Aircraft Thrust Reverser Door Segmentation for Aerodynamic Matching
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Solution Overview
Problem
Current thrust reversers for aircraft propulsion systems lack efficiency and performance in redirecting airflow for effective deceleration after landing, as they often require synchronized deployment and do not achieve optimal aerodynamic matching between stowed and deployed positions.
Innovation Solution
The design incorporates a pair of pivotally attached thrust reverser doors with actuators, allowing independent rotation and deployment, creating a blockage of the gas path to redirect airflow efficiently and achieve 'area match' without synchronized operation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If thrust reverser doors are deployed in a synchronized manner, then the structural control is simplified, but the aerodynamic matching efficiency is reduced
Solution Approach 1:
The thrust reverser system is divided into multiple independently controllable door assemblies, each with its own actuator. This segmentation allows each door to be deployed independently to achieve optimal aerodynamic matching while maintaining simplified individual control mechanisms.
Solution Approach 2:
The door deployment system transitions from static synchronized movement to dynamic independent control. Each door can adjust its position and deployment timing dynamically to optimize aerodynamic performance during different phases of thrust reversal operation.
2Productivity
If thrust reverser doors are designed to achieve optimal aerodynamic matching, then the deceleration performance is improved, but the deployment complexity increases
Solution Approach 1:
The complex deployment mechanism is segmented into multiple independent door assemblies, each capable of achieving aerodynamic matching independently. This reduces the overall system complexity by breaking down the coordinated movement of multiple doors into simpler individual door operations.
Solution Approach 2:
Each door assembly is designed with self-contained actuators and control mechanisms that automatically position the doors for optimal aerodynamic matching. This self-service capability reduces the need for complex external coordination systems while maintaining high deceleration performance.
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
This configuration enhances the efficiency of thrust reversal by ensuring aerodynamic matching and independent deployment of thrust reverser doors, improving deceleration performance and reducing operational complexity.
Implementation Method 1
redirecting the bypass airflow and/or core airflow from the rearward direction to, at least partially, a forward direction thus producing a rearward propulsion
Data Source
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Figure 5
AI summary
An assembly for an aircraft propulsion system is provided, the assembly having an axial centerline. The assembly comprises a fixed structure, a first thrust reverser door, and a second thrust reverser door. The first thrust reverser door being pivotally attached to the fixed structure along a first pivot axis, and the second thrust reverser door being pivotally attached to the fixed structure along a second pivot axis. The first pivot axis and the second pivot axis are both radially located at a first distance from the assembly axial centerline. The first pivot axis is located at a first axial position, and the second pivot axis is located at a second axial position. The second axial position is displaced from the first axial position.