Aerodynamic Flange for Thrust Reverser Bifurcation Wall Drag
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Solution Overview
Problem
The existing thrust reverser designs in propulsion systems suffer from aerodynamic drag due to the blunt, non-aerodynamic shape of the aft edge portions of the lower bifurcation walls, leading to inefficient thrust reversal and increased drag during operation.
Innovation Solution
The introduction of an aerodynamic feature, specifically a flange, is positioned at the aft end of the lower bifurcation walls to prevent aerodynamic drag, allowing for relative movement and adjustment to various operating conditions, thereby reducing drag and improving thrust efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If the aft edge portions of the lower bifurcation walls have a blunt, non-aerodynamic shape, then the structural simplicity and ease of manufacture are improved, but aerodynamic drag increases due to flow separation
Solution Approach 1:
The patent applies curvature by adding an aerodynamic feature (flange or fairing) to the aft edge portions of the lower bifurcation walls. This curved aerodynamic feature replaces the blunt, non-aerodynamic shape with a streamlined contour that reduces flow separation and minimizes aerodynamic drag, while maintaining ease of manufacture through modular addition rather than complete redesign.
2Device complexity
If the aft edge portions of the lower bifurcation walls have a blunt, non-aerodynamic shape, then the structural simplicity is improved, but thrust reversal efficiency deteriorates
Solution Approach 1:
The patent segments the lower bifurcation wall structure by separating the main structural portion from the aerodynamic feature. The aerodynamic feature is added as a distinct modular component (flange or fairing) that can be independently designed, manufactured, and installed. This segmentation allows the main structure to remain simple while the aerodynamic feature optimizes thrust reversal efficiency.
3Object-affected harmful factors
If an aerodynamic feature (flange) is added to the aft edge portions of the lower bifurcation walls, then aerodynamic drag is reduced, but device complexity increases
Solution Approach 1:
The patent applies local quality by adding the aerodynamic feature only at specific locations (aft edge portions of the lower bifurcation walls) where flow separation occurs, rather than redesigning the entire structure. This localized modification reduces aerodynamic drag at critical areas while maintaining the simplicity of the overall device structure.
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 aerodynamic feature effectively minimizes drag and enhances thrust reversal by smoothing the flow around the aft edge portions, improving the overall performance of the propulsion system without the need for costly redesigns.
Implementation Method 1
The respective aft edge portions of the lower bifurcation walls typically have a blunt, non-aerodynamic shape that can cause aerodynamic drag due to flow separation
Implementation Method 2
The respective aft edge portions of the lower bifurcation walls typically have a blunt, non-aerodynamic shape that can cause aerodynamic drag due to flow separation
Data Source
AI summary
A thrust reverser of a propulsion system nacelle is provided. The thrust reverser includes a fixed structure, a translating structure, and an aerodynamic feature. The fixed structure includes an annular wall that partially defines an annular bypass airstream duct. The fixed structure is bifurcated into left and right side sections. The annular wall extends between upper and lower bifurcation walls of the left side section, and extends between upper and lower bifurcation walls of the right side section. The translating structure is moveable relative to the fixed structure, between a stowed position and a deployed position. The aerodynamic feature that includes a flange disposed relative to an aft end portion of one of the lower bifurcation walls. The flange aids in preventing aerodynamic drag.