Turbomachine Blade Tip Flare for Leakage Reduction

The patent applies local quality by implementing a tip flare geometry specifically at the blade tip region while maintaining different characteristics along the blade span. The tip flare portion has increased curvature and altered stacking axis orientation compared to the root region, optimizing aerodynamic performance locally at the tip without compromising the structural integrity of the entire blade.

The patent utilizes curvature by introducing a tip flare geometry with increased curvature at the blade tip region. The stacking axis curvature increases from root to tip, creating a smoother, more rounded transition at the tip that reduces flow separation and improves aerodynamic efficiency while maintaining structural continuity.

The patent applies segmentation by dividing the blade into distinct regions along the stacking axis: a root region with standard geometry, a transition region with gradually increasing curvature, and a tip flare region with maximum curvature. This segmented approach allows complex geometry to be implemented only where aerodynamically beneficial while keeping other regions simpler.

The patent introduces dimensionality change by transitioning from a two-dimensional airfoil section view to a three-dimensional stacked blade geometry with varying curvature along the span. The tip flare is achieved by modifying the stacking axis orientation and curvature in the radial-axial-circumferential space, adding geometric complexity only in the tip region.