Patent ID: 8762025
Filing Date: 2014-06-24
Classification: F02C,F05D,Y02T

Abstract:
1. A method for controlling a gas turbine including a compressor assembly including at least one portion of variable geometry, a combustion chamber, a turbine assembly, and a control system, the method comprising: computing, by the system, a C/P Fuel Air Ratio setpoint value as a function of a desired speed of the gas turbine where C is a rate of fuel flow to be fed to the combustion chamber and P is a pressure at an outlet of the compressor assembly; computing, by the system, a minimum and a maximum Fuel Air Ratio threshold value depending on a thermodynamic state of the gas turbine; thresholding, by the system, the Fuel Air Ratio setpoint value for maintaining the Fuel Air Ratio setpoint value greater than or equal to the minimum threshold value and less than or equal to the maximum threshold value; generating, by the system, a flow setpoint value for fuel to be fed to the combustion chamber based on the Fuel Air Ratio thresholded setpoint value; controlling a position of the variable geometry portion by controlling an actuator as a function of the difference between detected position information representative of an instantaneous position of the variable geometry portion and setpoint position information; and automatically adjusting, the threshold values, by the system, by real time computing as a function of the detected position information or of the difference between the detected position information and the setpoint position information.