Abstract: Embodiments of the present disclosure are directed towards a system including a gas turbine engine, a selective catalytic reduction system, and a control system configured to regulate operation of the selective catalytic reduction system based at least partially on preset variations in an emissions compound of exhaust gases produced by the gas turbine engine.

Abstract: A system is provided for detecting and controlling flashback and flame holding in a combustor of a gas turbine. The system includes at least one flame indicator disposed in a combustor and at least one detector disposed downstream from the flame indicator. The flame indicator may be configured to produce light when exposed to a flame and the detector may be configured to detect the light produced by the flame indicator.

Abstract: A gas turbine includes a compressor section, a combustion section downstream from the compressor section, a turbine section downstream from the combustion section, and a controller. The controller controls the operation of the gas turbine at a reduced load, and is capable of querying a database including multiple sets of operational parameters for the gas turbine correlated with at least one measured output response at each set of operational parameters. One of the sets of operational parameters provides a desired gas turbine load that meets a target level for the output response. Related methods are also disclosed.

Abstract: Systems and methods for controlling mode transfers of a turbine combustor are provided. According to one embodiment, a system may include a controller to control a combustor, and a processor communicatively coupled to the controller. The processor may be configured to receive current operating conditions, target operating limits, and combustor transfer functions. The combustor transfer functions may be evaluated to estimate operating limits associated with one or more combustion modes under the current operating conditions. The estimated operating limits associated with the one or more combustor modes may be compared to the target operating limits, and, based on the comparison, at least one of the combustion modes may be selected. The combustor may then be selectively transferred to the selected combustion mode.

Abstract: A system and method control a gas turbine subject to fuel composition variation. The method includes operating a first effector to control the gas turbine based on fuel composition. The method also includes operating a second effector to maintain operation of the first effector within a first boundary limit, the second effector operation being initiated when the operating the first effector reaches a second boundary limit within the first boundary limit.

Abstract: Systems and methods for avoidance and correction of potentially adverse combustion states such as flame holding and flashback are disclosed. According to one embodiment of the disclosure, one or more sensors acquire sensor data from one or more sensors associated with combustion. An operational limit margin (OLM) is calculated using an OLM model and based at least in part on the sensor data. A determination is made as to the presence of a potentially adverse combustion state based at least in part on the OLM and the model. Once determined, corrective action may be taken to avoid an adverse combustion event prior to occurrence of the event.

Abstract: A system is provided for detecting and controlling flashback and flame holding in a combustor of a gas turbine. The system includes at least one flame indicator disposed in a combustor and at least one detector disposed downstream from the flame indicator. The flame indicator may be configured to produce light when exposed to a flame and the detector may be configured to detect the light produced by the flame indicator.

Abstract: Systems and methods for providing surge protection to turbine components are provided. A surge protection limit may be determined for the turbine component. One or more measurements associated with operation of the turbine component may be received and provided to a cycle model executed to predict an operating condition of the turbine component. The predicted operating condition of the turbine component may be adjusted based at least in part on the received one or more measurements. The surge protection limit may be adjusted based on the adjusted predicted operating condition of the turbine component.

Abstract: Methods and systems for controlling a combustor for a gas turbine engine are provided. According to one example embodiment, a system includes an air control assembly associated with at least one air path of a combustor for a gas turbine engine. Additionally, the system also includes at least one sensor for sensing at least one operating parameter of the gas turbine engine. Further, the system also includes a controller operable to receive at least one operating parameter sensed by the at least one sensor, and further operable to selectively control an air control assembly based at least in part on the at least one operating parameter sensed by the at least one sensor.

Abstract: Certain embodiments of the invention may include systems, methods, and apparatus for confirming ignition in a gas turbine. According to an example embodiment of the invention, a method is provided for confirming ignition associated with a gas turbine combustor. The method can include receiving one or more permissive signals associated with one or more gas flow control valves, receiving one or more fuel supply pressure signals, receiving one or more fuel igniter signals, and receiving one ore more compressor pressure discharge (CPD) signals. The method can also include determining an ignition status associated with the gas turbine combustor based at least in part on the one or more permissive signals, the one or more fuel supply pressure signals, the one or more fuel igniter signals, and a qualified change in the one or more CPD signals. The method can also include outputting an ignition status signal based on the determined ignition status.

Abstract: An insert for pre-mixing a secondary fuel in a pre-mixing annulus of a fuel nozzle assembly is disclosed. The insert includes a cartridge extending through at least a portion of the fuel nozzle assembly and configured to flow the secondary fuel therethrough. The insert further includes an adapter coupled to the cartridge, the adapter defining a fuel plenum and at least one radially extending injection bore. The at least one injection bore is configured to accept at least a portion of the secondary fuel from the cartridge and inject the secondary fuel into the pre-mixing annulus.

Abstract: Disclosed is a method and system for determining composition of a fuel entering a combustor. The method includes determining a temperature of the fuel entering the combustor, calculating a first estimated total fuel flow utilizing fuel properties and fuel nozzle effective area (Ae), and calculating a second estimated total fuel flow utilizing an aero-thermal cycle model analysis. The first estimated total fuel flow is compared to the second estimated total fuel flow and a lower heating value of the fuel is determined from a difference between the first estimated total fuel flow and the second estimated total fuel flow. A method and system for controlling a gas turbine includes calculating effects of the fuel composition on performance of the gas turbine and comparing one or more performance parameters to one or more parameter limits. One or more machine controls of the gas turbine are changed based on the results of the comparison.

Abstract: A method may detect a flashback condition in a fuel nozzle of a combustor. The method may include obtaining a current acoustic pressure signal from the combustor, analyzing the current acoustic pressure signal to determine current operating frequency information for the combustor, and indicating that the flashback condition exists based at least in part on the current operating frequency information.

Abstract: Systems and methods for providing surge protection to turbine components are provided. A surge protection limit may be determined for the turbine component. One or more measurements associated with operation of the turbine component may be received and provided to a cycle model executed to predict an operating condition of the turbine component. The predicted operating condition of the turbine component may be adjusted based at least in part on the received one or more measurements. The surge protection limit may be adjusted based on the adjusted predicted operating condition of the turbine component.

Abstract: A method may detect a flashback condition in a fuel nozzle of a combustor. The method may include obtaining a current acoustic pressure signal from the combustor, analyzing the current acoustic pressure signal to determine current operating frequency information for the combustor, and indicating that the flashback condition exists based at least in part on the current operating frequency information.

Abstract: Embodiments of methods and systems for controlling a combustor for a gas turbine engine are provided. According to one example embodiment, a system includes an air control assembly associated with at least one air path of a combustor for a gas turbine engine. Additionally, the system also includes at least one sensor for sensing at least one operating parameter of the gas turbine engine. Further, the system also includes a controller operable to receive at least one operating parameter sensed by the at least one sensor, and further operable to selectively control an air control assembly based at least in part on the at least one operating parameter sensed by the at least one sensor.

Abstract: A method for simulating a gas turbine including the steps of: sensing values of a plurality of first operating parameters of an actual gas turbine; applying the sensed values of the first operating parameters to a model of the gas turbine, wherein the model generates a plurality of predicted second operating parameters; determining difference values between the predicted second operating parameters and corresponding sensed second operating parameters of the actual gas turbine; modifying the difference values based on tuning factors generated by a Kalman filter gain matrix during operation of the gas turbine, and using the adjusted difference values to adjust the model of the gas turbine. The method may further comprise generating the tuning factors by applying to the model the sensed values of the plurality of first operating parameters and perturbated values of the adjusted different values to determine optimal tuning factors.

Abstract: A system includes a correction factor module that receives modeled data generated from a simulation model and measured data, that determines a difference between the modeled data and the measured data, and that applies a filter to the difference to determine a correction value; and a performance monitoring module that analyzes the correction value, and that generates a component alert based on the analysis.

Abstract: Disclosed is a method and system for determining composition of a fuel entering a combustor. The method includes determining a temperature of the fuel entering the combustor, calculating a first estimated total fuel flow utilizing fuel properties and fuel nozzle effective area (Ae), and calculating a second estimated total fuel flow utilizing an aero-thermal cycle model analysis. The first estimated total fuel flow is compared to the second estimated total fuel flow and a lower heating value of the fuel is determined from a difference between the first estimated total fuel flow and the second estimated total fuel flow. A method and system for controlling a gas turbine includes calculating effects of the fuel composition on performance of the gas turbine and comparing one or more performance parameters to one or more parameter limits. One or more machine controls of the gas turbine are changed based on the results of the comparison.

Abstract: Disclosed is a method and system for determining composition of a fuel entering a combustor. The method includes determining a temperature of the fuel entering the combustor, calculating a first estimated total fuel flow utilizing fuel properties and fuel nozzle effective area (Ae), and calculating a second estimated total fuel flow utilizing an aero-thermal cycle model analysis. The first estimated total fuel flow is compared to the second estimated total fuel flow and a lower heating value of the fuel is determined from a difference between the first estimated total fuel flow and the second estimated total fuel flow. A method and system for controlling a gas turbine includes calculating effects of the fuel composition on performance of the gas turbine and comparing one or more performance parameters to one or more parameter limits. One or more machine controls of the gas turbine are changed based on the results of the comparison.