Patent No. EP3676480 (titled "Turbomachine Fan Flow-Straightener Vane, Turbomachine Assembly Comprising Such A Vane, And Turbomachine Equipped With Said Vane Or With Said Assembly") was filed by Safran Aircraft Engines on Aug 28, 2018. The application was issued on Oct 5, 2022.
A flow-straightener vane for a bypass turbomachine comprises multiple vane sections stacked radially along a stacking line (L) between a root end and a tip end. Each section features tangentially opposed pressure-face and suction-face surfaces extending axially from an upstream leading edge to a downstream trailing edge. The profile chord length remains substantially constant from the root to the tip. The stacking line (L) is characterized by a curvature, located near the tip end in a plane passing through the longitudinal axis (X) and the stacking line, oriented from downstream to upstream. This continuous, progressive curvature reduces vortex formation and acoustic noise, optimizing the nacelle's drag and mass while maintaining a specific axial distance from fan blades.

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