Alternating Composite Laminates for Propulsion Impact Containment
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Solution Overview
Problem
Existing containment structures for propulsion devices, such as gas turbine engines, face challenges in effectively absorbing high-energy projectile impacts, particularly from fan blade failures, due to variations in material properties and failure mechanisms that can lead to localized damage and rapid fiber failure.
Innovation Solution
A containment structure comprising alternating laminates of primary and secondary fiber reinforcement materials, where the primary laminates have higher elongation to failure and the secondary laminates have higher elastic modulus, arranged in a helicoidal ply structure, allowing for a balanced and symmetrical distribution of impact energy and delayed critical fiber failure.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If a single type of fiber reinforcement material is used in containment structures, then the structure is simpler to manufacture, but it cannot effectively absorb high-energy projectile impacts due to localized damage and rapid fiber failure
Solution Approach 1:
The containment structure is segmented into multiple laminates with different fiber reinforcement materials arranged in alternating sequences. Each laminate type (first, second, third) contains specific fiber materials with distinct properties, creating a segmented structure that distributes impact energy across different material zones rather than concentrating damage in a single material type.
Solution Approach 2:
The invention uses composite laminate structures combining multiple fiber reinforcement material types (e.g., aramid, carbon, glass fibers) within a matrix material. Each laminate type contains different fiber materials configured to provide complementary properties, creating a multi-material composite system that leverages the strengths of each fiber type to resist projectile impact.
2Use of energy by moving object
If laminates with higher elongation to failure are used, then the structure absorbs more impact energy, but the structural stiffness and resistance to deformation decreases
Solution Approach 1:
Different laminates are assigned different local qualities based on their position and function within the stack. Laminates with higher elongation materials are positioned to maximize energy absorption where impact forces are greatest, while laminates with stiffer materials are positioned to maintain structural integrity and stiffness in regions requiring dimensional stability. Each laminate type contains fiber materials selected for specific local performance requirements.
Solution Approach 2:
The invention varies material parameters (elongation to failure, elastic modulus, fiber type) across different laminate types in the stack. By changing the physical and mechanical parameters of each laminate type, the structure achieves a balance between energy absorption and stiffness, allowing each laminate to contribute differently to the overall impact resistance based on its specific parameter set.
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 alternating laminate structure enhances the structural integrity and energy absorption capabilities of the containment structure by promoting controlled failure mechanisms, reducing localized damage, and preventing fiber cutting, thereby improving the overall resilience to high-energy impacts.
Implementation Method 1
the first fibre reinforcement material has a higher elongation to failure than the second fibre reinforcement material
Implementation Method 2
the second fibre reinforcement material has a higher elastic modulus than the first fibre reinforcement material
Implementation Method 3
a plurality of laminates arranged in a stack for absorbing projectile impact from the propulsion device
Data Source
AI summary
A containment structure for a propulsion device, comprising a plurality of laminates arranged in a stack for absorbing projectile impact from the propulsion device, each laminate comprising a multi-ply composite of fibre reinforcement material and matrix material. The plurality of laminates comprises a plurality of primary laminates and a plurality of secondary laminates provided in an alternating arrangement along a stacking direction S of the containment structure. The primary laminates comprise a first fibre reinforcement material and the secondary laminates comprises a second fibre reinforcement material. The first fibre reinforcement material has a higher elongation to failure than the second fibre reinforcement material.