Blade Containment Assembly With Inner Ring Weld Joint Shielding
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Solution Overview
Problem
In gas turbine engines, reinforcing the engine case to contain blade fragments in a blade off event is challenging when space is limited, and moving weld joints away from the containment zone is not always feasible or desirable.
Innovation Solution
A blade containment assembly with a flange ring and integrated inner containment ring protects the weld joint within the containment zone, using a flange ring with a monolithic body and inner containment ring to shield the weld joint from blade impacts, allowing for a compact design and additional space for exhaust ducts.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If a weld joint is used to join casing members in a blade containment zone, then structural strength is improved, but distortion of the rotor blade airfoil shape occurs during welding
Solution Approach 1:
A distortion prevention device is introduced as an intermediary element between the weld joint and the rotor blade airfoil. This device includes a first portion positioned near the weld joint and a second portion extending toward the airfoil, with a resilient element that actively counteracts welding-induced thermal distortion, thereby maintaining the precise airfoil geometry while allowing the weld to provide structural strength
Solution Approach 2:
The distortion prevention device is installed prior to the welding operation to preemptively counteract the distortion that will occur during welding. The resilient element is pre-configured to apply compensating forces that offset the thermal expansion and distortion effects, ensuring the airfoil maintains its intended shape throughout the welding process
2Reliability
If the casing structure is strengthened to contain blade fragments, then safety is improved, but the complexity of the casing structure increases
Solution Approach 1:
The distortion prevention device is segmented into distinct functional portions: a first portion that interfaces with the weld joint area, a resilient element that provides the distortion-counteracting force, and a second portion that extends toward the airfoil. This segmentation allows each component to perform its specific function while keeping the overall structure manageable and maintainable
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 contains blade fragments while preserving the structural integrity of the engine case, providing a compact design and reducing the need for a separate containment ring, thus saving weight and space.
Implementation Method 1
a resilient element extending between a first location forward of the weld joint to a second location aft of the weld joint
Data Source
Figure 1
Figure 2
AI summary
A blade containment assembly for a gas turbine engine (10) comprises a casing (15) having a first casing member (15a) surrounding a set of rotor blades (14c) and a second casing member (15b) extending axially from the first casing member (15a). The first casing member (15a) has an outer annular wall (15a') welded to the second casing member (15b) at a weld joint (15c) disposed in a blade containment zone (22) of the casing (15) and an inner containment ring (15a'") spaced radially inwardly from the outer annular wall (15a') and extending axially from a first location forward of the weld joint (15c) to a second location aft of the weld joint (15c).