Thrust Reverser Link Rod Elastic Mounting for Nacelle Thickness Reduction
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Solution Overview
Problem
The existing springs used in thrust reverser systems for turbojet engines are too bulky and radially thick, hindering the reduction of nacelle thickness and requiring additional space for connecting rod displacement, which is incompatible with modern design constraints aimed at optimizing weight and aerodynamics.
Innovation Solution
The use of elastic means, such as U-shaped springs or torsion springs, integrated into a recessed zone of the fixed internal structure, which minimizes the size of the connecting rod's interaction with the flap, allowing for a reduction in radial thickness by eliminating the need for additional elastic connection means and providing resistance to tearing forces.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional helical, leaf, or U-shaped springs are used to connect connecting rods to flaps, then tolerance compensation and structural deformation compensation are achieved, but radial thickness of the thrust reverser device increases
Solution Approach 1:
The patent relocates the spring from a radial arrangement (between connecting rod and flap) to an axial arrangement (between connecting rod and fixed internal structure). This dimensional change allows the spring to function along the axial direction rather than radially, thereby compensating for tolerances and deformations without increasing radial thickness of the thrust reverser device.
Solution Approach 2:
The patent extracts the elastic function from the traditional spring connection between connecting rod and flap, and relocates it to a new configuration where the spring connects the connecting rod to the fixed internal structure. This extraction allows the spring to be positioned in a recessed zone, removing its radial thickness contribution from the deflection grid area.
2Ease of operation
If traditional springs are used between connecting rods and flaps, then elastic connection is provided, but additional space for connecting rod displacement is required which is incompatible with reduction constraints
Solution Approach 1:
The patent changes the arrangement dimension of the elastic connection from radial to axial. The spring now operates in the axial direction between the connecting rod and fixed internal structure, allowing the connecting rod's displacement to occur without requiring additional radial space in the deflection grid area.
Solution Approach 2:
The patent nests the spring within a recessed zone of the fixed internal structure. This nesting arrangement allows the spring to be contained within the existing structural volume, eliminating the need for additional external space for the connecting rod's elastic connection and displacement movements.
3Loss of energy
If radial thickness of thrust reverser device is reduced for weight and aerodynamic optimization, then aerodynamic efficiency improves, but space for traditional spring arrangement and connecting rod displacement becomes insufficient
Solution Approach 1:
The patent resolves the space conflict by reorienting the spring arrangement from radial to axial dimension. This allows the thrust reverser device to maintain reduced radial thickness for aerodynamic optimization while the spring and connecting rod displacement occur in the axial direction within the recessed zone, avoiding interference with aerodynamic requirements.
Solution Approach 2:
The patent applies local quality by creating a specialized recessed zone in the fixed internal structure specifically for housing the spring and accommodating connecting rod displacement. This localized arrangement concentrates the elastic connection functionality in a specific region, allowing the rest of the deflection grid area to maintain minimal radial thickness for optimal aerodynamics.
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
This configuration reduces the radial thickness of the thrust reverser device, enhances aerodynamic efficiency, and maintains structural integrity by retaining the connecting rod in place even in the event of spring failure, while optimizing the nacelle's design for reduced weight and improved aerodynamics.
Implementation Method 1
elastic means comprising a spring suitable for connecting this connecting rod to this fixed internal structure
Implementation Method 2
the spring has better resistance to tearing forces exerted by the connecting rod
Implementation Method 3
said elastic means comprise a deformation limiting stop in inversion mode
Data Source
Figure 1~2
Figure 3~4
Figure 5~6
AI summary
In this arrangement of at least one thrust reverser flap (13) link rod (15) on the internal fixed structure of a turbo jet engine nacelle, said link rod (15) is connected to the internal fixed structure by elastic means (17).