Vortical–Potential Integrated Reduced-Order Solver for Non-Axisymmetric Turbomachinery Aerodynamics

Modern gas turbines contain non-axisymmetric components (e.g., bifurcations and transition ducts) that disturb circumferential uniformity and drive long-range potential fields across blade rows, degrading performance. We introduce Turbomachinery Aerodynamic Vortical–Potential Integrated Solver (TAVIS), a reduced-order method formulated on curved streamsurfaces to capture component interactions at orders-of-magnitude lower cost than three-dimensional unsteady Reynolds-averaged Navier–Stokes (URANS). On each streamsurface, the flow is represented as a circumferentially uniform mean with potential/vortical perturbations. Velocity perturbations are decomposed into five harmonically resolved modes (intake, rotor-bound potential, rotor-bound circulation, rotor-shed vorticity, and stator circulation). Rotor effects are modeled using an actuator disc, where nonreflecting transmission is enforced through linearized continuity across the disc with the rotor Kutta condition. Combined with wall impermeability and the stator Kutta condition, all constraints are imposed simultaneously within a single finite-element linear system. Validation on high-bypass fan-outlet guide vane (OGV)-pylon configurations shows that TAVIS reproduces dominant harmonics and Mach-number distortions with band-aware [Formula: see text] at mid- and tip-span; off-design discrepancies [Formula: see text]. Solutions converge in ten seconds, [Formula: see text] times faster than URANS, retaining accuracy. Including compressibility and geometric-variation effects, TAVIS delivers near–real-time predictions for optimization. The framework is readily extensible to other non-axisymmetric configurations (e.g., compressor struts, transition ducts, and propeller–rudder systems).