Aircraft Pylon Engine Mounting with Segmented Suspension Lugs

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Solution Overview

Problem

Existing solutions for suspending a turbine engine under an aircraft wing using a pylon fail to provide a safe, efficient, and fail-safe connection that allows for close positioning of the engine to the pylon, easy mounting, and efficient thrust transfer while minimizing pylon width, which affects aerodynamic performance.

Innovation Solution

A suspended assembly comprising a structural pylon with a pad and a beam attached to the turbine engine, featuring suspension lugs with integral C-clamps and a locking mechanism for fail-safe operation, allowing vertical alignment and clearance for easy mounting and efficient thrust transfer, and a finger for additional fail-safe support, enabling narrower pylon usage.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If a conventional suspension solution with two hooking means is used, then the connection between pylon and turbine engine is provided, but the pylon width increases, affecting aerodynamic performance

Engineering Contradiction:

Improveconnection safetyVSAvoidpylon width

Core Design Contradiction:

ReliabilityVSLength of stationary object

Solution Approach 1:

The connection system is segmented into distinct functional components: a single primary hooking means with two knuckles for normal operation, and a separate secondary hooking means activated only in degraded mode. This segmentation allows the pylon width to be minimized for aerodynamic efficiency while maintaining reliability through the staged activation of backup connection points.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The secondary hooking means is designed as a pre-positioned backup system that remains inactive during normal operation but can be immediately activated in case of failure of the primary hooking means. This beforehand cushioning ensures that connection safety is maintained without requiring increased pylon width, as the backup system is integrated into the original design geometry.

Inventive Principle:

Principle #11Beforehand cushioning (Prior cushioning)

2Object-affected harmful factors

If the turbine engine is positioned closer to the pylon, then aerodynamic performance improves, but the mounting complexity and clearance requirements increase

Engineering Contradiction:

Improveaerodynamic dragVSAvoidmounting complexity

Core Design Contradiction:

Object-affected harmful factorsVSDevice complexity

Solution Approach 1:

The mounting system incorporates dynamic adjustment capabilities through the articulated connection between the beam and suspension lugs, allowing the turbine engine position to be optimized for aerodynamic performance while maintaining adequate clearances. The system can adapt its configuration to accommodate the reduced spacing between pylon and engine without increasing overall complexity.

Inventive Principle:

Principle #15Dynamics

3Device complexity

If a single hooking means with two knuckles is used instead of two separate hooking means, then the device complexity is reduced, but the fail-safe capability is compromised

Engineering Contradiction:

Improvehooking system complexityVSAvoidfail-safe capability

Core Design Contradiction:

Device complexityVSReliability

Solution Approach 1:

Inventive Principle:

Principle #11Beforehand cushioning (Prior cushioning)

Solution Approach 2:

The beam acts as an intermediary element that connects the turbine engine to both the primary and secondary hooking means on the pylon. This intermediary structure allows the system to maintain low complexity by using a single beam component while still providing fail-safe capability through its connection to multiple hooking points, effectively mediating between the engine and the pylon's redundant connection system.

Inventive Principle:

Principle #24Intermediary (Mediator)

4Object-affected harmful factors

If the pylon width is reduced for aerodynamic efficiency, then drag is minimized, but the ease of operation and maintenance access is reduced

Engineering Contradiction:

Improveaerodynamic dragVSAvoidmaintenance access

Core Design Contradiction:

Object-affected harmful factorsVSEase of operation

Solution Approach 1:

The connection system is designed to utilize the vertical dimension rather than requiring increased horizontal width. The hooking means and beam connection are arranged vertically to provide all necessary connection points and maintenance access within the constrained horizontal space, allowing aerodynamic efficiency to be maintained while ensuring adequate accessibility for operation and maintenance activities.

Inventive Principle:

Principle #17Another dimension (Dimensionality change)

Data Source

PatentUS10836500B2Assembly between an aircraft pylon and a turbine engine

Publication Date: 2020.11.17 SAFRAN AIRCRAFT ENGINES SAS

AI summary

An assembly between an aircraft structural pylon and an aircraft turbine engine is disclosed, with the assembly comprising a beam intended to be attached to the turbine engine and wherein a knuckle intended for the installation of a pad integral with the pylon is mounted, with the beam comprising suspension lugs each including a bore for the passage of a shaft intended to further go through a bore formed in the pylon to connect the beam with the pylon.