Turbine Engine Pylon Vibration Control via Vortex Generation
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Solution Overview
Problem
The rear fairing of a bypass turbine engine suspension mast experiences damaging vibrations when deployed, due to interaction with high-speed cold flow, which is difficult to predict with current design tools and results in structural damage, leading to weight increase or costly aerodynamic redesigns.
Innovation Solution
Mounting aerodynamic elements, such as elongated fins with beveled leading edges, on the rear fairing to generate vortices that reduce or eliminate vibrations by interacting with the flow boundary layer, preferably two fins placed laterally to confine instationary phenomena to the upper portion.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the structure of the rear fairing is reinforced to withstand vibrations, then the reliability of the rear fairing is improved, but the weight of the aircraft increases
Solution Approach 1:
The invention uses the high-speed cold flow, which causes harmful vibrations, to generate beneficial vortices through aerodynamic elements. These vortices create a stabilizing effect on the boundary layer, converting the harmful vibrational energy into a useful flow control mechanism that protects the rear fairing without additional structural weight.
Solution Approach 2:
Aerodynamic elements (such as fins or vortex generators) are introduced as intermediary components between the cold flow and the rear fairing. These elements mediate the interaction by generating vortices that modify the flow characteristics, thereby protecting the fairing from direct vibrational damage without requiring structural reinforcement.
2Reliability
If the aerodynamic shape of the rear fairing is reddefined to reduce vibrations, then the reliability of the rear fairing is improved, but the manufacturing cost increases and drag may increase
Solution Approach 1:
The solution segments the problem by adding separate, modular aerodynamic elements to the existing rear fairing structure, rather than redesigning the entire fairing. This allows the original fairing design to be retained while adding vibration-mitigating features as distinct components.
Solution Approach 2:
Instead of changing the overall aerodynamic shape of the rear fairing, the invention applies localized aerodynamic elements at specific positions where vortex generation is most effective. This preserves the global aerodynamic optimization while addressing local vibration issues.
3Reliability
If the aerodynamic shape of the rear fairing is reddefined to reduce vibrations, then the reliability of the rear fairing is improved, but the drag increases leading to increased fuel consumption
Solution Approach 1:
The invention applies localized aerodynamic elements rather than changing the overall fairing shape, preserving the aerodynamically optimized contours that minimize drag while adding vibration control functionality at specific locations.
Solution Approach 2:
The aerodynamic elements are designed to be most effective specifically when the rear fairing is in the deployed position and exposed to cold flow. When retracted, these elements minimize their impact on overall aerodynamics, providing conditional vibration protection without permanent drag penalty.
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 high-energy vortices generated by these aerodynamic elements effectively reduce or eliminate vibrations, preventing damage to the rear fairing without increasing aircraft weight or drag, allowing for earlier identification and resolution of vibration issues during development.
Implementation Method 1
said rear fairing supports at least one aerodynamic element that generates vortices that reduce, if not eliminate, said vibrations
Implementation Method 2
the vortices, which are generated by said aerodynamic element and are very high-energy because of the high speed of the cold flow, act on the limit layer of said rear fairing
Data Source
AI summary
Disclosed is a mast for the suspension of a bypass turbine engine beneath a wing of an aircraft in which the wing has at least one flap. The mast includes a rear fairing that protrudes rearward of a trailing edge of the wing and is mounted so as to tilt in a deployed downward position as the flap is deployed in a downward position. The rear fairing is positioned to enter a cold flow of the turbine engine, when deployed in the downward position. The rear fairing further supports at least one aerodynamic element that generates vortices that reduce, if not eliminates, vibrations to which the rear fairing is subjected.