Aircraft Engine Thrust Link Damping Across LPT and HPT Resonance
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Solution Overview
Problem
Existing vibration damping devices for aircraft engines are unable to provide sufficient damping responses across the operating ranges of both the low-pressure turbine (LPT) and high-pressure turbine (HPT), leading to potential damage from resonant vibrations.
Innovation Solution
The implementation of thrust links with variable internal and external geometry, including bumpers, damping inserts, and external dampers, to create resonant vibration frequency responses that cover the entire operating range of the aircraft engine, using materials like metal, composite, elastomer, and fluorocarbon to manage vibrations from both turbines.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If existing vibration damping devices are used, then the device structure is simple, but the damping response is insufficient across the operating ranges of both LPT and HPT
Solution Approach 1:
The patent combines multiple damping mechanisms (bumpers, damping inserts, external dampers) into a unified vibration control system that addresses both LPT and HPT operating ranges simultaneously, rather than using separate devices for each turbine type
Solution Approach 2:
The thrust link structure is designed to perform multiple functions: structural support, vibration damping, and frequency response control across different turbine operating conditions, eliminating the need for separate specialized devices
2Reliability
If thrust links with variable geometry and multiple damping components are implemented, then damping response coverage is improved, but the device complexity increases
Solution Approach 1:
The vibration damping function is divided into distinct components (bumpers for impact damping, damping inserts for internal friction, external dampers for viscous damping), each targeting specific frequency ranges and vibration modes
Solution Approach 2:
The thrust link incorporates variable internal and external geometry that can adapt to different operating conditions, allowing the structural characteristics to change with engine operation to maintain optimal damping across the full operating range
3Reliability
If resonant vibration frequency responses are created to cover the entire operating range, then vibration damping effectiveness is improved, but the manufacturing complexity increases
Solution Approach 1:
The patent varies geometric parameters (internal diameter, external diameter, length proportions) and material properties to tune the resonant frequencies and damping characteristics, allowing customization for different engine configurations while following the same basic design approach
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 proposed solutions effectively dampen vibrations across the operating ranges of both LPT and HPT, preventing damage to the engine and its components by ensuring frequency responses are outside the damaging ranges.
Implementation Method 1
a piston rod, a chamber, and a fluid region wherein the piston rod is coupled to the thrust link at the aft end, the chamber is coupled to the engine carcass, and the fluid region includes a viscous damping fluid
Data Source
AI summary
Viscous damper apparatus and associated methods to control a response to a resonant vibration frequency are disclosed. An apparatus to support an aircraft engine includes a first thrust link including a forward end and an aft end, the forward end of the first thrust link coupled to the aircraft engine, a second thrust link including a forward end and an aft end, the forward end of the second thrust link coupled to the aircraft engine, and a damper coupled to the aft end of the first thrust link and to the aft end of the second thrust link.