| Patent application number | Description | Published |
|---|
| 20090044513 | Method Of Mitigating Undesired Gas Turbine Transient Response Using Event Based Actions - A method of managing transient events regularly seen during gas turbine operation that may cause undesirable operation and hardware damage. During certain transient operations, a lag may be seen between reference exhaust temperature and actual turbine exhaust temperature. This lag can result in an under-fired condition within the combustion system of variable magnitude and duration. Either fuel split schedules or a control algorithm can be positioned during these transients to prevent combustion dynamics or loss of flame. Combustion dynamics are known to cause damage that may require hardware replacement. Once the transient has completed, normal control operation is resumed. | 02-19-2009 |
| 20090063003 | Method And System For Detection Of Gas Turbine Combustion Blowouts Utilizing Fuel Normalized Power Response - A method and controller for identifying lean blowout conditions in a Dry Low NO | 03-05-2009 |
| 20090145126 | METHOD AND SYSTEM FOR CONTROLLING AN EXHAUST GAS RECIRCULATION SYSTEM - A method and system for controlling an exhaust gas recirculation (EGR) system is provided. The method and system may incorporate a device or devices that continuously monitors an exhaust stream for harmful constituents. The method and system may control components of the EGR system based on the concentration of harmful constituents within the exhaust. | 06-11-2009 |
| 20090157230 | METHOD FOR CONTROLLING A FLOWRATE OF A RECIRCULATED EXHAUST GAS - A method for controlling an exhaust gas recirculation (EGR) system is provided. The EGR system may allow for the removal and the sequestration of at least one constituent within the exhaust before the recirculation occurs. The method may monitor the level of at least one constituent and adjust an EGR recirculation rate. | 06-18-2009 |
| 20100168980 | OPERATING A TURBINE AT BASELOAD ON COLD FUEL WITH HOT FUEL COMBUSTION HARDWARE - A method and algorithm are provided to operate a gas turbine at baseload in an emission compliant capable mode to avoid combustion dynamics while operating with cold fuel and hot fuel combustion hardware. The method includes performing a gas turbine operational sequence such as a startup to an emission compliant capable mode. A gas fuel temperature is measured. The gas turbine is operated in the emissions compliant capable mode according to a designated fuel split for avoiding combustion dynamics when a temperature for a gas fuel is below a designated value. A determination is made whether a modified wobbe index for the gas fuel is below an emissions compliant value. An alarm is activated if the modified wobbe index is below the emissions compliant value to notify the operator of a potential emissions shift. | 07-01-2010 |
| 20110146290 | METHOD OF STARTING A TURBOMACHINE - The present invention has the technical effect of reducing the start-up time associated with starting a powerplant machine. An embodiment of the present invention provides a method of starting a powerplant machine, such as, but not limiting of, a turbomachine. An embodiment of the method of the present invention provides a new philosophy for starting a turbomachine. This new philosophy involves testing the turbomachine systems before the start-up process begins. | 06-23-2011 |
| 20110146293 | METHOD FOR CONNECTING A STARTING MEANS TO A TURBOMACHINE - An embodiment of the present invention provides a method of starting a powerplant machine, such as, but not limiting of, a turbomachine set to operate in a Fast Start mode. The turbomachine may include, but is not limited to, a steam turbine, a heavy-duty gas turbine, an aero-derivative gas turbine, and the like. An embodiment of the method of the present invention provides a new philosophy for controlling a starting system associated with the turbomachine. An embodiment of the present invention may be applied to a powerplant having multiple turbomachines and a starting system having multiple starting means, which may include at least one LCI system. Here, an embodiment of the present invention may eliminate the manual process of preparing and integrating a desired turbomachine with a desired starting means. | 06-23-2011 |
