Automatic Patents (Class 60/39.24)
  • Patent number: 10480416
    Abstract: Systems and methods for controlling a fluid based engineering system are disclosed. The systems and methods may include a model processor for generating a model output, the model processor including a set state module for setting dynamic states of the model processor, the dynamic states input to an open loop model based on the model operating mode. The model processor may include an input object for processing model input and setting a model operating mode, the model operating mode being a starting mode if the model input is within a data range associated with a starting operation of the control device. The model processor may further include an estimate state module for determining an estimated state of the model based on a prior state model output and the current state model of the open loop model.
    Type: Grant
    Filed: March 14, 2014
    Date of Patent: November 19, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Boris Karpman, Richard P. Meisner, David Sembiante, Thomas Niemczycki
  • Patent number: 10310456
    Abstract: A method of controlling and managing a process control system having a plurality of control loops includes implementing a plurality of control routines to control operation of the plurality of control loops, respectively, wherein the control routines may include at least one non-adaptive control routine. The method then collects operating condition data in connection with the operation of each control loop, and identifies a respective process model for each control loop from the respective operating condition data collected for each control loop. The identification of the respective process models may be automatic as a result of a detected process change or may be on-demand as a result of an injected parameter change. The process models are then analyzed to measure or determine the operation of the process control loops.
    Type: Grant
    Filed: April 22, 2014
    Date of Patent: June 4, 2019
    Assignee: FISHER-ROSEMOUNT SYSTEMS, INC.
    Inventors: John M. Caldwell, Terrence L. Blevins, Peter Wojsznis, Wilhelm K. Wojsznis
  • Patent number: 10227920
    Abstract: In one embodiment, a system includes a gas turbine system, having: a turbine driven by combustion products produced by a turbine combustion system; and a separation unit positioned between turbine stages of the turbine, wherein the separation unit separates oxygen out of the combustion products. The separation unit may include an ion transport membrane.
    Type: Grant
    Filed: December 17, 2014
    Date of Patent: March 12, 2019
    Assignees: General Electric Company, ExxonMobil Upstream Research Company
    Inventors: Veerappan Muthaiah, Ashok Kumar Anand, Sanyaswara Rao Ganti
  • Patent number: 10221776
    Abstract: Systems and methods for controlling a gas turbine engine are provided. The system comprises an interface to a fuel flow metering valve for controlling a fuel flow to the engine in response to a fuel flow command and a controller connected to the interface and configured for outputting the fuel flow command to the fuel flow metering valve in accordance with a required fuel flow. The controller comprises a feedforward controller configured for receiving a requested engine speed, obtaining a steady-state fuel flow for the requested engine speed as a function of the requested engine speed, the steady-state fuel flow, and the relationship between fuel flow and gas generator speed, and determining the required fuel flow to obtain the requested engine speed and the relationship between fuel flow and gas generator speed.
    Type: Grant
    Filed: November 25, 2016
    Date of Patent: March 5, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Gabriel Meunier, Reza Pedrami
  • Patent number: 10161313
    Abstract: Systems and methods for controlling a fluid based system are disclosed. The systems and methods may include a model processor for generating a model output, the model processor including a set state module for setting dynamic states, the dynamic states input to an open loop model based on the model operating mode, where the open loop model generates current state derivatives, solver state errors, and synthesized parameters as a function of the dynamic states and a model input vector. A constraint on the state derivatives and solver state errors is based on a material temperature utility for determining a material temperature associated with a component of the cycle of the control system. The model processor may include an estimate state module for determining an estimated state of the model based on at least one of a prior state, the current state derivatives, the solver state errors, and the synthesized parameters.
    Type: Grant
    Filed: March 14, 2014
    Date of Patent: December 25, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Boris Karpman, Ian Michael Dinsmore, Richard P. Meisner, John L. Shade
  • Patent number: 9639070
    Abstract: A method for controlling a turbine is proposed, which is characterized at any point in the control by a hidden state. The dynamic behavior of the turbine is modeled with a recurrent neural network comprising a recurrent hidden layer. In this case, the recurrent hidden layer is formed from vectors of neurons, which describe the hidden state of the turbine at the time points of the regulation, wherein two vectors are chronologically linked for each time point with a first connection bridging a time and second connection bridging at least two points in time. Short-term effects can be controlled by means of the first connections and long-term effects can be adjusted by means of the second connections. Secondly, emissions and also occurring dynamics in the turbine can be minimized. Furthermore, a regulating device and a turbine with such a regulating device are proposed.
    Type: Grant
    Filed: April 8, 2013
    Date of Patent: May 2, 2017
    Assignee: Siemens Aktiengesellschaft
    Inventors: Siegmund Düll, Steffen Udluft, Lina Weichbrodt
  • Patent number: 9482236
    Abstract: A turbine engine includes a compressor, and high and low pressure turbines. The configuration includes a mid-compression station which can be, in the case of a single compressor in the middle of that compressor, or at the exit of the first compressor in the case of two compressors. Also, there is an exit pressure station at the exit of the compression system. A first gas flow line is interposed between the mid-compression station of the compressor and the low pressure turbine, and a second gas flow line is interposed between the exit pressure station of the compression system and the high pressure turbine. A first valve is coupled to the first gas flow line and modulates a low pressure flow rate of coolant in the first gas flow line, and a second valve is coupled to the second gas flow line and modulates a high pressure flow rate of coolant in the second coolant flow line.
    Type: Grant
    Filed: September 27, 2013
    Date of Patent: November 1, 2016
    Assignee: Rolls-Royce Corporation
    Inventors: Syed Jalaluddin Khalid, Mark J. Gritton
  • Patent number: 9464534
    Abstract: A system configured to precisely control and/or modulate purge flow in a power plant system (e.g., a gas turbine) during operation is disclosed. In one embodiment, a system includes: at least one computing device adapted to control a purge flow in a gas turbine by performing actions comprising: obtaining operational data from the gas turbine; determining an inferred gas path pressure value for the gas turbine; determining an allowable purge flow for the gas turbine as a function of the operational data and the inferred gas path pressure value; and adjusting the purge flow based upon the allowable purge flow determination.
    Type: Grant
    Filed: March 15, 2013
    Date of Patent: October 11, 2016
    Assignee: General Electric Company
    Inventors: Robert Joseph Reed, Kevin Thomas McGovern
  • Patent number: 9376913
    Abstract: The aim of the invention is to improve the efficiency of an axial-piston motor. To this end, the axial-piston motor comprises at least one compressor cylinder, at least one working cylinder and at least one pressure line guiding the compressed fuel from the compressor cylinder to the working cylinder. A working piston comprising a working rod is provided in the working cylinder, and a compressor piston comprising a compressor rod is provided in the compressor cylinder. The axial-piston motor is characterized in that it at least one of the two rods comprises transverse stiffeners.
    Type: Grant
    Filed: July 26, 2010
    Date of Patent: June 28, 2016
    Assignee: GETAS Gesellschaft fuer thermodynamische Antriebssysteme mbH
    Inventors: Ulrich Rohs, Dieter Voigt
  • Patent number: 9284231
    Abstract: A turbine power generation system with enhanced stabilization of refractory carbides provided by hydrocarbon from high carbon activity gases is disclosed. The disclosure also includes a method of using high carbon activity gases to stabilize hot gas path components.
    Type: Grant
    Filed: December 16, 2011
    Date of Patent: March 15, 2016
    Assignee: General Electric Company
    Inventors: William Paul Minnear, Ronald Scott Bunker, Narendra Digamber Joshi, Andrei Tristan Evulet
  • Patent number: 9145213
    Abstract: A gas turbine engine is disclosed which is capable of being reconfigured for one operating mode to another. A display is provided that permits a pilot or other operator to select between engine modes. One aspect is the ability to provide variable cooling that can be controlled by various devices. The variable cooling features can be used with devices such as cooled turbine components like vanes and/or blades. Devices can be used to reconfigure the performance and/or operability of a gas turbine engine.
    Type: Grant
    Filed: December 18, 2013
    Date of Patent: September 29, 2015
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventors: Joseph D. Myer, Steven W. Tomlinson
  • Patent number: 9097187
    Abstract: An exemplary method is disclosed for operating a gas turbine power plant with exhaust gas recirculation, in which the exhaust gas recirculation is, for example, disengaged during starting and shutting down of the gas turbine, and in which the engaging or disengaging of the exhaust gas recirculation can be carried out in dependence upon an operating state of the gas turbine. An exemplary gas turbine power plant with exhaust gas recirculation is also disclosed which can include a control element, the closing speed of which is such that the control element can be closed within a time which is less than a time for exhaust gases to flow from the turbine through an HRSG.
    Type: Grant
    Filed: April 30, 2012
    Date of Patent: August 4, 2015
    Assignee: ALSTOM TECHNOLOGY LTD.
    Inventors: Stefan Rofka, Jürgen Hoffmann, Eribert Benz, Frank Sander, Martin Nicklas
  • Patent number: 9032703
    Abstract: In a gas turbine engine that includes a compressor and a combustor, wherein the combustor includes a primary fuel injector within a fuel nozzle and a secondary fuel injector that is upstream of the fuel nozzle and configured to inject fuel into a flow annulus of the combustor, a method for detecting a flame holding condition about a fuel injector. The method may include the steps of: detecting an upstream pressure upstream of the secondary fuel injector; detecting a downstream pressure downstream of the secondary fuel injector; determining a measured pressure difference between the upstream pressure and the downstream pressure; and comparing the measured pressure difference to an expected pressure difference.
    Type: Grant
    Filed: June 20, 2011
    Date of Patent: May 19, 2015
    Assignee: General Electric Company
    Inventors: Anthony Wayne Krull, Gilbert Otto Kraemer, Garth Curtis Frederick, David Kaylor Toronto
  • Patent number: 9021780
    Abstract: A gas turbine engine is provided having a variety of forms and features. The gas turbine engine can include a compressor having movable vanes. In one form of operation the compressor can close down the vanes to a relatively low flow capacity position and the compressor can be operated at a higher speed, whereupon the vanes can be repositioned and the gas turbine engine operated at a different condition. The gas turbine engine can include a turbine having movable vanes. In one form of operation the turbine can change the vane positions to a relatively low torque position and the engine operated at a higher fuel flow condition, whereupon the vanes can be repositioned and the gas turbine engine operated at a different condition. The gas turbine engine can have a heater that adds heat to a flow stream, a motor that provides energy to a shaft, and an external load.
    Type: Grant
    Filed: December 23, 2009
    Date of Patent: May 5, 2015
    Assignee: Rolls-Royce Corporation
    Inventors: Ray F. Bowman, Philip Ray Owen
  • Patent number: 8899008
    Abstract: A system includes an anti-icing heat recovery system, which includes a first heat exchanger, a second heat exchanger, and a variable speed fan. The first heat exchanger is configured to receive a working fluid from an exhaust section of a gas turbine engine and to transfer heat from the working fluid to a cooled intermediate heat transfer medium to generate a heated intermediate heat transfer medium. The second heat exchanger is configured to receive the heated intermediate heat transfer medium from the first heat exchanger and to transfer heat from the heated intermediate heat transfer medium to air entering the gas turbine engine. The variable speed fan is configured to urge the working fluid from the exhaust section of the gas turbine engine through the first heat exchanger.
    Type: Grant
    Filed: May 15, 2012
    Date of Patent: December 2, 2014
    Assignee: General Electric Company
    Inventors: Douglas Alan Jones, Gerardo Plata Contreras, Robert Allen Baten, Victor Gerardo Cabal Velarde, Jingmei Zhang, Jesus Elios Almendarez Mendez, Richard Michael Watkins
  • Patent number: 8850818
    Abstract: Systems and methods for supplying fuel to a gas turbine are described. A fuel may be received, and one or more parameters associated with the received fuel may be determined. Based at least in part upon the determined one or more parameters, a desired pressure for removing one or more liquids from the fuel utilizing a separator may be calculated. The operation of a pressure changing device may then be controlled in order to achieve the desired pressure. In certain embodiments, the operations of the method may be performed by a controller that includes one or more computers.
    Type: Grant
    Filed: October 18, 2010
    Date of Patent: October 7, 2014
    Assignee: General Electric Company
    Inventors: Timothy Russell Bilton, Daniel Martin Moss, Korey Frederic Rendo, Colin Wilkes
  • Publication number: 20140260177
    Abstract: An automated industrial system is provided that includes a sensor system configured to monitor multiple parameters. The automated industrial system also includes a controller. The controller is configured to determine if any of the multiple parameters has surpassed a respective constraint threshold of multiple constraint thresholds. If any of the parameters has surpassed a respective constraint threshold, the controller is configured to classify a parameter of the multiple parameters which has surpassed the respective constraint threshold by the highest degree as the most constrained parameter. The controller is also configured to calculate a minimum temperature load path based on the most constrained parameter, with the minimum temperature load path configured to transition the automated industrial system from a base load to a part load via a minimum temperature load path.
    Type: Application
    Filed: March 15, 2013
    Publication date: September 18, 2014
    Applicant: General Electric Company
    Inventor: Robert Joseph Reed
  • Publication number: 20140260287
    Abstract: Gas turbine firing temperature optimization based on a measured sulfur content of a fuel supply of the gas turbine system is provided. In one embodiment, a system includes a diagnostic system configured to determine a maximum firing temperature for a combustor of a gas turbine system. The diagnostic system may determine the maximum firing temperature based on a predetermined sulfur content to maximum firing temperature correlation and an actual sulfur content of a fuel supplied to the combustor. The diagnostic system may also be configured to provide an indicator for a change in an actual firing temperature in the combustor of the gas turbine system. The diagnostic system may provide the indicator in response to the determined maximum firing temperature differing from the actual firing temperature of the combustor of the gas turbine system.
    Type: Application
    Filed: March 15, 2013
    Publication date: September 18, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Robert Thomas Thatcher, Bradley Steven Carey, Paul Burchell Glaser, Ariel Harter Lomas, Andrew Mitchell Rodwell
  • Patent number: 8826670
    Abstract: A method is provided for operating a gas turbine in a power station in which limits of the operating concept, which provide limits for optimization of the power station operation in respect of efficiency, service life consumption, emissions and power provision to the grid system, are adapted during operation. In particular, temperature limits and compressor inlet guide vane position limits are varied as a function of the optimization aims. A gas turbine power station is also provided for carrying out the method.
    Type: Grant
    Filed: September 3, 2010
    Date of Patent: September 9, 2014
    Assignee: Alstom Technology Ltd
    Inventors: Jürgen Hoffmann, Johann Josef Daxer, Bernhard Wippel, Klaus-Dieter Liedtke
  • Publication number: 20140238035
    Abstract: The method for adjusting a natural gas temperature for a fuel supply line of a gas turbine engine includes measuring by infrared analysis the natural gas percentage content of methane (CH4), ethane (C2H6), propane (C3H8), butane (C4H10), carbon dioxide (CO2), calculating the nitrogen (N2) percentage content as the complement to 100 of the measured percentage content of methane (CH4), ethane (C2H6), propane (C3H8), butane (C4H10), carbon dioxide (CO2), calculating an index indicative of the natural gas energy content and adjusting the natural gas temperature on the basis of the index.
    Type: Application
    Filed: February 25, 2014
    Publication date: August 28, 2014
    Inventors: Klaus KNAPP, Peter MARX, Karl REYSER, Maria-Belen GASSER-PAGANI
  • Patent number: 8813472
    Abstract: A system includes a controller configured to control a semi-closed power cycle system. The controller is configured to receive at least one of a first signal indicative of an oxygen concentration within a first gas flow through a primary compressor, a second signal indicative of power output by the semi-closed power cycle system, a third signal indicative of a temperature of a second gas flow through a turbine, and a fourth signal indicative of a mass flow balance within the semi-closed power cycle system. The controller is also configured to adjust at least one of the first gas flow through the primary compressor, a fuel flow into a combustor, a fraction of the first gas flow extracted from the primary compressor, and an air flow through a feed compressor based on the at least one of the first signal, the second signal, the third signal, and the fourth signal.
    Type: Grant
    Filed: October 21, 2010
    Date of Patent: August 26, 2014
    Assignee: General Electric Company
    Inventors: James Anthony West, Alan Meier Truesdale
  • Publication number: 20140182298
    Abstract: In one embodiment, a system includes at least one sensor configured to communicate a signal representative of a gas turbine operations. The system further includes a controller communicatively coupled to the sensor. The system additionally includes a stoichiometric model configured to receive one or more inputs representative of the gas turbine operations and a measured equivalence ratio, wherein the controller is configured to transform the signal into the one or more inputs and to use the stoichiometric model to derive an actuation signal based on a target equivalence ratio.
    Type: Application
    Filed: October 30, 2013
    Publication date: July 3, 2014
    Applicants: ExxonMobil Upstream Research Company, General Electric Company
    Inventors: ANTHONY WAYNE KRULL, Rex Allen Morgan, Karl Dean Minto
  • Patent number: 8752393
    Abstract: One embodiment according to the present invention is a unique system for gas turbine engine control. Other embodiments include unique apparatuses, systems, devices, and methods relating to gas turbine engines. Further embodiments, forms, objects, features, advantages, aspects, and benefits of the present invention shall become apparent from the following description and drawings.
    Type: Grant
    Filed: December 22, 2009
    Date of Patent: June 17, 2014
    Assignee: Rolls-Royce Corporation
    Inventor: Ray F. Bowman
  • Publication number: 20140123663
    Abstract: A speed control system for an engine comprising at least one rotary load is provided. The speed control system may include a rotor speed controller configured to regulate speed in the rotary load based on a sensed rotor speed, exclusive of resonant mode speed oscillations, in closed loop feedback with a commanded rotor speed. To provide active damping of resonant mode speed oscillations, a resonance disturbance rejection controller may be configured to compensate a speed control signal by observing a component of the sensed rotor speed that is due to resonant mode oscillations. Based on the observed resonance component, the resonance disturbance rejection controller may compute an adjustment value for the speed control signal. In the particular case of gas turbine engines, the resonance disturbance rejection controller may effect active damping by compensation of a fuel flow request for a gas generator.
    Type: Application
    Filed: November 2, 2012
    Publication date: May 8, 2014
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventor: Peter FICKLSCHERER
  • Patent number: 8695321
    Abstract: A control apparatus for controlling a compressor driven by a driving unit generating driving power by a gas turbine and an electric motor includes: a temperature detection section for detecting an exhaust gas temperature of the gas turbine; and a control section for generating a motor torque instruction value for the electric motor based on the detected exhaust gas temperature. Such a control apparatus can realize a control so as not to distribute a load on the electric motor when the exhaust gas temperature of the gas turbine is low and a driving power is low. As a result, the operation efficiency can be enhanced.
    Type: Grant
    Filed: May 16, 2008
    Date of Patent: April 15, 2014
    Assignee: Mitsubishi Heavy Industries, Ltd.
    Inventors: Kazuhiro Takeda, Masahiro Kobayashi, Hideki Nagao, Yoshiyuki Okamoto
  • Patent number: 8682562
    Abstract: This invention relates generally to gas turbine engine thrust scheduling, and more particularly to systems and methods for smoothing thrust inputs to gas turbine engines. In one embodiment, a method for operating a gas turbine engine comprises, upon disengagement of an auto-throttle system, determining a first trim setting corresponding to a TLA setting, determining a second trim setting where the second trim setting reduces to zero during successive manual throttle lever movements, determining a third trim setting comprising a combination of the first trim setting and the second trim setting, and applying the third trim setting to the TLA setting to smoothly transition from auto-throttle to manual operation of the engine while maintaining engine thrust.
    Type: Grant
    Filed: May 7, 2010
    Date of Patent: March 25, 2014
    Assignee: Rolls-Royce Corporation
    Inventor: Angela J. Shepler
  • Publication number: 20140060065
    Abstract: Systems and methods for accelerating droop response in a combined cycle power plant are provided. According to one embodiment if the disclosure, a system may include a controller and a processor communicatively coupled to the controller. The processor may be configured to receive frequency variation data associated with a frequency variation of an electrical grid, determine, based at least in part on the frequency variation data, a target operational level of the combined cycle power plant and the droop response associated with the target operational level, calculate a variable compensation value, and apply the variable compensation value to the droop response until the target operational level is reached.
    Type: Application
    Filed: September 6, 2012
    Publication date: March 6, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Bryan Edward Sweet, Yuhui Chen
  • Publication number: 20140060066
    Abstract: A method is provided for operating a gas turbine in the event of load shedding and/or rapid shutdown. The method includes operating the gas turbine by the combustion of fuel in a combustion chamber of the gas turbine with the addition of combustion air via an air passage, and driving a load. Upon or directly after the load shedding or rapid shutdown, an additional gas volume is supplied to the combustion chamber via the air passage in order to slow the drop in pressure level in the combustion chamber.
    Type: Application
    Filed: October 31, 2011
    Publication date: March 6, 2014
    Inventor: Holger Hesse
  • Publication number: 20140053567
    Abstract: A method for controlling a turbine engine generator set is disclosed. The method comprises: sensing an operating parameter indicative of a load increase on the turbine engine generator set; operating the turbine engine generator set in a first mode when the sensed operating parameter is within a predetermined range; and operating the turbine engine generator set in a second mode when the sensed operating parameter is outside the predetermined range. The second mode provides a rate of adjustment of operation of the turbine engine generator set that is greater than a rate of adjustment during the first mode.
    Type: Application
    Filed: August 22, 2012
    Publication date: February 27, 2014
    Inventor: Fritz Langenbacher
  • Patent number: 8646278
    Abstract: A condition measurement apparatus is provided and includes a gas turbine engine combustor having an end cover, a liner defining a liner interior and a fuel nozzle communicative with the liner interior, the end cover being formed to separate a cold side thereof, which is a relatively low temperature environment, from a hot side thereof, which is a relatively high temperature environment in which the liner and the fuel nozzle are disposed, the combustor being formed to define a fuel flow path extending through piping disposed at the cold side of the end cover by which fuel is deliverable to the fuel nozzle, and a condition sensing device operably mounted on the piping.
    Type: Grant
    Filed: February 8, 2011
    Date of Patent: February 11, 2014
    Assignee: General Electric Company
    Inventors: Kwanwoo Kim, Geoffrey David Myers, Venkateswarlu Narra, Shiva Kumar Srinivasan
  • Publication number: 20140000272
    Abstract: A method and system for controlling a two-shaft turbine engine, the two-shaft turbine engine including a gas producer having a compressor with adjustable inlet guide vanes. The method includes monitoring a rotational speed of the gas producer, maintaining an inlet guide vane angle constant when a rotational speed of the gas producer is below a threshold value, and adjusting an inlet guide vane angle of the compressor at a predetermined rate when the rotational speed of the gas producer is above the threshold value.
    Type: Application
    Filed: June 29, 2012
    Publication date: January 2, 2014
    Inventors: Edward C. Fichtner, Garrett C. Bolander, Chad M. Holcomb, Paul V. Smith
  • Publication number: 20130327053
    Abstract: A system includes a gas turbine system model configured to model a turbine system operational behavior of a gas turbine system, and a shaft contribution model (SCM) including a bottoming cycle performance (BCP) model configured to model a bottoming cycle behavior of a bottoming cycle system. The gas turbine system model is configured to receive a SCM output from the SCM and to use the SCM output to control an actuator. The actuator is operatively coupled to the gas turbine system.
    Type: Application
    Filed: June 8, 2012
    Publication date: December 12, 2013
    Applicant: General Electric Company
    Inventors: Paul Jeffrey Mitchell, Randy Scott Rosson, Kevin Wood Wilkes
  • Publication number: 20130269362
    Abstract: A method of controlling a power plant that comprises a working fluid and a recirculation loop, wherein the power plant includes a combustor operably connected to a turbine, the method including the steps of: recirculating at least a portion of the working fluid through the recirculation loop; controlling the power plant such that the combustor at least periodically operates at a preferred stoichiometric ratio; and extracting the working fluid from at least one of a first extraction point and a second extraction point positioned on the recirculation loop during the periods when the combustor operates at the preferred stoichiometric ratio.
    Type: Application
    Filed: April 12, 2012
    Publication date: October 17, 2013
    Inventors: Lisa Anne Wichmann, Stanley Frank Simpson
  • Publication number: 20130255220
    Abstract: In one embodiment, a gas turbine engine control system includes an engine controller configured to control multiple parameters associated with operation of a gas turbine engine system. The gas turbine engine control system also includes multiple remote interface units communicatively coupled to the engine controller. The remote interface unit is configured to receive an input signal from the engine controller indicative of respective target values of at least one parameter, and the remote interface unit is configured to provide closed-loop control of the at least one parameter based on the input signal and feedback signals indicative of respective measured values of the at least one parameter.
    Type: Application
    Filed: March 30, 2012
    Publication date: October 3, 2013
    Applicant: General Electric Company
    Inventors: Harry Kirk Mathews, JR., Brent Jerome Brunell, Simon Shlomo Lis, R. Sheldon Carpenter, Samhita Dasgupta, Sridhar Adibhatla, Scott Douglas Waun, Emad Andarawis Andarawis
  • Publication number: 20130247577
    Abstract: A control method for controlling an overspeed safety system (5) of an aircraft (1) having at least a first engine (10) and a second engine (20), during which method an engine is shut down when a monitoring parameter of that engine exceeds a first threshold, and another engine distinct from this engine is shut down when the monitoring parameter for said other engine exceeds a second threshold, said second threshold being greater than said first threshold.
    Type: Application
    Filed: September 13, 2012
    Publication date: September 26, 2013
    Applicant: EUROCOPTER
    Inventors: Regis Rossotto, Hilario Vieira
  • Publication number: 20130232941
    Abstract: An apparatus for powering an aircraft by generating power from a pressure spool of a turbine engine includes a speed range reduction assembly that reduces the higher speed ranges of a low pressure spool to lower speed ranges within the tolerances of the same DC or VF generators used with the high pressure spool.
    Type: Application
    Filed: March 7, 2012
    Publication date: September 12, 2013
    Applicant: GE AVIATION SYSTEMS LLC
    Inventor: Hao Huang
  • Publication number: 20130219910
    Abstract: A gas turbine, computer software and a method for controlling an operating point of the gas turbine that includes a compressor, a combustor and at least a turbine is provided. The method comprises: determining an exhaust pressure at an exhaust of the turbine; measuring a compressor pressure discharge at the compressor; determining a turbine pressure ratio based on the exhaust pressure and the compressor pressure discharge; calculating a primary to lean-lean mode transfer threshold reference curve as a function of the turbine pressure ratio, where the primary to lean-lean mode transfer threshold curve includes points at which an operation of the gas turbine is changed between a primary mode to a lean-lean mode; and controlling the gas turbine to change between the primary mode and the lean-lean mode.
    Type: Application
    Filed: November 19, 2010
    Publication date: August 29, 2013
    Inventor: Claudio Botarelli
  • Publication number: 20130219906
    Abstract: A system for tuning the operation of a gas turbine is provided based on measuring operational parameters of the turbine and directing adjustment of operational controls for various operational elements of the turbine. A controller is provided for communicating with sensors and controls within the system. The controller receiving operational data from the sensors and comparing the data to stored operational standards to determining if turbine operation conforms to the standards. The controller then communicates selected adjustment in an operational parameter of the turbine. The controller then receives additional operational data from the sensors to determine if an additional adjustment is desired or is adjustment is desired of a further selected operational parameter.
    Type: Application
    Filed: April 2, 2013
    Publication date: August 29, 2013
    Applicant: Gas Turbine Efficiency Sweden AB
    Inventor: Gas Turbine Efficiency Sweden AB
  • Patent number: 8516829
    Abstract: Embodiments of the invention can provide systems and methods for modifying the operation and/or performance of a gas turbine. According to one embodiment, a method for modifying the performance of a gas turbine comprising one or more combustors can be provided. The method can include measuring a gas exhaust temperature for the gas turbine and estimating a heat transfer rate for the gas turbine based at least in part on the gas exhaust temperature. After estimating the heat transfer rate, the method can continue by estimating a transiently accurate combustion reference temperature and using this parameter to control the one or more combustors of the gas turbine. In doing so, the performance of the gas turbine can be modified to ensure reliable and consistent operation.
    Type: Grant
    Filed: May 27, 2009
    Date of Patent: August 27, 2013
    Assignee: General Electric Company
    Inventors: David Ewens, Kevin Wilkes, Christopher Long, Noemie Dion Ouellet
  • Publication number: 20130199196
    Abstract: In one embodiment of the present disclosure, a gas turbine system for part load efficiency improvement is described. The system includes a gas turbine having a compressor which receives inlet-air. An evaporative cooler system using heated fluid heats the inlet-air before the inlet-air flows to the compressor. Heating the inlet-air reduces an output of the gas turbine and extends the turndown range.
    Type: Application
    Filed: February 7, 2012
    Publication date: August 8, 2013
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Rahul Chillar, Vijay Nenmeni, Julio Enrique Mestroni, Jianmin Zhang, James Patrick Tomey
  • Patent number: 8504276
    Abstract: Embodiments for controlling a gas turbine engine to minimize combustion dynamics and emissions are disclosed. Methods and an apparatus are provided for controlling the gas turbine engine where a compressor inlet temperature is measured and a turbine reference temperature is calculated in real-time and utilized to determine the most-efficient fuel splits and operating conditions for each of the fuel circuits. The fuel flow for the fuel circuits are then adjusted according to the identified fuel split.
    Type: Grant
    Filed: February 28, 2008
    Date of Patent: August 6, 2013
    Assignee: Power Systems Mfg., LLC
    Inventors: Vincent C. Martling, Peter So, Zhenhua Xiao, Plazi Ricklin
  • Publication number: 20130192241
    Abstract: A method of managing a gas turbine engine operating line includes detecting an air speed and a fan speed. A data table is referenced that includes a desired variable area fan nozzle position based upon air speed and fan speed. The detected air speed and detected fan speed are compared to the data table to determine a target variable area fan nozzle position. An actual variable area fan nozzle position is adjusted to the target variable area fan nozzle position.
    Type: Application
    Filed: February 3, 2012
    Publication date: August 1, 2013
    Inventors: Geoffrey T. Blackwell, William J. McVey, William G. Tempelman
  • Publication number: 20130174567
    Abstract: A method of reducing engine noise for an engine under little or low load conditions includes the steps of: establishing an engine idle speed for the engine when the engine has less than a predetermined minimum level of load; measuring the level of load on the engine; measuring the speed of the engine; and reducing the speed of the engine to the engine idle speed if the measured level of load on the engine is less than the predetermined minimum level of load and the measured speed of the engine is greater than the engine idle speed.
    Type: Application
    Filed: January 10, 2012
    Publication date: July 11, 2013
    Applicant: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Stacey H. Light, James C. Napier
  • Patent number: 8456634
    Abstract: Certain embodiments of the invention may include systems and methods for providing optical interrogation sensors for combustion control. According to an example embodiment of the invention, a method for controlling combustion parameters associated with a gas turbine combustor is provided. The method can include providing an optical path through the gas turbine combustor, propagating light along the optical path, measuring absorption of the light within the gas turbine combustor, and controlling at least one of the combustion parameters based at least in part on the measured absorption.
    Type: Grant
    Filed: June 15, 2009
    Date of Patent: June 4, 2013
    Assignee: General Electric Company
    Inventors: Keith Robert McManus, Lewis Berkley Davis, Jr.
  • Publication number: 20130125557
    Abstract: A gas turbine system includes a compressor protection subsystem; a hibernation mode subsystem; and a control subsystem that controls the compressor subsystem and the hibernation subsystem. At partial loads on the turbine system, the compressor protection subsystem maintains an air flow through a compressor at an airflow coefficient for the partial load above a minimum flow rate coefficient where aeromechanical stresses occur in the compressor. The air fuel ratio in a combustor is maintained where exhaust gas emission components from the turbine are maintained below a predetermined component emission level while operating at partial loads.
    Type: Application
    Filed: November 23, 2011
    Publication date: May 23, 2013
    Inventors: Alston I. Scipio, Thomas John Freeman, Ryan Eric Obenhoff, Sanji Ekanayake, Michael Anthony Cocca, Mike Yarnold, Douglas Corbin Warwick, Joseph Klosinski
  • Publication number: 20130118146
    Abstract: A twin-shaft gas turbine can be used for 50 and 60 Hz power generation without using a reducer. A gas generator includes a compressor that generates compressed air, a burner that burns a fuel mixed with the compressed air received from the compressor so as to generate combustion gas, and a high-pressure turbine that is rotationally driven by the combustion gas received from the burner and generates driving force for the compressor. An output turbine includes a low-pressure turbine that is driven by exhaust gas received from the high-pressure turbine and a power generator that is driven by the low-pressure turbine. A control device reduces opening degree of IGV of the compressor and thereby reduces power of the compressor, and the rotational frequency of the gas generator is increased in a full-speed no-load operating state of the power generator.
    Type: Application
    Filed: November 13, 2012
    Publication date: May 16, 2013
    Inventor: Hitachi, Ltd.
  • Publication number: 20130111916
    Abstract: A system for operating a power plant is provided and includes a grid configured to generate a normal load and an abnormal load, a turbomachine configured to provide power to the grid in accordance with the normal load by firing at normal temperatures and in accordance with the abnormal load by firing at higher-than-normal temperatures, a cooling system disposed to cool components of the turbomachine with fluid supplied by an external reservoir and a controller configured to identify when the grid generates the abnormal load and to responsively operate the cooling system.
    Type: Application
    Filed: November 7, 2011
    Publication date: May 9, 2013
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Jason Edward Beard, Randy Scott Rosson
  • Patent number: 8434291
    Abstract: A system may detect a flame about a fuel nozzle of a gas turbine. The gas turbine may have a compressor and a combustor. The system may include a first pressure sensor, a second pressure sensor, and a transducer. The first pressure sensor may detect a first pressure upstream of the fuel nozzle. The second pressure sensor may detect a second pressure downstream of the fuel nozzle. The transducer may be operable to detect a pressure difference between the first pressure sensor and the second pressure sensor.
    Type: Grant
    Filed: January 8, 2009
    Date of Patent: May 7, 2013
    Assignee: General Electric Company
    Inventors: Gilbert Otto Kraemer, James Michael Storey, John Lipinski, Julio Enrique Mestroni, David Lee Williamson, Jason Randolph Marshall, Anthony Krull
  • Publication number: 20130104516
    Abstract: A method, apparatus and gas turbine for monitoring an operation of a valve of a gas turbine is disclosed. A first sensor obtains a first indicator of a configuration of the valve of the gas turbine. A second sensor measures a physical parameter affected by the valve configuration. A processor is used to obtain a second indicator of the valve configuration from the measured physical parameter and compare the first indicator to the second indicator to monitor the operation of the valve.
    Type: Application
    Filed: October 31, 2011
    Publication date: May 2, 2013
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Gerardo Fidel Varillas, John Edward Pritchard
  • Publication number: 20130091856
    Abstract: A control system is provided. The control system includes at least one sensor positioned within a turbine engine, wherein the sensor is configured to detect at least one first operating parameter within the turbine engine. A controller is coupled to the sensor and the controller is configured to receive at least one second operating parameter of the turbine engine. The controller is also configured to control a flow of a fluid to a rotor assembly within the turbine engine such that the fluid is distributed substantially uniformly within the rotor assembly and at least one of the first operating parameter and the second operating parameter is less than at least one threshold value.
    Type: Application
    Filed: October 12, 2011
    Publication date: April 18, 2013
    Inventor: Nathan Stafford Race