A system (10) for a gas turbine engine (20) includes an engine control system (22). The engine control system (22) includes a processor (62) in communication with 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), determine a normalized value of the engine parameter for an uninstalled gas turbine engine based on the current engine installation configuration and one or more of a normalized engine power ("SHPN") of the gas turbine engine (20), an airspeed, or an altitude, determine a fully deteriorated engine ("FDE") value of the engine parameter using the 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
Elektronische Ressource
Englisch
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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