In Situ Gas Turbine Crack Arrest Using Cable-Delivered Repair Tips
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Solution Overview
Problem
Conventional repair methods for gas turbine engines require disassembly and removal from aircraft, leading to increased time and costs due to the need for external maintenance.
Innovation Solution
A system and method for in situ repair using a repair tool with a controllable tip and cable delivery system to insert through access ports, allowing for precision work such as drilling, cleaning, and filling defects within the engine without disassembly, utilizing tools like fiber optic laser drills, water jets, and liquid metal supply.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of repair
If conventional repair methods are used, then repairs can be performed on engine components, but the engine must be removed from the aircraft and disassembled, resulting in increased time and costs
Solution Approach 1:
A repair tool system acts as an intermediary device that can be inserted through access ports to reach internal engine components. The system includes a controllable tip that can be positioned and temporarily attached to the component surface, enabling repair operations without engine removal or disassembly.
Solution Approach 2:
The repair system is divided into separable components: a cable delivery system for inserting the tool, a controllable tip for performing repair operations, and an attachment mechanism for temporary positioning. This segmentation allows the repair tool to be introduced through small access ports while maintaining full repair capability.
2Ease of repair
If conventional repair methods are used, then repairs can be performed on engine components, but engine removal and disassembly are required, leading to increased maintenance costs
Solution Approach 1:
The repair tool system serves as an intermediary that enables full repair capability to be achieved through minimal access ports. The controllable tip can perform drilling, cleaning, and filling operations on internal components without requiring the engine to be disassembled or removed from the aircraft, thereby reducing maintenance costs.
3Loss of time
If a repair tool is inserted through access ports to perform in situ repair, then engine disassembly is avoided, but the tool must be precisely positioned and temporarily attached to the component surface
Solution Approach 1:
The attachment mechanism acts as an intermediary between the cable delivery system and the component surface. It enables temporary positioning and secure attachment of the controllable tip to the component, providing stability for precision operations while maintaining the ability to remove and reposition the tool as needed.
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
Enables efficient and cost-effective in situ repair of gas turbine engine components, reducing downtime and maintenance costs by allowing repairs to be performed internally, without the need for engine disassembly.
Implementation Method 1
utilizing tools like fiber optic laser drills
Implementation Method 2
utilizing tools like fiber optic laser drills, water jets
Data Source
AI summary
Methods provided for remotely stopping a crack in a component of a gas turbine engine are provided, along with methods of remotely cleaning a surface area of a component of a gas turbine engine. The method can include inserting an integrated repair interface attached to a cable delivery system within a gas turbine engine; positioning the tip adjacent to a defect within a surface of the component; temporarily attaching the tip adjacent to the defect within the surface on the component; and drilling a hole into the base of the defect. An integrated repair interface is also provided.