CONTROL TECHNOLOGIES FOR TURBINE ENGINE WITH INTEGRATED INLET PARTICLE SEPARATOR AND INFRARED SUPPRESSION SYSTEM

A propulsion system (10) includes a gas turbine engine (14), an inlet particle separator (12), an infrared suppression system (32), and an engine controller (34). The engine controller may be configured to determine an activation state of the inlet particle separator, adjust one or more engine opera...

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Bibliographische Detailangaben
Hauptverfasser:	Dougherty, Michael P, Zeller, Robert J, Skertic, Richard J, Cline, C Harvey O
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING PERFORMING OPERATIONS PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL SEPARATION TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	A propulsion system (10) includes a gas turbine engine (14), an inlet particle separator (12), an infrared suppression system (32), and an engine controller (34). The engine controller may be configured to determine an activation state of the inlet particle separator, adjust one or more engine operating parameters based on the activation state, and control the gas turbine engine based on the adjusted engine operating parameters. The engine operating parameters may be adjusted based on inlet flow, which is determined based on the activation state. The engine controller may be further configured to determine an activation state of the infrared suppression system, adjust one or more engine operating parameters based on the activation state, and control the gas turbine engine based on the adjusted engine operating parameters. The engine operating parameters may be adjusted based on backpressure, which is determined based on the activation state.