Engine Cowling Support Link for Fan Blade Off Load Relief
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Current solutions to withstand fan blade off events in aircraft engines by reinforcing the nacelle increase weight and decrease aerodynamic efficiency.
Innovation Solution
A device with a support member and connectors, including a fusible link, secures the cowl to the engine, allowing the cowl to move radially outward during a fan blade off event, absorbing the force without detaching from the engine.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the nacelle is designed to be stronger and stiffer to withstand fan blade off events, then the nacelle can contain the fan blade and prevent damage to the aircraft, but the weight and size of the nacelle increase, decreasing overall efficiency and aerodynamic performance
Solution Approach 1:
The support member is divided into multiple links that can pivot relative to each other, creating a telescopic mechanism. This segmentation allows the support member to extend and absorb energy during FBO events without requiring the entire nacelle to be strengthened, thus maintaining light weight while achieving reliable containment.
Solution Approach 2:
The support member transitions from a static rigid structure to a dynamic telescopic mechanism with multiple pivotable links. This dynamic structure can adapt its configuration during FBO events, extending to absorb blade impact energy while maintaining structural integrity, thereby achieving reliability without excessive weight.
2Reliability
If the nacelle is designed to be stronger and stiffer to withstand fan blade off events, then the nacelle can contain the fan blade and prevent damage to the aircraft, but the aerodynamic efficiency of the aircraft decreases
Solution Approach 1:
By segmenting the support member into multiple links, the design achieves the necessary containment capability without requiring a uniformly stronger and stiffer nacelle structure. This localized solution preserves the overall aerodynamic shape and efficiency of the nacelle while providing the required safety function.
Solution Approach 2:
The telescopic mechanism is implemented only in the support member where it is needed for FBO containment, rather than strengthening the entire nacelle. This local quality approach maintains the aerodynamic efficiency of the nacelle's external surface while providing enhanced containment capability where required.
3Stability of the object's composition
If the cowl is rigidly connected to the engine, then the cowl remains stable during normal operation, but the cowl cannot move radially outward during a fan blade off event to absorb the force
Solution Approach 1:
The support member transforms from a rigid static connection to a dynamic telescopic mechanism with pivotable links. During normal operation, the mechanism remains compact and stable. During FBO events, it can extend dynamically to allow the cowl to move radially outward and absorb blade impact energy, thus achieving both stability and adaptability.
Solution Approach 2:
The telescopic support member acts as an intermediary between the engine and the cowl. It provides a stable connection during normal operation while enabling controlled movement during FBO events. The mechanism mediates between the conflicting requirements of rigidity for stability and flexibility for energy absorption.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
The solution effectively absorbs the force of a fan blade off event while maintaining the cowl's connection to the engine, preventing damage to the aircraft, without increasing weight or reducing aerodynamic efficiency.
Implementation Method 1
The second connector is weaker than the first connector and configured to fail in a fan blade off event to enable the cowl to remain connected to the support member at the first connector and to enable the cowl to move radially outward away from the engine
Data Source
AI summary
A device to secure a cowl to an engine of an aircraft. The device has a support member with an elongated shape with a first end section configured to be connected to the engine and an opposing second end section configured to be connected to the cowl. A first connector and a second connector are positioned at the second end section to connect the support member to the cowl. The second connector is weaker than the first connector and configured to fail in a fan blade off event to enable the cowl to remain connected to the support member at the first connector and to enable the cowl to move radially outward away from the engine and the first end section of the support member.