Aircraft Engine Forward Mounting System with Dual Linkage
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Current forward mounting systems for aircraft engines result in a larger fairing configuration, reducing aerodynamic performance and increasing fuel inefficiency due to the engine being mounted further away from the wing, as they connect the support structure above the fan case, leading to undesired load distribution and fairing size.
Innovation Solution
A forward mounting system comprising a frame with a first linking system connected to the fan case and a second linking system connected to the engine core case, allowing for a reduced support structure height and fairing size by distributing loads effectively, using materials like titanium or steel alloys, and incorporating fixed and floating links to manage side and vertical loads.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Weight of moving object
If the forward mounting system connects the support structure above the fan case, then the engine can be mounted further away from the wing, but the fairing configuration becomes larger and aerodynamic performance deteriorates
Solution Approach 1:
The mounting system is divided into separate functional components: the frame provides structural support, the first linking system connects to the fan case for lateral positioning, and the second linking system connects to the engine core case for longitudinal positioning. This segmentation allows independent optimization of each component's function, enabling the engine to be positioned closer to the wing while maintaining proper alignment and reducing fairing size.
Solution Approach 2:
The frame acts as an intermediary structure between the wing-mounted support structure and the engine. By introducing this intermediate component with specific geometric constraints, the system achieves precise engine positioning closer to the wing without requiring direct connection above the fan case, thereby reducing the fairing configuration and improving aerodynamics.
2Use of energy by moving object
If the support structure height is reduced to improve aerodynamics, then fuel efficiency improves, but load distribution and engine stability may be compromised
Solution Approach 1:
The linking systems incorporate dynamic characteristics that allow controlled movement and load distribution. The first linking system with lateral movement capability and the second linking system with longitudinal movement capability enable the structure to adapt to operational loads while maintaining reduced height, ensuring both fuel efficiency and mounting stability.
Solution Approach 2:
The system changes key geometric parameters: the frame has a height smaller than the support structure, and the linking systems provide controlled degrees of freedom. These parameter changes enable the engine to be positioned lower for better aerodynamics while the dynamic linking systems maintain proper load distribution and engine stability during operation.
3Device complexity
If a single linking system is used to connect the support structure to the engine, then the device complexity is reduced, but the ability to manage different load directions (side loads and vertical loads) is insufficient
Solution Approach 1:
The linking system is segmented into two distinct subsystems: the first linking system dedicated to carrying side loads and allowing lateral movement, and the second linking system dedicated to carrying vertical loads and allowing longitudinal movement. This segmentation assigns specific load management functions to each subsystem, providing comprehensive load distribution capability while keeping each individual subsystem relatively simple.
Solution Approach 2:
Each linking system is designed with multi-functionality: the first linking system not only carries side loads but also provides lateral positioning adjustment, while the second linking system carries vertical loads and provides longitudinal positioning adjustment. This multi-functionality reduces the need for additional specialized components, balancing complexity and versatility.
Data Source
Figure 1
Figure 2
Figure 3
AI summary
A method and apparatus comprising a frame 124, a first linking system 126 connected to the frame, and a second linking system 128 connected to the frame. The frame is configured to be connected to a support structure 108 for an engine 102 of an aircraft 100. The first linking system is configured to be connected to a fan case 116 in the engine. The second linking system is configured to be connected to an engine core case 118 in the engine.