Reduced-Order Aerodynamic Models For Analysis of Mistuned Bladed Disks

1. Reduced-Order Aerodynamic Models For Analysis of Mistuned Bladed Disks Tan Bui, Prof. Karen Willcox • Motivation: • Mistuning is when the blades in a compressor or turbine of an engine are not quite identical, e.g. because of random manufacturing variation, or wear and tear. This asymmetry can cause a significant increase in the resonant amplitude for some of the blades, leading to a critical phenomenon called high cycle fatigue (HCF). HCF can cause major problems in gas turbine engines. • Goals: • Formulate, implement and demonstrate a coupled aerodynamic/structural framework for analysis of mistuned bladed disks. • Reduced-order aerodynamic models will be created from a high-order CFD code and coupled with an existing structural mistuning framework. • Investigate the effects of aerodynamic damping on aeroelastic behavior of mistuned bladed disks and quantify the impact on aerodynamic performance of intentional mistuning. Funded by Dr. James Kenyon, AFRL. Collaboration with Dr. Feiner and Prof. Griffin, CMU.

2. Methodology Blade forces Discontinuous Galerkin Aerodynamic CFD Model Finite Element Structural model Blade displacements Proper Orthogonal Decomposition Fundamental Mistuning Model Blade forces Low Order Structural model Low Order Aerodynamic Model Blade displacements Low Order Aeroelastic model INVESTIGATE AERODYNAMIC EFFECTS FOR MISTUNED BLADED DISKS