Aircraft Engine Mounting Geometry for Lower Core Bending Loads
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Solution Overview
Problem
Existing propulsion system mounting systems for aircraft gas turbine engines do not effectively manage gravitational, lateral, and torque loads, leading to excessive bending loads on the engine core.
Innovation Solution
Aircraft mounting system comprising a pylon, forward mount, aft mount, and thrust link, where the thrust link vector intersects with the mount plane below the engine centerline, mitigating bending loads through optimized mounting configurations and geometric parameters.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If conventional propulsion system mounting systems are used, then the engine can be attached to the aircraft, but excessive bending loads are imposed on the engine core due to ineffective load management
Solution Approach 1:
The thrust link is positioned and oriented to create a counterbalancing moment that offsets the bending loads on the engine core. By strategically locating the thrust link intersection point below the engine centerline and configuring its orientation, the system generates counteracting forces that neutralize the harmful bending moments produced by gravitational and lateral loads on the engine and nacelle.
Solution Approach 2:
The invention introduces a vertical dimension consideration by positioning the thrust link intersection point below the engine centerline rather than in the conventional plane. This three-dimensional positioning creates additional moment arms and load paths that effectively distribute and mitigate bending loads across multiple spatial dimensions, reducing the concentration of stress on the engine core.
2Force
If the thrust link vector intersects with the mount plane below the engine centerline, then bending loads are mitigated, but the mounting system complexity increases
Solution Approach 1:
The invention modifies key geometric parameters of the mounting system, specifically the vertical position of the thrust link intersection point (placing it below the engine centerline) and the orientation angle of the thrust link. These parameter changes enable the system to generate beneficial counteracting moments while maintaining a relatively simple mechanical structure, achieving load mitigation through optimized geometry rather than complex mechanisms.
Data Source
AI summary
An aircraft system is provided that includes a pylon, a gas turbine engine, a forward mount, an aft mount, and a thrust link. The gas turbine engine includes a compressor section, a fan section, and a turbine exhaust case (TEC). The gas turbine engine has an axially extending engine centerline. The forward mount is connected to the compressor section and the pylon along a mount plane. The aft mount is connected to the TEC and the pylon. The thrust link extends along a thrust link centerline between the forward mount and the compressor section. The thrust link is oriented such that a thrust link vector coincident with the thrust link centerline intersects with the mount plane at an intersection point that is located below the engine centerline.