Gas Turbine Compressor Mistuned Arrays Fluttering

The patent applies local quality by introducing structural variations in specific locations within the flow-directing element arrays. Different elements within the same array have different structures (different airfoil profiles, thicknesses, or geometries), creating localized differences that disrupt the uniformity required for fluttering while maintaining overall functional consistency. This allows the compressor to avoid fluttering without requiring complete redesign of all components.

The patent employs asymmetry by deliberately designing flow-directing elements with non-uniform characteristics. Instead of symmetric, identical elements throughout, the design incorporates elements with varying geometries, profiles, or structural properties within each array. This asymmetric distribution of properties breaks the conditions necessary for synchronized fluttering while preserving the aerodynamic function of each element.

The patent applies segmentation by dividing the flow-directing element arrays into distinct groups or segments with different structural characteristics. Rather than creating entirely unique complex designs, the system segments the elements into manageable categories (e.g., different airfoil types, thickness variations) that can be manufactured using standardized processes. This segmentation approach reduces fluttering while controlling complexity through modular design.

The patent utilizes parameter changes by systematically varying specific geometric parameters of the flow-directing elements (such as airfoil shape, thickness ratio, or chord length) within defined ranges. These controlled parameter variations create the mistuning effect that reduces fluttering, while the variations remain within manufacturing capabilities and do not require fundamentally new design approaches, thus limiting the increase in device complexity.