Monolithic Aircraft Engine Mount Structure
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Solution Overview
Problem
Large turbofan engines experience backbone bending due to inlet overturning moments during takeoff, leading to blade tip wear and performance loss, and current mounting structures are heavy, occupy excessive shop space, and inefficiently manage nacelle maneuvering forces.
Innovation Solution
A monolithic structure with an integral nacelle and support portion that transmits nacelle maneuvering forces directly to the aircraft, featuring a non-rigid interface between the engine and the ring member to isolate the engine from these forces, and includes a stiffening region and composite materials for reduced weight and space usage.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If conventional bolted flange and mount systems are used to attach engine components, then structural strength and reliability are improved, but device complexity and weight increase
Solution Approach 1:
The patent combines the nacelle and support structure into a single monolithic integral structure, eliminating the need for separate bolted flange connections between the nacelle and support structure. This merging reduces the number of parts and assembly complexity while maintaining structural strength through the integrated design.
Solution Approach 2:
The monolithic structure serves multiple functions simultaneously: it provides both the nacelle housing and the support structure for mounting the engine to the aircraft. This multi-functionality eliminates the need for separate dedicated support structures, reducing overall device complexity while maintaining all necessary structural functions.
2Strength
If substantial support structures are used to cantilever the propulsion system from the aircraft pylon, then structural strength and stability are improved, but weight increases
Solution Approach 1:
By merging the support structure with the nacelle into a monolithic integral structure, the patent eliminates redundant structural elements. The support structure is optimized to work in conjunction with the nacelle geometry, reducing material usage and weight while maintaining the necessary strength to cantilever the propulsion system from the aircraft pylon.
3Stability of the object's composition
If the fan module remains attached to engine components during service, then structural integrity is maintained, but shop floor space is wasted during overhauls
Solution Approach 1:
The patent enables segmentation of the fan module from the engine core by providing a monolithic support structure that facilitates clean separation points. The integral structure is designed with defined interfaces that allow the fan module to be removed independently during overhauls, reducing shop floor space requirements while maintaining structural integrity when assembled.
4Force
If inlet overturning moments are transmitted through the mount system to the pylon, then force transmission is achieved, but backbone bending and blade tip wear increase
Solution Approach 1:
The monolithic integral structure acts as an intermediary between the inlet overturning moments and the pylon mount system. By integrating the support structure with the nacelle, the patent creates a stiffer, more direct load path that reduces unwanted backbone bending while still transmitting the necessary forces to the pylon through the mount system.
Data Source
AI summary
Assembly includes an integral monolithic structure for mounting an engine to an aircraft. The monolithic structure includes a nacelle portion and a support structure. The nacelle portion includes an inlet region and a fan case region defining an annular wall about an axial channel. A ring member disposed in the axial channel is connected through a plurality of radial elements to the annular wall. The support structure portion includes a forward section integral with the nacelle portion and an aft section including at least one aircraft mount region for mounting the monolithic structure to an aircraft. The forward section includes an inlet stiffening region radially outward of the annular wall. When mounted on the aircraft, the nacelle portion and the support structure portion cooperate to form a first load path operable to transmit an applied nacelle maneuvering force directly to the aircraft instead of through the engine core.