Gas Turbine Combustor Liner Anti-Rotation and Removal Integration
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Solution Overview
Problem
Existing combustor liners in gas turbine engines face challenges with additional weight and increased installation time due to separate removal features like puller grooves and threaded inserts, which can loosen during engine operation, necessitating re-installation during overhauls.
Innovation Solution
Integration of anti-rotation features with threaded holes in combustor liners that serve as dual-purpose devices for preventing relative rotation and facilitating separation through a threaded tool, allowing for interference fit detachment without additional material or complex installation processes.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of repair
If a separate puller groove is added to the liner for removal, then the liner can be separated for maintenance, but the weight of the combustor increases due to additional material
Solution Approach 1:
The patent combines the anti-rotation feature and the removal feature into a single integrated structure. The anti-rotation tab includes a threaded hole that serves dual purposes: preventing rotation during operation and providing a mounting point for removal tools during maintenance. This eliminates the need for separate puller grooves or additional removal features, thereby reducing weight while maintaining ease of repair.
2Ease of repair
If a threaded insert is added to the liner for removal, then the liner can be separated for maintenance, but the installation time increases due to additional installation steps
Solution Approach 1:
The removal functionality is merged into the anti-rotation tab structure itself. The threaded hole is formed directly in the tab during the same manufacturing process, eliminating the need for separate insert installation steps. This reduces installation time while maintaining the ability to easily remove and reinstall the liner for maintenance.
Solution Approach 2:
The threaded hole is pre-formed in the anti-rotation tab during manufacturing, before the liner is assembled into the combustor. This preliminary preparation eliminates the need for time-consuming field installation of removal features, allowing maintenance personnel to simply attach removal tools to the pre-existing threaded holes when liner removal is needed.
3Ease of repair
If a threaded insert is added to the liner for removal, then the liner can be separated for maintenance, but the insert may loosen during engine operation requiring re-installation
Solution Approach 1:
The removal feature is integrated directly into the anti-rotation tab structure rather than being a separate insert. The threaded hole is formed as part of the tab itself, eliminating the interface between separate components that could lead to loosening. This integrated approach ensures reliable retention throughout engine operation while maintaining ease of repair capabilities.
Data Source
AI summary
A combustor liner for a gas turbine engine including first and second annular liner portions engaged to one another with an interference fit. The first liner portion includes at least one anti-rotation feature extending therefrom and engaging the second liner portion and having a threaded hole defined therethrough at least substantially perpendicularly to an adjacent radially extending surface of the second liner portion for threadingly receiving a pushing tool for pushing against that surface.