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

What is it about?

Jet engines contain non-axisymmetric components such as pylons, struts, and ducts that disturb the airflow and can reduce efficiency. Studying these effects using high-fidelity CFD simulations is accurate but computationally expensive. This paper introduces a fast reduced-order solver, TAVIS, that predicts how these flow distortions propagate through turbomachinery while running in seconds instead of the days/weeks typically required for URANS simulations. The method captures the dominant aerodynamic interactions with good agreement to high-fidelity simulations, enabling rapid design exploration and earlier identification of performance issues. The framework can be applied to a wide range of turbomachinery configurations involving non-axisymmetric flow disturbances, including compressors, wind turbines, and propellers.

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