Turbine Blade Trailing Edge Concavity for Cooling
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Solution Overview
Problem
Existing turbine blade designs face a trade-off between aerodynamic efficiency and cooling effectiveness, where improvements in one aspect often lead to a reduction in the other, particularly in the trailing edge region.
Innovation Solution
A turbine blade design featuring a concavity at the trailing edge with varying widths between and across cooling openings, which reduces blockage and enhances cooling efficiency by creating a contoured geometry that streamlines airflow and reduces cooling air requirements.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If cooling openings are added to the trailing edge, then cooling effectiveness is improved, but aerodynamic efficiency deteriorates due to increased blockage
Solution Approach 1:
The patent applies curvature by forming a concavity at the trailing edge that contours around the cooling openings. This curved geometry streamlines the airflow around the openings, reducing turbulence and blockage effects while maintaining effective cooling air discharge. The concave shape allows the cooling openings to be integrated more smoothly into the trailing edge profile, mitigating the aerodynamic penalty of having openings in the flow path.
2Productivity
If pressure side discharge is used, then aerodynamic efficiency is improved, but cooling effectiveness deteriorates
Solution Approach 1:
The patent applies local quality by creating a localized concavity specifically at the trailing edge region where cooling openings are present. This localized geometric modification targets the specific area where the contradiction between aerodynamic efficiency and cooling effectiveness occurs, allowing the cooling openings to be positioned and shaped in a way that optimizes both cooling performance and aerodynamic flow characteristics in that critical region.
3Productivity
If trailing edge blockage is reduced, then aerodynamic efficiency is improved, but cooling air requirements increase
Solution Approach 1:
The concave curvature at the trailing edge streamlines airflow around the cooling openings, reducing flow separation and turbulence. This improved flow pattern maintains effective cooling with less cooling air required, as the curved geometry helps direct the cooling air more efficiently through the trailing edge region rather than allowing it to dissipate in turbulent eddies.
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 design improves aerodynamic efficiency, reduces cooling air needs, and minimizes temperature migration, thereby enhancing turbine reliability and performance.
Implementation Method 1
a contoured geometry that streamlines airflow and reduces cooling air requirements
Data Source
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AI summary
Disclosed is a turbine blade or vane (10) including a blade or vane body (12) including a leading edge (14) and a trailing edge (16), a plurality of cooling openings (18) disposed along the trailing edge, a first width (20) of the trailing edge, the first width being disposed across the cooling openings, and a second width (22) of the trailing edge the second width being disposed between the cooling openings (18), wherein the second width (22) is smaller than the first width.