Push-lock pin connector for gas turbine insulation tiles
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Solution Overview
Problem
Current fastener designs for aircraft engine insulation tiles require removal of the engine to access and replace tiles, significantly increasing costs due to the need for engine disassembly.
Innovation Solution
A push-lock pin system with a housing, shaft assembly, and locking mechanism that allows for secure attachment and detachment of insulation tiles to a gas turbine engine wall without requiring access to the backside of the engine substructure, enabling tile replacement without engine removal.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If current fastener designs are used to attach insulation tiles to the engine substructure, then the tiles can be securely attached, but the engine must be removed from the aircraft to access the backside of the substructure for tile installation or replacement
Solution Approach 1:
The fastener design inverts the traditional approach by providing access to the locking mechanism from the front side of the engine substructure rather than requiring access from the backside. The release button and actuating mechanism are positioned on the outer surface, allowing technicians to install and replace tiles without removing the engine from the aircraft.
Solution Approach 2:
The push-lock pin acts as an intermediary mechanism between the tile and the substructure. It includes a shaft assembly with a locking mechanism that can be actuated from the front side through a release button, mediating the connection and release functions without requiring direct access to the backside of the substructure.
2Ease of repair
If the engine is removed from the aircraft to facilitate replacing or repairing an insulation tile, then the tile can be accessed and replaced, but the cost increases significantly beyond the actual costs of replacing the tile itself
Solution Approach 1:
The fastener design incorporates a preliminary action mechanism where the release button is pre-positioned on the front side of the substructure. This allows the locking mechanism to be actuated in advance without requiring engine removal, enabling quick tile replacement during routine maintenance while the engine remains installed in the aircraft.
Solution Approach 2:
The fastener system segments the tile replacement operation into independent steps that can be performed without engine removal. The release button, shaft assembly, and locking mechanism are designed as separate components that can be actuated independently from the front side, allowing tile replacement to be performed as a standalone maintenance task.
3Strength
If a locking mechanism is used to secure the tile to the engine wall, then the tile is firmly attached, but the mechanism must be accessible from the backside of the substructure
Solution Approach 1:
The locking mechanism is designed to operate in a different dimensional space by positioning the actuating elements on the front side of the substructure. The release button and shaft assembly are arranged so that the locking and release actions occur in a dimension accessible from the outer surface, eliminating the need for backside access while maintaining secure attachment.
Solution Approach 2:
The release button is nested within or positioned on the front surface of the substructure, with the shaft assembly and locking mechanism nested within the fastener housing. This nested arrangement allows the locking mechanism to be actuated from the front side while maintaining secure attachment strength, as the internal components are contained within the fastener structure.
Data Source
AI summary
A push-lock pin for connecting a tile to a gas turbine engine wall according to an exemplary aspect of the present disclosure includes, among other things, a housing extending longitudinally along an axis; a shaft assembly within the housing, the shaft assembly including a push-down pop-up mechanism and a locking mechanism, the locking mechanism moveable to a locked position such that the locking mechanism limits movement of a tile away from a gas turbine engine wall; and a stop feature to limit movement of the tile toward the gas turbine engine wall.