Aircraft Engine Front Mount with Three Link Points
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Solution Overview
Problem
Aircraft engine designs face challenges with reduced space between the core and primary structure, leading to increased thermal stresses, higher costs, and aerodynamic drag due to bulky equipment placement and complex fan casing designs, particularly in dual-flow jet engines.
Innovation Solution
The engine assembly features a pylon with a primary structure connected by a front engine mount with three link points, allowing for a more efficient distribution of forces and reduced thermal stresses, enabling the accommodation of supplementary equipment like heat exchangers without restricting the fan casing diameter, thus simplifying the fan design and reducing drag.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Length of stationary object
If the primary structure is positioned close to the engine core, then the distance between structures is reduced, but thermal stresses on the primary structure increase and the zone for supplementary equipment is reduced
Solution Approach 1:
The engine link is segmented into multiple components: rear engine mount, front engine mount with multiple link points, and push rods. This segmentation allows the primary structure to be positioned closer to the engine core while distributing thermal and mechanical loads across multiple connection points, reducing thermal stresses on any single structure.
2Length of stationary object
If the primary structure is positioned close to the engine core, then the distance between structures is reduced, but the zone for supplementary equipment is reduced
Solution Approach 1:
The front engine mount utilizes a three-dimensional arrangement with multiple link points (first, second, and third link points) positioned at different locations. This spatial distribution creates volume in multiple dimensions, accommodating supplementary equipment like heat exchangers in the zone between the primary structure and engine core while maintaining a compact overall distance.
3Volume of stationary object
If the front engine mount connects to the fan casing, then the zone for supplementary equipment is increased, but the fan casing diameter is restricted
Solution Approach 1:
Instead of directly connecting to the fan casing, the front engine mount connects to the engine core at multiple link points, creating a replicated connection system that provides the same structural support function without interfering with the fan casing diameter. The multiple link points effectively copy the support function across different locations.
4Device complexity
If a single front link point is used, then the structure is simpler, but the forces on the rear engine mount increase
Solution Approach 1:
The front engine mount is segmented into multiple link points (first, second, and third link points) positioned at different locations on the engine core. This segmentation distributes the forces across multiple connection points, reducing the force burden on the rear engine mount while maintaining structural simplicity through a modular design.
Data Source
AI summary
An aircraft engine assembly has a front engine mount connecting an engine and a primary structure of a pylon comprising at least one front rod having at least three front link points. A first front link point is configured to connect the front rod and the front end of the primary structure. A second front link point is configured to connect the front rod and the core of the engine. A third front link point is configured to connect the front rod and the engine core and is offset relative to the second front link point in a horizontal transverse direction. The first front link point of the front engine mount is separated from the rotation axis of the engine by a distance greater than an exterior radius of the rear casing of the core of the engine at the rear link point of the rear engine mount.