Fluid-Filled Thrust Link Structure for Engine Resonance Damping
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Solution Overview
Problem
Existing vibration damping devices for aircraft engines are unable to provide a damping response that covers the entire operating range of both the low-pressure turbine (LPT) and the high-pressure turbine (HPT), leading to potential damage from resonant vibrations.
Innovation Solution
The development of fluid-filled thrust link systems with variable internal and external geometry, including the use of dampers and bumpers, to create resonant vibration frequency responses that cover the operating range of aircraft engines, regardless of the thrust link's size or footprint.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If existing vibration damping devices are used, then the structure is simple, but the damping response cannot cover the entire operating range of both LPT and HPT
Solution Approach 1:
The thrust link incorporates variable internal geometry with adjustable damping inserts that can be positioned at different locations along the thrust link span. This dynamic configuration allows the damping characteristics to be adjusted to match different operating conditions (LPT and HPT ranges), enabling comprehensive vibration damping coverage while maintaining a relatively simple overall structure.
Solution Approach 2:
The patent applies different damping characteristics at different locations along the thrust link by positioning damping inserts selectively. The internal geometry varies locally to provide optimized damping for specific frequency ranges, allowing the same thrust link structure to handle both low-pressure and high-pressure turbine operating conditions through localized geometric variations.
2Reliability
If variable internal geometry with damping inserts is implemented, then comprehensive vibration damping is achieved, but manufacturing complexity increases
Solution Approach 1:
The damping inserts are nested within the hollow internal geometry of the thrust link, allowing them to be positioned inside the existing structural framework. This nesting approach enables the addition of complex damping functionality without significantly increasing external dimensions or requiring complete structural redesign, thereby improving vibration protection while managing manufacturing complexity.
3Adaptability or versatility
If multi-directional dampers are added, then vibration damping coverage is enhanced, but device complexity increases
Solution Approach 1:
The thrust link is designed with multi-directional damping capability integrated into its structure, allowing a single component to provide vibration damping in multiple directions and for multiple operating ranges. This multi-functional design eliminates the need for separate damping devices for different directions, enhancing adaptability while controlling overall system complexity.
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
These systems effectively dissipate resonant vibrations across the entire operating range of aircraft engines, reducing the risk of damage and enhancing the structural integrity and performance of the engines.
Implementation Method 1
fluid-filled thrust link systems with variable internal and external geometry, including damping inserts and multi-directional dampers
Data Source
AI summary
Fluid-filled thrust link apparatus and associated method are disclosed. A thrust link for an aircraft engine includes a first wall having a forward portion and an aft portion at opposite ends of the thrust link, the forward portion coupled to the aircraft engine, the aft portion coupled to the aircraft engine, a pylon, or an aircraft associated with the aircraft engine, and a second wall within an interior area surrounded by the first wall, the second wall spaced apart from the first wall, a space between the first wall and the second wall defining a channel within the interior area, the channel including a fluid, the fluid pressurized based on a damping ratio to withstand a resonant vibration frequency generated by the aircraft engine.