For helicopter turbo-shaft engines good transient handling is a key requirement. The acceleration performance is predominantly restricted by the aerodynamic stability limit of the compressor. An exceedence of this limit results in an engine surge, causing high mechanical stress on the engine and an immediate, severe loss of shaft power. Helicopter engines in particular are affected, because these engines are frequently operated close to the surge line during accelerations and because the nominal stability limit may be changed by some factors, e.g. inlet distortions. On a test bed engine equipped with a digital engine control system, the surge inception process was studied in detail. Based on these insights a compressor monitoring system was developed, which monitors pressure signals for stall precursors. As soon as those indicators are detected, appropriate control actions are taken to avoid the surge event. In addition new control laws were added to the control system in order to provide an improved recovery capability from engine surge.
Advanced engine surge monitoring and recovery control for turbo-shaft engines
Fortgeschrittene Überwachung des Triebwerkspumpens und Regenerierungssteuerung für Propeller-Turbinen-Luftstrahltriebwerke
1998
20 Seiten, 19 Bilder, 12 Quellen
Aufsatz (Konferenz)
Englisch
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