Aeroelastic stability enhancement in mistuned turbomachinery cascades under compressible flow

This study proposes a novel methodology to improve the aeroelastic stability of turbomachinery cascades operating under compressible subsonic flow. The blades are modeled as rotating beams that incorporate bending, torsional, warping, and setting-angle effects, initially considered in a geometrically nonlinear form and subsequently linearized for tractable analysis. Aerodynamic forces are described using cascade unsteady aerodynamic theory, while flutter suppression is achieved through the integration of distributed piezoelectric sensor–actuator layers combined with a state feedback control system. Validation against analytical references, finite element simulations, and experimental data confirms the accuracy and robustness of the proposed modeling framework. The results highlight the critical influence of Mach number, rotational speed, and blade setting angle on the natural frequencies and stability margins of cascades. The study further demonstrates that active piezoelectric control can effectively extend the stability boundary when properly tuned, while preserving the baseline dynamic and structural characteristics of the blades. Overall, the findings establish the proposed approach as a computationally efficient and reliable alternative to high-cost CFD-based analyses, making it particularly suitable for early-stage design. Beyond offering cost and time efficiency, the integration of smart structural control provides a scalable pathway for extending service life, reducing maintenance demands, and enhancing the operational reliability of turbomachinery systems. • Cascade flutter suppressed via piezoelectric control under subsonic compressible flow. • Full-order model integrates rotating beam dynamics with active control. • Framework enables rapid flutter prediction beyond CFD, aiding early-stage design. • Mistuning effects analyzed through coupled 3D aeroelastic cascade formulations. • Active control extends aeroelastic stability boundaries.