Aircraft Engine Connecting Rods in Air Inlet
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Solution Overview
Problem
The existing configuration of connecting rods in aircraft propulsion assemblies interferes with the secondary air flow, adversely affecting aerodynamic performance and increasing energy consumption due to the significant volume of the bifurcation fairing.
Innovation Solution
The connecting rods are positioned at least partially within the air inlet of the engine, with offset anchoring points to avoid interference with the secondary flow, and are arranged to form an angle less than 25° with the engine's rotation axis, allowing them to be symmetrical and positioned in a horizontal plane, reducing the volume of the bifurcation and eliminating the need for an aft pylon fairing.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If connecting rods are positioned outside the air inlet, then they do not interfere with the secondary flow, but the bifurcation fairing volume increases significantly, adversely affecting aerodynamic performance
Solution Approach 1:
The connecting rods are repositioned from an external location to the inner zone of the air inlet, utilizing the three-dimensional space within the air inlet structure. This dimensional relocation allows the rods to be positioned where they do not interfere with the secondary flow path, while the fairing volume is minimized because the rods are contained within the existing air inlet boundaries rather than requiring external fairing extension.
2Volume of stationary object
If connecting rods are positioned in the air inlet, then the bifurcation fairing volume is reduced, but the rods may interfere with the secondary air flow
Solution Approach 1:
The anchoring points of the connecting rods are specifically positioned within the inner zone of the air inlet, a localized region that does not interfere with the secondary flow path. This local quality differentiation allows the rods to occupy space in the air inlet without disrupting the aerodynamic flow, as the inner zone is distinct from the secondary flow region.
3Weight of moving object
If traditional pylon configuration is used, then engine mounting is simplified, but weight and energy consumption increase
Solution Approach 1:
The traditional pylon structure is extracted and replaced with a crossmember configuration. The crossmember is a lighter structural element that can be integrated into the fuselage framework, eliminating the need for a separate pylon assembly. This extraction of the pylon function and its replacement with a simpler crossmember structure reduces overall weight while maintaining the necessary engine mounting capability.
Data Source
AI summary
An aircraft which comprises a fuselage and at least one propulsion assembly linked to the fuselage by at least two connecting rods positioned at least partially in an inner zone of the air inlet of the nacelle of the propulsion assembly. Thus, the connecting rods do not interfere with the secondary flow flowing inside the nacelle and do not affect the aerodynamic performance levels of the propulsion assembly.