Abstract: Systems and methods for gas turbine combustion profile monitoring are disclosed. In one embodiment, a method for detecting an anomaly in a combustion section of a gas turbine is disclosed. The method includes receiving, from a plurality of thermal sensors disposed around an exhaust section of a gas turbine, exhaust profile data of the gas turbine. The method further analyzes the exhaust profile data to calculate statistical features associated with a peak-trough pattern. The method further determines, using a machine learning algorithm, that the statistical features are abnormal. In response to the determination, the method processes the exhaust profile data for a predetermined period of time and reports an anomaly in a combustion section of the gas turbine if the statistical features remain abnormal for the predetermined period of time.

Abstract: Systems and methods for gas turbine combustion profile monitoring are disclosed. In one embodiment, a method for detecting an anomaly in a combustion section of a gas turbine is disclosed. The method includes receiving, from a plurality of thermal sensors disposed around an exhaust section of a gas turbine, exhaust profile data of the gas turbine. The method further analyzes the exhaust profile data to calculate statistical features associated with a peak-trough pattern. The method further determines, using a machine learning algorithm, that the statistical features are abnormal. In response to the determination, the method processes the exhaust profile data for a predetermined period of time and reports an anomaly in a combustion section of the gas turbine if the statistical features remain abnormal for the predetermined period of time.

Abstract: Methods and systems for a dry low NOx gas turbine engine system include a gas turbine engine including at least one dry low NOx combustor. The combustor includes a plurality of injection points wherein at least some of the injection points are configured to inject a fuel into the combustor at a plurality of different locations. The system includes a water source coupled to the combustor and operable to inject water into others of the plurality of injection points. The system also includes a control system that includes a sensor configured to measure an exhaust gas concentration of the turbine, a processor programmed to receive a signal indicative of the turbine exhaust gas concentration, and to automatically control the water injection using the received exhaust gas concentration signal. Such systems in use together can mitigate visible emissions from the exhaust stack.

Abstract: A method of operating a gas turbine engine is provided. The method includes introducing a fuel into a combustor, detecting a failure of ignition of the fuel, and preventing ignition until the introduced fuel is substantially removed from the gas turbine engine.

Abstract: A computer implemented process is provided for assessing and characterizing the degree of success or failure of an operational event of a machine system such as a fluid compressor machine or turbine machine or the like on a continuous numerical scale. The computer implemented process develops and tracks machine unit signatures, machine site signatures and machine fleet signatures to evaluate various operational events and provide fault detection. At least some sensor data acquired from the machine system during an operational event is transformed to correct or at least reduce variabilities in the data caused by ambient conditions and fuel quality. The transformed data is then analyzed using statistical methods to determine how closely the operational event conforms to an expected normal behavior and the information is used to develop a single comprehensive quality assessment of the event.

Abstract: In a gas turbine having a compressor, a combustor and a turbine, a gaseous fuel supply coupled to provide gaseous fuel to the combustor, a liquid fuel supply coupled to provide liquid fuel to the combustor via nozzle assembly. The nozzle assembly includes a plurality of passageways for flowing a fluid into the combustor, one of the passageways being an atomizing air passageway conduit interconnecting the atomizing air passageway to one of the plurality of passageways to enable fluid flow therebetween, while not allowing the flow of fluid back into the atomizing air passageway. High pressure air from the atomizing air passageway is diverted into one of the plurality of passageways via the conduit to protect the nozzle from ingestion of hot combustor gases, thus eliminating a need for a dedicated air purge system for that one of the plurality of passageways.

Abstract: A system for cooling at least one gas turbine liquid fuel component located in a high temperature environment to eliminate coking in the component is disclosed. The system includes a sleeve surrounding the liquid fuel component, a device for providing a current of cool air, and a conduit connected between the cool air device and the sleeve to direct the current of cool air into the sleeve to cool the liquid fuel component. The system can also include a manifold connected to the conduit and a plurality of second conduits for connecting the manifold to a plurality of sleeves surrounding a plurality of liquid fuel components, each sleeve being connected to a corresponding second conduit. Each sleeve includes a plurality of spacing devices for centering the sleeve around the at least one liquid fuel component so as to form an annulus between the sleeve and the liquid fuel component through which the current of cool air flows.