Gas Turbine Composite Platform with Honeycomb Core
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Solution Overview
Problem
Existing gas turbine engine fan platforms face challenges in efficiently supporting airfoils and maintaining aerodynamic surfaces due to limitations in material durability and weight reduction, particularly in composite materials used for fan spacers and platforms.
Innovation Solution
The use of a composite wrap with honeycomb cores and retention members co-molded with composite layers to form platform flanges, which are dimensioned to span between airfoils and include internal ribs for compartmentalization, providing structural support and reduced weight.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Weight of moving object
If composite materials are used for fan spacers and platforms, then weight is reduced, but material durability and structural integrity deteriorate
Solution Approach 1:
The platform utilizes composite materials consisting of multiple layers including a core layer and outer layers, creating a structure that combines the lightweight properties of the core with the durability and stress distribution capabilities of the outer composite layers, thereby resolving the contradiction between weight reduction and material durability
Solution Approach 2:
The platform is divided into multiple functional layers (core layer, outer layers) with distinct roles: the core provides weight reduction while the outer layers provide structural integrity and durability. This segmentation allows each layer to optimize for its specific function, resolving the contradiction between lightweight design and durability requirements
2Weight of moving object
If composite materials are used for fan spacers and platforms, then weight is reduced, but structural integrity and stress distribution deteriorate
Solution Approach 1:
The multi-layer composite structure distributes stresses across multiple layers, with the core layer providing lightweight support and the outer layers providing structural integrity. This composite approach maintains strength while reducing weight, resolving the contradiction between structural integrity and weight reduction
Solution Approach 2:
The platform merges multiple material properties into a single integrated structure where the core layer and outer layers work together to provide both lightweight characteristics and structural integrity, combining the benefits of different materials to resolve the contradiction
3Strength
If traditional fan platform designs are used, then structural support is provided, but aerodynamic performance and load deflection resistance deteriorate
Solution Approach 1:
The composite platform structure provides both structural support and aerodynamic surface stability through its multi-layer design, where the outer layers maintain the aerodynamic surface integrity while the core layer provides lightweight structural support, resolving the contradiction between structural support and aerodynamic performance
Solution Approach 2:
The platform applies different material properties to different regions: the outer layers are optimized for aerodynamic surface stability while the core layer is optimized for structural support. This local differentiation allows the structure to simultaneously provide both functions, resolving the contradiction
Data Source
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AI summary
A platform (70) for a gas turbine engine (20) according to an example of the present disclosure includes, among other things, a platform body (70A) that has a gas path surface extending axially between a leading edge (70LE) and a trailing edge (70TE) and extending circumferentially between opposed mate faces (70M). A plurality of platform flanges (70B) extend from the platform body (70A) to define one or more slots (70C). The one or more slots (70C) are dimensioned to receive a respective flange (62B) of a rotatable hub (62), and each platform flange (70B) has a retention member (73) dimensioned to receive a retention pin (71) to mount the platform body (70A). The platform body (70A) includes a composite wrap (70E) extending about a perimeter of the platform body (70A) to define an internal cavity (70F). At least one honeycomb core (74) has a plurality of cells (74A) that is disposed in the internal cavity (70F).