Aircraft Engine Pylon Arch Box Extension for Mass Reduction
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Solution Overview
Problem
Existing aircraft engine mounting systems are bulky, heavy, and generate aerodynamic disturbances due to the presence of pylon attachment means, which are inefficient in load transmission and require additional thrust-load reacting link rods.
Innovation Solution
The engine assembly features a turbofan turbine engine with a reduction gear-driven fan, a mounting pylon with a central box extension comprising one-piece arch components that allow improved load transmission, eliminating the need for lateral thrust-load reacting link rods, and attaching the reducing-gear case directly to these components for reduced bulk and mass, with attachments reacting loads close to the engine's center of gravity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If traditional attachment means with lateral thrust-load reacting link rods are used, then the engine assembly has sufficient load transmission capability, but the bulk and mass of the engine assembly increase
Solution Approach 1:
The patent combines the functions of the central box and the arch-shaped components into an integrated structure. The first and second arch-shaped components are directly connected to the central box, eliminating the need for separate lateral thrust-load reacting link rods. This merging of structures reduces the overall mass while maintaining load transmission capability, as the arch-shaped components themselves serve to react thrust loads laterally.
2Strength
If complex attachment devices are used to mount engines to the wing structure, then the engine assembly has adequate structural support, but the aerodynamic disturbances increase
Solution Approach 1:
The patent employs arch-shaped components that can be covered with aerodynamic fairings or shells. These smooth external surfaces reduce aerodynamic disturbances while the internal arch structure maintains the necessary structural support. The arch-shaped design allows for streamlined coverage that minimizes airflow disruption compared to traditional link rod arrangements.
3Power
If reduction gearing is added to drive the fan, then the turbofan engine achieves improved performance, but the bulk and mass of the engine assembly increase
Solution Approach 1:
The patent nests the reduction gear assembly within the engine structure, with the reducing-gear case positioned centrally and surrounded by the arch-shaped components. This nested arrangement allows the reduction gearing to be integrated into the existing engine architecture rather than adding external bulk. The compact integration of the reduction gear with the fan and turbine sections minimizes the overall increase in engine assembly mass while maintaining the performance benefits of geared turbofan technology.
4Strength
If the box extension with arch components is used, then the load transmission is improved and mass is reduced, but the device complexity increases
Solution Approach 1:
The patent segments the load transmission function into distinct components: the central box handles primary load bearing, while the first and second arch-shaped components specifically handle lateral thrust loads. This segmentation allows each component to be optimized for its specific function and simplifies the overall design by clearly defining the role of each element. The modular nature of the arch components, which can be produced as single pieces, actually reduces manufacturing complexity compared to traditional multi-part link rod assemblies.
Data Source
AI summary
An engine assembly for an aircraft rigid structure comprising a mounting pylon comprising a central box and a box extension connected to a reducing gear case of the turboreactor. The box extension includes two parts bearing the front engine attachments, these pieces each comprising a structure forming a reinforcing rib of the central box, as well as two parts of horseshoe shape surrounding the reducing gear case.