Multi-turn Thrust Reverser with Side Turning Vanes
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Solution Overview
Problem
Existing thrust reverser systems in commercial airplanes are complex and inefficient, particularly due to the lattice pattern design which results in a complicated mechanical system and suboptimal deceleration performance.
Innovation Solution
A thrust reverser system comprising a first reverser portion that directs gas flow in a forward direction to create reverse thrust, and a second reverser portion positioned radially outward, which directs gas flow in a circumferential direction to divert the flow away from the fuselage and wings, thereby improving deceleration efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If a cascade thrust reverser with lattice pattern design is used, then the thrust reverser can turn the jet engine exhaust to create reverse thrust, but the mechanical system becomes complicated and the exit area for reversed flow is minimized
Solution Approach 1:
The thrust reverser system is divided into multiple independent cascade assemblies, each capable of operating autonomously. The blocker doors are segmented into multiple sections that can move independently to control flow to different cascade assemblies, simplifying the overall mechanical system while maintaining reverse thrust capability
Solution Approach 2:
The patent transitions from a traditional lattice pattern design to a cascade assembly configuration where multiple cascade assemblies are arranged in a circular pattern around the engine exhaust. This spatial reorganization eliminates the complex lattice structure while providing adequate exit area through the radial arrangement of cascades
2Ease of operation
If the aft nacelle sleeve is translated aft to expose the cascades during deployment, then the thrust reverser can be activated, but the mechanical system becomes more complicated
Solution Approach 1:
The blocker doors are extracted as separate, independently actuated components from the nacelle sleeve assembly. This allows the cascades to remain exposed and stationary while only the blocker doors move to control flow, eliminating the need for complex nacelle sleeve translation mechanisms
Solution Approach 2:
The system employs dynamically adjustable blocker doors that can be positioned at different angles to control flow distribution to various cascade assemblies. This dynamic control mechanism is simpler than translating the entire nacelle sleeve while providing flexible deployment control
3Productivity
If the lattice pattern design is used with minimum exit area, then the vanes and strongbacks can turn the fan flow, but the deceleration performance becomes suboptimal
Solution Approach 1:
Multiple cascade assemblies are arranged radially around the exhaust, with each assembly providing its own exit area. This segmentation of the flow path increases the total effective exit area compared to a single lattice structure, improving mass flow and deceleration performance
Solution Approach 2:
The cascade assemblies are arranged in a circular pattern around the engine exhaust, utilizing the radial dimension to maximize exit area. This three-dimensional arrangement provides superior flow turning capability and exit area compared to the two-dimensional lattice pattern
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
The proposed thrust reverser system enhances deceleration performance by creating a more efficient reverse thrust mechanism, reducing the axial length and weight of the system, and minimizing the risk of damage to the aircraft during deceleration.
Implementation Method 1
The first reverser portion turns the air and the exhaust at least partially in a forward direction to create reverse thrust
Implementation Method 2
The second reverser portion turns the air and the exhaust at least partially in the circumferential direction with respect to the central engine axis such that the air and the exhaust are directed away from a fuselage and a wing of the airplane
Implementation Method 3
The louvers each rotate around their respective central louver axes as the thrust reverser actuates into the deployed state
Data Source
AI summary
A thrust reverser in an engine includes a first reverser portion configured to direct a gas in a first direction to create reverse thrust. The thrust reverser also includes a second reverser portion configured to direct the gas in a second direction that is different than the first direction. The second reverser portion is upstream or downstream from the first reverser portion.