Contoured Trailing Edge Airfoil Platform Flow Loss Reduction
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Solution Overview
Problem
Turbine performance in gas turbine engines is hindered by the balance between higher pressure ratios and core gas path temperatures, leading to increased stress and wear on airfoil components, particularly in the hot sections of the compressor and turbine, where advanced cooling configurations and thermal coating systems are utilized but still face inefficiencies due to flow path losses.
Innovation Solution
The airfoil platform features a contoured trailing edge with distinct flowpath regions, including a convex, intermediate, and concave or linear contour, designed to minimize flow losses and enhance cooling efficiency by matching slopes and radii of curvature, thereby optimizing the transition between stator and rotor airfoils.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If higher pressure ratios are used to improve turbine performance, then efficiency increases, but stress and wear on airfoil components increase
Solution Approach 1:
The patent applies local quality by creating a specialized trailing edge geometry with specific curvature characteristics (convex, intermediate, and concave regions) that are locally optimized to reduce flow losses and thermal stress concentration, while maintaining the overall airfoil structure for high pressure ratio operation
2Duration of action of stationary object
If advanced cooling configurations are used to reduce thermal stress, then component life improves, but flow path losses increase
Solution Approach 1:
The trailing edge geometry is locally optimized with specific curvature characteristics that reduce flow separation and mixing losses in the cooling flow path, while maintaining effective cooling coverage. The convex-intermediate-concave contour sequence creates smooth flow transitions that minimize energy losses
Solution Approach 2:
The patent extensively uses curvature principles by defining the trailing edge with convex, intermediate, and concave regions with specific radius of curvature relationships. This curved geometry optimizes flow attachment and reduces separation losses compared to sharp or flat trailing edges, thereby reducing flow path losses while maintaining cooling effectiveness
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
This design reduces flow losses and improves cooling efficiency, leading to increased turbine performance, reduced thermal stress, and extended service life by minimizing hot spots and peak gas path temperatures downstream.
Implementation Method 1
The trailing edge portion has a first region with a convex flowpath contour, a second region with an intermediate flowpath contour, and a third region with a concave or linear flowpath contour
Implementation Method 2
designed to minimize flow losses and enhance cooling efficiency by matching slopes and radii of curvature
Implementation Method 3
enhance cooling efficiency by matching slopes and radii of curvature, thereby optimizing the transition between stator and rotor airfoils
Implementation Method 4
reduced thermal stress, and extended service life by minimizing hot spots and peak gas path temperatures downstream
Data Source
AI summary
An airfoil platform comprises a leading edge portion and a trailing edge portion. The trailing edge portion comprises a first region having a convex flowpath contour, a second region having an intermediate flowpath contour extending downstream from the convex flowpath contour, and a third region having a concave or linear flowpath contour extending downstream from the intermediate flowpath contour to a downstream end of the trailing edge portion of the platform.