Turbine Blade Camber Deviation for Vortex Reduction
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Solution Overview
Problem
Turbine engine blades in low-pressure gas turbines experience secondary phenomena such as turbulence and vibration due to vortices, leading to reduced propulsive efficiency and mechanical fatigue, which existing solutions only partially address.
Innovation Solution
Optimizing the blade shape by varying the camber line deviation from the root to the tip, with a minimum at the root and a maximum in the 30% to 80% height range, decreasing continuously to the tip, and ensuring the tip deviation is at least 5° greater than the root deviation, reduces secondary vortex phenomena and mechanical loads.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If conventional blade shapes are used, then the blade structure is simple, but secondary vortex phenomena and mechanical fatigue increase
Solution Approach 1:
The patent applies local quality by varying the camber line deviation specifically in the 30% to 80% height range of the blade, creating different aerodynamic characteristics in different sections. The deviation angle is optimized locally to reduce vortices at critical locations (root and tip regions) while maintaining overall blade functionality, thereby reducing secondary vortex phenomena without requiring complete redesign of the entire blade structure.
Solution Approach 2:
The patent implements dynamics by introducing a variable deviation angle along the blade height rather than using a constant angle. The deviation angle dynamically changes from the root (minimum) through the intermediate section (maximum in 30%-80% range) to the tip (decreasing but at least 5° greater than root), creating a dynamic aerodynamic profile that adapts to the varying flow conditions at different blade sections.
2Productivity
If blade deviation is increased at the tip, then propulsive efficiency improves, but mechanical loads on the blade increase
Solution Approach 1:
The patent applies parameter changes by systematically varying the deviation angle parameter along the blade height. The deviation angle is set to minimum at the root, increases to a maximum in the 30%-80% height range, then decreases toward the tip while maintaining a value at least 5° greater than the root. This controlled parameter variation optimizes propulsive efficiency while distributing mechanical loads more favorably along the blade structure.
Solution Approach 2:
The patent utilizes curvature by defining the camber line with a specific deviation profile that creates a curved aerodynamic shape. The deviation angle variation along the blade height creates a smooth, continuous curvature pattern that optimizes flow attachment and reduces vortices, thereby improving propulsive efficiency while the gradual curvature changes prevent sudden load concentrations that would compromise blade strength.
Data Source
AI summary
A turbine engine blade having a plurality of blade sections stacked along a radial axis between a root and a tip. Each section extends along a longitudinal axis between a leading edge and a trailing edge, and along a tangential axis between a pressure-side face and a suction-side face. Each section presents a camber line, a deviation defined for each section as the difference between an angle between the tangent to the camber line at the leading edge and the longitudinal axis, and an angle between the tangent to the camber line at the trailing edge and the longitudinal axis. The minimum deviation is at the root of the blade, and the maximum deviation is present at sections situated in the range 0.3H to 0.8H, where H is the height of the blade measured from its root to its tip.