重要意义。建立了静/动热气动弹性动力学分析框架，深入研究了静/动热气动弹性对三维高超声速进气道流场结构和性能影响的规律和机理。静热气动弹性分析结果表明，双向耦合方法得到的气动热弹性变形相对较大，入口唇前缘变形量最大。结构变形改变了唇缘附近的激波结构，增强了进气道内部的激波强度，增加了分离区长度和外壁面温度，改变了出口流场。同时，热气动弹性变形会导致质量流量系数和压升比的增大，降低了总压恢复系数。动热气动弹性分析结果表明，对于模型，不考虑气动加热时，结构位移响应逐渐呈现收敛趋势；考虑气动加热后，结构位移响应呈现极限环的趋势。气动加热可能会改变进气道结构动态响应特征。由于进气道结构频率非常接近，结构动力响应中存在着"拍"现象。前缘变形较大而振幅较小，尾缘变形较小而振幅较大。结构振动导致流场结构产生明显的动态变化，且导致性能参数存在明显的波动，尤其是出口反压比波动幅度较大。希望通过研究加深对进气道中复杂波系结构中热气动弹性问题的理解与认识，以期为未来进气道的精细化设计提供参考。
Abstract:Hypersonic inlet is very easy to induce aerothermoelastic problems under the aerodynamic load and aero-thermal action of complex flow. Deeply understanding the aerothermoelasticity mechanism of complex internal flow is of great significance for the detailed design of hypersonic inlet in the future. In this paper, a static/dynamic aerothermoelastic analysis framework was established, and the mechanism of the influence of static/dynamic aerothermoelasticity on the flow field structure and performance of three-dimensional hypersonic inlet was studied in depth. The results of static aerothermoelastic analysis show that the aerothermoelastic deformation obtained by the two-way coupling method is relatively large, and the deformation of the leading edge of the inlet lip is the largest. The structural deformation changes the shock wave structure near the lip edge, enhances the shock wave intensity inside the inlet, increases the length of the separation zone and the temperature of the outer wall, and changes the flow field at the outlet. At the same time, the aerothermoelastic deformation will lead to the increase of mass flow coefficient and pressure rise ratio, and reduce the total pressure recovery coefficient. The results of dynamic aerothermoelastic analysis show that the displacement response of the structure converges when the aerodynamic heating is not taken into account. After considering aerodynamic heating, the structural displacement response presents a limit cycle trend. Aerodynamic heating may change the dynamic response characteristics of the inlet structure. Because the structural frequencies of the intake ports are very close to each other, ″beat″ phenomenon exists in the dynamic response of the structure. The leading edge deformation is large and the amplitude is small, while the trailing edge deformation is small and the amplitude is large. The structure vibration leads to significant dynamic changes in the flow field structure and significant fluctuations in the performance parameters, especially for the pressure rise ratio at the outlet. It is hoped that the research in this paper will deepen the understanding of the aerothermoelasticity in the complex flow structure of the inlet, in order to provide reference for the detailed design of the inlet in the future.
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Key words:
- hypersonic /
- inlet /
- aerothermoelastic /
- nonlinear dynamics /
- CFD/CSD
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图 2 计算的压力分布与实验数据的对比
Figure 2. Comparison of pressure coefficient between calculated results and experimental data
图 4 计算极限环幅值随动压的变化与文献结果的对比
Figure 4. Comparison of the variation of limit cycle amplitude with dynamic pressure
图 8 不同网格尺度下中间剖面上压力和温度分布的对比
Figure 8. Comparison of the pressure coefficient and the temperature under different grid scales
图 9 监测点位移变化历程
Figure 9. Displacement change of the observation point with coupling step in three cases
图 10 中间剖面位移量的对比
Figure 10. Comparison of displacement distribution at the middle section in three cases
图 11 不同耦合方法下的热气动弹性变形云图
Figure 11. Aerothermoelastic deformation contour by different methods
图 12 进气道中间剖面上的压力分布的对比
Figure 12. Comparison of pressure coefficient at the middle section
图 13 不同计算方式下物面压力系数云图的对比
Figure 13. Comparison of pressure contour on the wall by different methods
图 18 出口中间剖面上压力分布的对比
Figure 18. Comparison of pressure distribution at the middle section of the exit
图 21 不同时间步长下位移和总压恢复系数随时间的变化
Figure 21. Displacement and total pressure recovery coefficient with time at different time steps
图 23 监测点的位移随时间的变化及其功率谱分析
Figure 23. Displacement of the monitoring points with time and power spectrum analysis
图 24 瞬时物面位移云图
Figure 24. Comparison of transient aerothermoelastic deformation contour
图 29 进气道性能参数随时间的变化及其功率谱分析
Figure 29. Inlet performance parameters with time and power spectrum analysis
表 1 进气道分离区起始、终止位置以及长度的对比
Table 1. Comparison of the location and length of the separation zone in four cases
methods xstart/m xend/m L/m rigid model 8.177 8.624 0.447 without heating 8.148 8.629 0.481 one-way coupling 8.114 8.648 0.534 two-way coupling 8.106 8.656 0.550 
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表 2 进气道性能参数对比
Table 2. Comparison of the performance parameters of the inlet
parameter rigid without heating one-way coupling two-way coupling value value Δ/(%) value Δ/(%) value Δ/(%) φ 0.675 8 0.695 5 2.92 0.725 4 7.34 0.726 7 7.53 σ 0.208 1 0.201 6 -3.12 0.190 1 -8.65 0.189 8 -8.79 RP 16.313 16.928 3.77 17.980 10.22 18.021 10.47
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表 3 进气道结构固有频率
Table 3. Natural mode frequency of the inlet structure
mode order natural mode frequency/Hz without heating with heating 1 48.919 28.497 2 49.952 30.099 3 54.361 32.725 4 62.476 37.952 5 67.864 41.509 6 75.125 45.616 7 92.967 56.734 8 116.26 70.851 9 135.59 78.202 10 142.05 85.242
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表 4 进气道性能参数时均值及波动幅度
Table 4. Time average and fluctuation amplitude of inlet performance parameters
parameter without heating with heating rigid model time average value fluctuation amplitude time average value fluctuation amplitude φ 0.675 8 0.695 4 2.91% 0.724 8 7.25% σ 0.208 1 0.201 6 -3.11% 0.190 4 -8.49% RP 16.313 16.921 7 3.73% 18.019 4 10.46%
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