Methods and apparatus for operating gas turbine engines
AssigneeGeneral Electric Company
InventorJames William Simunek
Life of this patent
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Abstract
A fuel control system for a gas turbine engine includes logic that is used to facilitate enhanced compressor stall margin when the engine is operating in potential icing conditions is described. The fuel control system is coupled to at least one fuel regulator within the engine, and receives input from a plurality of sensors coupled to the engine. More specifically, the system receives input from environmental sensors, as well as inputs representing compressor inlet temperature, compressor discharge pressure, and corrected core engine speed. Furthermore, the fuel control system also receives input from the other engine fuel regulators.
Claims11
A control system for controlling an aircraft engine, said control system coupled to the aircraft engine for receiving a plurality of reference inputs from engine sensors coupled to the engine including a compressor discharge pressure, a corrected core speed and a compressor inlet temperature, said control system comprising stored values of corrected fuel flow in a corrected fuel flow schedule, said control system controls a fuel system regulator coupled to the aircraft engine by producing a commanded fuel flow based on the corrected fuel flow stored values and a fuel flow deviation that is based on the current engine operating conditions as determined by the engine sensor values.
An aircraft engine fuel control system, said system coupled to the aircraft engine to receive reference inputs from the engine including a compressor discharge pressure, a corrected core speed and a compressor inlet temperature to determine a state of the aircraft engine, said system configured to generate a commanded fuel flow in response to a corrected fuel flow variable determined with a corrected fuel flow schedule, a delta fuel flow variable to decrease fuel enrichment to the aircraft engine determined with a delta fuel flow schedule, and the engine sensor input values.
Dependencies are inferred from the claim text.