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Coupled simulation of flow-structure interaction in turbomachinery

机译：涡轮机械中流固耦合的耦合模拟

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The aeroelastic behaviour of vibrating blade assemblies is usually investigated in the frequency domain where the determination of aeroelastic stability boundaries is separated from the computation of linearized unsteady aerodynamic forces. However, nonlinear fluid-structure interaction caused by oscillating shocks or strong flow separation may significantly influence the aerodynamic damping and hence effect a shift of stability boundaries. In order to investigate such aeroelastic phenomena, the governing equations of structural and fluid motion have to be simultaneously integrated in time. In this paper a technique is presented which analyses the flutter behaviour of turbomachinery bladings in the time domain. The structural part of the governing aeroelastic equations is time-integrated according to the algorithm of Newmark, while the unsteady airloads are computed at every time step by a Navier-Stokes code. The link between the two time integrations is an automatic grid generation in which the used mesh is dynamically deformed so that it conforms with the deflected blades at every time step. The computed time series of the aeroelastic simulation of an assembly of highly loaded compressor blades vibrating freely in transonic flow are presented. The energy transfer between fluid and structure is here dominated by vibrating shocks and shock-boundary layer interaction. It is investigated if the predicted aeroelastic stability boundaries differ from those of a linearised method.
机译：通常在频域中研究振动叶片组件的气动弹性行为，在该频域中，气动弹性稳定边界的确定与线性化非稳态气动动力的计算是分开的。但是，由振荡冲击或强流分离引起的非线性流体-结构相互作用可能会严重影响空气动力学阻尼，从而影响稳定性边界的移动。为了研究这种空气弹性现象，必须及时整合结构和流体运动的控制方程。本文提出了一种在时域内分析涡轮机械叶片颤振特性的技术。根据Newmark的算法，控制气动弹性方程的结构部分是时间积分的，而不稳定的空气载荷则通过Navier-Stokes代码在每个时间步进行计算。两次时间积分之间的链接是自动生成网格，其中所使用的网格会动态变形，以使其在每个时间步均与偏转的叶片一致。给出了在跨音速流中自由振动的高负荷压缩机叶片组件的空气弹性模拟的计算时间序列。流体和结构之间的能量传递在这里主要由振动冲击和冲击边界层相互作用所决定。研究了预测的气动弹性稳定性边界是否不同于线性方法的边界。

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