A method for a gas turbine engine includes calculating an inlet airflow distortion value at a reference area within an airflow duct and in front of a fan of the gas turbine engine. The inlet airflow distortion value is indicative of an air pressure of an air vortex at the reference area caused by a set of crosswind conditions. The calculating is based on a ratio between an inlet airflow static air pressure in the reference area and a total ambient air pressure. The inlet airflow distortion value is compared to a threshold corresponding to a permissible amount of inlet airflow distortion at the reference area for the set of crosswind conditions, and, based on the comparison indicating that the inlet airflow distortion exceeds the threshold, an inlet airflow distortion notification is provided. A system for a gas turbine engine and a method for a gas turbine engine are also disclosed.
METHOD OF INLET DISTORTION PREDICTION AND MONITORING
2025-01-02
Patent
Electronic Resource
English
IPC: | G01M TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES , Prüfen der statischen oder dynamischen Massenverteilung rotierender Teile von Maschinen oder Konstruktionen / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / G08G Anlagen zur Steuerung, Regelung oder Überwachung des Verkehrs , TRAFFIC CONTROL SYSTEMS |
NTRS | 1955
|NTRS | 1955
|NTRS | 1955
|PREDICTION OF INLET DISTORTION OF BOUNDARY LAYER INGESTING PROPULSION SYSTEM
European Patent Office | 2020
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