Variable Area Fan Nozzle Thrust Reverser Integration
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Solution Overview
Problem
Conventional thrust reversers in gas turbine engines provide limited functionality and contribute to engine inefficiency due to their additional weight and lack of integration with other engine systems for non-landing conditions.
Innovation Solution
A variable fan nozzle integrated with a thrust reverser, featuring nozzle doors and a linkage system that moves between stowed, intermediate, and thrust reverse positions to manipulate bypass airflow, enhancing thrust control and efficiency across different flight conditions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a conventional thrust reverser is added to the gas turbine engine, then thrust reversal capability is improved, but device complexity and weight increase
Solution Approach 1:
The patent combines the thrust reverser system with the fan nozzle into a single integrated structure. The nozzle doors that control bypass airflow are the same physical components that function as thrust reverser doors, eliminating the need for separate thrust reverser mechanisms and reducing overall device complexity
Solution Approach 2:
The nozzle doors serve dual functions: controlling bypass airflow during normal operation and deflecting airflow for thrust reversal during landing. This multi-functionality allows a single component to replace what would traditionally require separate systems, reducing weight and complexity
2Adaptability or versatility
If a conventional thrust reverser is added to the gas turbine engine, then thrust reversal capability is improved, but weight increases
Solution Approach 1:
The thrust reverser functionality is merged with the existing fan nozzle structure, meaning no additional weight-bearing components are required. The same door structures and actuation mechanisms serve both nozzle control and thrust reversal purposes
Solution Approach 2:
By making the nozzle doors universally functional for both airflow control and thrust reversal, the patent eliminates redundant components that would add weight, achieving weight savings while maintaining full thrust reversal capability
3Productivity
If the nozzle doors move to intermediate position, then take-off performance is improved, but airflow control complexity increases
Solution Approach 1:
The nozzle doors are designed to be dynamically adjustable to at least two different positions (stowed and intermediate), allowing the system to optimize performance for different flight conditions. The intermediate position specifically enhances take-off by adjusting bypass airflow
Solution Approach 2:
The same nozzle door mechanism that provides thrust reversal capability is also used to create the intermediate position for take-off enhancement. This universal mechanism handles multiple functions without requiring separate control systems, managing complexity effectively
Data Source
AI summary
A nozzle for use in a gas turbine engine includes nozzle doors coupled with a fan nacelle wherein the nozzle doors move in unison between a plurality of positions to influence a bypass airflow through a fan bypass passage. A linkage connects the nozzle doors and an actuator. A louver section coupled with the linkage moves in unison with the nozzle doors between a plurality of louver positions to direct a portion of the bypass airflow in a selected direction.