Whole-annulus aeroelasticity analysis of a 17-bladerow WRF compressor using an unstructured Navier–Stokes solver
Whole-annulus aeroelasticity analysis of a 17-bladerow WRF compressor using an unstructured Navier–Stokes solver
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使用非结构化纳维-斯托克斯求解器对 17 叶片 WRF 压缩机进行全环空气动弹性分析
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发表时间：
2005
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通讯作者：
M. Imregun
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作者：
X. Wu;M. Vahdati;A. Sayma;M. Imregun
本文对某型航空发动机机芯压气机进行了大规模气动弹性计算。计算域包括所有17个叶片，产生了一个超过6800万个点的网格。Favre平均的Navier-Stokes方程被用来在混合单元的非结构网格上以非线性、时间精度的方式表示流动。前两个旋翼叶片的结构模型是基于标准的有限元表示。流体网格根据结构运动在每个时间步长移动，从而能够自动适应叶片气动阻尼和流动不稳定的变化。作为工作的一部分，开发了一种高效的域分解技术，其中特别注意平衡不同处理器的内存需求。计算是在SGI Origin 3000的128个CPU上以并行模式进行的。使用超过2.2CPU年，获得了10个振动周期，但所用时间仅为一周。稳态流动测量结果与预测结果吻合较好。将平均非定常流动与定常流动进行了比较，发现两者有一定的差异。结论是，在适当的时候，工业界将采用这种方法来对整个带有振动叶片的压缩机组件的非定常流动进行常规的数值模拟，不仅为了尽量减少发动机和试验台的测试，而且还为了改进性能预测。
This paper describes a large-scale aeroelasticity computation for an aero-engine core compressor. The computational domain includes all 17 bladerows, resulting in a mesh with over 68 million points. The Favre-averaged Navier–Stokes equations are used to represent the flow in a non-linear time-accurate fashion on unstructured meshes of mixed elements. The structural model of the first two rotor bladerows is based on a standard finite element representation. The fluid mesh is moved at each time step according to the structural motion so that changes in blade aerodynamic damping and flow unsteadiness can be accommodated automatically. An efficient domain decomposition technique, where special care was taken to balance the memory requirement across processors, was developed as part of the work. The calculation was conducted in parallel mode on 128 CPUs of an SGI Origin 3000. Ten vibration cycles were obtained using over 2.2 CPU years, though the elapsed time was a week only. Steady-state flow measurements and predictions were found to be in good agreement. A comparison of the averaged unsteady flow and the steady-state flow revealed some discrepancies. It was concluded that, in due course, the methodology would be adopted by industry to perform routine numerical simulations of the unsteady flow through entire compressor assemblies with vibrating blades not only to minimise engine and rig tests but also to improve performance predictions.