Patent ID: 8061118
Filing Date: 2011-11-22
Classification: F02C,F23N,F23R

Abstract:
1. A method for adjusting fuel flow to individual combustion chambers in a gas turbine having fuel nozzles for each combustion chamber, manifolds for supplying fuel to at least one fuel nozzle in each combustion chamber, wherein the manifolds have flow metering devices for said fuel nozzles and a controller for adjusting the flow metering devices, said method comprising: a. supplying fuel to the combustion chambers through at least one of said manifolds; b. combusting the fuel in the combustion chambers and generating exhaust gases which drive the gas turbine; c. sensing a condition of the exhaust gases at various exhaust regions in the exhaust gas before performing step d; d. actuating a corresponding flow metering device to the one of the combustion chambers to adjust fuel flowing to the one of the combustion chambers; e. after step d, sensing a condition of the exhaust gases at various exhaust regions in the exhaust gases; f. determining a change in the condition of the exhaust gas due to the actuation of the corresponding flow metering device in step d and based on a comparison of the conditions of the exhaust gases sensed in steps c and e; g. correlating the change in the sensed condition of the exhaust gases to the at least one combustion chamber, and h. repeating steps d through g wherein the one of the combustion chambers becomes another one of the combustion chambers.