Patent ID: 6364602
Filing Date: 2002-04-02
Classification: F01D,F02C,F04D

Abstract:
A method of controlling a gas turbine to optimize performance thereof, comprising:providing a control system including a controller coupled to a plurality of turbine actuator systems, said actuator systems being coupled to a gas turbine that includes inlet guide vanes (IGV), a compressor, a combustor, and a combustion turbine, so as to control the operation of the gas turbine in response to respective actuator system control signals generated by the controller, said control system further comprising an operator interface; the controller comprising a processor for generating said respective actuator system control signals in correspondence with input from said operator interface and a plurality of turbine operating condition signals, said control system being programmed to define a pressure ratio Operating Limit Line that provides a surge margin from a surge line defined by pressure ratios associated with physical limits to compressor operation for the gas turbine; during operation of said gas turbine, determining a compressor air-flow rate; and comparing said determined air-flow rate to a stored air-flow rate.