Aircraft Engine Linkage Mounting for Backbone Deflection
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Solution Overview
Problem
High-bypass turbofan engines experience significant backbone deflection due to aerodynamic and thrust loads during aircraft operation, which existing reinforcement methods fail to adequately address, particularly in flight regimes like take-off, leading to increased weight, cost, and potential blade tip rubs.
Innovation Solution
A mounting system utilizing a rigid structure and linkage mechanism with pivotally connected links that define a focal point located below the engine centerline and aft of the inlet load vector, opposing the moments of thrust and inlet loads to reduce backbone bending.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Stability of the object's composition
If existing reinforcement methods are used to reduce backbone deflection, then backbone stability is improved, but engine weight increases
Solution Approach 1:
The patent introduces a linkage mechanism with pivotally connected links as an intermediary system between the engine backbone and the aircraft structure. This mechanism mediates the load transmission, allowing the backbone to remain stable under aerodynamic and thrust loads without requiring additional reinforcement that would increase engine weight.
Solution Approach 2:
The patent changes the mounting configuration parameters by positioning the focal point of the linkage mechanism at a specific location (distance from centerline of not more than 15% of inlet diameter and aft of inlet load vector). This parameter optimization allows the system to reduce backbone deflection while maintaining acceptable weight levels.
2Stability of the object's composition
If existing reinforcement methods are used to reduce backbone deflection, then backbone stability is improved, but manufacturing cost increases
Solution Approach 1:
The linkage mechanism serves as an intermediary mounting system that achieves backbone stability through a different approach than direct reinforcement. By using pivotally connected links with a specific focal point configuration, the system reduces deflection without requiring costly reinforcement modifications to the engine structure itself.
3Device complexity
If traditional mounting configurations are used, then device simplicity is maintained, but backbone deflection increases leading to blade tip rubs
Solution Approach 1:
The patent introduces a linkage mechanism with pivotally connected links as an intermediary mounting system. This mechanism mediates between the simple traditional mounting approach and the need to prevent blade tip rubs, providing the necessary support to reduce backbone deflection while maintaining reasonable system complexity.
Solution Approach 2:
The patent optimizes the mounting configuration parameters by positioning the focal point at specific locations (not more than 15% of inlet diameter from centerline and aft of inlet load vector). This parameter change enables the system to prevent blade tip rubs caused by backbone deflection while keeping the mounting system relatively simple.
Data Source
AI summary
A mounting system and method capable of reducing backbone deflection in a high-bypass turbofan engine. The system includes a rigid structure and a linkage mechanism having at least first and second links that are each pivotally connected to the rigid structure and adapted to be pivotally connected to an engine support structure of the aircraft. The first and second links are configured to define a focal point thereof at a location that is a distance from a centerline of the engine of not more than 15% of an inlet diameter at an inlet of the engine, and is located aft of a vector of an inlet load to which the engine is subjected when the aircraft is in a climb maneuver. The location of the focal point is such that a moment of a thrust load of the engine and a moment of the inlet load oppose each other, thereby reducing backbone bending of the engine during the climb maneuver.