Twin Target Thrust Reverser Module Fuselage Integration
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Solution Overview
Problem
Conventional thrust reversing devices are not compatible with gas turbine engines mounted within the aircraft fuselage, necessitating the development of alternative structures that can provide thrust reversing and variable nozzle functions for such configurations.
Innovation Solution
A nozzle assembly with pivotally mounted upper and lower doors, driven by a single actuator and linkage system, which can vary the cross-sectional area of the nozzles for thrust reversing and propulsive efficiency, and is mountable to the aircraft structure to provide both thrust reversing and variable area nozzle functions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If conventional thrust reversing devices are used for under-wing mounted engines, then thrust reversing function is achieved, but the device is not compatible with fuselage mounted engine configurations
Solution Approach 1:
The nozzle assembly is designed to perform multiple functions: it serves as both a thrust reverser and a variable area nozzle for different flight conditions. The same movable doors that redirect airflow for thrust reversal also control nozzle area for propulsive efficiency, eliminating the need for separate dedicated structures for each function.
Solution Approach 2:
The nozzle assembly incorporates movable doors that can dynamically adjust their position to vary the cross-sectional area of the nozzle. This dynamic adjustment capability allows the structure to adapt between different operational modes (thrust reversal and propulsive efficiency optimization) without requiring complex static structures.
2Adaptability or versatility
If separate structures are added for thrust reversing and variable nozzle functions, then both functions are achieved, but structural complexity increases
Solution Approach 1:
The invention merges the thrust reversing function and variable area nozzle function into a single integrated nozzle assembly. The movable doors serve dual purposes: redirecting exhaust gases for thrust reversal and controlling nozzle cross-sectional area for propulsive efficiency, thereby combining multiple functions into one structure rather than adding separate systems.
Solution Approach 2:
The nozzle assembly is designed as a multi-functional component that simultaneously provides thrust reversal capability and variable area control. The same actuated doors perform both functions depending on their position, making the structure universal rather than requiring specialized separate components for each function.
3Device complexity
If a single actuator and linkage system is used to drive upper and lower doors, then device complexity is reduced, but control precision may be affected
Solution Approach 1:
A single actuator and linkage system is used to drive both upper and lower doors, merging the control functions into one actuation mechanism. This reduces the number of independent actuators and simplifies the overall control system while maintaining coordinated movement of all door components through the linkage mechanism.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
Enables efficient reverse thrust generation and improved propulsive efficiency during flight operations by redirecting airflow and exhaust gases, while maintaining favorable fan operating characteristics without additional structural complexity.
Implementation Method 1
A thrust reverser is utilized once an aircraft has landed, and creates a reverse thrust force to aid in slowing the aircraft
Implementation Method 2
The first and second nozzles are variable area nozzles and the cross-sectional area of the nozzles can be varied
Data Source
Figure 1
Figure 2A~2B
Figure 3
AI summary
A nozzle assembly for a dual gas turbine engine propulsion system includes a housing mountable proximate to a first bypass passage of a first gas turbine engine and a second bypass passage of a second gas turbine engine, first and second upper doors, and first and second lower doors. Each of the first and second upper doors and the first and second lower doors are pivotally mounted to the housing for movement between a stowed position and a deployed position in which airflow through the first and second bypass passages is redirected relative to respective centerline axes of the first and second gas turbine engines.