Abstract: A method of augmenting power output by a gas turbine engine includes channeling fuel into the gas turbine engine at a predetermined fuel flow rate to generate a first power output. Steam is then injected into the gas turbine engine at a first steam flow rate, and a firing temperature bias is determined based at least on the first steam flow rate. The predetermined fuel flow rate is then adjusted based on the determined firing temperature bias such that the gas turbine engine generates a second power output greater than the first power output.

Abstract: Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective power output to match a nominal power output value, and subsequently measuring an actual emissions value for each GT; adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual emissions value and a nominal emissions value at the ambient condition; and setting a target operating condition for each GT to match the adjusted operating condition after the adjusting of the operating condition.

Abstract: A method and system for transferring between combustion modes in a gas turbine engine is provided. A processor generates data representative of an initial set of splits for providing at least one of fuel and air to at least one combustor in the gas turbine engine. A gas turbine engine model module generates data representative of at least one engine operating condition. A first split calculation module generates data representative of at least one set of active control splits to control the engine in a first combustion mode, using as an input the initial split data. A second split calculation module generates data representative of at least one set of passive control splits to control the engine in at least a second combustion mode. Transfer between combustion modes may be accomplished via use of at least one of the active control splits and the passive control splits.

Abstract: A system may include a memory storing a turbomachinery degradation model configured to model degradation of a turbine system over time. Further, the system may include a controller communicatively coupled to the memory, which derives a turbomachinery wash timing based on at least one input signal from the turbine system and the turbomachinery degradation model. The turbomachinery degradation model may derive a desired wash point by estimating a modeled power of the turbine system, a modeled heat rate of the turbine system, or both. Furthermore, the controller may use the desired wash point to determine a time for washing components of the turbine system.

Abstract: A system may include a memory storing a turbomachinery degradation model configured to model degradation of a turbine system over time. Further, the system may include a controller communicatively coupled to the memory, which derives a turbomachinery wash timing based on at least one input signal from the turbine system and the turbomachinery degradation model. The turbomachinery degradation model may derive a desired wash point by estimating a modeled power of the turbine system, a modeled heat rate of the turbine system, or both. Furthermore, the controller may use the desired wash point to determine a time for washing components of the turbine system.

Abstract: A system includes a controller configured to control one or more parameters of a gas turbine engine based on a feedback and a predicted lifespan of one or more components of the gas turbine engine to substantially maintain at least one of power output or heat rate above a threshold level in response to degradation or fouling of the gas turbine engine.

Abstract: A method and system for transferring between combustion modes in a gas turbine engine is provided. A processor generates data representative of an initial set of splits for providing at least one of fuel and air to at least one combustor in the gas turbine engine. A gas turbine engine model module generates data representative of at least one engine operating condition. A first split calculation module generates data representative of at least one set of active control splits to control the engine in a first combustion mode, using as an input the initial split data. A second split calculation module generates data representative of at least one set of passive control splits to control the engine in at least a second combustion mode. Transfer between combustion modes may be accomplished via use of at least one of the active control splits and the passive control splits.

Abstract: A method of augmenting power output by a gas turbine engine includes channeling fuel into the gas turbine engine at a predetermined fuel flow rate to generate a first power output. Steam is then injected into the gas turbine engine at a first steam flow rate, and a firing temperature bias is determined based at least on the first steam flow rate. The predetermined fuel flow rate is then adjusted based on the determined firing temperature bias such that the gas turbine engine generates a second power output greater than the first power output.

Abstract: A system is provided that includes a memory storing a turbomachinery degradation model configured to model degradation of a turbomachinery over time. The system also includes a controller communicatively coupled to the memory and configured to control the turbomachinery based on a feedback signal and the turbomachinery degradation model. Moreover, the turbomachinery degradation model is configured to use a target power to derive a control parameter by estimating a modeled power of the turbomachinery, and the controller is configured to use the control parameter to control the turbomachinery.

Abstract: Embodiments of the disclosure relate to systems and methods for controlling a gas turbine. In one embodiment, a method can be provided. Measurement data associated with the operation of a gas turbine may be received to determine if the current operating state of the gas turbine is associated with a predefined risk. Thereafter, the measurement data and one or more model operating parameters for operation of the inlet bleed heat system that minimizes the risk may be identified in order to generate one or more control signals operable to adjust the operation of the inlet bleed heat system for the gas turbine to adjust the one or more model operating parameters.

Abstract: A system is provided that includes a memory storing a turbomachinery degradation model configured to model degradation of a turbomachinery over time. The system also includes a controller communicatively coupled to the memory and configured to control the turbomachinery based on a feedback signal and the turbomachinery degradation model. Moreover, the turbomachinery degradation model is configured to use a target power to derive a control parameter by estimating a modeled power of the turbomachinery, and the controller is configured to use the control parameter to control the turbomachinery.

Abstract: A system includes a controller configured to control one or more parameters of a gas turbine engine based on a feedback and a predicted lifespan of one or more components of the gas turbine engine to substantially maintain at least one of power output or heat rate above a threshold level in response to degradation or fouling of the gas turbine engine.

Abstract: Methods and systems for modeling turbine operation are disclosed. In one embodiment a method for modeling turbine operation may include: determining current performance parameters of a turbine; providing at least one external factor for current or future operation of the turbine; and modeling, by a predictive model, at least one operating characteristic of the turbine based at least in part on the current performance parameters of the turbine and the at least one external factor.

Abstract: A coordinated air-fuel controller and associated method provide a fuel controller, a combustion air controller and a steady-state air versus fuel model. The fuel controller generates a fuel control output signal and the combustion air controller generates a combustion air control output signal. The fuel controller determines a preliminary fuel control signal based on at least one of first and second loop control signals, and determines the fuel control output signal based on the preliminary fuel control signal. The steady-state air versus fuel model processes the preliminary fuel control signal to determine an expected steady-state combustion air control signal. The combustion air controller determines a preliminary combustion air control signal based on at least one of a third loop control signal and a fourth loop control signal, and determines the combustion air control output signal based on the preliminary combustion air control signal and the expected steady-state combustion air control signal.

Abstract: Methods, systems, and program products for improved accuracy in estimating a combustion reference temperature (CRT) are provided. In one embodiment, the invention provides a method of estimating a combustion reference temperature (CRT) in a gas turbine, the method comprising: obtaining a measurement of at least one dynamic operating condition of the gas turbine selected from a group consisting of: an ambient condition, a compressor condition, a fuel condition, and a turbine condition; inputting a measurement of the at least one operating condition into a physics-based model; calculating at least one estimated internal state for the gas turbine using the physics-based model; and calculating an estimated CRT based on the at least one gas turbine internal state.

Abstract: Methods and systems for modeling turbine operation are disclosed. In one embodiment a method for modeling turbine operation may include: determining current performance parameters of a turbine; providing at least one external factor for current or future operation of the turbine; and modeling, by a predictive model, at least one operating characteristic of the turbine based at least in part on the current performance parameters of the turbine and the at least one external factor.

Abstract: A method, system, and computer program for turbo-machine temperature control is presented. The method includes: receiving an exhaust temperature (Texh) parameter, a firing temperature (Tfire) parameter, and a combustor temperature rise (Trise) parameter of the turbo-machine during operation using a computing device; comparing the Texh parameter, the Tfire parameter, and the Trise parameter to corresponding Texh, Tfire, and Trise operational boundaries of the turbo-machine using the computing device; and creating an action in response to at least one of: the Texh parameter exceeding the Texh operational boundary, the Tfire parameter exceeding the Tfire operational boundary, and the Trise parameter exceeding the Trise operational boundary for a user.

Abstract: A coordinated air-fuel controller and associated method provide a fuel controller, a combustion air controller and a steady-state air versus fuel model. The fuel controller generates a fuel control output signal and the combustion air controller generates a combustion air control output signal. The fuel controller determines a preliminary fuel control signal based on at least one of first and second loop control signals, and determines the fuel control output signal based on the preliminary fuel control signal. The steady-state air versus fuel model processes the preliminary fuel control signal to determine an expected steady-state combustion air control signal. The combustion air controller determines a preliminary combustion air control signal based on at least one of a third loop control signal and a fourth loop control signal, and determines the combustion air control output signal based on the preliminary combustion air control signal and the expected steady-state combustion air control signal.