Boomerang Link Vibration Filtering Aircraft Engine Mount
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Solution Overview
Problem
Aircraft engine mounts connected to pylons via boomerang links transmit vibrations from jet engines to the aircraft fuselage, causing structural wear and passenger discomfort, especially in propulsion systems attached to the fuselage.
Innovation Solution
A boomerang link with a novel shape, featuring offset orifices and specific geometrical properties that provide elasticity to filter transverse forces and vibrations, combined with a mechanical energy dissipating device and optional rigid boomerang links to manage extreme loads.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If a conventional boomerang link is used to connect the jet engine to the pylon, then the structural strength and load transmission capability are sufficient, but vibrations from the jet engine are transmitted to the pylon and fuselage, causing structural wear and passenger discomfort
Solution Approach 1:
The patent changes the geometric parameters of the boomerang link by introducing a specific curvature in its configuration. This curvature modifies the link's mechanical properties to provide vibration filtering capability while maintaining its load transmission function. The curved geometry allows the link to absorb and dissipate vibrational energy through elastic deformation.
Solution Approach 2:
The curved boomerang link acts as an intermediary element between the jet engine and the pylon. Its specific curvature provides a compliant connection that filters vibrations before they reach the pylon and fuselage, while still transmitting the necessary thrust loads. The link serves as a mediator that decouples the rigid connection while maintaining structural integrity.
2Object-affected harmful factors
If the boomerang link is made more flexible to filter vibrations, then vibration filtering improves, but the link's ability to transmit thrust forces and withstand extreme loads may be compromised
Solution Approach 1:
The patent optimizes the geometric parameters of the boomerang link, specifically the curvature radius and configuration, to achieve the right balance between flexibility and strength. The curvature is designed to provide sufficient elastic deformation for vibration filtering while maintaining the structural integrity needed to withstand extreme loads during malfunction conditions.
Solution Approach 2:
The curved boomerang link exhibits dynamic behavior that adapts to different loading conditions. During normal operation, the link flexes to filter vibrations. During extreme events like blade loss, the link's geometry allows it to withstand high loads while still providing some vibration filtering. The dynamic response of the curved structure allows it to perform differently under various conditions.
3Force
If a rigid connection is used between the engine and pylon, then load transmission is efficient, but vibrations are directly transmitted to the fuselage structure
Solution Approach 1:
The patent modifies the geometric parameters of the boomerang link by introducing a specific curvature that provides compliant characteristics. This curved geometry allows the link to deform elastically under vibration loads, filtering out high-frequency vibrations while still transmitting the primary thrust forces efficiently through its structural design.
Solution Approach 2:
The curved boomerang link serves as an intermediary element that decouples the rigid connection between the engine and pylon. Its specific curvature provides a compliant interface that absorbs and dissipates vibrational energy, preventing direct transmission to the fuselage while maintaining efficient force transmission through its optimized geometry.
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 boomerang link effectively filters vibrations and transverse forces, reducing structural wear and improving passenger comfort by absorbing and dissipating energy, while maintaining flexibility during normal operations and extreme conditions like blade loss.
Implementation Method 1
said boomerang link being conformed so that, when it is seen in section in any plane orthogonal to the axes, a second straight line segment extending from the axis of said second orifice to the axis of said third orifice crosses said region external to the boomerang link
Implementation Method 2
The boomerang link effectively filters vibrations and transverse forces, reducing structural wear and improving passenger comfort by absorbing and dissipating energy
Data Source
AI summary
A boomerang link for aircraft engine mounts, including a first orifice and a second orifice both designed to connect the boomerang link to an aircraft pylon, and a third orifice designed to connect the boomerang link to an aircraft engine. The third orifice is offset relative to a plane passing simultaneously through an axis of the first orifice and through an axis of the second orifice. When the boomerang link is seen in section in any plane orthogonal to the axes, a straight line segment extending from the axis of the second orifice to an axis of the third orifice crosses a region external to the boomerang link. This conformation confers on the boomerang link a flexibility enabling it to filter transverse vibrations between an engine and an aircraft pylon.