Opposed Thrust Beams for Aircraft Engine Mounting
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Solution Overview
Problem
Current engine mounting systems on aircraft wings experience engine bending due to gravity, thrust, and maneuvering loads, leading to reduced engine performance and increased fuel consumption, as well as positioning of flammable fluids and ignition sources in the same pylon, which poses safety risks.
Innovation Solution
The use of two opposed thrust beams instead of a single center top pylon to react thrust loads, with one beam carrying flammable fluids and the other ignition sources, and positioning the thrust beams to counteract eccentric thrust forces, thereby reducing engine bending and improving specific fuel consumption (SFC).
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If a single center top pylon is used to support the engine, then the structure is simpler, but engine bending increases due to gravity and thrust loads
Solution Approach 1:
The single pylon structure is divided into two separate pylons, each supporting opposite sides of the engine. This segmentation allows the engine weight and thrust loads to be distributed more effectively, reducing bending moments on each individual pylon and improving overall structural efficiency.
2Device complexity
If flammable fluids and ignition sources are positioned in the same pylon, then the device complexity is reduced, but safety risks increase
Solution Approach 1:
The mounting structure is segmented into two separate pylons, with flammable fluids (fuel) positioned in one pylon and ignition sources (exhaust, electrical systems) positioned in the other pylon. This physical separation eliminates the safety hazard of having combustible materials and ignition sources in close proximity, while maintaining structural efficiency.
3Device complexity
If a single pylon is used to react thrust loads, then the structure is simpler, but fuel consumption increases due to engine bending
Solution Approach 1:
The support structure is divided into two pylons that collectively react thrust loads more efficiently. By distributing the load path through two separate structures, engine bending is reduced, improving engine performance and reducing specific fuel consumption (SFC).
Solution Approach 2:
The two pylons are positioned to counteract eccentric thrust forces through their geometric arrangement and load distribution characteristics, creating a balanced system that minimizes net bending moments on the engine.
Data Source
AI summary
Methods and apparatus for supporting engines and nacelles relative to aircraft wings are disclosed. An example apparatus includes a nacelle; a first support structure coupled between a wing and a first side of the nacelle along a thrust axis of an engine; a second support structure coupled between the wing and a second side of the nacelle along the thrust axis, the first support structure spaced apart from the second support structure on the wing, a longitudinal plane to extend through the first support structure, the second support structure, and the thrust axis, the first support structure to be rigidly fixed relative to the wing to substantially prevent movement of the engine by the first support structure, the second support structure to be rigidly fixed relative to the wing to substantially prevent movement of the engine by the second support structure, the first and second support structures to be coupled to opposite sides of the engine to enable thrust loads to be reacted through the first and second support structures to the wing.