An assembly for an aircraft propulsion system includes a case assembly, at least one seal, a first pressure sensor, and a computing system. The case assembly forms a cavity. The at least one seal is disposed on the case assembly. The at least one seal is configured to seal the cavity. The first pressure sensor is in fluid communication with the cavity. The first pressure sensor is configured to measure a first pressure within the cavity. The computing system is in signal communication with the first pressure sensor. The computing system includes a processor in communication with a non-transitory memory storing instructions, which instructions when executed by the processor, cause the processor to compare the first pressure to a pressure threshold value to identify a wear condition of the at least one seal.
SYSTEMS AND METHODS FOR IDENTIFYING A CONDITION OF GAS TURBINE ENGINE SEALS
SYSTEMES ET METHODES POUR DETERMINER UNE CONDITION DE JOINTS DE TURBINE A GAZ
2024-04-04
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / G05D SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES , Systeme zum Steuern oder Regeln nichtelektrischer veränderlicher Größen |
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