Curved Engine Pylon Trailing Edge for Lift Compensation
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Solution Overview
Problem
The presence of engine pylons and turbo engines on aircraft wings causes significant aerodynamic disturbances, leading to a sharp drop in lift on the root side and an increase on the distal end side, resulting in vortex layers and increased induced drag.
Innovation Solution
The engine pylon is designed with curved lower rear parts that deflect the cold stream towards the root, shifting the trailing edge towards the root, which increases pressure on the root side and decreases pressure on the distal end side, compensating for lift variations and reducing induced drag.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If a conventional engine pylon with straight trailing edge is used, then the engine can be suspended from the wing, but the lift distribution is disturbed with sharp drop on root side and increase on distal end side
Solution Approach 1:
The trailing edge of the engine pylon is curved such that it is shifted toward the root of the wing relative to the vertical mid-plane of the engine. This curvature modifies the aerodynamic stream flow around the pylon, redirecting the cold stream to reduce vortex formation and correct the lift distribution disturbance caused by the pylon's presence.
2Loss of energy
If a conventional engine pylon is used, then the engine mounting is simple, but induced drag increases due to vortex layers shed by the wing trailing edge
Solution Approach 1:
The curved trailing edge geometry of the pylon modifies the wake structure and reduces the intensity of vortex layers shed from the wing trailing edge. This curvature design directly addresses the energy loss from induced drag while maintaining structural integrity and functional simplicity.
3Strength
If the pylon trailing edge is curved toward the root, then lift compensation is achieved, but the pylon structure becomes more complex
Solution Approach 1:
The pylon trailing edge exhibits asymmetric curvature relative to the engine's vertical mid-plane, being shifted toward the root side. This asymmetric geometry creates differential pressure distribution across the pylon, generating lift compensation effects that counteract the adverse aerodynamic disturbances without requiring complex active control systems.
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 design enhances lift distribution, reducing induced drag and allowing for increased payload by several tens or hundreds of kilograms for the same fuel consumption.
Implementation Method 1
at least said lower part of the rear of the engine pylon is curved toward the root of said wing so that at least the trailing edge of said lower part is shifted toward said root with respect to said vertical mid-plane. Thus it is possible to deflect the aerodynamic stream of the cold stream from the turbo engine sweeping at least over the lower part of the rear of the engine pylon.
Implementation Method 2
This deflection generates, on the one hand, an increase in pressure on the side of the lateral face directed toward the root, making it possible to increase the local lift and thus compensate for the sharp drop in lift caused by the presence of the engine pylon and, on the other hand, a reduced pressure of the side of the lateral face directed toward the distal end
Data Source
AI summary
According to the invention, the engine pylon for the suspension of a turbo engine under an aircraft wing is such that the trailing edge of the rear lower part of the engine pylon is shifted toward the root of the wing.