Dual Triangular Engine Mount for Aircraft Pylon Redundancy
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Solution Overview
Problem
Current engine mounting systems for aircraft gas turbine engines lack flexibility and redundancy, making them vulnerable to damage from turbine or compressor bursts and complicating maintenance access.
Innovation Solution
A dual triangular frame mounting system with axially separated and parallel frames, providing load sharing and redundancy, and featuring elongate spars for simplified mounting and dismounting, positioned to minimize exposure to potential damage zones and facilitate easy access for maintenance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a single triangular frame mounting system is used, then the structure is simple, but the system lacks redundancy and is vulnerable to damage from turbine or compressor bursts
Solution Approach 1:
The mounting system is divided into two separate triangular frames (first frame and second frame) that are axially separated and parallel to each other. Each frame independently supports the engine, providing segmentation that enhances reliability through redundancy while maintaining manageable structural complexity through modular design
Solution Approach 2:
The dual frame structure provides beforehand cushioning by creating redundant load paths. If one frame is damaged by turbine or compressor bursts, the second frame remains intact to continue supporting the engine, preventing catastrophic failure and providing advance protection against single-point failures
2Strength
If the mounting system is positioned closer to the engine core, then the attachment is more secure, but the system is exposed to potential damage zones from engine components
Solution Approach 1:
The mounting system transitions from a single-plane attachment to a three-dimensional configuration with two axially separated frames positioned forward of the turbine stages. This dimensional change allows the frames to engage the engine core at multiple axial locations, maintaining secure attachment while moving the primary attachment points away from the high-risk zones of rotating components
3Reliability
If the mounting system structure is complex, then redundancy and load sharing are improved, but maintenance access to the engine core is restricted
Solution Approach 1:
The mounting system uses two separate triangular frames with three elongate members each, creating segmented structural units that provide load sharing and redundancy. The axial separation between frames creates clearances that facilitate maintenance access to the engine core, allowing technicians to work on the engine without removing the entire mounting system
Solution Approach 2:
Instead of positioning the mounting structure behind or around the engine core where it would block access, the frames are positioned axially forward of the turbine stages, inverting the conventional arrangement. This inversion allows maintenance personnel to access the engine core from the rear without obstruction from the mounting structure
Data Source
Figure 1~2a
Figure 2b~3
AI summary
A mounting system (30) for attaching a gas turbine engine (32) to a pylon (34) of an aircraft. The mounting system comprises a first frame (36) of three elongate members (38) arranged in a triangle. The first frame is arranged such that a core of the gas turbine engine is positioned extending through the area defined between the three elongate members. The first frame forms at least part of a load bearing connection between the pylon and gas turbine engine. The first frame consists of two portions (62,64), one corresponding to each side of the gas turbine engine when attached to the pylon. The triangle is symmetrical about a plane separating the two portions of the first frame.