Gas Turbine Vane with Localized Platform Thickness Variation
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Solution Overview
Problem
Designing static vanes for gas turbine engines to effectively manage stresses, particularly where the airfoil merges into the platform, is challenging due to the unique stress distribution in these areas.
Innovation Solution
The vane design features thicker portions circumferentially located beyond the leading and trailing edges, with thinner portions beyond the circumferential edges of the airfoil, and variable thickness bumps to provide additional resistance to stresses, with a thickness ratio of 1.1 to 5.0 compared to adjacent areas.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If the platform thickness is increased at critical stress locations, then the strength and stress resistance are improved, but the overall weight and material usage increase
Solution Approach 1:
The platform thickness is varied locally rather than uniformly throughout. Thicker portions are positioned circumferentially beyond the leading and trailing edges where stress concentrations occur, while thinner portions are located beyond the circumferential edges of the airfoil where stresses are lower. This localized thickness variation optimizes strength where needed while minimizing unnecessary material elsewhere.
Solution Approach 2:
The platform thickness parameter is changed from a constant value to a variable value that depends on the circumferential position. The thickness ratio between the thickest and thinnest portions is maintained between 1.1 and 5.0, allowing the structure to adapt its mechanical properties to the local stress conditions at different locations around the vane.
2Strength
If thicker portions are added to the platform, then the structural integrity is improved, but the manufacturing complexity increases
Solution Approach 1:
The variable thickness profile is integrated into the platform design, creating thicker portions at specific circumferential locations beyond the leading and trailing edges. This localized geometric modification can be achieved through conventional manufacturing methods such as selective material deposition, targeted machining, or forming processes, rather than requiring complex multi-step manufacturing sequences.
Data Source
AI summary
A vane for use in a gas turbine engine has an airfoil extending between a leading edge and a trailing edge, and is generally hollow. The vane has a radially outer platform and a radially inner platform. At least one of the radially inner and radially outer platforms has thicker portions circumferentially located beyond one of the leading edge and the trailing edge, and thinner portions circumferentially beyond circumferential edges of the airfoil. A mid-turbine frame and a gas turbine engine are also disclosed.