Fuel flow is scheduled to a plurality of combustion stages by putting a plurality of engine fuel flow governors in parallel with each other and letting the governor which outputs the lowest fuel demand signal be the one which schedules the total fuel flow to the engine. Fuel flows to the plurality of combustion stages are then individually scheduled to achieve the lowest fuel flows consistent with predefined temperature limits for the corresponding stages of combustion.

Turbine engine control system

The invention provides a method of operating a gas turbine arranged in a power generation system and comprising a source of compressed air, a combustor having a combustion chamber and multiple burners. A gas turbine controller controls the activation and deactivation of the single burners and/or burner groups according to a switching criterion that is proportional to the difference between a combustion chamber air inlet temperature and a temperature downstream of the combustion chamber. The switching criterion according to the invention fully accounts for large temperature fluctuations of the combustion chamber inlet air, which then result in only relatively small variations in burner equivalence ratio. The invention is particularly suited for application in compressed air energy power generation plants.

Method of operation of gas turbine having multiple burners

A control system and methodology for a gas turbine having multiple fuel valves for multiple combustion chambers involves tuning the fuel values to associated combustion chambers to optimize nitrous oxide emissions; dynamic pressure, and variation in fuel/air ratio. Further, fine tuning of the fuel values is then used to maintain dynamic pressure oscillations, nitrous oxide emissions or variation in fuel/air ratio within predetermined limits.

Performance enhanced control of dln gas turbines

A system for tuning the operation of a gas turbine is provided based on measuring operational parameters of the turbine and directing adjustment of operational controls for various operational elements of the turbine. A controller is provided for communicating with sensors and controls within the system. The controller receiving operational data from the sensors and comparing the data to stored operational standards to determining if turbine operation conforms to the standards. The controller then communicates selected adjustment in an operational parameter of the turbine. The controller then receives additional operational data from the sensors to determine if an additional adjustment is desired or is adjustment is desired of a further selected operational parameter.

Automated tuning of gas turbine combustion systems

An actual Wobbe Index is calculated for a turbine and compared to a reference Wobbe Index. By comparing the actual and reference Wobbe Indices and recognizing that the reference Wobbe Index has acceptable combustion dynamics, a measure of the combustion dynamics of the operating turbine can be obtained. To lower the possibility of combustion dynamics, causing combustor distress, a feedback signal is provided to change the temperature of the fuel gas provided the combustor. Since the Wobbe Index is a function of temperature and fuel composition, the variation in temperature can be effected to change the Wobbe Index to a reference Wobbe Index having known low combustion dynamics.

Combustion dynamics control for variable fuel gas composition and temperature based on gas control valve feedback

A fuel trimming unit has been adapted to each combustion chamber in a multi-chamber combustor of an industrial gas turbine. The fuel trim unit matches the combustion air flow into each combustion chamber. This adjusts the fuel-air mixture to account for air flow variations into the individual combustion reaction zones of each combustion chamber. Because of the fuel trim unit, a uniform fuel-air mixture is provided to each combustion chamber in a gas turbine. The fuel trim unit is adjusted using sensor inputs of the fuel flow rate to each combustion chamber, the dynamic pressure in each combustion chamber, and the turbine exhaust temperature.

Iasillo Robert Joseph

Papers

Fuel trim system for a multiple chamber gas turbine combustion system