Lockable Cam Support Links for Gas Turbine Core Centering
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Solution Overview
Problem
Traditional gas turbine engine mounting systems suffer from distortion and tip clearance loss due to inertia and thrust loads, leading to inefficiencies in axial compressor operation.
Innovation Solution
A support-link system with lockable adjustment features is introduced, comprising rods connecting an annular outer and inner case, and a cam-type apparatus for centering the core portion within the bypass duct, allowing for adjustable and secure positioning to mitigate load-induced distortions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional engine mount systems are used, then the engine can be mounted to the fuselage, but the core portion suffers from distortion and tip clearance loss due to inertia and thrust loads
Solution Approach 1:
The support system is divided into multiple discrete support links (first support link, second support link, third support link) that can be independently adjusted and locked. Each support link connects the inner case to the outer case at different locations, segmenting the load path to distribute and counteract distortion forces more effectively than a monolithic mounting system.
Solution Approach 2:
The support links incorporate adjustable and lockable mechanisms that allow the engine core to be dynamically positioned and secured in multiple configurations. The lockable adjustment features enable the system to adapt to different operational conditions while maintaining structural integrity, allowing the core to be held in an optimized position that minimizes distortion under various load conditions.
2Reliability
If the core portion is supported at the rear mount, then the engine can be mounted, but significant bending of the core portion is caused by thrust loads
Solution Approach 1:
The support system uses multiple discrete support links distributed around the core portion rather than a single rear mount. This segmentation distributes the thrust loads across multiple connection points, preventing concentrated bending at a single location and reducing the overall bending moment on the core portion.
Solution Approach 2:
The support links are configured to provide counterbalancing forces that oppose the thrust loads. By strategically positioning the support links and using the lockable adjustment mechanisms, the system creates counter moments that counteract the bending caused by thrust, effectively balancing the forces acting on the core portion.
3Reliability
If cantilever core mounting is used, then the engine can be mounted to the bypass duct, but distortion due to inertia loads causes tip clearance loss
Solution Approach 1:
The support system divides the mounting structure into multiple independent support links that can be individually adjusted and locked. This segmentation allows for precise control over the position of each support link, enabling optimization of tip clearance at the axial compressor while maintaining the overall mounting structure.
Solution Approach 2:
The lockable adjustment features allow the support links to be positioned dynamically during assembly and then locked in place to maintain precise tip clearance. This dynamic positioning capability enables the system to accommodate manufacturing tolerances and achieve the optimal clearance configuration that minimizes distortion under inertia loads.
Data Source
AI summary
A cam-type apparatus is included in a support link between outer and inner cases of gas turbine engines for centering the cases one to another. The cam-type apparatus is lockable to allow locking an adjusted position of the cam-type apparatus.