Thrust reverser cascade with one or more flow stabilizers
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United States of America Patent
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Jan 16, 2024
Grant Date -
N/A
app pub date -
Aug 1, 2022
filing date -
Aug 1, 2022
priority date (Note) -
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status (Latency Note)
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Abstract
An apparatus is provided for an aircraft propulsion system. This apparatus includes a thrust reverser cascade extending 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 a cascade inner face and a cascade outer face. The thrust reverser cascade includes a plurality of vanes and a wall. The vanes are arranged in a longitudinally extending array along the cascade inner face. The vanes include a first vane and a second vane. The wall is configured to block gas flow radially through the thrust reverser cascade between the first vane and the second vane.
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