Patent application number | Description | Published |
20080243352 | Methods and Systems for Model-Based Control of Gas Turbines - Embodiments of systems and methods for tuning a turbine are provided. In one embodiment, a method may include receiving at least one of a measured operating parameter or a modeled operating parameter of a turbine during operation; and tuning the turbine during operation. The turbine may be tuned during operation by applying the measured operating parameter or modeled operating parameter or parameters to at least one operational boundary model, applying the measured operating parameter or modeled operating parameter or parameters to at least one scheduling algorithm, comparing the output of the operational boundary model or models to the at output of the scheduling algorithm or algorithms to determine at least one error term, and closing loop on the one error term or terms by adjusting at least one turbine control effector during operation of the turbine. | 10-02-2008 |
20090005951 | Systems and Methods for Using a Combustion Dynamics Tuning Algorithm with a Multi-Can Combustor - Embodiments of the invention can provide systems and methods for using a combustion dynamics tuning algorithm with a multi-can combustor. According to one embodiment of the invention, a method for controlling a gas turbine engine with an engine model can be implemented for an engine comprising multiple cans. The method can include obtaining operating frequency information associated with multiple cans of the engine. In addition, the method can include determining variation between operating frequency information of at least two cans. Furthermore, the method can include determining a median value based at least in part on the variation. Moreover, the method can include inputting the median value to an engine model, wherein based at least in part on the median value, the engine model determines an engine control action. In addition, the method can include outputting a control command to implement the engine control action. | 01-01-2009 |
20090043447 | Systems and Methods for Model-Based Sensor Fault Detection and Isolation - The systems and method may include receiving a plurality of measured tuning inputs associated with an operating parameter of an engine, providing a plurality of parameter estimation modules that utilize one or more component performance maps having adjustable knobs to generate model outputs, where each parameter estimation module is configured independently of a respective one of the operating parameters of the engine, and where each parameter estimation module generates the model outputs based upon fundamental inputs associated with the engine. The systems and methods may further include calculating residual values for each parameter estimation module, adjusting knobs of each parameter estimation module, and determining that a sensor associated with a measured tuning input or a fundamental input is faulty based at least in part upon values of the knobs and residual values. | 02-12-2009 |
20090064682 | METHOD AND SYSTEM TO DETERMINE COMPOSITION OF FUEL ENTERING COMBUSTOR - Disclosed is a method and system for determining composition of a fuel entering a combustor. The method includes determining a temperature of the fuel entering the combustor, calculating a first estimated total fuel flow utilizing fuel properties and fuel nozzle effective area (A | 03-12-2009 |
20090183492 | COMBUSTION LEAN-BLOWOUT PROTECTION VIA NOZZLE EQUIVALENCE RATIO CONTROL - Disclosed is a method and system for controlling a combustor of a gas turbine utilizing fuel nozzle equivalence ratio. The equivalence ratio of at least one fuel nozzle of the combustor, the combustor having at least one fuel nozzle disposed in at least one combustor can, is measured. The measured equivalence ratio is compared to a threshold value for lean blowout. The fuel flow from the at least one nozzle is modified thereby adjusting the equivalence ratio to prevent lean blowout. | 07-23-2009 |
20100011851 | METHOD AND SYSTEM TO DETERMINE COMPOSITION OF FUEL ENTERING COMBUSTOR - Disclosed is a method and system for determining composition of a fuel entering a combustor. The method includes determining a temperature of the fuel entering the combustor, calculating a first estimated total fuel flow utilizing fuel properties and fuel nozzle effective area (A | 01-21-2010 |
20100089067 | ADAPTIVE PERFORMANCE MODEL AND METHODS FOR SYSTEM MAINTENANCE - A system includes a correction factor module that receives modeled data generated from a simulation model and measured data, that determines a difference between the modeled data and the measured data, and that applies a filter to the difference to determine a correction value; and a performance monitoring module that analyzes the correction value, and that generates a component alert based on the analysis. | 04-15-2010 |
20100162724 | Methods and Systems for Controlling a Combustor in Turbine Engines - Embodiments of methods and systems for controlling a combustor for a gas turbine engine are provided. According to one example embodiment, a system includes an air control assembly associated with at least one air path of a combustor for a gas turbine engine. Additionally, the system also includes at least one sensor for sensing at least one operating parameter of the gas turbine engine. Further, the system also includes a controller operable to receive at least one operating parameter sensed by the at least one sensor, and further operable to selectively control an air control assembly based at least in part on the at least one operating parameter sensed by the at least one sensor. | 07-01-2010 |
20100180674 | Systems and Methods of Monitoring Acoustic Pressure to Detect a Flame Condition in a Gas Turbine - A method may detect a flashback condition in a fuel nozzle of a combustor. The method may include obtaining a current acoustic pressure signal from the combustor, analyzing the current acoustic pressure signal to determine current operating frequency information for the combustor, and indicating that the flashback condition exists based at least in part on the current operating frequency information. | 07-22-2010 |
20100269481 | SYSTEMS AND METHODS FOR PROVIDING SURGE PROTECTION TO A TURBINE COMPONENT - Systems and methods for providing surge protection to turbine components are provided. A surge protection limit may be determined for the turbine component. One or more measurements associated with operation of the turbine component may be received and provided to a cycle model executed to predict an operating condition of the turbine component. The predicted operating condition of the turbine component may be adjusted based at least in part on the received one or more measurements. The surge protection limit may be adjusted based on the adjusted predicted operating condition of the turbine component. | 10-28-2010 |
20110314827 | FUEL NOZZLE ASSEMBLY - An insert for pre-mixing a secondary fuel in a pre-mixing annulus of a fuel nozzle assembly is disclosed. The insert includes a cartridge extending through at least a portion of the fuel nozzle assembly and configured to flow the secondary fuel therethrough. The insert further includes an adapter coupled to the cartridge, the adapter defining a fuel plenum and at least one radially extending injection bore. The at least one injection bore is configured to accept at least a portion of the secondary fuel from the cartridge and inject the secondary fuel into the pre-mixing annulus. | 12-29-2011 |
20140075953 | SYSTEM AND METHOD FOR DETECTING AND CONTROLLING FLASHBACK AND FLAME HOLDING WITHIN A COMBUSTOR - A system is provided for detecting and controlling flashback and flame holding in a combustor of a gas turbine. The system includes at least one flame indicator disposed in a combustor and at least one detector disposed downstream from the flame indicator. The flame indicator may be configured to produce light when exposed to a flame and the detector may be configured to detect the light produced by the flame indicator. | 03-20-2014 |
20140144153 | SYSTEM AND METHOD TO CONTROL A GAS TURBINE SUBJECT TO FUEL COMPOSITION VARIATION - A system and method control a gas turbine subject to fuel composition variation. The method includes operating a first effector to control the gas turbine based on fuel composition. The method also includes operating a second effector to maintain operation of the first effector within a first boundary limit, the second effector operation being initiated when the operating the first effector reaches a second boundary limit within the first boundary limit. | 05-29-2014 |
20140182297 | GAS TURBINE AND METHOD OF CONTROLLING A GAS TURBINE AT PART-LOAD CONDITION - A gas turbine includes a compressor section, a combustion section downstream from the compressor section, a turbine section downstream from the combustion section, and a controller. The controller controls the operation of the gas turbine at a reduced load, and is capable of querying a database including multiple sets of operational parameters for the gas turbine correlated with at least one measured output response at each set of operational parameters. One of the sets of operational parameters provides a desired gas turbine load that meets a target level for the output response. Related methods are also disclosed. | 07-03-2014 |