Patents by Inventor Andrew Healy
Andrew Healy has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
-
Patent number: 7742904Abstract: A method for simulating a gas turbine including the steps of: sensing values of a plurality of first operating parameters of an actual gas turbine; applying the sensed values of the first operating parameters to a model of the gas turbine, wherein the model generates a plurality of predicted second operating parameters; determining difference values between the predicted second operating parameters and corresponding sensed second operating parameters of the actual gas turbine; modifying the difference values based on tuning factors generated by a Kalman filter gain matrix during operation of the gas turbine, and using the adjusted difference values to adjust the model of the gas turbine. The method may further comprise generating the tuning factors by applying to the model the sensed values of the plurality of first operating parameters and perturbated values of the adjusted different values to determine optimal tuning factors.Type: GrantFiled: September 27, 2005Date of Patent: June 22, 2010Assignee: General Electric CompanyInventors: Timothy Andrew Healy, Randy Scott Rosson
-
Publication number: 20100089067Abstract: 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.Type: ApplicationFiled: October 10, 2008Publication date: April 15, 2010Applicant: GENERAL ELECTRIC COMPANYInventors: Kevin Wood Wilkes, Timothy Andrew Healy, Randy Scott Rosson
-
Publication number: 20100011851Abstract: 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 (Ae), and calculating a second estimated total fuel flow utilizing an aero-thermal cycle model analysis. The first estimated total fuel flow is compared to the second estimated total fuel flow and a lower heating value of the fuel is determined from a difference between the first estimated total fuel flow and the second estimated total fuel flow. A method and system for controlling a gas turbine includes calculating effects of the fuel composition on performance of the gas turbine and comparing one or more performance parameters to one or more parameter limits. One or more machine controls of the gas turbine are changed based on the results of the comparison.Type: ApplicationFiled: September 29, 2009Publication date: January 21, 2010Applicant: GENERAL ELECTRIC COMPANYInventors: Timothy Andrew Healy, John Charles Intile, Joseph Vincent Citeno, Garth Curtis Frederick
-
Patent number: 7628062Abstract: 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 (Ae), and calculating a second estimated total fuel flow utilizing an aero-thermal cycle model analysis. The first estimated total fuel flow is compared to the second estimated total fuel flow and a lower heating value of the fuel is determined from a difference between the first estimated total fuel flow and the second estimated total fuel flow. A method and system for controlling a gas turbine includes calculating effects of the fuel composition on performance of the gas turbine and comparing one or more performance parameters to one or more parameter limits. One or more machine controls of the gas turbine are changed based on the results of the comparison.Type: GrantFiled: September 6, 2007Date of Patent: December 8, 2009Assignee: General Electric CompanyInventors: Timothy Andrew Healy, John Charles Intile, Joseph Vincent Citeno, Garth Curtis Frederick
-
Patent number: 7620461Abstract: 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.Type: GrantFiled: June 26, 2007Date of Patent: November 17, 2009Assignee: General Electric CompanyInventors: Garth Frederick, II, Thomas Raymond Farrell, Timothy Andrew Healy, John Carver Maters, Jonathan Carl Thatcher
-
Patent number: 7593803Abstract: A method for determining a target exhaust temperature for a gas turbine including: determining a target exhaust temperature based on a compressor pressure condition; determining a temperature adjustment to the target exhaust temperature based on at least one parameter of a group of parameters consisting of specific humidity, compressor inlet pressure loss and turbine exhaust back pressure; and adjusting the target exhaust temperature by applying the temperature adjustment.Type: GrantFiled: March 16, 2007Date of Patent: September 22, 2009Assignee: General Electric CompanyInventors: Timothy Andrew Healy, Derrick Walter Simons
-
Publication number: 20090183492Abstract: 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.Type: ApplicationFiled: January 22, 2008Publication date: July 23, 2009Applicant: GENERAL ELECTRIC COMPANYInventors: Timothy Andrew Healy, Garth Curtis Frederick
-
Publication number: 20090064682Abstract: 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 (Ae), and calculating a second estimated total fuel flow utilizing an aero-thermal cycle model analysis. The first estimated total fuel flow is compared to the second estimated total fuel flow and a lower heating value of the fuel is determined from a difference between the first estimated total fuel flow and the second estimated total fuel flow. A method and system for controlling a gas turbine includes calculating effects of the fuel composition on performance of the gas turbine and comparing one or more performance parameters to one or more parameter limits. One or more machine controls of the gas turbine are changed based on the results of the comparison.Type: ApplicationFiled: September 6, 2007Publication date: March 12, 2009Applicant: GENERAL ELECTRIC COMPANYInventors: Timothy Andrew Healy, John Charles Intile, Joseph Vincent Citeno, Garth Curtis Frederick
-
Publication number: 20090043447Abstract: 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.Type: ApplicationFiled: August 7, 2007Publication date: February 12, 2009Applicant: GENERAL ELECTRIC COMPANYInventors: Mikhail Vershinin, Timothy Andrew Healy, Garth Curtis Frederick
-
Publication number: 20090005951Abstract: 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.Type: ApplicationFiled: June 26, 2007Publication date: January 1, 2009Applicant: GENERAL ELECTRIC COMPANYInventors: Garth Frederick, Thomas Raymond Farrell, Timothy Andrew Healy, John Carver Maters, Jonathan Carl Thatcher
-
Publication number: 20080243352Abstract: 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.Type: ApplicationFiled: March 25, 2008Publication date: October 2, 2008Applicant: GENERAL ELECTRIC COMPANYInventor: Timothy Andrew Healy
-
Publication number: 20080178600Abstract: Embodiments of the invention can provide systems and methods for initializing dynamic model states using a Kalman or similar type filter. In one embodiment, an adaptable model-based control system for controlling a gas turbine engine is provided. The system can include at least one sensor adapted to obtain dynamic-type information about a current state of the engine. Furthermore, the system can include an engine model adapted to receive information from the sensor, and further adapted to reflect the current state of the engine. In addition, the system can include a model filter adapted to initialize the model with at least a portion of the dynamic-type information, wherein at least one value based at least in part on the dynamic-type information is input to the engine model. Moreover, the model can be further adapted to determine an output from the engine model based at least in part on the at least one value.Type: ApplicationFiled: January 26, 2007Publication date: July 31, 2008Applicant: General Electric CompanyInventors: Timothy Andrew Healy, Randy S. Rosson, Kevin Wood Wilkes
-
Patent number: 7246002Abstract: A method for determining a target exhaust temperature for a gas turbine including: determining a target exhaust temperature based on a compressor pressure condition; determining a temperature adjustment to the target exhaust temperature based on at least one parameter of a group of parameters consisting of specific humidity, compressor inlet pressure loss and turbine exhaust back pressure; and adjusting the target exhaust temperature by applying the temperature adjustment.Type: GrantFiled: November 20, 2003Date of Patent: July 17, 2007Assignee: General Electric CompanyInventors: Timothy Andrew Healy, Derrick Walter Simons
-
Patent number: 7127898Abstract: A method for determining an estimated operating parameter for a gas turbine including the steps of: determining an estimated operating parameter using an algorithm have an input from a sensor, wherein the algorithm includes a trim factor; determining a first trim factor based on a comparison of the first estimated operating parameter and the output of the sensor when a condition of the sensor is in a first mode, and during a subsequent determination of the estimated operating parameter, applying the first trim factor to subsequently determine the estimated operating condition if the condition of second sensor is in a second mode.Type: GrantFiled: December 16, 2005Date of Patent: October 31, 2006Assignee: General Electric CompanyInventor: Timothy Andrew Healy
-
Patent number: 7100357Abstract: A system for determining a target exhaust temperature for a gas turbine including: determining a target exhaust temperature based on a compressor pressure condition; determining a temperature adjustment to the target exhaust temperature based on at least one parameter of a group of parameters consisting of specific humidity, compressor inlet pressure loss and turbine exhaust back pressure; and adjusting the target exhaust temperature by applying the temperature adjustment.Type: GrantFiled: March 10, 2005Date of Patent: September 5, 2006Assignee: General Electric CompanyInventors: Rex Allen Morgan, Timothy Andrew Healy
-
Patent number: 7032388Abstract: A method for determining an estimated operating parameter for a gas turbine including the steps of: determining an estimated operating parameter using an algorithm have an input from a sensor, wherein the algorithm includes a trim factor; determining a first trim factor based on a comparison of the first estimated operating parameter and the output of the sensor when a condition of the sensor is in a first mode, and during a subsequent determination of the estimated operating parameter, applying the first trim factor to subsequently determine the estimated operating condition if the condition of second sensor is in a second mode.Type: GrantFiled: November 17, 2003Date of Patent: April 25, 2006Assignee: General Electric CompanyInventor: Timothy Andrew Healy
-
Patent number: 6912856Abstract: A method for determining a target exhaust temperature for a gas turbine including: determining a target exhaust temperature based on a compressor pressure condition; determining a temperature adjustment to the target exhaust temperature based on at least one parameter of a group of parameters consisting of specific humidity, compressor inlet pressure loss and turbine exhaust back pressure; and adjusting the target exhaust temperature by applying the temperature adjustment.Type: GrantFiled: June 23, 2003Date of Patent: July 5, 2005Assignee: General Electric CompanyInventors: Rex Allen Morgan, Timothy Andrew Healy
-
Publication number: 20040255595Abstract: A method for determining a target exhaust temperature for a gas turbine including: determining a target exhaust temperature based on a compressor pressure condition; determining a temperature adjustment to the target exhaust temperature based on at least one parameter of a group of parameters consisting of specific humidity, compressor inlet pressure loss and turbine exhaust back pressure; and adjusting the target exhaust temperature by applying the temperature adjustment.Type: ApplicationFiled: June 23, 2003Publication date: December 23, 2004Inventors: Rex Allen Morgan, Timothy Andrew Healy