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Abstract The advances in turbomachinery methods over the last decade have led to unsurpassed simulation fidelity. Computational Fluid Dynamics (CFD) methods for turbomachinery, including multistage blade rows, have become reliable and robust. Finite Element Methods (FEM) in the area of mistuning have become established throughout the industry. However, current day-to-day aerodynamic methodology still relies heavily on simplifications, reduced methods, and low-fidelity analyses. One impediment is the workflow bottlenecks: taking data from one system, transforming it, and using it another. This paper lays out a streamlined workflow for forced response of bladed turbomachinery components, linking CFD with FEM for tuned or mistuned forced response. At each stage, high fidelity solutions are used eliminating the need for simplifying assumptions and limiting methods. Additionally, manual steps are replaced with automated and verifiable steps. Both the CFD and FEM rely on making use of the cyclic symmetric nature of the solution fields, leading to fast and accurate solutions. Technologies such as phase lag approach on CFD side, and mode superposition on FEA side are explained to speed up overall time to solution significantly. Lastly, the forced response workflow includes built-in utility to quickly extract the vibrational stresses and strains, especially equivalent (von Mises) and principal values, required for high-cycle fatigue and lifing calculations. Forced response of the NASA Rotor 67 fan subjected to inlet distortion is used in this work to highlight the streamlined workflow.
Patil et al. (Mon,) studied this question.