Rear-Mounted Reverse Core Engine Thrust Reverser
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Solution Overview
Problem
Traditional gas turbine engines with axial flow orientation face challenges in deploying thrust reversers due to the long axial in-line design, requiring two separate thrust reversers for bypass fan and engine core, which complicates the arrangement and increases weight and fuel consumption.
Innovation Solution
A reverse core engine design with an angled core configuration allows for a single thrust reverser to block both bypass and core engine exhaust flows, utilizing pivoting doors in a clamshell arrangement actuated by a mechanism, reducing overall engine length and weight, and enabling vertical deployment without interfering with adjacent engines.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If a standard axial flow gas turbine engine configuration is used with the compressor section positioned nearer the fan than the turbine section, then the engine provides conventional thrust, but the engine core extends beyond the end of the fan nozzle preventing the shell halves from pivoting inwardly to a thrust reverse position
Solution Approach 1:
The patent inverts the conventional axial flow arrangement by positioning the turbine section adjacent the fan and the compressor section farthest from the fan. This reversal allows the engine core to be retracted within the nacelle, enabling the shell halves to pivot inwardly to a thrust reverse position without contacting the engine core, thereby resolving the deployment interference problem.
2Reliability
If two separate thrust reversers are used to block both bypass flow and engine core exhaust flow in traditional engines, then complete flow reversal is achieved, but the number of parts increases and weight and fuel consumption increase
Solution Approach 1:
The patent merges the functions of two separate thrust reversers into a single integrated system. The inverted engine core configuration allows one thrust reverser to block both bypass flow from the fan and core exhaust flow simultaneously, reducing the number of parts and associated weight while maintaining complete flow reversal capability.
Solution Approach 2:
The single thrust reverser in the inverted configuration performs multiple functions: it blocks bypass flow from the fan and blocks core exhaust flow. This multi-functionality eliminates the need for separate thrust reversers for each flow path, reducing system complexity and weight while ensuring complete flow reversal.
3Ease of manufacture
If the engine core is positioned in-line with the fan nozzle, then conventional engine layout is maintained, but the overall engine length increases and complicates the thrust reverser arrangement
Solution Approach 1:
The patent inverts the conventional in-line arrangement by positioning the turbine section adjacent the fan and the compressor section farthest from the fan. This reversal, combined with angling the engine core, allows the core to be retracted within the nacelle, significantly reducing the overall engine length and simplifying the thrust reverser arrangement while maintaining manufacturability.
Data Source
AI summary
In one embodiment, a gas turbine engine for mounting to a rear of an aircraft fuselage has a propulsor that rotates on a first axis, and an engine core including a compressor section, a combustor section, and a turbine section, with the turbine section being closer to the propulsor than the compressor section. The engine core is aerodynamically connected to the propulsor and has a second axis. A nacelle is positioned around the propulsor and engine core. The nacelle is attached to the wing of the aircraft. A downstream end of the nacelle has at least one pivoting door with an actuation mechanism to pivot the door between a stowed position and a vertical deployed position in which the door inhibits a flow to provide a thrust reverse of the flow.