Aircraft Engine Mounting System Backbone Bending Reduction
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Solution Overview
Problem
Aircraft engine backbone deflection due to aerodynamic, gravitational, and thrust loads is not effectively addressed by existing mounting systems, leading to increased blade tip clearances and reduced fuel efficiency.
Innovation Solution
A mounting system with a rigid structure, including a forward-leaning engine forward mount and aft-leaning engine aft mount, coupled with a linkage structure that intersects load vectors within specific vertical plane segments, reducing backbone bending by optimizing the position of focal points relative to the engine centerline and inlet loading.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Stability of the object's composition
If traditional engine mounting systems are used, then the engine can be mounted to the aircraft, but backbone deflection occurs due to aerodynamic, gravitational, and thrust loads
Solution Approach 1:
The mounting system is divided into multiple discrete components: forward mount, aft mount, link mount, and thrust links. Each component performs a specific function in supporting different portions of the engine weight and managing thrust loads, allowing the system to address backbone deflection through distributed support points rather than a single complex mounting structure.
Solution Approach 2:
The patent introduces angular orientation of mounting components relative to the engine axis of rotation. The forward mount is angled forward, the aft mount is angled aft, and thrust links are positioned at specific angles to create a three-dimensional load distribution system. This angular arrangement creates focal points that intersect within specific vertical plane segments, adding a dimensional aspect to load management that reduces backbone bending moments.
2Adaptability or versatility
If open tip clearances are increased to accommodate backbone bending, then the engine can operate with flexible mounting, but fuel efficiency is reduced
Solution Approach 1:
The mounting system is designed to preemptively counteract backbone bending through its structural configuration before operation. The forward and aft mounts, positioned and angled to create focal points within specific vertical plane segments, generate opposing forces that balance aerodynamic, gravitational, and thrust loads. This preliminary structural arrangement prevents backbone deflection from occurring in the first place, eliminating the need for compensatory open tip clearances and maintaining optimal blade tip clearances for fuel efficiency.
3Ease of manufacture
If the engine is mounted with focal point on or near the centerline, then mounting is simplified, but backbone bending moment increases
Solution Approach 1:
The mounting system deliberately employs asymmetric angular orientations: the forward mount angles forward, the aft mount angles aft, and thrust links are positioned at non-symmetric angles relative to the engine axis. This asymmetric configuration creates focal points that intersect within specific vertical plane segments rather than on the simple centerline, generating a more complex but effective load distribution pattern that reduces backbone bending moments while maintaining manufacturing feasibility.
Data Source
AI summary
A system for mounting an engine to an aircraft includes an engine forward mount angled toward the forward end of the engine at a first angle. At least two thrust links extend between an engine aft mount to a link support connection at a second angle. The engine aft mount is angled toward the forward end of the engine at a third angle. A projection of a load vector of the engine forward mount onto a vertical plane extending through the axis of rotation of the engine and a projection of a load vector of each of the at least two thrust links onto the vertical plane intersect the axis of rotation of the engine within a first vertical plane segment extending between a forward end of a nose of a fan assembly and forward of a forward mount interface.