This case study describes how Rolls-Royce Deutschland improved axial compressor blade optimization using a parametric 3D blade modeling approach. Previously, blade sections were optimized individually using B-spline curves, requiring extensive computation and long iteration cycles. By transitioning to a unified 3D parameterization in CAESES, Rolls-Royce reduced the number of design variables while maintaining precise control over hub, mid-span, and tip regions. Optimization was performed across multiple sections simultaneously, dramatically reducing computational effort. The new method achieved comparable aerodynamic improvements, expanded working range, shortened design cycles from weeks to days, improved manufacturability, and increased confidence in final blade geometries.

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