Abstract: A method of controlling an operating temperature of a first combustion zone of a combustor of a rotary machine includes determining a current operating temperature and a target operating temperature of a first combustion zone using a digital simulation. The method further includes determining a derivative of the current operating temperature with respect to a current fuel split using the digital simulation. The fuel split apportions a total flow of fuel to the combustor between the first combustion zone and a second combustion zone. The method also includes calculating a calculated fuel split that results in a calculated operating temperature approaching the target operating temperature. The method further includes channeling a first flow of fuel to the first combustion zone and a second flow of fuel to the second combustion zone.

Abstract: A gas turbine engine that includes a stage of guide vanes, a compressor downstream from the stage of guide vanes, and a combustor downstream from the compressor. The combustor includes a primary combustion zone and a secondary combustion zone downstream from the primary combustion zone. The primary combustion zone includes an exit configured to channel combustion gases towards the secondary combustion zone. A controller is communicatively coupled with the stage of guide vanes, the controller configured to monitor a temperature at the exit of the primary combustion zone, and selectively open and close the guide vanes to maintain the temperature within a predefined temperature range.

Abstract: A method of controlling an operating temperature of a first combustion zone of a combustor of a rotary machine includes determining a current operating temperature and a target operating temperature of a first combustion zone using a digital simulation. The method further includes determining a derivative of the current operating temperature with respect to a current fuel split using the digital simulation. The fuel split apportions a total flow of fuel to the combustor between the first combustion zone and a second combustion zone. The method also includes calculating a calculated fuel split that results in a calculated operating temperature approaching the target operating temperature. The method further includes channeling a first flow of fuel to the first combustion zone and a second flow of fuel to the second combustion zone.

Abstract: A gas turbine engine that includes a stage of guide vanes, a compressor downstream from the stage of guide vanes, and a combustor downstream from the compressor. The combustor includes a primary combustion zone and a secondary combustion zone downstream from the primary combustion zone. The primary combustion zone includes an exit configured to channel combustion gases towards the secondary combustion zone. A controller is communicatively coupled with the stage of guide vanes, the controller configured to monitor a temperature at the exit of the primary combustion zone, and selectively open and close the guide vanes to maintain the temperature within a predefined temperature range.

Abstract: A fuel system is provided and includes inert gas, fuel and air sources to provide a supply of inert gas, fuel and air, respectively, piping including valves delimiting cavities therein to which the inert gas, fuel and air are supplied such that the inert gas separates the respective cavities containing fuel and air, a pressure control valve disposed on the piping to modulate a pressure of the inert gas supplied to the piping and a controller coupled to the pressure control valve to control an operation thereof in accordance with at least variable pressures of the fuel and air in the respective cavities containing the fuel and the air.

Abstract: Embodiments of the present invention incorporate a relatively slow acting valve to throttle the fuel flow through the compressor. Embodiments of the present invention seek to reduce the need for recirculating compressed fuel that is not needed by the turbomachine. This may increase the net power output and efficiency of a turbomachine-fuel gas compressor system.

Abstract: A system and method for providing fuel mixes a first fuel with a second fuel at a mixing point to create a mixed fuel having a first calorie content. A control valve is located upstream of the mixing point. A process system downstream of the mixing point processes the mixed fuel to create a processed mixed fuel having a second calorie content. A first control signal is reflective of the first calorie content of the mixed fuel. A second control signal is reflective of the second calorie content of the processed mixed fuel. A third control signal is reflective of the operating level of the combustion engine. A controller connected to the control valve operates the control valve based on the first, second, and third control signals.

Abstract: The present invention pertains generally to a system and method for providing fuel having a desired calorie content to a combustion engine over a range of operating levels. The system mixes a first fuel from a first fuel supply pipe with a second fuel from a second fuel supply pipe at a mixing point to create a mixed fuel having a first calorie content. A control valve is located in the second fuel supply pipe upstream of the mixing point. A process system downstream of the mixing point processes the mixed fuel to create a processed mixed fuel having a second calorie content. A first control signal is reflective of the first calorie content of the mixed fuel. A second control signal is reflective of the second calorie content of the processed mixed fuel. A third control signal is reflective of the operating level of the combustion engine. A controller connected to the control valve operates the control valve based on the first, second, and third control signals.