Hybrid Composite Blade Metalwork Repair With Localized Patch Bonding
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Solution Overview
Problem
Conventional methods for repairing composite blades, particularly those with metallic edges, often require the replacement of the entire metallic material due to localized damage, which is economically and time-wise inefficient, and involves complex debonding processes.
Innovation Solution
A method for repairing composite blades involves determining and isolating locally damaged metal work portions, detaching and debonding specific wing portions, reconditioning surfaces, and applying adhesive layers to bond a metal work patch, allowing for localized repair without replacing the entire metal work, thus reducing material and time costs.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the entire metallic material is replaced due to localized damage, then the blade can be restored to full strength, but material cost and time consumption increase significantly
Solution Approach 1:
The metallic material is divided into damaged and undamaged segments. Only the damaged portion is removed and replaced, while the undamaged portions are retained. This segmentation allows selective repair rather than complete replacement, reducing material waste and cost.
Solution Approach 2:
The repair process applies local quality by treating only the damaged area with a patch, while the rest of the metallic material maintains its original properties. This localized approach preserves the valuable undamaged material and reduces overall material consumption.
2Reliability
If the entire metallic material is replaced, then structural integrity is ensured, but repair time and complexity increase
Solution Approach 1:
The repair process is segmented into focused steps: remove only damaged material, prepare the localized area, apply a patch, and bond. This segmented approach eliminates time-consuming steps associated with complete removal and replacement of the entire metallic material.
Solution Approach 2:
Instead of performing the complete action of removing and replacing the entire metallic material, only the partial action necessary to address the localized damage is performed. This partial action significantly reduces repair time while maintaining structural integrity.
3Ease of manufacture
If sophisticated tools and complex debonding processes are used for replacement, then complete removal is achieved, but device complexity and cost increase
Solution Approach 1:
The complex debonding process and sophisticated tools are extracted from the repair procedure. Instead of using complex chemical or mechanical debonding methods, the repair uses simple adhesive bonding to attach the patch, eliminating the need for sophisticated removal tools and processes.
Solution Approach 2:
The bonding method parameter is changed from complex debonding processes to simple adhesive bonding. This parameter change simplifies the tool requirements and reduces device complexity while maintaining repair effectiveness.
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
This method enables localized repair of composite blades, saving material and time by salvaging undamaged components, eliminating the need for sophisticated tools and complex debonding processes, and reducing repair costs.
Implementation Method 1
an adhesive layer bonding the metal work to the composite part
Data Source
Figure 1A~1B
Figure 2
Figure 3
AI summary
A method (200) of repairing a composite blade (100). The composite blade includes a metal work (106) bonded to a composite part (104) through an adhesive layer (118). The method includes determining a locally damaged portion (302) of the metal work, and removing a bullet portion (402) corresponding to the locally damaged portion. The method further includes detaching, debonding, and removing a first wing portion (502) from the composite part to obtain a first exposed surface portion (602). The method further includes detaching, debonding, and removing a second wing portion (506) from the composite part to obtain a second exposed surface portion (604). The method further includes reconditioning the first and second exposed surface portions to obtain first and second reconditioned surface portions, respectively, and applying first and second adhesive layers (902, 904) to the first and second reconditioned surface portions respectively. The method further includes bonding a metal work patch (906) to the first and second adhesive layers.