METHOD AND APPARATUS FOR ACTUATING FUEL TRIM VALVES IN A GAS TURBINE

摘要

A gas turbines (10) has multiple combustion chambers (14), and within each chamber are multiple fuel nozzles (16, 18, and 20). Each nozzle has its own fuel control valve (28, 30, 32) to control the fuel flowing to the nozzles. To minimize the pressure drop through the fuel control valves, multiple manifolds (22, 24, and 26) are employed. A plurality of thermocouples (40) for measuring exhaust gas from said multiple combustion chambers are employed to sense gas exhaust temperature. In one method of operation, because it is desirable that each combustion chamber in the gas turbine be well balanced relative to the remaining combustion chambers, the multiple combustion chambers are tuned such that no specific combustion chamber is rich or lean, and all are operating within about 1 % of the average of the remaining combustion chambers.