Reverse Core Engine Thrust Reverser Nacelle Design
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Solution Overview
Problem
Traditional gas turbine engines with axial flow orientation face challenges in mounting a thrust reverser due to the long axial in-line design, which requires two separate thrust reversers for bypass fan and engine core, leading to increased length and weight, and complexity.
Innovation Solution
A reverse core engine design with an angled core configuration allows for a single thrust reverser to be used, utilizing a pivoting door mechanism within a nacelle that pivots between stowed and deployed positions to block both bypass and core engine exhaust flows, reducing overall length and weight by integrating the thrust reverser into the nacelle.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a standard axial flow gas turbine engine configuration is used, then the engine can provide bypass air propulsion, but the engine core extends beyond the end of the nozzle making it impossible to pivot shell halves inwardly to a thrust reverse position
Solution Approach 1:
The patent inverts the traditional engine core arrangement by positioning the turbine section adjacent to the fan and the combustor section at the inner end of the turbine section, with the compressor positioned farthest from the fan. This reverse flow configuration allows the engine core to be shorter and enables the thrust reverser shell halves to pivot inwardly to a thrust reverse position, resolving the contradiction between maintaining bypass air propulsion and achieving thrust reverse capability.
2Reliability
If two separate thrust reversers are used for bypass fan and engine core, then both flows can be blocked, but the overall length and weight of the engine increase
Solution Approach 1:
The patent merges the thrust reverse function into a single integrated system. The reverser assembly includes a plurality of reverser panels that can be positioned to block both the bypass air flow from the fan and the engine core exhaust flow from the nozzle. This single unified thrust reverser structure eliminates the need for separate reversers for the bypass fan and engine core, thereby reducing overall engine weight while maintaining the ability to block both flows effectively.
3Reliability
If two separate thrust reversers are used for bypass fan and engine core, then both flows can be blocked, but the device complexity increases
Solution Approach 1:
The patent creates a universal thrust reverser system that serves multiple functions. The reverser assembly with its plurality of panels can block both bypass air flow and engine core exhaust flow, and the shell halves can pivot to a thrust reverse position. This multi-functional design eliminates the need for separate thrust reverser systems for the bypass fan and engine core, thereby reducing device complexity while maintaining the ability to block both flows effectively.
Data Source
AI summary
A gas turbine engine for mounting under a wing of an aircraft 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 horizontal deployed position in which the door inhibits a flow to provide a thrust reverse of the flow.