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

VSEngineering 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

Engineering Contradiction:
Improvekinetic energy absorption capabilityVSAvoidcontainment structure complexity
Core Design Contradiction:
StrengthVSDevice complexity

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.

Inventive Principle:
Principle #1Segmentation

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.

Inventive Principle:
Principle #17Another dimension (Dimensionality change)

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

Engineering Contradiction:
Improvefragment containment speedVSAvoidthermal damage risk
Core Design Contradiction:
SpeedVSObject-affected harmful factors

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.

Inventive Principle:
Principle #3Local quality

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.

Inventive Principle:
Principle #35Parameter changes

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

Methodology Applied
Scientific EffectKinetic energy absorption: Deformation

Implementation Method 2

The containment structure is configured from or otherwise includes corrugated sheet metal

Methodology Applied
Scientific EffectCorrugation: Corrugation

Data Source

PatentUS12631126B2Multi-layered containment structure for a bladed rotor of a gas turbine engine
Publication Date: 2026.05.19 PRATT & WHITNEY CANADA CORP
  • US12631126B2 patent drawing
  • US12631126B2 patent drawing
  • US12631126B2 patent drawing

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.