Turbine Engine Pylon Support Structure for Universal Fastening
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Solution Overview
Problem
Current turbine engine fastening systems to aircraft pylons are not universally adaptable and cause stress-related performance issues and deformation, particularly when fastening to unducted propellers, and hoisting of turbine engines is cumbersome due to multiple directional movements.
Innovation Solution
A linking structure with a first and second axial segment allows for a cantilevered mounting of the turbine engine, integrating front and rear suspensions, facilitating a single vertical hoisting motion and reducing stress-related issues by distributing forces through multiple connecting rods and pivoting members.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If dedicated fastening members are used for specific turbine engine types, then the fastening system is optimized for that engine type, but the adaptability to different engine types is reduced
Solution Approach 1:
The pylon structure is designed with universal fastening members that can accommodate different turbine engine types. The upstream fastening members include connecting rods with spherical joints that can interface with various engine configurations (ducted and unducted propellers), while the downstream fastening members provide similar versatility. This multi-functional design allows the same pylon structure to reliably fasten different engine types without requiring dedicated fastening systems for each engine variant.
2Strength
If downstream fastening members are used to suspend the turbine engine, then the engine is securely fastened to the pylon, but stress-induced deformation and clearance changes occur
Solution Approach 1:
The fastening system is divided into separate upstream and downstream segments. The upstream fastening members handle the primary suspension and load transfer, while the downstream fastening members provide additional support. This segmentation allows the upstream members to be positioned optimally for minimizing stress on the gas generator, reducing deformation and clearance changes while maintaining secure fastening through the combined action of both segments.
Solution Approach 2:
The upstream fastening members act as intermediaries between the pylon and the turbine engine, positioned to optimize stress distribution. By introducing these intermediate fastening points upstream of the gas generator, the system mediates the stress transmission path, reducing the direct moment applied to the gas generator and thereby minimizing deformation and clearance variations.
3Reliability
If the turbine engine is fastened in a cantilevered manner, then stress on the gas generator is reduced, but the fastening system complexity increases
Solution Approach 1:
The cantilevered fastening system is segmented into upstream fastening members (connecting rods with spherical joints) and downstream fastening members. This segmentation allows the primary load-bearing function to be performed by the upstream members in a cantilevered configuration, reducing gas generator stress, while the downstream members provide additional support and stability. The modular segmented design manages complexity by assigning specific functions to each segment.
Solution Approach 2:
The upstream fastening members incorporate spherical joints that provide dynamic adaptation capabilities. These joints allow the connecting rods to self-adjust and accommodate minor misalignments or movements, maintaining optimal stress distribution and gas generator protection. The dynamic特性 of the spherical joints simplifies the overall system by providing passive adaptation without requiring complex active control mechanisms.
4Ease of manufacture
If multiple directional movements are required for hoisting, then the turbine engine can be precisely positioned, but the hoisting operation becomes cumbersome
Solution Approach 1:
The linking structure is designed with its center of gravity positioned to align with the hoisting attachment point. This equipotential configuration allows the turbine engine to be hoisted vertically in a single direction without requiring complex multi-directional movements for positioning. The structure's geometry and mass distribution are optimized so that vertical lifting naturally positions the engine correctly relative to the pylon, simplifying the hoisting operation while maintaining precise positioning capability.
Data Source
AI summary
A structure for linking and supporting a turbine engine on an aircraft pylon, the structure having a first longitudinal axis intended to extend parallel to a second longitudinal axis of the pylon, the structure including a first axial portion for fastening to the pylon, the first portion having an upper end that defines a substantially horizontal plane of interface with the pylon, and a lower end bearing suspension rods for suspending the turbine engine, which extend in a rear vertical plane; and a second axial portion that is intended to extend forward of the pylon and includes at least one suspension member of the turbine engine in a front vertical plane.