Turbofan Engine Support Assembly for Alternative Airframes
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Solution Overview
Problem
Traditional turbofan engines are difficult to mount on alternative airframe architectures such as blended wing body (BWB) or hybrid wing body (HWB) aircraft due to non-traditional engine mounting requirements.
Innovation Solution
A support assembly comprising first and second support structures with bypass flow assemblies and a fairing, designed to secure turbofan engines above the airframe, featuring a quick engine change module for easy installation and removal.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If traditional turbofan engines are mounted below or to the side of the aircraft body, then the engine mounting is straightforward and well-established, but the aircraft cannot adopt alternative airframe architectures such as blended wing body or hybrid wing body
Solution Approach 1:
The engine support assembly is divided into multiple detachable components: a first support structure secured to the airframe, a second support structure releasably connected to the first, and a quick engine change module releasably connected to the second. This segmentation allows the assembly to be configured for alternative airframe architectures while maintaining ease of installation and removal.
Solution Approach 2:
The engine support assembly is designed with universal mounting interfaces and adjustable components that can accommodate both traditional and alternative airframe architectures. The support structures include multiple connection points and adjustment mechanisms that enable the same assembly to serve different mounting requirements.
2Adaptability or versatility
If a custom engine mounting system is designed for alternative airframe architectures, then the engine can be mounted above or on top of the airframe, but the installation and removal process becomes time-consuming
Solution Approach 1:
The support assembly is segmented into modular components that can be independently installed and removed. The quick engine change module is designed as a separate unit that can be rapidly attached to or detached from the second support structure, significantly reducing engine installation and removal time while maintaining mounting flexibility.
Solution Approach 2:
The first and second support structures are pre-configured with mounting interfaces and alignment features that facilitate rapid assembly. The quick engine change module includes pre-positioned connection points and adjustment mechanisms that enable quick engagement with the support structures without requiring complex alignment procedures.
3Reliability
If the engine support assembly includes multiple support structures and bypass flow assemblies, then the engine mounting is secure and aerodynamic, but the device complexity increases
Solution Approach 1:
The support assembly is divided into functionally independent segments: the first support structure provides structural attachment to the airframe, the second support structure provides engine mounting and positioning, and the bypass flow assemblies provide aerodynamic flow management. This segmentation allows each component to be optimized for its specific function while simplifying the overall design and assembly process.
Solution Approach 2:
The quick engine change module is nested within the second support structure, with the bypass flow assemblies integrated into the support structure geometry. This nesting arrangement reduces the overall number of separate components and simplifies the assembly process while maintaining mounting security and aerodynamic performance.
Data Source
AI summary
An engine support assembly for operatively connecting an engine to an aircraft, the aircraft, the aircraft having a support frame surrounded by opposing first and second skins. The engine support assembly broadly comprises first and second support structures. The first support structure is secured to the support frame and extends away from the first skin. The second support structure is releasably connected to the first support structure and releasably connected to the engine.