Multi-Layer Rotor Containment Structure for Blade Fragment Absorption
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Solution Overview
Problem
Existing containment structures in gas turbine engines are inadequate in effectively absorbing and containing blade fragments during rotor failure, necessitating improvements for enhanced safety and reliability.
Innovation Solution
A multi-layered containment structure formed by wrapping a sheet of metal multiple times around the axis to create a tubular configuration, which includes a housing and support structure, designed to absorb kinetic energy and prevent further radial movement of blade fragments.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If a traditional single-layer containment structure is used, then the device complexity is low, but the kinetic energy absorption capability is insufficient
Solution Approach 1:
The containment structure is divided into multiple discrete layers (typically 3-5 layers) of corrugated metal sheets, each layer capable of independently absorbing kinetic energy through deformation. This segmentation allows the structure to handle higher energy impacts while maintaining manageable complexity through standardized layer design and spacing.
Solution Approach 2:
The containment structure transitions from a single-layer two-dimensional barrier to a multi-layer three-dimensional configuration with controlled spacing between layers. This dimensional expansion creates a progressive deformation zone that increases the path length and energy absorption capacity while distributing the structural complexity across multiple simplified repeating elements.
2Speed
If the containment structure is positioned closer to the bladed rotor, then the response time to contain fragments is reduced, but the risk of thermal damage and interference with engine operation increases
Solution Approach 1:
The containment structure uses corrugated metal sheets with specific local geometric properties (wave depth, wavelength, thickness) that optimize the balance between rapid fragment containment and thermal resistance. The corrugation geometry provides high strength-to-weight ratio and thermal barrier properties, allowing the structure to be positioned optimally close to the rotor without suffering thermal damage.
Solution Approach 2:
The containment structure parameters (layer spacing, sheet thickness, corrugation geometry) are optimized to achieve the desired response speed while maintaining thermal integrity. By adjusting these parameters, the structure can be positioned at an optimal distance that provides rapid fragment containment without exposing the metal sheets to temperatures that would cause thermal damage.
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 multi-layered containment structure effectively decelerates and contains blade fragments, enhancing the safety and reliability of gas turbine engines by preventing further radial movement and potential damage.
Implementation Method 1
configured to absorb kinetic energy from and slow down/stop radial outward movement of any objects (e.g., blade fragments) liberated from the bladed rotor
Implementation Method 2
The containment structure is configured from or otherwise includes corrugated sheet metal
Data Source
AI summary
An apparatus is provided for a gas turbine engine. This apparatus includes a gas turbine engine case extending axially along and circumferentially around an axis. The gas turbine engine case includes a sheet of metal wrapped multiple times around the axis to form a containment structure having a multi-layered configuration. The containment structure is configured to contain at least one of a blade or a blade fragment from a bladed rotor of the gas turbine engine within the at least one of a plurality of sections.


