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.
CIRCUMFERENTIALLY TAILORED INLET GUARD FOR AN AIRCRAFT ENGINE INLET
2025-04-10
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
VARIABLE INLET GUARD SCREEN FOR AN INLET OF AN AIRCRAFT ENGINE
European Patent Office | 2025
|Aircraft-engine inlet and exhaust porting
Engineering Index Backfile | 1944
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