Asymmetric Thrust Reverser Cowl Interface for Wing Clearance
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Solution Overview
Problem
Existing thrust reverser systems in gas turbine engines for aircraft often require complex geometries and alignments that can lead to interference with aircraft wing components, such as slats, during deployment and stowage, limiting the flexibility and efficiency of thrust redirection.
Innovation Solution
A thrust reverser design featuring a first cowl that translates between a stowed and deployed position, with a cowl interface circumferentially offset by more than 18 degrees from the top circumferential apex, allowing for thrust redirection without contacting the aircraft wing slats, and utilizing a pylon mount at the top circumferential apex for secure attachment.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the thrust reverser cowl is positioned at the top circumferential apex for secure pylon attachment, then the structural stability and attachment reliability are improved, but the cowl may interfere with aircraft wing components such as slats during deployment and stowage
Solution Approach 1:
The patent applies asymmetry by offsetting the cowl interface position from the top circumferential apex by more than 18 degrees circumferentially. This asymmetric positioning allows the pylon to be attached near the apex for structural stability while the cowl interface is shifted to a position that avoids interference with wing slats during thrust reverser deployment and stowage operations
2Length of moving object
If the engine is positioned closer to the aircraft wing for compact design, then the overall aircraft structure is optimized, but the thrust reverser cowl may contact the wing slats during operation
Solution Approach 1:
By offsetting the cowl interface position circumferentially from the top apex by more than 18 degrees, the patent creates an asymmetric configuration that provides sufficient circumferential clearance between the cowl and the wing slats. This allows the engine to be positioned closer to the wing for compact design while preventing cowl contact with the slats during thrust reverser operation
Data Source
AI summary
An example thrust reverser of a gas turbine engine is configured to connect to an aircraft wing via a pylon via one or more thrust reverser mounts located adjacent to a top circumferential apex of the engine according to an exemplary aspect of the present disclosure includes, among other things, a first cowl moveable between a stowed position and a deployed position relative to a second cowl. The first cowl in the deployed position configured to permit thrust to be redirected from an engine to slow the engine. The first cowl forming a portion of a substantially annular encasement of the engine. The first cowl directly interfaces with second cowl of the encasement at a cowl interface position that is more than 18 degrees circumferentially offset from the top circumferential apex when the first cowl is in the stowed position.