Patents by Inventor David Allen Gutz
David Allen Gutz 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).
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Patent number: 11053861Abstract: In accordance with one exemplary embodiment of the present disclosure, a method for providing overspeed protection for a gas turbine engine is provided. The gas turbine engine may include an engine core and an engine shaft. The method may include determining an overspeed condition of the engine. The overspeed condition may be indicative of an above normal rotational speed of the engine shaft. The method may also include reducing an airflow through the engine core of the gas turbine engine in response to the determined overspeed condition to reduce the rotational speed of the engine shaft.Type: GrantFiled: March 3, 2016Date of Patent: July 6, 2021Assignee: General Electric CompanyInventors: David Anthony Moster, William James Mailander, David Allen Gutz
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Patent number: 10800536Abstract: A hybrid electric propulsion system includes a gas turbine engine and an electric machine coupled to the gas turbine engine. A method for operating the propulsion system includes determining, by one or more computing devices, a baseline power output for the gas turbine engine; operating, by the one or more computing devices, the gas turbine engine to provide the baseline power output; determining, by the one or more computing devices, a desired power output greater than or less than the baseline power output; and providing, by the one or more computing devices, power to, or extracting, by the one or more computing devices, power from, the gas turbine engine using the electric machine such that an effective power output of the gas turbine engine matches the determined desired power output.Type: GrantFiled: June 9, 2017Date of Patent: October 13, 2020Assignee: General Electric CompanyInventors: Nicholas Adam Wagner, Daniel E. Bergsten, David Allen Gutz
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Patent number: 10633104Abstract: A method of operating a hybrid-electric propulsion system for an aircraft includes determining a flight phase parameter for the aircraft is equal to a first value, and operating the hybrid-electric propulsion system in an electric charge mode in response to determining the flight phase parameter for the aircraft is equal to the first value. The method also includes determining the flight phase parameter for the aircraft is equal to a second value different from the first value, and operating the hybrid-electric propulsion system in an electric discharge mode in response to determining the flight phase parameter for the aircraft is equal to the second value.Type: GrantFiled: May 17, 2017Date of Patent: April 28, 2020Assignee: General Electric CompanyInventors: Brandon Wayne Miller, Michael Thomas Gansler, Sridhar Adibhatla, Daniel E. Bergsten, Nicholas Adam Wagner, David Allen Gutz
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Patent number: 10302020Abstract: A computer-implemented method for controlling a fuel flow to a gas turbine engine of an aircraft includes determining a control initiated fuel flow demand that is based, at least in part, on an operator command. In addition, the method includes determining a first rate of change of fuel flow demand based, at least in part, on a tracking error of the gas turbine engine that indicates a difference between a desired rotational speed and an actual rotational speed. The method also includes integrating the first rate of change of fuel flow demand to determine a tracking error fuel flow demand. In addition, the method includes summing the control initiated fuel flow demand and tracking error fuel flow demand to determine a composite fuel flow demand. The method also includes controlling a fuel flow to the gas turbine engine based, at least in part, on the composite fuel flow demand.Type: GrantFiled: December 12, 2016Date of Patent: May 28, 2019Assignee: General Electric CompanyInventors: David Allen Gutz, Robert Edward Goeller
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Patent number: 10252812Abstract: A system for an aircraft having a first gas turbine engine and a second gas turbine engine includes a first engine controller comprising a first motion sensor. The first motion sensor defines a first orthogonal coordinate system, and is configured for determining first motion sensor data indicating motion of the aircraft along at least one axis of the first orthogonal coordinate system. The system further includes a second engine controller comprising a second motion sensor spaced apart from the first motion sensor. The second motion sensor defines a second orthogonal coordinate system, and is configured for determining second motion sensor data indicating motion of the aircraft along at least one axis of the second orthogonal coordinate system. In addition, the second engine controller is communicatively coupled to the first engine controller such that the first engine controller receives the second motion sensor data.Type: GrantFiled: September 28, 2016Date of Patent: April 9, 2019Assignee: General Electric CompanyInventor: David Allen Gutz
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Publication number: 20190002115Abstract: A method of operating a hybrid-electric propulsion system for an aircraft includes determining a flight phase parameter for the aircraft is equal to a first value, and operating the hybrid-electric propulsion system in an electric charge mode in response to determining the flight phase parameter for the aircraft is equal to the first value. The method also includes determining the flight phase parameter for the aircraft is equal to a second value different from the first value, and operating the hybrid-electric propulsion system in an electric discharge mode in response to determining the flight phase parameter for the aircraft is equal to the second value.Type: ApplicationFiled: May 17, 2017Publication date: January 3, 2019Inventors: Brandon Wayne Miller, Michael Thomas Gansler, Sridhar Adibhatla, Daniel E. Bergsten, Nicholas Adam Wagner, David Allen Gutz
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Publication number: 20180354635Abstract: A hybrid electric propulsion system includes a gas turbine engine and an electric machine coupled to the gas turbine engine. A method for operating the propulsion system includes determining, by one or more computing devices, a baseline power output for the gas turbine engine; operating, by the one or more computing devices, the gas turbine engine to provide the baseline power output; determining, by the one or more computing devices, a desired power output greater than or less than the baseline power output; and providing, by the one or more computing devices, power to, or extracting, by the one or more computing devices, power from, the gas turbine engine using the electric machine such that an effective power output of the gas turbine engine matches the determined desired power output.Type: ApplicationFiled: June 9, 2017Publication date: December 13, 2018Inventors: Nicholas Adam Wagner, Daniel E. Bergsten, David Allen Gutz
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Patent number: 10006375Abstract: A hybrid electric propulsion system includes a turbomachine, an electric machine coupled to the turbomachine, and a propulsor coupled to the turbomachine. A method for operating the hybrid electric propulsion system includes operating the turbomachine to drive the propulsor; receiving data indicative of a failure condition of the hybrid electric propulsion system; reducing a fuel flow to a combustion section of the turbomachine in response to receiving the data indicative of the failure condition; and extracting power from the turbomachine using the electric machine to slow down one or more rotating components of the turbomachine in response to receiving the data indicative of the failure condition.Type: GrantFiled: July 11, 2017Date of Patent: June 26, 2018Assignee: General Electric CompanyInventors: Nicholas Adam Wagner, Daniel E. Bergsten, David Allen Gutz
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Publication number: 20180163638Abstract: A computer-implemented method for controlling a fuel flow to a gas turbine engine of an aircraft includes determining a control initiated fuel flow demand that is based, at least in part, on an operator command. In addition, the method includes determining a first rate of change of fuel flow demand based, at least in part, on a tracking error of the gas turbine engine that indicates a difference between a desired rotational speed and an actual rotational speed. The method also includes integrating the first rate of change of fuel flow demand to determine a tracking error fuel flow demand. In addition, the method includes summing the control initiated fuel flow demand and tracking error fuel flow demand to determine a composite fuel flow demand. The method also includes controlling a fuel flow to the gas turbine engine based, at least in part, on the composite fuel flow demand.Type: ApplicationFiled: December 12, 2016Publication date: June 14, 2018Inventors: David Allen Gutz, Robert Edward Goeller
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Publication number: 20180086474Abstract: A system for an aircraft having a first gas turbine engine and a second gas turbine engine includes a first engine controller comprising a first motion sensor. The first motion sensor defines a first orthogonal coordinate system, and is configured for determining first motion sensor data indicating motion of the aircraft along at least one axis of the first orthogonal coordinate system. The system further includes a second engine controller comprising a second motion sensor spaced apart from the first motion sensor. The second motion sensor defines a second orthogonal coordinate system, and is configured for determining second motion sensor data indicating motion of the aircraft along at least one axis of the second orthogonal coordinate system. In addition, the second engine controller is communicatively coupled to the first engine controller such that the first engine controller receives the second motion sensor data.Type: ApplicationFiled: September 28, 2016Publication date: March 29, 2018Inventor: David Allen Gutz
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Publication number: 20170254295Abstract: In accordance with one exemplary embodiment of the present disclosure, a method for providing overspeed protection for a gas turbine engine is provided. The gas turbine engine may include an engine core and an engine shaft. The method may include determining an overspeed condition of the engine. The overspeed condition may be indicative of an above normal rotational speed of the engine shaft. The method may also include reducing an airflow through the engine core of the gas turbine engine in response to the determined overspeed condition to reduce the rotational speed of the engine shaft.Type: ApplicationFiled: March 3, 2016Publication date: September 7, 2017Inventors: David Anthony Moster, William James Mailander, David Allen Gutz
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Patent number: 9399955Abstract: A method and apparatus for local loop closure is provided. The apparatus includes a component for use in a gas turbine engine. The component includes at least one of an actuator and a servo-valve, at least one sensor, and an electronic module comprising controller electronics and memory. The electronic module is configured to receive and process commands for the at least one of an actuator and a servo-valve and queue received commands in an input buffer.Type: GrantFiled: May 1, 2012Date of Patent: July 26, 2016Assignee: General Electric CompanyInventors: Mitchell Donald Smith, Charles Francis Hanley, David Allen Gutz
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Publication number: 20150377145Abstract: A method and apparatus for local loop closure is provided. The apparatus includes a component for use in a gas turbine engine. The component includes at least one of an actuator and a servo-valve or electric motor, at least one sensor, and an electronic module comprising controller electronics and memory. The electronic module is configured to receive and process commands for the at least one of an actuator and a servo-valve and queue received commands in an input buffer.Type: ApplicationFiled: September 4, 2015Publication date: December 31, 2015Inventors: Mitchell Donald Smith, Charles Francis Hanley, David Allen Gutz
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Publication number: 20130223976Abstract: A method and apparatus for local loop closure is provided. The apparatus includes a component for use in a gas turbine engine. The component includes at least one of an actuator and a servo-valve, at least one sensor, and an electronic module comprising controller electronics and memory. The electronic module is configured to receive and process commands for the at least one of an actuator and a servo-valve and queue received commands in an input buffer.Type: ApplicationFiled: May 1, 2012Publication date: August 29, 2013Inventors: Mitchell Donald Smith, Charles Francis Hanley, David Allen Gutz
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Patent number: 8364340Abstract: A method and systems for engine control of a vehicle propulsion system are provided. The system includes a plurality of engine model modules executing independently and programmed to receive engine operating condition values from a plurality of sensors positioned on an engine wherein each of the plurality of engine model modules is programmed to determine an estimate of a process parameter of a location in the engine where a sensor is not available, not present at the location, has failed, or is determined to be inaccurate. The system also includes an estimate source selector configured to determine model blending factors and a model blending module configured to determine an estimated virtual sensor value using the determined estimates from at least two of the plurality of engine model modules and the model blending factors.Type: GrantFiled: March 31, 2009Date of Patent: January 29, 2013Assignee: General Electric CompanyInventors: Brian Francis Nestico, Sridhar Adibhatla, David Allen Gutz, Daniel Edgardo Viassolo
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Patent number: 8087880Abstract: Apparatus and method of operating a centrifugal compressor and active control system includes a centrifugal compressor with compressor blades mounted on an impeller, an annular cavity bounded in part by a shroud adjacent to the blades, and an active control system for controlling a clearance between the shroud and the blades by controlling a cavity pressure in the cavity. An electronic controller for controlling a control pressure valve for pressurizing using a source of compressor discharge pressure air and depressurizing the cavity respectively may open and close the valves using pulse width modulation. Pressure and clearance sensors positioned for measuring the cavity pressure the blade tip clearance respectively in signal supply communication with the electronic controller may be used. The shroud may be supported by radially spaced apart annular radially outer and inner supports connected to a casing by a bolted joint bounding the cavity.Type: GrantFiled: December 3, 2008Date of Patent: January 3, 2012Assignee: General Electric CompanyInventors: Apostolos Pavlos Karafillis, Kenneth Allen Loehle, Robert Patrick Tameo, David Allen Gutz
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Publication number: 20110002774Abstract: Apparatus and method of operating a centrifugal compressor and active control system includes a centrifugal compressor with compressor blades mounted on an impeller, an annular cavity bounded in part by a shroud adjacent to the blades, and an active control system for controlling a clearance between the shroud and the blades by controlling a cavity pressure in the cavity. An electronic controller for controlling a control pressure valve for pressurizing using a source of compressor discharge pressure air and depressurizing the cavity respectively may open and close the valves using pulse width modulation. Pressure and clearance sensors positioned for measuring the cavity pressure the blade tip clearance respectively in signal supply communication with the electronic controller may be used. The shroud may be supported by radially spaced apart annular radially outer and inner supports connected to a casing by a bolted joint bounding the cavity.Type: ApplicationFiled: December 3, 2008Publication date: January 6, 2011Inventors: Apostolos Pavlos Karafillis, Kenneth Allen Loehle, Robert Patrick Tameo, David Allen Gutz
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Publication number: 20100250051Abstract: A method and systems for engine control of a vehicle propulsion system are provided. The system includes a plurality of engine model modules executing independently and programmed to receive engine operating condition values from a plurality of sensors positioned on an engine wherein each of the plurality of engine model modules is programmed to determine an estimate of a process parameter of a location in the engine where a sensor is not available, not present at the location, has failed, or is determined to be inaccurate. The system also includes an estimate source selector configured to determine model blending factors and a model blending module configured to determine an estimated virtual sensor value using the determined estimates from at least two of the plurality of engine model modules and the model blending factors.Type: ApplicationFiled: March 31, 2009Publication date: September 30, 2010Inventors: Brian Francis Nestico, Sridhar Adibhatla, David Allen Gutz, Daniel Edgardo Viassolo