A blade forced response prediction system has been developed using an implicit 2D CFD solver to model the rotor blade forced response due to the static pressure distortion (potential disturbance) from the downstream stator vanes and struts. The CFD solver predicts the static pressure distortion upstream of the stator vanes and struts, which is used to calculate the induced velocity perturbation at the rotor inlet. Using the velocity perturbation and the blade’s natural frequencies and mode shapes from a finite element model, the unsteady aerodynamic modal forces and the aerodynamic damping are calculated. A modal response solution is then performed. The results show that the stator vanes cause a significant amplification of the potential disturbances due to the struts. Effects of strut and vane modifications are examined using the analysis. A vane modification with an “optimized” flow angle distribution shows that the disturbance can be greatly reduced. Recent testing of the strut modification shows exceptional correlation with the prediction.
Compressor Blade Forced Response due to Downstream Vane-Strut Potential Interaction
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Chiang, HD, & Turner, MG. "Compressor Blade Forced Response due to Downstream Vane-Strut Potential Interaction." Proceedings of the ASME 1993 International Gas Turbine and Aeroengine Congress and Exposition. Volume 3B: General. Cincinnati, Ohio, USA. May 24–27, 1993. V03BT16A043. ASME. https://doi.org/10.1115/93-GT-287
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