Thrust Reverser Cascade Flow Disrupters for Noise Reduction
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Solution Overview
Problem
Existing thrust reverser systems for aircraft propulsion systems suffer from noise generation due to gas flow interaction with cascade structures, which affects the overall efficiency and noise signature of the aircraft.
Innovation Solution
The introduction of a cascade structure with a thrust reverser cascade and a flow disruptor, such as a groove or protrusion, arranged at the cascade inner face and forward of the vanes, disrupts the boundary layer air flow, reducing noise generation by minimizing interaction with the vanes.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If a thrust reverser cascade with vanes is used to redirect gas flow, then reverse thrust is produced, but noise is generated due to gas flow interaction with the cascade structures
Solution Approach 1:
A flow disruptor element is introduced as an intermediary component between the incoming gas flow and the cascade vanes. This flow disruptor modifies the boundary layer characteristics of the gas flow before it reaches the vanes, reducing the harmful interaction and resulting noise while maintaining the thrust reversal function
Solution Approach 2:
The flow disruptor changes the physical parameters of the gas flow, specifically the boundary layer properties, by introducing controlled disturbances. This modification alters the flow characteristics to reduce noise generation during thrust reversal operation
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 implementation of the flow disruptor within the thrust reverser cascade effectively attenuates noise generation, enhancing the operational efficiency and reducing the noise signature of the aircraft propulsion system.
Implementation Method 1
The flow disruptor is configured to disrupt boundary layer air flowing towards the vanes
Data Source
AI summary
An apparatus is provided for an aircraft propulsion system. This apparatus includes a cascade structure including a thrust reverser cascade and a flow disruptor. The thrust reverser cascade extends longitudinally between a cascade forward end and a cascade aft end. The thrust reverser cascade extends laterally between a cascade first side and a cascade second side. The thrust reverser cascade extends radially between an inner face and an outer face. The thrust reverser cascade includes a plurality of vanes arranged in a longitudinally extending array along the inner face. The flow disruptor is arranged at the cascade inner face and forward of the vanes. The flow disruptor is configured to disrupt boundary layer air flowing towards the vanes.