Serrated Thrust Reverser Scoop for Aircraft Nacelle Weight Reduction
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Solution Overview
Problem
Existing thrust reverser systems for aircraft propulsion face challenges in increasing efficiency, reducing size and weight, and minimizing nacelle diameter while maintaining effective thrust reversal during landing.
Innovation Solution
The proposed solution involves a thrust reverser system with a scoop configuration featuring a serrated leading edge and protrusions, which directs airflow into upstream flow passages, enhancing fluid flow and momentum, and is connected to a bullnose ramp for efficient transition between forward and reverse thrust configurations.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Weight of moving object
If a conventional thrust reverser system is used, then the system can redirect airflow during landing, but the system size and weight are excessive
Solution Approach 1:
The thrust reverser system is divided into multiple cascade structures, each with individual flow passages and scoop elements. This segmentation allows the system to achieve effective thrust reversal through distributed flow control while reducing overall system weight by eliminating redundant structural components.
Solution Approach 2:
The invention introduces a new dimensional element by adding protrusions that extend into the flow passages from the cascade structures. These protrusions create three-dimensional flow control features within the existing two-dimensional flow passages, enhancing thrust reversal effectiveness without increasing system weight or size.
2Volume of moving object
If the thrust reverser system is made more compact, then the nacelle diameter can be reduced, but the efficiency of thrust reversal decreases
Solution Approach 1:
The cascade structures are equipped with locally optimized features including protrusions at specific positions within flow passages. These local modifications enhance flow control and thrust reversal efficiency in critical areas without requiring increases in overall system volume, allowing compact design while maintaining high efficiency.
Solution Approach 2:
The invention optimizes geometric parameters of the cascade structures, including the shape and position of protrusions, the angle and curvature of cascade surfaces, and the dimensions of flow passages. These parameter optimizations enable efficient thrust reversal in a compact volume by maximizing the aerodynamic effectiveness of each component.
3Productivity
If the scoop configuration is added with serrated leading edge, then fluid flow and momentum are enhanced, but device complexity increases
Solution Approach 1:
The scoop structure is merged with the cascade structures, combining the flow directing function of the scoop with the thrust reversal function of the cascades. The protrusions are integrated into the cascade structure itself rather than being separate components. This merging reduces device complexity by eliminating additional parts while maintaining enhanced fluid flow and momentum characteristics.
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 increases the efficiency of the thrust reverser system, allows for a more compact design, reduces weight, and improves the area match between the thrust reverser and bypass nozzle, resulting in enhanced negative thrust and reduced system size.
Implementation Method 1
The protrusions are operable to generate vortices in a second stream of the fluid passing by the serrated leading edge
Data Source
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AI summary
An assembly (72) is provided for an aircraft propulsion system (20). This aircraft propulsion system assembly (72) includes a thrust reverser system (38). The thrust reverser system (38) includes a cascade structure (68) and a scoop (94). The cascade structure (68) is configured with a plurality of flow passages (92). Each of the flow passages (92) extends through the cascade structure (68). The flow passages (92) include a first flow passage (92A). The scoop (94) is configured to direct fluid into at least the first flow passage (92A). The scoop (94) includes a serrated leading edge (102).