Abstract This study develops a two-way loosely coupled aeroelastic analysis framework based on a finite-volume fluid solver, a nonlinear finite-element solid solver and the Mesh-based parallel Code Coupling Interface. Research focuses on aeroelastic behaviour in a turbine-based combined cycle inlet after verifying the fluid solver and the coupling strategy through three benchmarks consisting of the inlet experimental model, the classical panel flutter problem and the deformation of a cantilever plate subjected to a shock tube flow. Coupling calculation shows that structural damping is limited only to the vibration suppression of deformable components under constant backpressure but exerts no evident influence on flow field oscillation induced by splitter plate vibration or perturbation from downstream dynamic backpressure. Interestingly, panel deformation (or forced vibration) has a positive impact on the stabilisation of the flow field. The use of a flexible panel with low thickness ( e 05 ) successfully prevents the shock train from transitioning, stabilising the performance profiles at the outlet even under dynamic backpressure. Pressure adjustment in the potentially unstable region through panel deformation is assumed to be the solution to weakening the disturbance from splitter plate vibration, which differs from the energy transfer theory under dynamic backpressure that is often found in the literature.

中文翻译：

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汽轮机联合循环进气道气动弹性行为的抑制与利用

摘要 本研究基于有限体积流体求解器、非线性有限元实体求解器和基于网格的并行代码耦合接口，开发了一种双向松耦合气动弹性分析框架。在通过入口实验模型、经典面板颤振问题和受激波管流作用的悬臂板变形三个基准验证流体求解器和耦合策略后，研究重点是基于涡轮的联合循环入口的气动弹性行为. 耦合计算表明，结构阻尼仅限于在恒定背压下对可变形部件的振动抑制，而对分流板振动或下游动背压扰动引起的流场振荡没有明显影响。有趣的是，面板变形（或强制振动）对流场的稳定性有积极影响。使用具有低厚度 (e 05) 的柔性面板成功地防止了冲击链的转变，即使在动态背压下也能稳定出口处的性能曲线。假设通过面板变形在潜在不稳定区域进行压力调整是减弱分流板振动扰动的解决方案，这与文献中经常发现的动态背压下的能量传递理论不同。即使在动态背压下也能稳定出口处的性能曲线。假设通过面板变形在潜在不稳定区域进行压力调整是减弱分流板振动扰动的解决方案，这与文献中经常发现的动态背压下的能量传递理论不同。即使在动态背压下也能稳定出口处的性能曲线。假设通过面板变形在潜在不稳定区域进行压力调整是减弱分流板振动扰动的解决方案，这与文献中经常发现的动态背压下的能量传递理论不同。