Composite Turbomachine Blade Fillet Transition Design
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Solution Overview
Problem
The interface between turbomachine blades and their platforms often experiences stress concentrations due to sharp corners or joints, leading to potential stress and reduced lifespan.
Innovation Solution
A concave fillet transition is created using laminated layers of composite material, with interface ply segments extending across the exterior surface of the airfoil and platform to form a continuous, smooth interface, providing additional support against vibratory stress and wear.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a sharp corner or joint is used at the interface between the blade portion and the platform, then the manufacturing process is simple, but stress concentrations occur leading to reduced blade life
Solution Approach 1:
The patent applies curvature by replacing the sharp corner joint with a fillet transition that has a continuous curved surface. This fillet transition eliminates the abrupt geometric discontinuity at the interface between the blade portion and platform, thereby reducing stress concentrations and improving blade reliability without significantly complicating the manufacturing process.
Solution Approach 2:
The patent changes the geometric parameters of the interface by introducing a fillet radius and transitioning from a sharp corner (zero radius) to a curved surface with a defined radius of curvature. This parameter change smooths the stress distribution and prevents stress concentrations while maintaining manufacturing feasibility through standard composite lamination techniques.
2Strength
If a fillet transition is added to reduce stress concentrations, then blade durability is improved, but the manufacturing complexity increases
Solution Approach 1:
The patent segments the composite structure into distinct components: blade portion layers, fillet transition layers, and platform layers. Each segment can be independently laid and positioned during the lamination process, which simplifies the overall manufacturing by breaking down the complex fillet transition into manageable discrete layers that can be sequentially applied.
Solution Approach 2:
The patent applies local quality by using interface ply segments specifically at the critical fillet transition region where stress concentrations occur. These interface plies are oriented at specific angles and positioned locally at the curved interface, providing enhanced stress resistance precisely where needed without requiring complex modifications to the entire blade structure.
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 concave fillet transition enhances the durability of turbomachine blades by reducing stress concentrations and preventing premature wear and degradation, thereby increasing their lifespan.
Implementation Method 1
The plurality of airfoil layers are laminated to one another to form an airfoil. The plurality of platform layers are laminated to one another to form a platform
Data Source
AI summary
A system includes a turbomachine blade segment including an airfoil with an exterior surface, and a platform coupled to the airfoil having a first side and a second side. The system also includes a concave fillet transition extending between the airfoil and the platform. The concave fillet transition includes one or more interface ply segments extending across the exterior surface of the airfoil and the first or the second side of the platform to form a continuous surface between the airfoil and the platform.