Gas Turbine Airfoil Platform Contoured Edge Geometry
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Solution Overview
Problem
The existing airfoil platform geometry in gas turbine engines has sharp, right-angled corners that can lead to inefficiencies in energy extraction and increased wear, particularly due to the proximity of adjacent lateral surfaces and the need for precise sealing, which affects the overall performance and compactness of the engine.
Innovation Solution
The airfoil component features a contoured surface with a generally uniform radius and a thickness ratio of 4:1 to 10:1, which includes a flat, planar ledge and non-radiused edges, arranged inboard of the aft edges, to reduce stress and improve sealing without cooling holes, enhancing the platform's structural integrity and sealing efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If a sharp, right-angled corner geometry is used at the platform edge, then manufacturing is simpler, but stress concentration increases and sealing efficiency deteriorates
Solution Approach 1:
The patent applies curvature by replacing the sharp, right-angled corner geometry with a contoured surface that has a generally uniform radius. This curved transition surface between the lateral surface and the flow path surface eliminates stress concentration points while maintaining manufacturing feasibility, thereby improving sealing efficiency without significantly complicating the manufacturing process.
2Temperature
If cooling holes are added to the platform surface, then thermal management improves, but structural integrity deteriorates
Solution Approach 1:
The patent extracts the cooling function from the platform structure by specifically excluding cooling holes from the contoured surface area. The design accepts that this particular surface region will not have cooling holes, thereby maintaining the structural integrity and stress distribution of the platform edge while other areas of the platform may still incorporate cooling holes as needed.
3Strength
If the platform thickness is increased, then structural strength improves, but engine compactness deteriorates
Solution Approach 1:
The patent optimizes the platform thickness parameter within a specific range (0.10-0.20 inch or 2.54-5.08 mm) to achieve the desired balance between structural strength and engine compactness. This parameter optimization, combined with the contoured surface geometry, allows the platform to maintain sufficient strength while minimizing the overall engine volume.
Data Source
AI summary
An airfoil component for a gas turbine engine includes a platform. The airfoil component includes a flow path surface from which an airfoil extends. A laterally extending aft surface is adjacent to the flow path surface. A contoured surface adjoins the flow path surface and the aft surface. An airfoil component for a gas turbine engine includes a platform. The airfoil component includes a flow path surface from which an airfoil extends. A laterally extending aft surface is adjacent to the flow path surface. A contoured surface adjoins the flow path surface and the aft surface. The aft surface extends from a first aft edge to a second aft edge at a circumferentially extending edge. The contoured surface is arranged inboard from at least one of the first and second edges.