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 gas turbine engine having a combustor, and a fuel blending system. The fuel blending system further includes a first fuel supply configured to supply a first fuel, a second fuel supply configured to supply a second fuel, a first fuel circuit, a second fuel circuit, and a controller. The first fuel circuit may be configured to blend the first fuel and the second fuel to form a first to form a first fuel mixture. The second fuel circuit may be configured to blend the first fuel and the second fuel to form a second fuel mixture. The controller may be configured to regulate blending of the first fuel mixture and the second fuel mixture based on a measured operating parameter of the combustor.

Abstract: A system includes a gas turbine engine having a combustor, and a fuel blending system. The fuel blending system further includes a first fuel supply configured to supply a first fuel, a second fuel supply configured to supply a second fuel, a first fuel circuit, a second fuel circuit, and a controller. The first fuel circuit may be configured to blend the first fuel and the second fuel to form a first fuel mixture. The second fuel circuit may be configured to blend the first fuel and the second fuel to form a second fuel mixture. The controller may be configured to regulate blending of the first fuel mixture and the second fuel mixture based on a measured composition of the first fuel.

Abstract: A system, method, and computer-readable medium for blending a fuel for use in a gas turbine are disclosed. A measurement of a heating value of a process gas and a measurement of a molecular weight of the process gas is obtained. An estimate of a composition of the process gas is obtained using the obtained measurement of the heating value and the obtained measurement of the molecular weight. A blending ratio of the process gas and a natural gas is selected based on the estimate of the composition of the process gas. The process gas and the natural gas are then blended according to the selected blending ratio to obtain a fuel mixture for use in the gas turbine.

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 gas turbine engine having a combustor, and a fuel blending system. The fuel blending system further includes a first fuel supply configured to supply a first fuel, a second fuel supply configured to supply a second fuel, a first fuel circuit, a second fuel circuit, and a controller. The first fuel circuit may be configured to blend the first fuel and the second fuel to form a first to form a first fuel mixture. The second fuel circuit may be configured to blend the first fuel and the second fuel to form a second fuel mixture. The controller may be configured to regulate blending of the first fuel mixture and the second fuel mixture based on a measured operating parameter of the combustor.

Abstract: A system includes a gas turbine engine having a combustor, and a fuel blending system. The fuel blending system further includes a first fuel supply configured to supply a first fuel, a second fuel supply configured to supply a second fuel, a first fuel circuit, a second fuel circuit, and a controller. The first fuel circuit may be configured to blend the first fuel and the second fuel to form a first fuel mixture. The second fuel circuit may be configured to blend the first fuel and the second fuel to form a second fuel mixture. The controller may be configured to regulate blending of the first fuel mixture and the second fuel mixture based on a measured composition of the first fuel.

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 a semi-closed power cycle system. The controller is configured to receive at least one of a first signal indicative of an oxygen concentration within a first gas flow through a primary compressor, a second signal indicative of power output by the semi-closed power cycle system, a third signal indicative of a temperature of a second gas flow through a turbine, and a fourth signal indicative of a mass flow balance within the semi-closed power cycle system. The controller is also configured to adjust at least one of the first gas flow through the primary compressor, a fuel flow into a combustor, a fraction of the first gas flow extracted from the primary compressor, and an air flow through a feed compressor based on the at least one of the first signal, the second signal, the third signal, and the fourth signal.

Abstract: A combined cycle power plant includes a compressor section including a compressor inlet and a compressor outlet, and a turbine section operatively connected to the compressor section. The turbine section includes a turbine inlet and a turbine outlet. A heat recovery steam generator (HRSG) is fluidly connected to the turbine outlet. A combustor includes a head end and a combustor discharge. The head end is fluidly connected to the compressor outlet and the combustor discharge is fluidly connected to the turbine inlet. A carbon dioxide collection system is fluidly connected to one of the compressor outlet and the head end of the combustor. The carbon dioxide collection system is configured and disposed to extract a first fluid comprising carbon dioxide and a second fluid from a substantially oxygen free fluid flow passed from the one of the compressor outlet and the head end of the combustor.

Abstract: A method for controlling the generation of turbine cooling air from air extracted from a compressor of a gas turbine including: extracting compressed air from a low pressure and a high pressure stage of the compressor; adding in an ejector the compressed air from the low pressure stage to the air from the high pressure stage and discharging the combined air as turbine cooling air; bypassing the ejector with a bypass portion of the extracted compressed air from the high pressure stage; in response to turning on the flow of extracted compressed air from the low pressure stage, changing a set point for an actual pressure ratio that includes a pressure of the turbine cooling air, and adjusting the bypass flow in response to the changed set point to cause the actual pressure ratio to approach the changed set point.

Abstract: A method for controlling the generation of turbine cooling air from air extracted from a compressor of a gas turbine including: extracting compressed air from a low pressure and a high pressure stage of the compressor; adding in an ejector the compressed air from the low pressure stage to the air from the high pressure stage and discharging the combined air as turbine cooling air; bypassing the ejector with a bypass portion of the extracted compressed air from the high pressure stage; in response to turning on the flow of extracted compressed air from the low pressure stage, changing a set point for an actual pressure ratio that includes a pressure of the turbine cooling air, and adjusting the bypass flow in response to the changed set point to cause the actual pressure ratio to approach the changed set point.

Abstract: A combined cycle power plant includes a compressor section including a compressor inlet and a compressor outlet, and a turbine section operatively connected to the compressor section. The turbine section includes a turbine inlet and a turbine outlet. A heat recovery steam generator (HRSG) is fluidly connected to the turbine outlet. A combustor includes a head end and a combustor discharge. The head end is fluidly connected to the compressor outlet and the combustor discharge is fluidly connected to the turbine inlet. A carbon dioxide collection system is fluidly connected to one of the compressor outlet and the head end of the combustor. The carbon dioxide collection system is configured and disposed to extract a first fluid comprising carbon dioxide and a second fluid from a substantially oxygen free fluid flow passed from the one of the compressor outlet and the head end of the combustor.

Abstract: A system includes a controller configured to control a semi-closed power cycle system. The controller is configured to receive at least one of a first signal indicative of an oxygen concentration within a first gas flow through a primary compressor, a second signal indicative of power output by the semi-closed power cycle system, a third signal indicative of a temperature of a second gas flow through a turbine, and a fourth signal indicative of a mass flow balance within the semi-closed power cycle system. The controller is also configured to adjust at least one of the first gas flow through the primary compressor, a fuel flow into a combustor, a fraction of the first gas flow extracted from the primary compressor, and an air flow through a feed compressor based on the at least one of the first signal, the second signal, the third signal, and the fourth signal.

Abstract: Control of gas turbine speed and acceleration during unloaded rotation may limit stresses on components and facilitate timely operational performance. Operation of a torque converter driving a gas turbine shaft from a starter motor provides control over acceleration and speed of the gas turbine shaft. Hydraulic coupling between the input and output of the torque converter is adjusted by draining and refilling the working fluid in a body of the torque converter to control acceleration and speed of the rotor shaft during a first speed range. Vane positioning within the torque converter may be alternated between discrete speed settings to control acceleration and speed of the rotor shaft during a second speed range. A turbine control system with an acceleration schedule may provide control signals for these functions.