Abstract: The unexpected failure of a turbomachine can be costly and dangerous. Processes may collect data from a turbomachine, calculate durations of machine events from the collected data, and apply a model to those machine-event durations to predict future machine-event durations and/or detect trends in the machine-event durations. This predictive output may be utilized to inform downstream functions regarding the health of the turbomachine. For example, a downstream function may utilize the predictive output to detect degradation or a potential future failure in the turbomachine and trigger remedial functions, such as alerts and/or controls, to prevent or mitigate the degradation or failure of the turbomachine.

Abstract: It is important to accurately measure the emissions of a turbomachine for a variety of reasons. However, continuous emission monitoring systems (CEMS) can be expensive to install and maintain. Accordingly, a digital platform is disclosed that hosts physics-based and/or statistical models that can be tailored to specific turbomachines and calibrated over the life of the turbomachine. The model for a turbomachine can be applied to data collected from the turbomachine to predict the emissions of the turbomachine. This enables monitoring of emissions, remotely and without the need of a CEMS. In addition, the platform may utilize the predicted emissions for alerts, compliance monitoring, health monitoring, control of the turbomachine, reporting, and/or the like.

Abstract: A method for servicing a gas turbine engine to enhance the power output of the gas turbine engine including a control system, inlet guide vanes, and a third stage power turbine nozzle is disclosed. The control system includes an inlet guide vane module. The method includes increasing an operating range of each inlet guide vane to at least 62 degrees. The method also includes modifying a total flow area of the third stage power turbine nozzle by 2% to 12%, the total flow area including flow areas between adjacent airfoils in the third stage power turbine nozzle.

Abstract: A method for servicing a gas turbine engine to enhance the power output of the gas turbine engine including a control system, inlet guide vanes, and a third stage power turbine nozzle is disclosed. The control system includes an inlet guide vane module. The method includes increasing an operating range of each inlet guide vane to at least 62 degrees. The method also includes modifying a total flow area of the third stage power turbine nozzle by 2% to 12%, the total flow area including flow areas between adjacent airfoils in the third stage power turbine nozzle.