Pivoting Sensor Assembly for Gas Turbine Fairing Access
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Solution Overview
Problem
Accessing sensors within gas turbine engines for repair or replacement is costly and time-consuming due to the need for partial or full disassembly of engine modules, often requiring removal from an airplane wing.
Innovation Solution
An inspection assembly with an elongate member and pivotable sensor member that allows insertion through a static aerodynamic fairing, utilizing a combination of linear and pivotal movements to reach sensing position, enabling quick installation and removal without extensive disassembly, and featuring a locking mechanism for optimal sensing.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of repair
If sensors are accessed for repair or replacement by disassembling engine modules, then sensors can be reached and maintained, but maintenance time and operational costs increase significantly
Solution Approach 1:
The inspection assembly is divided into separable components: an elongate member for insertion through the fairing, and a sensor member that can be independently positioned and removed. This segmentation allows the sensor member to be accessed and replaced without disassembling the entire engine module, significantly reducing maintenance time while maintaining sensor accessibility.
2Ease of repair
If sensors are accessed by removing the gas turbine engine from the airplane wing, then complete access to sensors is achieved, but operational costs and maintenance time further increase
Solution Approach 1:
The sensor member is extracted from the engine core and made accessible through the fairing using the elongate member. This extraction allows sensors to be reached and maintained without removing the entire engine from the airplane wing, preserving operational efficiency while achieving the necessary accessibility for repair.
3Stability of the object's composition
If a rigid inspection assembly is used for sensor inspection, then structural stability is maintained, but the assembly cannot adapt to different sensing positions and engine configurations
Solution Approach 1:
The inspection assembly transitions from a rigid structure to a dynamic one by making the sensor member pivotable relative to the elongate member. This allows the sensor member to be positioned at different angles and orientations while maintaining structural stability during insertion and inspection, enabling adaptation to various sensing positions and engine configurations.
Data Source
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AI summary
An inspection system (50, 150) for a gas turbine engine (10) having an engine core (11), a casing (35), and a static aerodynamic fairing (40) includes an inspection assembly (100) including: an elongate member (102) extending along a longitudinal axis (60) from a first end (104) to a second end (106) and configured to be at least partially inserted through the static aerodynamic fairing (40) into a portion of the engine core (11) radially inboard of the static aerodynamic fairing (40); a coupler (108) disposed proximal to the first end (104) and configured to removably couple the elongate member (102) to the casing (11); and a sensor member (110) pivotally coupled to the elongate member (102) at the second end (106) and including a sensor (111). The sensor member (110) is pivotable between an insertion position (130) and a sensing position (135). The inspection system (50, 150) further includes: a guidance member (120) located within the engine core (11) and including a guidance surface (122); and a locking mechanism (124) operatively coupled to the sensor member (110).