Abstract: The systems, methods, and computer-readable media set a gas turbine firing temperature to maintain gas turbine metal surface temperatures. In certain embodiments, a method of setting a gas turbine firing temperature is disclosed that may comprise determining a critical temperature at which ash from ash bearing fuels becomes unremovable by conventional water wash procedures, determining hot gas path component metal surface temperatures, and adjusting the gas turbine firing temperature to maintain the metal surface temperatures below the critical temperature. Determining the metal surface temperatures may be based at least in part on measured gas turbine parameters, gas turbine performance models, and empirical models.

Abstract: A method of cooling a gas turbine engine is provided. The method includes removing a load from the gas turbine engine. The method also includes operating the gas turbine engine at a rated speed of the gas turbine engine. The method further includes modulating an angle of at least one stage of inlet guide vanes disposed proximate an inlet of a compressor section of the gas turbine engine, wherein modulating the angle modifies a flow rate of an inlet flow for reducing a cooling time of the gas turbine engine.

Abstract: A method, system and generator for controlling a flow of fuel during a shut down of a gas turbine generator is disclosed. A first fuel flow rate to a combustion flame of the gas turbine generator is set at a beginning of a shut-down sequence. A sensor is configured to measure a rotation rate of a turbine rotor of the generator. A processor determines a deceleration of the turbine rotor from the measured rotation rates corresponding to the first fuel flow rate and compares the determined deceleration to a selected criterion. When the deceleration matches the selected criterion, the processor adjusts the fuel flow rate from the first fuel flow rate to a second fuel flow rate.

Abstract: A method of operating a combustor in a gas turbine that receives combustion air from a compressor includes a) controlling combustion temperature as a function of compressor discharge air bled from the compressor by determining a minimum amount of compressor discharge air required for maintaining a predetermined minimum combustion temperature; and b) bleeding compressor discharge air in excess of the minimum amount from the compressor via a control valve.

Abstract: A method of operating a combustor in a gas turbine that receives combustion air from a compressor includes a) controlling combustion temperature as a function of compressor discharge air bled from the compressor by determining a minimum amount of compressor discharge air required for maintaining a predetermined minimum combustion temperature; and b) bleeding compressor discharge air in excess of the minimum amount from the compressor via a control valve

Abstract: An optimized combustor cooperating with a compressor in driving a gas turbine comprises a cylindrical outer combustor wall having an upstream fuel entry region and a downstream turbine entry region. An array of mixing holes are disposed about the periphery of the outer combustor wall adjacent to the fuel entry region so as to lower Nox production therein. An array of dilution holes are medially disposed within the outer combustor wall to provide an entry for dilution air to the combustor.