Ducted fan gas turbine engine control system
AssigneeROLLS-ROYCE plc
InventorArthur L Rowe
Life of this patent
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Abstract
A control system for a ducted fan gas turbine engine (10) comprises a control unit (29) that receives input signals from a pressure transducer (27) located within the engine's fan duct (11) downstream of the fan (13) and a rotational speed transducer (32) mounted adjacent the shaft (24) carrying the fan (13). In the event of the control unit (29) detecting a fall in the air pressure downstream of the fan (13) and an increase in fan speed, it commands a temporary reduction in the fuel flow to the engine (10). Such a decrease in the air pressure downstream of the fan (13) and increase in fan speed is indicative of the fan (13) entering a stall condition. The temporary reduction in fuel flow to the engine (10) enables the fan (13) to recover from that stall condition.
Claims8
A control system for a ducted fan gas turbine engine having a propulsive fan driven by a core engine, said control system comprising means to monitor the rotational speed of said propulsive fan, means to monitor the power absorption of said fan and means to provide a temporary reduction in the fuel flow to said core engine in the event of a fall in the monitored power absorption of said fan accompanied by an increase in the monitored rotational speed of said fan.
Dependencies are inferred from the claim text.