CIRCUMFERENTIALLY TAILORED INLET GUARD FOR AN AIRCRAFT ENGINE INLET
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United States of America Patent
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Issued Date -
Apr 10, 2025
app pub date -
Oct 5, 2023
filing date -
Oct 5, 2023
priority date (Note) -
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status (Latency Note)
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Abstract
A system is provided for an aircraft. This aircraft system includes a gas turbine engine, a flowpath and an inlet guard. The gas turbine engine includes a compressor section. The flowpath projects longitudinally into the gas turbine engine from an airflow inlet and longitudinally through the compressor section. The inlet guard extends across the flowpath longitudinally upstream of the compressor section. The inlet guard extends circumferentially about an axis. The inlet guard includes a first screen and a second screen. The first screen includes a plurality of first perforations with a first perforation size. The second screen is circumferentially adjacent the first screen about the axis. The second screen includes a plurality of second perforations with a second perforation size that is different than the first perforation size.
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