External Fan Blade Containment Shield
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Solution Overview
Problem
Aircraft with single jet engines do not require integrated fan blade containment systems, which are costly and weigh heavily, but these systems are necessary for safety in multi-engine aircraft, and retrofitting engines with integrated systems is expensive and time-consuming.
Innovation Solution
A fan blade containment system that is externally mounted to the aircraft structure, partially surrounding the engine circumference, using a shield with high-impact energy-absorbing materials and connectors to anchor to the aircraft structure, allowing for existing production engines to be used without retesting or recertification.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If an integrated fan blade containment system is installed in the engine, then fan blade fragment containment capability is improved, but device complexity and manufacturing cost increase
Solution Approach 1:
The containment system is divided into separate modular components: an energy absorbing structure (shield) and a fragment containment structure (cage), which can be independently designed, manufactured, and installed. This segmentation allows the system to be retrofitted to existing engines without complex integration, resolving the contradiction between containment capability and system complexity.
Solution Approach 2:
The energy absorbing structure serves as an intermediary component positioned between the engine and the fragment containment structure. This mediator absorbs impact energy from fan blade fragments, reducing the complexity requirements of the containment structure itself while maintaining overall containment effectiveness.
2Reliability
If an integrated fan blade containment system is installed in the engine, then fan blade fragment containment capability is improved, but manufacturing cost increases
Solution Approach 1:
By segmenting the containment system into separate energy absorbing and containment structures, each component can be manufactured using optimized processes for its specific function. The energy absorbing structure can use cost-effective materials and simple geometries, while the containment structure focuses only on fragment retention, reducing overall manufacturing cost compared to a fully integrated system.
Solution Approach 2:
The energy absorbing structure is designed as a sacrificial component that may be replaced rather than repaired after impact events. Using cost-effective materials and simple geometries for this disposable component reduces the overall system cost compared to making the entire containment system expensive and repairable.
3Reliability
If an integrated fan blade containment system is installed in the engine, then fan blade fragment containment capability is improved, but weight increases
Solution Approach 1:
Segmenting the containment system allows the energy absorbing structure to use lighter materials optimized for energy absorption rather than full structural strength. The fragment containment structure can be positioned to only contain fragments in critical areas, reducing overall weight compared to a fully integrated containment system.
Solution Approach 2:
The energy absorption function is extracted from the traditional integrated containment structure and placed in a separate shield. This allows the containment structure to be optimized purely for fragment retention with minimal weight, while the energy absorption function is handled by a dedicated component positioned outside the critical containment path.
4Reliability
If an integrated fan blade containment system is retrofitted to existing engines, then fan blade fragment containment capability is improved, but installation time and cost increase
Solution Approach 1:
The segmented design with separate energy absorbing and containment structures allows for modular installation. Components can be prepared independently and installed in a standardized sequence, reducing installation time compared to a fully integrated system that would require complex assembly and testing procedures.
Solution Approach 2:
The containment system is designed with universal mounting interfaces and standardized components that can be adapted to multiple engine types without custom fabrication. This multi-functionality enables rapid retrofitting across different engine models, significantly reducing installation time and cost.
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
Enables the selection of optimal production engines for multi-engine aircraft without the need for costly redesign or retesting, providing effective fan blade containment while minimizing weight and maintaining normal engine operation.
Implementation Method 1
an energy absorbing structure to be spaced from an outer surface of the aircraft engine when the means for capturing and absorbing is coupled to the aircraft structure
Data Source
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AI summary
The present invention relates to a gas turbine engine fan blade containment system including a shield (318) to be coupled to an aircraft structure (302) and to at least partially surround a circumference of an aircraft engine (100). The shield (318) is to be spaced from an outer surface (102) of the aircraft engine (100) when coupled to the aircraft structure (302). The shield (318) forms a laminated clevis (606) at an end (326) of the shield (318). A retention rod (608) is positioned in the laminated clevis (606) of the shield (318). The retention rod (608) is to engage a lug hook (602) of the aircraft structure (302) to anchor the shield (318) to the aircraft structure (302). The present containment system may be integrated with the airframe completely external to the engine, enabling aircraft manufacturers to select optimal engines independently of the presence of internal fan blade containment.