Gas Turbine Fuel Nozzle Flow Guides Prevent Separation

The shroud is divided into multiple sections along its length, with each section having a different curvature radius. The first shroud section has a first curvature radius and the second shroud section has a second curvature radius that is greater than the first, creating segmented flow guidance zones that prevent flow separation while maintaining effective airflow direction

The shroud employs varying curvature radii along its length to guide compressed air smoothly. By increasing the curvature radius from the first section to the second section, the design creates a gradual transition that reduces flow separation and pressure loss while maintaining the shroud's ability to direct airflow effectively

The shroud is segmented into multiple sections with different curvature characteristics. This segmentation allows the design to move away from a simple cylindrical shape to a more complex multi-section structure that prevents flow separation, thereby improving combustor performance while remaining manufacturable through standard processes

Different sections of the shroud have different local geometric properties (curvature radii). The first shroud section has a smaller curvature radius while the second has a larger curvature radius, creating localized flow control zones that prevent flow separation at critical areas, thus improving combustor reliability without requiring complete redesign of the entire shroud