A system for a gas turbine engine (20) includes an engine control system (22). The engine control system (22) includes a processor (62) and a non-transitory memory (64) storing instructions, which instructions when executed by the processor (62), cause the processor (62) to: obtain a current engine installation configuration for the gas turbine engine (20) and the aircraft, determine an expected normalized value of the engine parameter based on the current engine installation configuration and one or more of a normalized engine power (SHPN) of the gas turbine engine (20), an engine inlet temperature, an airspeed, or an altitude, determine a fully deteriorated engine (FDE) value of the engine parameter using the expected normalized value of the engine parameter, determine a current value of the engine parameter for the gas turbine engine (20), and determine the engine operating margin for the engine parameter based on the FDE value of the engine parameter and the current value of the engine parameter.
SYSTEMS AND METHODS FOR DETERMINING GAS TURBINE ENGINE OPERATING MARGINS
SYSTEME UND VERFAHREN ZUR BESTIMMUNG VON GASTURBINENTRIEBWERKS-BETRIEBSMARGEN
SYSTÈMES ET PROCÉDÉS DE DÉTERMINATION DE MARGES DE FONCTIONNEMENT DE MOTEUR À TURBINE À GAZ
2024-02-28
Patent
Electronic Resource
English
IPC: | F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / G06F ELECTRIC DIGITAL DATA PROCESSING , Elektrische digitale Datenverarbeitung |
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