Patterned Airfoil Coating Reduces Flow Separation
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Solution Overview
Problem
Erosion-resistant coatings on gas turbine engine airfoils cause premature leading edge blunting, leading to reduced aerodynamic performance, especially in sand-laden environments, as they are insufficiently resistant to erosion and impact, resulting in negative aerodynamic effects and performance degradation.
Innovation Solution
A patterned leading edge design for the erosion-resistant coatings on airfoils, with specific uncoated portions and strategically applied coatings on the concave and convex surfaces, reduces flow separation and turbulence, maintaining aerodynamic performance while preventing premature blunting and erosion.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If an erosion-resistant coating is applied to the leading edge of an airfoil, then erosion and impact resistance are improved, but aerodynamic performance deteriorates due to leading edge blunting and flow separation
Solution Approach 1:
The leading edge coating is segmented into discrete pattern elements (such as ridges, grooves, or protrusions) rather than a continuous coating. This segmentation creates multiple small leading edges that collectively provide erosion resistance while minimizing the overall disruption to airflow, thereby reducing flow separation and maintaining aerodynamic performance
Solution Approach 2:
The coating pattern is designed with varying local geometries (different ridge heights, groove depths, or element spacing) to optimize both erosion resistance and aerodynamic flow characteristics at different locations along the leading edge, achieving a balance between protection and performance
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
The patterned leading edge design minimizes aerodynamic losses and maintains compressor efficiency by reducing flow separation and turbulence, while providing adequate protection against erosion and impact, thus improving the overall performance of gas turbine engines in harsh environments.
Implementation Method 1
The patterned leading edge includes pattern elements shaped to create less flow separation aft of the leading edge of the erosion-resistant coating layer
Data Source
AI summary
An airfoil of a gas turbine engine includes a leading edge and an opposed trailing edge defining a chord between the leading edge and the trailing edge, wherein the chord has a chord length. A concave surface is between the leading edge and the trailing edge, which includes a first portion proximal the leading edge of the airfoil and a second portion proximal the trailing edge of the airfoil, wherein the first portion of the concave surface includes about 10% to about 50% of the chord length. An erosion-resistant ceramic, cermet or intermetallic coating is on the second portion of the concave surface, which includes a coating leading edge pattern. The first portion of the concave surface is free of the erosion-resistant coating.