Gas Turbine Airfoil Platform Laminated Composite Design
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Solution Overview
Problem
Current airfoil platforms in gas turbine engines face challenges with interlaminar effects and weight reduction due to deformation under loading, which affects the efficiency and design flexibility of rotor systems.
Innovation Solution
The use of laminated carbon composite structures with topology optimization and specific layer configurations, including separate and continuous layers, and support bodies formed from various materials, to minimize interlaminar effects and enhance attachment to rotor disks, reducing stress and weight while maintaining aero performance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Weight of moving object
If laminated composite structures are used to reduce weight, then weight is reduced, but interlaminar effects and stress concentrations increase under loading
Solution Approach 1:
The patent uses laminated composite structures with multiple layers of fiber-reinforced materials (e.g., carbon fiber, fiberglass) combined with resin matrices to achieve weight reduction while maintaining structural integrity. The composite material system allows optimization of strength-to-weight ratio through layer orientation and material selection.
Solution Approach 2:
The patent implements localized reinforcement strategies by varying fiber orientation, layer thickness, and material composition in different regions of the platform. High-stress areas receive enhanced layer configurations to resist interlaminar stresses, while low-stress areas use lighter constructions to minimize weight.
2Volume of moving object
If platform size is reduced to decrease rotor blade size and cost, then manufacturing cost and size are reduced, but structural strength and attachment reliability may be compromised
Solution Approach 1:
The patent divides the platform into multiple functional layers and zones, each optimized for specific purposes. The segmented structure includes separate load-bearing layers, flow-path layers, and attachment interface layers, allowing strength to be concentrated where needed while reducing overall volume.
Solution Approach 2:
High-strength composite materials enable the platform to maintain adequate attachment strength despite reduced size. The use of high-modulus fibers and optimized resin systems provides superior strength-to-volume ratios compared to traditional materials.
Data Source
Figure 1
Figure 2
Figure 3A~3B
AI summary
Platforms (506; 606) for gas turbine engines (20) are described. The platforms include a flow structure (538; 638) having a gaspath surface (526; 626) and a non-gaspath surface (524; 624) with a front end (614), a rear end (618), a first edge (648), and a second edge (650). A platform connector (516a-c; 616a-c) extends from the flow structure. A first layer (540; 640) forms a part of the gaspath surface and is a non-continuous layer terminating at the ends and the edges. A second layer (542; 642) forms a part of the platform connector and is a non-continuous layer terminating at the ends and the edges. The second layer contacts the first layer proximate the first and second edges. A third layer (546; 646) defines an internal void (652) and is a continuous layer arranged between the first layer and the second layer and defines a part of the flow structure and a part of the platform connector.