Gas Turbine Airfoil Leading Edge Radius Optimization
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Solution Overview
Problem
Recent advances in aerodynamically high-performing, high-pressure turbine blades, particularly at the tip, have complicated the design of gas turbine engine airfoils, necessitating improved ratios of leading edge radius to maximum chord thickness and axial chord length to enhance efficiency and durability.
Innovation Solution
The design incorporates specific ratios of leading edge radius to maximum chord thickness and axial chord length, varying from approximately 0.39 to 0.47 and 0.15 to 0.29 respectively, across different span positions, with a generally linear increasing pattern, to optimize aerodynamic performance and manage heat loads, while extending the airfoil from the platform to an unshrouded end.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If aerodynamically high-performing, high-pressure turbine blade designs are used, then aerodynamic efficiency is improved, but design complexity and manufacturing difficulty increase
Solution Approach 1:
The patent applies parameter changes by optimizing the leading edge radius to maximum chord thickness ratio and leading edge radius to axial chord length ratio within specific ranges (0.39-0.47 and 0.15-0.29 respectively). These parameter optimizations enable high aerodynamic efficiency while maintaining manufacturability, resolving the contradiction between performance and complexity.
2Productivity
If leading edge radius to maximum chord thickness ratio is increased, then aerodynamic performance is improved, but blade thickness and structural weight increase
Solution Approach 1:
The patent optimizes the leading edge radius to maximum chord thickness ratio within a specific range of 0.39-0.47. This parameter optimization achieves high aerodynamic performance while controlling blade thickness, preventing excessive weight gain.
3Productivity
If aerodynamic performance is optimized, then efficiency is improved, but ability to manage external heat loads becomes more difficult
Solution Approach 1:
The patent optimizes geometric parameters including leading edge radius to maximum chord thickness ratio (0.39-0.47) and leading edge radius to axial chord length ratio (0.15-0.29) to achieve a balance between aerodynamic efficiency and heat load management capability.
Solution Approach 2:
The patent applies different geometric characteristics at different span positions, with the leading edge radius to maximum chord thickness ratio varying from 0.39-0.47 at various spans. This local optimization allows different regions of the blade to be tailored for either aerodynamic performance or heat load management as needed.
Data Source
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AI summary
A component (64) for a gas turbine engine (20) includes a platform (76) that has a radially inner side and a radially outer side. A root portion (74) extends from the radially inner side of the platform (76). An airfoil (78) extends from the radially outer side of the platform (76). The airfoil (78) includes a pressure side (94) that extends between a leading edge (82) and a trailing edge (96). A suction side (96) extends between the leading edge (82) and the trailing edge (84). A ratio of leading edge radius (r) to maximum thickness (Tmax) is between 0.39 (r/ Tmax) and 0.47 (r/ Tmax) and a ratio of leading edge radius (r) to axial chord length (bx) is between 0.15 (r/bx) and 0.29 (r/bx).