| Entries |
| Document | Title | Date |
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| 20080208429 | Systems and methods for steam turbine remote monitoring, diagnosis and benchmarking - Systems and methods for steam turbine remote monitoring, calculating corrected efficiency, monitoring performance degradation, diagnosing and benchmarking are disclosed with an example turbine system including a turbine, a data acquisition device coupled to the turbine, the data acquisition device for collecting turbine data that includes performance parameters of the turbine and a central monitoring system coupled to the data acquisition device, the central monitoring system for receiving the collected turbine data and processing the turbine data to determine turbine performance. | 08-28-2008 |
| 20080221772 | CONTROL SYSTEM FOR GAS TURBINE IN MATERIAL TREATMENT UNIT - This invention discloses systems and methods for control of a gas turbine or a gas turbine generator, where the gas turbine is connected to a dryer vessel in which gas turbine exhaust gases are used to heat treat a material in the dryer vessel. The control system comprises one or more sensors for temperature, moisture and/or flow rate in the dryer vessel and/or of the material inside, entering and/or exiting the dryer vessel and a controller responsive to the sensor for controlling the fuel and/or air flow into the gas turbine. This control system and method enables providing the appropriate heat output from the gas turbine to meet the process heat required for the desired material treatment. Optionally, the gas turbine can be a liquid fuel turbine engine, or a reciprocating engine can be substituted for the turbine engine. | 09-11-2008 |
| 20080228370 | SYSTEM FOR DETECTING IGNITION FAILURE IN A GAS TURBINE ENGINE - A method of operating a gas turbine engine is provided. The method includes introducing a fuel into a combustor, detecting a failure of ignition of the fuel, and preventing ignition until the introduced fuel is substantially removed from the gas turbine engine. | 09-18-2008 |
| 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 |
| 20080270003 | FEEDBACK CONTROL SYSTEM AND METHOD THAT SELECTIVELY UTILIZES OBSERVER ESTIMATES - A system and method implements improved machine performance, most preferably for gas turbine engines. The system and method implement a control law that receives sensed operational parameter feedback signals. For each sensed engine operational parameter, the feedback signals that are supplied to the control law selectively comprise the sensor signal representative of the engine operational parameter, if the sensor signal is valid, or an observer estimate of the sensed engine operational parameter, if the sensor signal is invalid. | 10-30-2008 |
| 20080275619 | Ignition detecting method for gas turbine - A gas turbine which can detect ignition in a combustor regardless of startup conditions of the gas turbine, such as the hot startup or the cold startup. An ignition detecting method for the gas turbine comprises the steps of calculating a difference between the exhaust temperature detected at a particular time before outputting of an ignition command for a combustor and the exhaust temperature detected after the outputting of the ignition command, and determining that the combustor is ignited, when the calculated difference is not less than a predetermined value. As an alternative, the method includes a step of determining that the combustor is ignited, when a change amount or rate of the exhaust temperature exceeds a predetermined value in a predetermined period from the outputting time of the ignition command. | 11-06-2008 |
| 20080275620 | Ignition detecting method for gas turbine - A gas turbine which can detect ignition in a combustor regardless of startup conditions of the gas turbine, such as the hot startup or the cold startup. An ignition detecting method for the gas turbine comprises the steps of calculating a difference between the exhaust temperature detected at a particular time before outputting of an ignition command for a combustor and the exhaust temperature detected after the outputting of the ignition command, and determining that the combustor is ignited, when the calculated difference is not less than a predetermined value. As an alternative, the method includes a step of determining that the combustor is ignited, when a change amount or rate of the exhaust temperature exceeds a predetermined value in a predetermined period from the outputting time of the ignition command. | 11-06-2008 |
| 20080294322 | METHOD FOR CONTROLLING THE PRESSURE DYNAMICS AND FOR ESTIMATING THE LIFE CYCLE OF THE COMBUSTION CHAMBER OF A GAS TURBINE - A method is described for controlling the combustion in a gas turbine. The method comprises the phases of measuring, by means of one or more probes ( | 11-27-2008 |
| 20080319629 | METHOD AND APPARATUS FOR CONTROLLING AND REGULATING A ROTORCRAFT TURBINE ENGINE - The present invention relates to a method and to apparatus ( | 12-25-2008 |
| 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 |
| 20090005952 | 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 determining whether the median value exceeds at least one operating threshold. The method can also include implementing at least one engine control action to modify at least one of the operating frequencies if at least one operating threshold is exceeded. | 01-01-2009 |
| 20090024295 | SYSTEM AND METHOD FOR REMOTELY MONITORING A TURBOCHARGED ENGINE - A method and system for remotely monitoring the operation of a multicylinder, turbocharged reciprocating engine includes monitoring one or more operating parameters predictive of the turbocharger's output, and generating a parametric output signal corresponding to the value of the sampled operating parameter. The parametric output signal is transmitted via telemetry to a remote diagnostic center, where actual mass flow is determined with a flow detection system, and then the charge air mass flow is compared with a predetermined flow rate corresponding to the monitored operating parameter, such as turbocharger speed or turbocharger pressure ratio. A condition flag is set if the actual charge air flow rate is less than a predetermined flow rate based upon the parametric output signal. | 01-22-2009 |
| 20090055070 | SYSTEM AND METHOD FOR PREDICTION OF GAS TURBINE TRIPS DUE TO THERMOCOUPLE FAILURES - Systems and methods for prediction of gas turbine trips due to component failures such as thermocouple failures. Exemplary embodiments include prediction of gas turbine trips due to component failures, including collecting raw gas turbine operational data and using the raw gas turbine operational data to generate a prognostic indicator for the prediction of a turbine trip due to the failed thermocouples. | 02-26-2009 |
| 20090055071 | ACTIVE SURGE CONTROL - The present invention generally relates to a system for preventing surges in turbine engines and/or rotating compressors. Furthermore, some embodiments comprise sensors for monitoring engine operating characteristics and detecting surge and pre-surge conditions. Some embodiments also include means for adjusting engine operation in response to sensor data. Still other embodiments relate to methods of preventing surges in turbine engines and/or rotating compressors. | 02-26-2009 |
| 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 |
| 20090069998 | Event-driven starter controller - An event-driven starter controller regulates the speed of a gas turbine engine based on detected events. The event-driven starter controller is used to supply motive force to the gas turbine engine, prior such that the gas turbine engine is able to ignite (i.e., achieve light-off). In particular, in response to engine speed reaching a defined threshold, the event-driven starter controller causes the speed of the starter motor to ramp or increase through a defined range of speeds suitable for engine light-off (i.e, light-off window). Upon reaching an upper threshold of the light-off window, the event-driven starter controller causes the speed of the starter motor to decrease through the range of speeds suitable for engine light-off. If at any time during the light-off window the event-driven starter controller detects a successful light-off condition, the event-driven starter controller causes the speed of the gas turbine engine to increase toward a second threshold. | 03-12-2009 |
| 20090099750 | Manuever-based aircraft gas turbine engine speed control system and method - A system and method for controlling the rotational speed of a gas turbine engine in an aircraft includes appropriate devices and processes for determining a pressure of lubricant supplied to the turbine engine, and for determining a maneuver state of the aircraft. The rotational speed of the gas turbine engine is controlled based at least partially on the determined pressure and the determined maneuver state. Thus, if the aircraft is in a maneuver state that may cause a reduction or loss of lubricant to the gas turbine engine, the rotational speed of the gas turbine engine can be reduced to a magnitude sufficient to increase turbomachine tolerance to the reduced or no lubricant flow. | 04-16-2009 |
| 20090125205 | METHOD OF OPTIMIZING THE PERFORMANCE ENVELOPE OF A TURBINE ENGINE - A method of optimizing an initial performance envelope of a rotorcraft turbine engine, the initial envelope being associated with a maximum number of flying hours that the turbine engine can perform before being overhauled, and also with at least a first initial rating defined by two first initial performance levels relating respectively to a first power and to a first utilization time of the first power. The method is remarkable in that in order to perform the optimization, an alternative performance envelope is defined by modifying the initial envelope, the modification being compensated by reducing at least one of the first initial performance levels of the first initial rating. In addition, the overall service life of the turbine engine is not modified insofar as the alternative envelope is associated with the maximum number of flying hours authorized for operating the turbine engine in compliance with the initial envelope. | 05-14-2009 |
| 20090125206 | Automatic detection and notification of turbine internal component degradation - An automated computer-implemented steam turbine engine monitoring and control arrangement provides continual monitoring and performs ongoing analysis of turbine system operational parameters to identify turbine internal component degradation. Current operational data for selected parameters are compared with accumulated past operational parameter data on a continuing basis to detect gradual changes occurring over an extended period of turbine operation. Based upon a comparison of some or all of the particular monitored turbine system operational parameters, and on the amount or rate of detected change occurring over time, a determination is made as to whether internal component degradation has progressed to a significant degree and to which particular turbine internal components are most likely to have incurred damage or degradation. A report or warning notification is then automatically generated which provides this information that maintenance planning and/or appropriate damage mitigation procedures may be implemented. In addition, the system also is configured to utilize the Internet or other communications network to allow turbine operator interaction with the monitoring system and access to information via a local on-site operator's control console or remotely via a web browser application interface over the Internet or other suitable communications network. | 05-14-2009 |
| 20090125207 | GAS TURBINE CONTROL DEVICE AND GAS TURBINE SYSTEM - An object of the present invention is to provide a gas turbine control device which is capable of performing correction on the basis of a fuel composition of fuel gas to be supplied to a gas turbine, and is capable of changing an amount of correction in response to variation with time of the gas turbine. To attain this, a frequency analyzing unit | 05-14-2009 |
| 20090138170 | METHOD FOR OPERATING A GAS TURBINE AND ALSO GAS TURBINE FOR CARRYING OUT THE METHOD - A method is provided for operating a gas turbine, which especially feeds power to a local isolated power supply network, and which comprises a compressor for compressing combustion air which is drawn in from the environment, a combustion chamber for combusting supplied fuel by the compressed combustion air, a turbine which is driven by the hot gas from the combustion chamber, and a generator, which is driven by the turbine, for generating electric power. With such a method, an improvement of controlling is achieved by one or more parameters of the gas turbine being measured or determined, by the effective thermal output power of the gas turbine being calculated from the measured or determined parameters, and by the calculated effective thermal output power being used for controlling the gas turbine. | 05-28-2009 |
| 20090150040 | METHOD FOR CONTROLLING A GAS TURBINE IN A POWER PLANT AND POWER PLANT FOR CARRYING OUT THE METHOD - With a method for controlling a gas turbine in a power plant, a multiplicity of operating lines for the gas turbine for different gas turbine inlet temperatures TIT or gas turbine exhaust temperatures TAT and positions of the compressor inlet guide vane cascade VIGV are specified as a function of the load. For minimizing the electricity production costs during operation switching can be optionally carried out between different operating lines during constant or varying power output of the power plant. | 06-11-2009 |
| 20090177363 | Method and apparatus for monitoring gas turbine blades - A method (and corresponding apparatus) for monitoring gas turbine blades. The output from an eddy current sensor monitoring the movement of turbine blades past the sensor is processed to determine when the signal train from the sensor omits a signal or pulse corresponding to one of the shaft's full complement of blades. The signal processor compares sensed blade periods with average blade periods. | 07-09-2009 |
| 20090204305 | TURBINE BYPASS CONTROL APPARATUS AND TURBINE BYPASS CONTROL METHOD - A turbine bypass control method includes: a high-pressure side pressure controller configured to output a first operation amount signal corresponding to a valve opening; a low-pressure side pressure controller configured to output a second operation amount signal corresponding to a valve opening; a high value selector configured to output as a high value operation amount signal, one of the first operation amount signal and the second operation amount signal which indicates a larger opening; a first signal switching unit configured to receive the high value operation amount signal and the second operation amount signal and output a first bypass valve operation amount signal; a second signal switching unit configured to receive the high value operation amount signal and the first operation amount signal and output a second bypass valve operation amount signal; and a rapid opening controller. Before start of trip of a turbine, the turbine is driven by steam which flows from the high-pressure side header to the low-pressure side header through the turbine. | 08-13-2009 |
| 20090204306 | METHODS AND SYSTEMS FOR MODULATING FUEL FLOW FOR GAS TURBINE ENGINES - A method of combustion stability control for a gas turbine engine is provided, and includes the steps of receiving by a stability controller, information regarding environmental and operating conditions, and comparing the environmental and operating conditions to pre-programmed information to determine if a likelihood of combustion instability exists. The method further includes the steps of determining optimal fuel modulation frequency and amplitude for the environmental condition to reduce combustion instability, if a likelihood of combustion instability exists, and actuating at least one fuel modulation valve to, at the optimal fuel modulation frequency and amplitude, reduce combustion instability, if a likelihood of combustion instability exists. Systems for modulating fuel flow are also provided. | 08-13-2009 |
| 20090222187 | GAS TURBINE ENGINE CONTROLS FOR MINIMIZING COMBUSTION DYNAMICS AND EMISSIONS - 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. | 09-03-2009 |
| 20090234554 | GAS TURBINE ENGINE FIXED COLLECTIVE TAKEOFF COMPENSATION CONTROL SYSTEM AND METHOD - A system and method of controlling a gas turbine engine controller in a rotorwing aircraft includes determining when a fixed collective takeoff (FCTO) of the rotorwing aircraft is being conducted. A control loop gain of the gas turbine engine controller is at least selectively varied when the FCTO is being conducted. | 09-17-2009 |
| 20090259379 | REDUCED TAKE-OFF FIELD LENGTH USING VARIABLE NOZZLE - A turbofan engine control system and method includes a core nacelle housing ( | 10-15-2009 |
| 20090271085 | METHOD AND SYSTEM FOR OPERATING GAS TURBINE ENGINE SYSTEMS - Methods and systems for operating a gas turbine engine system are provided. The system includes a gas turbine engine that includes at least one combustor configured to receive a flow of fuel from a flow control device and a fuel control system. The fuel control system includes a piping system configured to channel the flow of fuel from a fuel source to the flow control device, a sensor configured to generate a signal indicative of a property of the flow of fuel wherein the property of the flow of fuel is variable over time, and a controller including a processor. The processor is programmed to receive the generated signal, using a flow model of the piping system and the received signal, iteratively track the progress of a plurality of discrete volumes flowing through the piping system, and control the flow of fuel using the flow control devices. | 10-29-2009 |
| 20090271086 | Hybrid Engine Accessory Power System - A system for generating accessory power from a gas turbine engine is provided by the present invention. The system includes an electronic control device for monitoring at least one parameter which provides information about an incipient change in power demand, a control valve operated by the control device for supplying bleed air from the engine during a transient state in response to the at least one monitored parameter, and a pneumatically operated device for receiving the bleed air and for generating power to operate equipment onboard an aircraft. The pneumatically operated device may be an air turbine or a pneumatically integrated generator. | 10-29-2009 |
| 20090276136 | METHOD FOR CALCULATING CONFIDENCE ON PREDICTION IN FAULT DIAGNOSIS SYSTEMS - A method and system is developed that provides a confidence measure of a prediction of a fault in a gas turbine engine. The confidence measure is developed based upon evaluating the results of a plurality of past predictions and comparing them to an actual fault. | 11-05-2009 |
| 20090292436 | CONTROL OF COMBINED CYCLE POWER GENERATION SYSTEM - A control system for a combined cycle power generation system including a gas turbine engine (GT), a heat recovery steam generator (HRSG), and a steam turbine (ST) includes a display wherein an operator may observe information about predicted operating parameters; a user interface wherein an operator may provide additional operating constraints; and a controller configured to generate input profiles of the GT, the HRSG, and the ST that satisfy the nominal constraints and any additional constraints and to generate the information about the predicted operating parameters. The controller may be configured to detect a stage transition of power generation system operation and update the input profiles. The controller may be configured to generate alternative operating scenarios by mapping alternative control actions to an operating constraint of at least one of the system components. | 11-26-2009 |
| 20090292437 | Systems and Methods Involving Multiplexed Engine Control Signals - Systems and methods involving multiplexed engine control signals are provided. In this regard, a representative engine control system for a gas turbine engine includes: a signal relay device operative to receive multiplexed signals from an engine electronic control (EEC), demultiplex the signals, and provide demultiplexed signals to corresponding ones of multiple control devices of the engine. | 11-26-2009 |
| 20090312930 | STALL PREDICTION APPARATUS, PREDICTION METHOD THEREOF, AND ENGINE CONTROL SYSTEM - A stall prediction apparatus of an axial compressor provided with: a rotor provided with a plurality of rotor blades; and a cylindrical casing facing the rotor blades and provided so as to cover the outer circumference of the rotor, comprising: pressure sensors provided in equal numbers at a plurality of locations in a circumferential direction of an inner wall surface of the casing, an index calculator for calculating an index (stall risk index) for evaluating the stall risk based on time-series data detected by each of the pressure sensors, and a signal processor for predicting the stall occurrence based on the stall risk indexes obtained corresponding to said each of the pressure sensors. In accordance with the present invention, it is possible to obtain a stall risk index which is highly accurate (supersensitive) and stable necessary for the active stall control, and to realize an engine control system with high reliability. | 12-17-2009 |
| 20090319150 | METHOD, SYSTEM, AND APPARATUS FOR REDUCING A TURBINE CLEARANCE - Methods, systems, and apparatus for controlling a turbine clearance in an aircraft engine are provided. A method includes activating a turbine clearance control based on a flight phase of an aircraft using the aircraft engine, and adjusting the turbine clearance based on a preselected turbine clearance value. | 12-24-2009 |
| 20090326781 | TURBINE ENGINE TRAINING MANUAL MODE FUEL FLOW CONTROL SYSTEM AND METHOD - A method of controlling a gas turbine engine in a vehicle having an automatic system configured to control fuel flow includes determining whether a vehicle operator is requesting to manually control fuel. A pre-relinquishment value of an engine operating condition is determined while fuel flow is controlled by the automatic system. Fuel flow control is relinquished to the vehicle operator if the vehicle operator is requesting to manually control fuel flow and the pre-relinquishment value is within a predetermined range. A post-relinquishment value of the engine operating condition is determined while fuel flow is controlled by the vehicle operator. Fuel flow control is returned to the automatic system if the post-relinquishment value is not maintained within the predetermined range. | 12-31-2009 |
| 20090326782 | AIRCRAFT GAS TURBINE ENGINE CONTROLLER WITH REMOVABLE MEMORY AND DIAGNOSTIC SYSTEM AND METHOD THEREFOR - A system and method of analyzing aircraft gas turbine engine performance data includes receiving, in an engine controller, engine performance data representative of a plurality of aircraft gas turbine engine parameters. At least a portion of the received engine performance data are stored in a fixed memory device that is fixedly coupled to a fixed-memory mount in the engine controller, and in a removable memory device that is non-fixedly coupled to a removable memory mount in the engine controller in a manner that allows the removable memory device to be hand-removable from the removable memory mount. The removable memory device is removed from the removable memory mount in the engine controller, and inserted in a port of a computing device that is not coupled to the engine controller. | 12-31-2009 |
| 20090326783 | FLUID-POWERED THRUST REVERSER ACTUATION SYSTEM SPEED CONTROL - A fluid-powered thrust reverser actuation speed control system and method are provided. A drive fluid is supplied to a fluid-powered drive mechanism that is coupled to a thrust reverser movable component to thereby move the thrust reverser movable component at a first movement speed. A determination is made as to when the thrust reverser movable component attains a predetermined position. In response to the thrust reverser movable component attaining the predetermined position, the drive fluid supplied to the fluid-powered drive mechanism is controlled to thereby move the thrust reverser movable component at a second movement speed that is less than the first movement speed. | 12-31-2009 |
| 20090326784 | Methods and Apparatuses For Monitoring A System - A method for determining probable fail cases of a system includes the steps of:
| 12-31-2009 |
| 20100010720 | METHODS AND SYSTEMS TO FACILITATE OVER-SPEED PROTECTION - A method for assembling a gas turbine engine to prevent rotor over-speeding is described. The method includes serially coupling a first fuel system interface to a second fuel system interface, such that at least one of the first fuel system interface and the second fuel system interface is coupled to the gas turbine engine. The method also includes coupling a control system to the first fuel system interface and to the second fuel system interface. The control system is configured to identify an occurrence of an over-speed condition. The method also includes programming the control system to discontinue fuel flow to the engine when both the first fuel system interface and the second fuel system interface indicate an over-speed condition has occurred. | 01-14-2010 |
| 20100010721 | METHODS AND SYSTEMS TO FACILITATE OVER-SPEED PROTECTION - A method for assembling a gas turbine engine is described. The method includes coupling a first fuel system interface (FSI-1) to a second fuel system interface (FSI-2), and coupling one of the FSI-1 and the FSI-2 to the engine. The method includes coupling a first control system and a second control system to the FSI-1 and to the FSI-2. The first control system includes a first driver A and a second driver A, and the second control system includes a first driver B and a second driver B. The method includes configuring the first control system and the second control system to apply a first over-speed logic algorithm and a second over-speed logic algorithm to determine operation of the first driver A, the second driver A, the first driver B, and the second driver B. | 01-14-2010 |
| 20100017092 | HYBRID FAULT ISOLATION SYSTEM UTILIZING BOTH MODEL-BASED AND EMPIRICAL COMPONENTS - A method of operating and a fault diagnosis system compares readings to predicted faults using a model-based component, and a database of previous actual fault examples. A predicted fault is provided to an output based upon a combination of both the model-based component and the actual fault examples. | 01-21-2010 |
| 20100017093 | Control system - A control system provides an aggregate driven quantity demand signal for controlling an actuatable component. The system has a summing junction which generates the aggregate driven quantity demand signal by summing a first output signal, which converges on a steady state driven quantity requirement value, and a change in driven quantity demand signal. The system further has a feedback loop which generates the first output signal in response to the aggregate driven quantity demand signal. The system also has a first variable gain which tunes the change in driven quantity demand signal in response to a reference demand signal. The feedback loop includes a second variable gain which tunes the rate at which the first output signal converges on the steady state driven quantity requirement value. Typically, the reference demand signal corresponds to a desired value or desired change in value of a parameter which is itself varied or controlled by actuation of the actuatable component. | 01-21-2010 |
| 20100023238 | METHOD AND SYSTEMS FOR CONTROLLING GAS TURBINE ENGINE TEMPERATURE - A method and systems for controlling an engine are provided. The system includes an engine model programmed to receive engine operating condition values from a plurality of sensors on an engine. The engine model is programmed to determine a plurality of engine operating parameter values. The system also includes a processor configured to compare the operating parameter values to a predetermined allowable range for the operating parameter and control the operation of the engine to facilitate returning the determined operating parameter to the allowable range or maintaining the determined operating parameter within the allowable range, output the determined operating parameter values to a user, and/or generate maintenance requests based on the comparison. | 01-28-2010 |
| 20100023239 | POWER DEMAND MANAGEMENT - A method is disclosed of determining the power demand on a power subsystem ( | 01-28-2010 |
| 20100036579 | LOW MINIMUM IMPULSE BIT PROPELLANT GAS THRUSTER - A gas thruster is configured to supply thrust over a relatively wide range, from a relatively low value to a relatively high thrust value, and exhibits relatively fine minimum impulse bit (MIB) performance. The gas thruster includes a thrust nozzle, a main stage, a main valve element, and a pilot valve. The gas thruster responds to thruster control signals supplied to the pilot valve and is configured such that for commands of relatively short duration, only the pilot valve responds and relatively low thrust is produced. Conversely, for command or relatively longer duration, the pilot valve and main valve element both respond and relatively higher thrust is produced. | 02-11-2010 |
| 20100049417 | Dual ECU for aftermarket conversions of vehicles and boats to oxy-hydrogen or hybrid fuels - Modern ECU's control fuel flow and efficiency of high performance vehicles. Converting a standard fossil fuel vehicle or boat to oxy-hydrogen requires monitoring of additional factors such as oxy-hydrogen burn rates, oxy-hydrogen flow, oxy-hydrogen temperature, oxy-hydrogen production rates and overall factors such as barometric pressure, altitude, humidity, ambient temperatures etc. When a vehicle operating as a hybrid, experiences difficulties with oxy-hydrogen production, burn rate, fuel flow, or operating temperature, the ECU must compensate and revert back to fossil fuel operating status, or suffer engine failure and potentially costly mechanical damages. | 02-25-2010 |
| 20100082217 | METHOD AND SYSTEM FOR PROVIDING COOLING AND POWER - A method for providing cooling and power is provided. The method includes providing a cooling unit that includes a first turbine rotatably coupled to a generator by a first shaft and providing a power unit that includes a second turbine rotatably coupled to a compressor by a second shaft. The method further includes coupling the power unit in flow communication with the cooling unit to form a turbine assembly, wherein the first shaft and the second shaft are independently rotatable relative to one another. | 04-01-2010 |
| 20100088003 | SYSTEM AND METHOD FOR PROVIDING GAS TURBINE ENGINE OUTPUT TORQUE SENSOR VALIDATION AND SENSOR BACKUP USING A SPEED SENSOR - Methods and apparatus are provided for verifying proper operation of a gas turbine engine output torque sensor using a speed sensor, and using the speed sensor as a backup torque sensor. Gas turbine engine output torque is sensed using a reference torque sensor, and gas turbine engine output shaft rotational speed is sensed. Gas turbine engine output torque is calculated from the sensed gas turbine engine output shaft rotational speed. The sensed gas turbine engine output torque is compared to the calculated gas turbine engine output torque to determine if the reference torque sensor is operating properly. The gas turbine engine is controlled at least partially based on the sensed gas turbine engine output torque if the reference torque sensor is determined to be operating properly, and is controlled at least partially based on the calculated output torque if the reference torque sensor is determined to be not operating properly. | 04-08-2010 |
| 20100121553 | Engine Relight Method - An engine windmill relight method is described for use with a fuel control system (FCS) having a metering valve (MV), the method comprising the steps of determining a desired fuel delivery rate, and moving the MV to a nominal fuel delivery setting higher than that corresponding to the desired fuel delivery rate. | 05-13-2010 |
| 20100131169 | METHOD OF CONTROLLING AN AIR PREHEATING SYSTEM OF A GAS TURBINE - An embodiment of the present invention has the technical effect of controlling an air preheating system integrated with a gas turbine. The present invention may offer the benefit of extending a turndown range by beating the air (hereinafter “inlet-air”) entering the compressor of the gas turbine. The present invention may also offer the benefit of increasing an efficiency of the powerplant. | 05-27-2010 |
| 20100138132 | ENGINE HEALTH MONITORING - A method of monitoring the health of a gas turbine engine of at least a pair of engines of an aircraft for example. The method comprising the steps of: a) obtaining steady state readings from predetermined sensors on the engines; b) calculate a percentage difference of the steady state readings from a unique engine linear synthesis model for each engine; c) compare the difference between the percentage differences for each engine and d) where this difference exceeds a predetermined value issue a warning as to an engine health problem. Maintenance of the engine can therefore be advantageously scheduled. | 06-03-2010 |
| 20100145590 | SYSTEM AND METHOD FOR LEAN BLOWOUT PROTECTION IN TURBINE ENGINES - A lean blowout protection system and method is provided that facilitates improved lean blowout protection while providing effective control of turbine engine speed. The lean blowout protection system and method selectively and gradually biases the lean blowout (LBO) schedule based on current engine data. This facilitates improved lean blowout protection while providing effective control of turbine engine speed and temperature. | 06-10-2010 |
| 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 |
| 20100168981 | Differential Focus Blade Clearance Probe and Methods for Using Same - An apparatus and a method for ascertaining a gap between a stationary member and a rotating member are disclosed. At least a reference beam and a signal beam, which have different focal lengths or which diverge/converge at different rates, are fixed to the stationary member and proximate to each other. The beams are projected across a gap between the stationary member and the rotating member toward the rotating member. The reference and signal beams are reflected by the translating member when it intersects the reference and signal beam, and the reflected reference and signal pulses are obtained. One or more features of the reflected reference pulse and the reflected signal pulse, such as a rise time of the pulses, a fall time of the pulses, a width of the pulses and a delay between the reflected reference pulse and the reflected signal pulse, among other factors, are obtained. The width of the gap is obtained using at least one of these factors. | 07-01-2010 |
| 20100168982 | METHOD AND SYSTEM FOR CONTROLLING AT LEAST ONE ACTUATOR FOR ACTUATING THE COWLINGS OF A THRUST INVERTER IN A TURBOJET ENGINE - The invention relates to a method for controlling at least one actuator for actuating the cowlings of a thrust inverter in a turbojet engine, the actuator being driven by an electric motor including a relative position sensor providing information on the evolution of the movement thereof, wherein the motor is controlled based on the instantaneous position of the cowling in at least one portion of the movement thereof between an open position and a closed position, the instantaneous position of the cowling being determined from at least one reference position absolute data and relative position data relative to said reference position provided by the relative position sensor of the motor, wherein in case the actuation is resumed after an interruption, a new determination of the reference position is initiated. | 07-01-2010 |
| 20100174466 | LATE LEAN INJECTION WITH ADJUSTABLE AIR SPLITS - A gas turbine engine is provided and includes a combustor having a first interior in which a first fuel is combustible, a turbine into which products of at least the combustion of the first fuel are receivable, a transition zone, including a second interior in which a second fuel and the products of the combustion of the first fuel are combustible, a plurality of fuel injectors which are configured to supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages, a compressor, by which air is supplied to the first and second interiors for the combustion therein, and a control system configured to control relative amounts of the air to the first and second interiors and relative amounts of the first and second fuels supplied to the first and second interiors. | 07-08-2010 |
| 20100185377 | SYSTEM AND METHOD FOR STARTING A GAS TURBINE ENGINE WITH INOPERABLE EXHAUST GAS TURBINE TEMPERATURE SENSOR - A system and method are provided for controlling the start-up of a gas turbine engine having an exhaust gas temperature (EGT) sensor. A determination is made as to whether the EGT sensor is available or unavailable. The gas turbine engine is commanded to accelerate at a nominal acceleration rate during the start-up operation if the EGT sensor is available, and to accelerate at an off-nominal acceleration rate during the start-up operation if the EGT sensor is unavailable. The off-nominal acceleration rate is lower than the nominal acceleration rate. | 07-22-2010 |
| 20100198479 | METHOD OF CONTROLLING A VTG ENGINE - When controlling an engine having a Variable Turbine Geometry (VTG) the VTG is closed some predicted time period before an up-gear shift is performed. This is advantageous because when the gear shift begins the engine breaking is already maximized and full engine brake can be obtained during the entire gear shift operation. | 08-05-2010 |
| 20100198480 | METHOD FOR DETECTING A "ROTATING STALL" FAULT IN A COMPRESSOR FED BY AN INVERTER - The invention relates to a method for detecting a rotating stall fault in a compressor ( | 08-05-2010 |
| 20100241331 | CONTROL OF GAS TURBINE ENGINE - Systems, devices, and methods for controlling a fuel supply for a turbine or other engine using direct and/or indirect indications of power output and optionally one or more secondary control parameters. | 09-23-2010 |
| 20100241332 | METHOD FOR MAKING UNIFORM THE THRUST COMMAND OF THE ENGINES OF AN AIRCRAFT - According to this invention, artificial force gradient means ( | 09-23-2010 |
| 20100262350 | CORRECTED MEGAWATT BACKUP CURVE METHODOLOGY - The subject application involves a method of controlling operation of a gas turbine. The method includes determining a first temperature associated with a portion of the gas turbine during operation of said gas turbine, and sensing an operational parameter of the gas turbine during operation of the gas turbine. An ambient pressure in an ambient environment of the gas turbine is also sensed, and the operational parameter corrected using the ambient pressure sensed in the ambient environment of the gas turbine to establish a corrected operational parameter. A threshold temperature is determined based at least in part on the corrected operational parameter, and a backup routine is initiated to limit operation of the gas turbine when the temperature associated with the gas turbine is greater than or equal to the threshold temperature. | 10-14-2010 |
| 20100274461 | AIRCRAFT ENGINE MANAGEMENT FOR FUEL CONSERVATION METHOD AND APPARATUS - A method includes controlling an aircraft during descent, and controlling the engine pressure ratio of a jet engine so that the engine has a substantially equal pressure at the exhaust, and at the front of the engine during the descent. | 10-28-2010 |
| 20100280730 | METHOD OF MONITORING A GAS TURBINE ENGINE - Operation of gas turbine engines and in particular gas turbine engines utilised for aircraft, in an efficient manner is a desired objective. Thus engine efficiency is typically determined through use of an engine performance parameter. One such engine performance parameter is with regard to specific fuel consumption. However, such parameters may vary as a result of inherent deterioration with regard to the engine. By utilising a computational model to determine variations in the performance parameter such as the specific fuel consumption changes as a result of such inherent engine degradation can be accommodate. Thus, such degradation may not swamp actual changes in fuel consumption or the engine performance parameter which are indicative of changes of engine efficiency. Generally and initially, computational results are utilised in order to provide a value with regard to degradation changes in the performance parameter, but such changes may be augmented by practical test results in order to tune the off-set constants a, b for an individual engine. | 11-04-2010 |
| 20100280731 | SYSTEMS AND METHODS FOR CONTROLLING FUEL FLOW TO A TURBINE COMPONENT - Systems and methods for controlling fuel flow to a turbine component are provided. One or more parameters associated with a fuel flow to a turbine component may be monitored. The fuel flow may be modeled based at least in part on the one or more monitored parameters. The fuel flow may be adjusted to a target flow based at least in part on the modeling of the fuel flow. | 11-04-2010 |
| 20100280732 | METHOD FOR DETECTING GAS TURBINE ENGINE FLASHBACK - A method for monitoring and controlling a gas turbine, comprises predicting frequencies of combustion dynamics in a combustor using operating conditions of a gas turbine, receiving a signal from a sensor that is indicative of combustion dynamics in the combustor, and detecting a flashback if a frequency of the received signal does not correspond to the predicted frequencies. | 11-04-2010 |
| 20100280733 | GAS TURBINE SHUTDOWN - A gas turbine includes a rotor, and a controller for controlling a shutdown of the gas turbine based on a target fuel-to-air ratio profile and/or controlling a rotor speed according to a target speed schedule to attain a specified duration for the shutdown. The controller controls the rotor speed by engaging the starting system to turn the rotor. | 11-04-2010 |
| 20100286889 | METHODS RELATING TO GAS TURBINE CONTROL AND OPERATION - A method of controlling variable extraction flow in a combustion turbine engine, wherein extraction flow comprises a supply of compressed air extracted from the compressor and supplied to the turbine through extraction conduits, and wherein the extraction conduits includes a variable extraction orifice, the method comprising the steps of: measuring a plurality of turbine engine operating parameters; monitoring, by a control unit, the measured operating parameters of the combustion turbine engine; setting the variable extraction orifices to a setting that allows an approximate maximum level of extraction flow; calculating, by the control unit, at least one calculated operating parameter based upon model-based control and the measured operating parameters, including at least a current turbine inlet temperature and a maximum turbine inlet temperature; and manipulating the setting for the supply of fuel to the combustor such that an increased and/or maximum level of engine output is determined by comparing the values for the current turbine inlet temperature and the maximum turbine inlet temperature. | 11-11-2010 |
| 20100286890 | AUTOMATED TUNING OF GAS TURBINE COMBUSTION SYSTEMS - 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. | 11-11-2010 |
| 20100292905 | SYSTEM AND METHOD OF ESTIMATING GAS TURBINE ENGINE PERFORMANCE - An example method of estimating gas turbine engine performance deterioration includes monitoring debris in at least a portion of an engine and estimating performance deterioration of at least one component of the engine using information from the monitoring. The method may use gas path parameters, such as pressures, temperatures, and speeds to establish the estimated performance deterioration. An example gas turbine engine performance assessment system includes a debris monitoring system configured to monitor debris moving through a portion of an engine and a controller programmed to estimate performance deterioration of at least one component of the engine based on information from the debris monitoring system. | 11-18-2010 |
| 20100292906 | Method of controlling engine performance - The present invention provides a method of controlling engine performance that includes obtaining at least one optical wavelength-dependent measurement from at least one combustion event in at least one combustion chamber. The method further includes analyzing the optical wavelength-dependent measurement for determining adjustments to the at least one combustion event. Additionally, the method includes adjusting the at least one combustion event or at least a next combustion event by changing at least one physical parameter, at least one constituent parameter, or at least one physical parameter and at least one constituent parameter to control the engine performance. The engine can include steady-flow engines or periodic flow engines, and the engine performance can be selected by an engine user. | 11-18-2010 |
| 20100312450 | METHOD FOR DETECTING THE OPENING OF A THRUST REVERSER FOR A JET ENGINE OF AN AIRCRAFT - A method for detecting the opening of a thrust reverser for a jet engine of an aircraft is disclosed. According to the method, an operating parameter of the turbojet ( | 12-09-2010 |
| 20100318274 | Combustor Flashback/Flame Holding Detection Via Temperature Sensing - A combustor includes a combustor housing defining a combustion chamber having a plurality of combustion zones. A plurality of temperature detectors are disposed in communication with the combustion chamber. The plurality of temperature detectors detect a temperature in the plurality of combustion zones. A controller communicating with the plurality of temperature detectors is programmed to determine an occurrence of a flame holding condition or a flashback condition in the plurality of combustion zones based on signals from the plurality of temperature detectors. | 12-16-2010 |
| 20100324799 | TURBINE ENGINE SPEED AND VIBRATION SENSING SYSTEM - A turbo machine includes a speed probe that is configured to detect a speed of a rotating feature. Engine controls are used by a processor to control operation of the turbo machine. The processor communicates with the speed sensor and receives the speed signal to produce a command signal. A detection module is arranged in parallel with the processor and communicates with the speed probe to receive the speed signal. The detection module compares the speed signal with data to determine whether the speed signal is reliable. In one example, the detection module bypassed the processor and sends a corrective command directly to an engine control device in response to an unreliable speed signal. | 12-23-2010 |
| 20100332103 | NOX Compliant Peak for Gas Turbine - A gas turbine comprises a plurality of target exhaust temperature determination modules, the plurality of target exhaust temperature modules comprising a nitrogen oxide (NOx) compliance module configured to determine an exhaust temperature at which an exhaust of the gas turbine complies with a maximum permitted level of NOx; at least one bias module, the at least one bias module configured to apply a bias to an output of at least one of the plurality of target exhaust temperature determination modules; and a controller configured to operate the gas turbine to produce the exhaust temperature determined by the NOx compliance module. | 12-30-2010 |
| 20110004388 | TURBOFAN TEMPERATURE CONTROL WITH VARIABLE AREA NOZZLE - A control system for a turbofan comprises a variable area nozzle for regulating core flow through the turbofan, an actuator, a temperature sensor, a flight controller and a nozzle control. The actuator is coupled to the variable area nozzle to regulate the core flow by positioning the variable area nozzle. The temperature sensor is positioned in the turbofan to sense a gas path temperature of the core flow. The flight controller is connected to the turbofan to make a thrust demand based on a flight condition of the turbofan. The nozzle control is connected to the flight controller and the actuator for directing the actuator based on the gas path temperature and the flight condition, such that the gas path temperature is controlled by adjusting the variable area nozzle to regulate the core flow while the turbofan meets the thrust demand. | 01-06-2011 |
| 20110004389 | APPARATUS FOR CONTROLLING INTAKE AIR HEATING OF GAS TURBINE - In a heating apparatus for heating the air sucked into a gas turbine by a heat exchanger, the temperature fluctuation of the heated air is suppressed even in the period, for which a steam source to be fed to the heat exchanger is changed. For that suppression, a heat exchanger ( | 01-06-2011 |
| 20110004390 | GAS TURBINE CONTROL METHOD AND DEVICE - Provided is a gas turbine control method and control device whereby a design performance and an operating state based on ideal fuel flow rate and air flow rate simulated at the time of designing can be maintained by preventing an operation deviated from an operating condition that is based on ideal fuel flow rate and air flow rate simulated by initial design values, in a gas turbine control method designed to search optimal operating conditions automatically using control inputs such as a pilot ratio. The gas turbine controller comprises a second database that stores load sensitivity, i.e. the correlation between the load amount of a gas turbine and control inputs such as a fuel flow rate, air flow rate, pilot fuel ratio, and top hat fuel ratio in the gas turbine, wherein the amount of load variation for at least one of control inputs, a fuel flow rate or an air flow rate supplied to a combustor is predicted according to operational conditions obtained by searching using the load sensitivity, regulation is made according to the prediction results, and the regulation results are stored in the second database. | 01-06-2011 |
| 20110010069 | GAS TURBINE ENGINE OIL CONSUMPTION MONITORING SYSTEM AND METHOD - A system and method of monitoring oil consumption in a gas turbine engine system are provided. When the gas turbine engine is not running the reservoir oil level, reservoir oil temperature, and reservoir attitude are sensed. The current gas turbine engine system oil quantity is determined based on at least the sensed reservoir oil level, the sensed reservoir oil temperature, and the sensed reservoir attitude. When a predetermined event has occurred, an average gas turbine engine system oil quantity is automatically calculated. The gas turbine engine system oil consumption rate is determined from a plurality of the average oil quantities. | 01-13-2011 |
| 20110040469 | GAS TURBINE COMBUSTION DYNAMICS CONTROL SYSTEM AND METHOD - A gas turbine engine control system comprises a data acquisition and analysis system for receiving a signal from a combustion dynamics sensor and providing an output signal and a combustion dynamics control system for controlling combustion dynamics based on the output signal. The control system is associated with a purge-air flow and comprises an acoustic driver, or a flow-manipulating device, or both to perturb the purge-air flow entering the combustor can for controlling combustion dynamics. | 02-17-2011 |
| 20110040470 | Starter Control Valve Failure Prediction Machine To Predict and Trend Starter Control Valve Failures In Gas Turbine Engines Using A Starter Control Valve Health Prognostic, Program Product and Related Methods - Starter control valve failure prediction machines, systems, program products, and computer implemented methods to predict and trend starter control valve failures in gas turbine engines using a starter control valve health prognostic and to make predictions of starter control valve failures, are provided. A computer implemented method according to an embodiment of the present invention can include the steps of generating a continuous starter control valve deterioration trend function responsive to a plurality of health indices derived from gas turbine engine startup data downloaded from gas turbine engine sensors for a plurality of startups and analyzing the continuous starter control valve deterioration trend function to identify potential starter control valve failure points where the points on the starter control valve deterioration trend function correlate to a starter control valve health prognostic responsive to historic gas turbine engine startup data downloaded from gas turbine engine sensors. | 02-17-2011 |
| 20110046863 | CONTROL APPARATUS FOR AEROPLANE GAS TURBINE ENGINE - An apparatus for controlling an aeroplane gas turbine engine has various sensors and devices for operating the engine, and two control channels each calculating a command value for controlling operation of the engine based on signals outputted from the sensors. In each of the control channels, it is determined whether any of the sensors and devices is abnormal based on the signals to determine a failure level of the control channel concerned with a numerical value. The failure level is compared with that of the other control channel and based thereon, the command value calculated by the control channel of smaller failure level is sent to the devices. With this, even when both control channels are failed, the engine control can be continued with taking the failure level into account. | 02-24-2011 |
| 20110118950 | METHOD FOR ESTIMATION OF AT LEAST ONE ENGINE PARAMETER - A system comprising determination of tuning parameters enabling optimal estimation of unmeasured engine outputs, e.g., thrust. The level of degradation of engine performance is generally described by unmeasurable health parameters related to each major engine component. Accurate thrust reconstruction depends upon knowledge of these health parameters, but there are usually too few sensors to estimate their values. A set of tuning parameters is determined which accounts for degradation by representing the overall effect of the larger set of health parameters as closely as possible in a least squares sense. The method utilizes the singular value decomposition of a matrix to generate a tuning parameter vector of low enough dimension that it can be estimated by a Kalman filter. Generation of a tuning vector specifically takes into account the variables of interest. The tuning parameters facilitate matching of both measured and unmeasured engine outputs, as well as state variables. | 05-19-2011 |
| 20110130941 | SYSTEMS AND METHODS FOR UNCHOKED CONTROL OF GAS TURBINE FUEL GAS CONTROL VALVES - Certain embodiments of the invention may include systems and methods for providing unchoked control of gas turbine fuel control valves. According to an exemplary embodiment of the invention, a method is provided for active control of a gas flow control valve. The method may include receiving a desired fuel command and an inlet pressure parameter, and determining a gas flow gain based at least in part on the inlet pressure parameter. The method may also include determining a valve flow coefficient based at least in part on the desired fuel command and the gas flow gain, and controlling the gas flow control valve based at least in part on the valve flow coefficient. | 06-02-2011 |
| 20110137536 | 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 determining whether the median value exceeds at least one operating threshold. The method can also include implementing at least one engine control action to modify at least one of the operating frequencies if at least one operating threshold is exceeded. | 06-09-2011 |
| 20110160979 | METHOD OF ESTIMATING THE MAXIMUM POWER GENERATION CAPACITY AND FOR CONTROLLING A SPECIFIED POWER RESERVE OF A SINGLE CYCLE OR COMBINED CYCLE GAS TURBINE POWER PLANT, AND A POWER GENERATING SYSTEM FOR USE WITH SAID METHOD - An estimation unit can estimate, on a real-time basis, a maximum power generation capacity of a single cycle or combined cycle gas turbine power plant. For example, the actual power output and the maximum power generation capacity can be calculated relying on a mathematical process model. Subsequently, the calculated actual power output can be compared with the measured power output yielding a model-estimation error. Based on the model-estimation error, a correction signal can be deduced, to correct the calculated maximum power generation capacity. A controller can maintain a specified power reserve. The controller can use an estimate of the maximum power generation capacity as a reference, subtract a load offset, and apply the resulting signal as upper limit of the load set-point. | 06-30-2011 |
| 20110160980 | ESTIMATING HEALTH PARAMETERS OR SYMPTOMS OF A DEGRADING SYSTEM - The present invention is concerned with the estimation of health parameters p(k) representing symptoms of a slowly degrading system, in particular industrial gas turbines. According to the invention, an estimation of a true health or independent parameter vector at time step k uses the estimation of the true health or parameter vector at a previous time step k−1 as a starting value for the production of a predicted health parameter vector at time step k. Based on the latter and a set of measured values of input variables of an extended model of the system, a prediction of output variables of the model is produced. This predicted model output is compared with measured values of the output variables to yield an error. From this error, a health parameter estimator in turn produces a health parameter estimate as a revision of the predicted health parameters. Preferably, the estimation of a true health or independent parameter vector at time step k includes a generalised process noise representing stochastic uncertainty and/or a-priori knowledge of an evolution of the health parameters. | 06-30-2011 |
| 20110172893 | GAS TURBINE CONTROL DEVICE AND GAS TURBINE SYSTEM - An object of the present invention is to provide a gas turbine control device which is capable of performing correction on the basis of a fuel composition of fuel gas to be supplied to a gas turbine, and is capable of changing an amount of correction in response to variation with time of the gas turbine. To attain this, a frequency analyzing unit | 07-14-2011 |
| 20110191004 | GAS TURBINE CONTROL METHOD AND DEVICE - To restrain combustion vibration more precisely by alleviating the relationship between the composition or heat quantity of the fuel and the combustion vibration characteristic and by grasping the combustion vibration characteristic more accurately. The combustion vibration generated by burner of gas turbine as well as the composition or heat quantity and other plant status amounts of fuel f supplied to the burner are detected. The combustion vibration characteristic is grasped based on the detected values. When the combustion flow rate or air flow rate supplied to the burner is increased/decreased in order to obtain operation condition under which no combustion vibration occurs, the detected values of the combustion vibration as well as the composition or heat quantity and other plant status amounts of the fuel are divided and stored in multiple databases corresponding to the value of the composition or heat quantity of the fuel. | 08-04-2011 |
| 20110196593 | SYSTEM AND METHOD FOR MONITORING A GAS TURBINE - A system for monitoring a gas turbine includes a memory containing information from comparable gas turbines and an input device that generates a unit data signal and a risk signal. A processor in communication with the memory and the input device incorporates the unit data signal into the database, projects information for the gas turbine, and calculates a conditional risk that the gas turbine will reach a limit. An output signal includes repair or maintenance schedules. A method for monitoring a gas turbine includes receiving information from comparable gas turbines, adding information from the gas turbine to the information from comparable gas turbines, and projecting information for the gas turbine. The method further includes calculating a conditional risk that the gas turbine will reach a limit and generating an output signal containing repair or maintenance schedules. | 08-11-2011 |
| 20110202251 | Apparatus and method for reducing aircraft fuel consumption - A method and apparatus for improving fuel efficiency in an aircraft having a digital avionics system and at least first and second engines. The avionics system includes first and second full-authority digital engine control (FADEC) systems and corresponding first and second engines. At least one processor is provided that is programmed with a differential specific fuel consumption (DSFC) algorithm and first and second engine optimization algorithms. The DSFC algorithm adjusts the throttle of the first and second engines to substantially equalize the differential specific fuel consumption of the engines and thereby improve the fuel efficiency of the aircraft. The first and second engine optimization algorithms adjust at least one operating parameter of the first and second engines respectively to improve the fuel efficiency of the first and second engines. | 08-18-2011 |
| 20110208400 | SYSTEM AND METHOD FOR CONTOLLING A SINGLE-SPOOL TURBOSHAFT ENGINE - A controller receives a power-level command representative of a level of power to be transmitted by a single-spool turboshaft engine to a controllable load. A torque command determined responsive to a measure of inlet pressure, from a control schedule responsive to the power-level command, is representative of a level of torque to be transmitted by an element to drive the controllable load. Under some operating conditions, a rotational speed command provides for at least nearly minimizing a measure of associated fuel consumption when the transmitted torque is regulated to the level corresponding to the torque command by controlling one of the controllable load and a fuel flow to the engine, and the other of the controllable load and the fuel flow to the engine is controlled so as to regulate an associated rotational speed to a level corresponding to the rotational speed command. | 08-25-2011 |
| 20110213537 | Electronic Shaft Shear Detection Conditioning Circuit - An electrical control system for distinguishing between an electrical fault and a shaft shear condition in a gas turbine engine, the control system including, in one aspect, a detection circuit including: two or more probes, each probe including an associated resistor having a predetermined range of resistance, and each probe being disposed in the engine adjacent a rotary mounted shaft component, where mechanical interference between one or more of the probes and the shaft component renders the associated resistor substantially non-conductive; sensor processor(s) in communication with each probe, determining a probe operational status based on a measured resistance to current conducted through each probe, and generating a fault code when the measured resistance of at least one of the plurality of probes is not within the predetermined range of resistance. | 09-01-2011 |
| 20110257864 | SYSTEMS, METHODS, AND APPARATUS FOR DETECTING FAILURE IN GAS TURBINE HARDWARE - Certain embodiments of the invention may include systems, methods, and apparatus for detecting failure in gas turbine hardware. According to an example embodiment of the invention, a method for detecting a failure in a gas turbine is provided. The method can include monitoring a parameter associated with the turbine, wherein the monitored parameter comprises at least one turbine bucket temperature, detecting an event associated with operation of the turbine, wherein the event is based at least in part on the monitored parameter, and initiating shutdown of the turbine upon detection of the event wherein the monitored parameter is above a predetermined value for at least a predetermined time duration. | 10-20-2011 |
| 20110270502 | EMPLOYING FUEL PROPERTIES TO AUTO-TUNE A GAS TURBINE ENGINE - A tuning process is provided for monitoring fuel properties of a fuel being consumed by a gas turbine (GT) engine, and for dynamically tuning the GT engine as a function of changes to the monitored fuel properties. Initially, readings are taken from the GT engine during a reference calibration, or commissioning, and utilized to calculate an initial-pressure-drop reference value. The tuning process during commercial operation takes post-calibration readings from the GT engine to calculate a fuel property parameter, which represents a heating value of the fuel. Specifically, the fuel property parameter is calculated by deriving a corrected-pressure-drop dynamic value as a function of pressure and temperature readings of the fuel at a point upstream of a combustor and pressure drops across fuel nozzles that introduce the fuel into the combustor, and solving a ratio of the dynamic value and the reference value. | 11-03-2011 |
| 20110270503 | SELECTING AND APPLYING TO FUEL-FLOW SPLITS BIAS VALUES TO CORRECT FOR ELEVATED INLET AIR HUMIDITY - Methods for controlling a gas turbine engine are provided, where a compressor inlet temperature, ambient temperature, and relative humidity are measured. Utilizing these measurements, it is first determined whether an evaporation cooler is actively importing water content into inlet air entering the compressor. This determination is based on whether the inlet air is substantially cooler than the ambient temperature. If so, an EC correction factor is added to an inlet air temperature value (CTIM) and set as an air temperature parameter (INLETIM). Second, it is determined whether the relative humidity is greater than a predefined threshold. If so, a relative humidity (RH) correction factor is added to CTIM and set as the INLETIM. Next, the INLETIM and TTRF are located in a look-up table, and a bias value corresponding to these inputs is identified. The fuel-flow for a fuel circuit is adjusted according to the identified bias value. | 11-03-2011 |
| 20110276247 | METHOD AND A SYSTEM FOR MONITORING VIBRATORY PHENOMENA THAT OCCUR IN AN AVIATION GAS TURBINE ENGINE IN OPERATION - The invention relates to a method and a system for monitoring vibratory phenomena that occur in an aviation gas turbine engine in operation. The method consists: in establishing (E | 11-10-2011 |
| 20110288740 | Engine synchronization method - This invention relates to an engine synchronization method for aircraft equipped with at least two gas-turbine engines, where the respective speeds N | 11-24-2011 |
| 20110301822 | METHOD AND SYSTEM FOR CONTROLLING A GAS TURBINE AND A GAS TURBINE INCLUDING SUCH A SYSTEM - A method for controlling a gas turbine including a compressor assembly including at least one variable geometry portion, a combustion chamber, and a turbine assembly. The method generates a flow rate setpoint value for fuel to be fed to the combustion chamber as a function of a desired speed of the gas turbine, computes threshold values for maintaining the fuel flow setpoint value in a given range, the threshold values depending on a thermodynamic state of the gas turbine, and controls the position of the variable geometry portion by controlling an actuator as a function of the difference between position information representative of the instantaneous position and setpoint position information. The threshold values are automatically adjusted by computation in real time as a function of the instantaneous position information of the variable geometry portion or of the difference between this position information and the setpoint position information. | 12-08-2011 |
| 20120010800 | AIRCRAFT ENGINE MANAGEMENT FOR FUEL CONSERVATION METHOD - A method includes controlling an aircraft during descent, and controlling the engine pressure ratio of a jet engine so that the engine has a substantially equal pressure at the exhaust, and at the front of the engine during the descent. | 01-12-2012 |
| 20120029786 | AIRCRAFT ENGINE CONTROL DURING ICING OF TEMPERATURE PROBE - Methods for controlling an aircraft turbofan engine during icing of a temperature probe and devices for carrying out such methods are described. The methods may comprise: using one or more signals representative of temperature received from a heated temperature probe to generate one or more control signals for use in controlling the engine; determining that an icing condition associated with the probe exists; and using data representing one or more substitute signals in place of signals representative of temperature received from the heated temperature probe to generate the one or more control signals for use in controlling the engine. | 02-02-2012 |
| 20120072091 | TEMPERATURE ESTIMATION APPARATUS FOR AEROPLANE GAS TURBINE ENGINE - In a temperature estimation apparatus for an aeroplane gas turbine engine, there are provided with a calculator that calculates a low-pressure turbine outlet temperature change (dEGT) based on low-pressure turbine rotational speed (N | 03-22-2012 |
| 20120095663 | FMU MOUNTED EEC FOR SMALL AIRCRAFT ENGINE APPLICATIONS - A fuel metering unit (FMU) for an aircraft engine includes an effector and an electronic engine controller (EEC). The effector is electrically connected to the EEC to adjust a rate of fuel flowing into the engine. The adjustment is in response to a control signal sent from the EEC. The control signal sent from the EEC is responsive to an engine sensor signal and to airframe sensor information. | 04-19-2012 |
| 20120101706 | METHOD AND A DEVICE FOR MONITORING A SERVO-CONTROL LOOP OF AN ACTUATOR SYSTEM FOR ACTUATING VARIABLE-GEOMETRY COMPONENTS OF A TURBOJET - A method for monitoring a servo-control loop ( | 04-26-2012 |
| 20120109486 | METHOD AND A DEVICE FOR MONITORING A REDUNDANT MEASUREMENT SYSTEM - The invention relates to monitoring a redundant measurement system of an aeroengine by means of an electronic unit. The monitoring comprises a step of obtaining first measurements of a physical magnitude measured in said engine, and a step of obtaining second measurements of said physical magnitude. According to the invention, the method includes a step of calculating detection residues as a function of differences between the first and second measurements, a step of determining a mean-jump flag, a step of determining a variance-jump flag, a step of determining a change-of-slope flag, and a step of generating a diagnostic notice as a function of said mean-jump flag, of said variance-jump flag, and of said change-of-slope flag. | 05-03-2012 |
| 20120136550 | CONTROL OF GAS TURBINE ENGINE - Systems, devices, and methods for controlling a fuel supply for a turbine or other engine using direct and/or indirect indications of power output and optionally one or more secondary control parameters. | 05-31-2012 |
| 20120150413 | GAS TURBINE ENGINE CONTROL USING ACOUSTIC PYROMETRY - A method and apparatus for operating a gas turbine engine including determining a temperature of a working gas at a predetermined axial location within the engine. Acoustic signals are transmitted from a plurality of acoustic transmitters and are received at a plurality of acoustic receivers. Each acoustic signal defines a distinct line-of-sound path from one of the acoustic transmitters to an acoustic receiver corresponding to the line-of-sound path. A time-of-flight is determined for each of the signals traveling along the line-of-sound paths, and the time-of-flight for each of the signals is processed to determine a temperature in a region of the predetermined axial location. | 06-14-2012 |
| 20120166061 | HUB UNIT FOR A HIGH TEMPERATURE ELECTRONIC MONITORING SYSTEM - A hub unit adapted for use in a monitoring system that monitors engine performance parameters of a gas turbine engine. The hub unit includes a housing, at least one signal conditioning circuit board within the housing and adapted to receive the analog sensor outputs from the sensors, and a control circuit board within the housing, connected to the signal conditioning circuit board, and adapted to produce digital data corresponding to analog sensor outputs. The signal conditioning circuit board multiplexes a plurality of the analog sensor outputs generated by the sensors to produce an individual multiplexed analog output, and has at least one amplifier with adjustable gain for scaling the analog sensor outputs of the individual multiplexed analog output to produce an individual conditioned multiplexed analog output from which the corresponding digital data are produced. The amplifier and the adjustable gain thereof are controlled by the control circuit board. | 06-28-2012 |
| 20120185144 | STOICHIOMETRIC EXHAUST GAS RECIRCULATION AND RELATED COMBUSTION CONTROL - A fuel control system for a gas turbine engine that includes a primary fuel circuit, a fuel tuning circuit, a plurality of combustors connected to the fuel tuning circuit, oxygen and carbon dioxide sensors in the exhaust stream and a feedback control loop operatively connected to the fuel tuning circuit and to the oxygen and carbon monoxide sensors which serve to control the precise amount of fuel and air being fed to each one of the plurality of combustors in the engine. A parallel array of control valves in a tuning fuel circuit connect to corresponding ones of the plurality of combustors in the gas turbine engine. The fuel control system thereby “fine tunes” the amount of fuel and air being fed to each combustor using data regarding the detected oxygen and carbon monoxide concentrations in the exhaust gas as provided through a feedback control loop. | 07-19-2012 |
| 20120215417 | SYSTEM FOR CONTROLLING THE ANGULAR POSITION OF STATOR BLADES AND METHOD FOR OPTIMIZING SAID ANGULAR POSITION - A system for controlling angular position of stator blades including: a mechanism for calculating a set angular position of the blades according to one of speeds; and a module for correcting the set position including: a mechanism for determining the angular position of the blades; a mechanism for measuring fuel flow rate of the turbine engine; a memory unit in which consecutive angular positions of the blades are combined with the fuel flow rates of the turbine engine measured at the angular positions; and a mechanism for determining a correcting angle according to the difference between the fuel flow rates measured between two consecutive angular position of the blades. A method for optimizing the common angular position can utilize the system. | 08-23-2012 |
| 20120232768 | SYSTEM AND METHOD FOR TRANSITIONING BETWEEN FUEL SUPPLIES FOR A COMBUSTION SYSTEM - A system includes a turbine fuel controller. The turbine fuel controller includes a purge control logic configured to control a purge sequence of mixing a purge gas with a first fuel during a first fuel shutdown, wherein the purge sequence is configured to open a purge valve for the purge gas before fully closing a fuel valve for the first fuel. | 09-13-2012 |
| 20120259528 | CONTROL OF COMPRESSION SYSTEM WITH INDEPENDENTLY ACTUATED INLET GUIDE AND/OR STATOR VANES - A compression system includes a compressor with adjustable inlet guide vanes (IGVs) and variable stator vanes (VSVs) that are adjustable independently of each other. IGV and VSV control units produce respective IGV and VSV reference commands responsive to respective first and second inputs that may be responsive to measured properties of the compression system. The second input may be provided by a model of the compressor or of the compression system responsive to measured properties. The second input may particularly be an estimate of a property not directly observable, such as stall margin or efficiency. | 10-11-2012 |
| 20120271527 | DISTRIBUTED AIRCRAFT ENGINE FUEL SYSTEM - A gas turbine engine includes a plurality of fuel injectors grouped operatively by stages in a multistage combustor. A fuel system for the gas turbine engine includes at least one fuel metering module per stage of the multistage combustor. Each fuel metering module includes a pump, a flow meter, a pressure sensor, a controller, and a motor, which work together to control fuel output. | 10-25-2012 |
| 20120277968 | MOISTURE MONITORING SYSTEM FOR GAS TURBINE ENGINES - A moisture monitoring system includes a control in communication with a sensor system to determine moisture data from a moisture level in a composite material structure. | 11-01-2012 |
| 20120277969 | PASSING FROM A NON-SYNCHRONIZED STATE BETWEEN AN ENGINE AND A ROTOR TO A SYNCHRONIZED STATE - In order to regulate a power plant ( | 11-01-2012 |
| 20120316748 | Method And Device For Monitoring A Turbine Engine Of An Aircraft - The device includes means for determining a value illustrating a thermomechanical state (ET) of the turbine engine, means for comparing this value with at least one threshold (S | 12-13-2012 |
| 20130054108 | SYSTEM AND METHOD FOR PREDICTING TURBINE RUB - A system for predicting turbine rub includes a monitoring system configured to form operational values for a turbine based on information received from the turbine and a correlation engine configured to form at least one correlated value from the operating values that correlates a first operating value to a second operating value. The system also includes a variable deriver configured to form at least one derived variable from a one of the operating values and a rub predictor that forms a rub prediction based on the at least one correlated value and the at least one derived value. | 02-28-2013 |
| 20130073170 | SYSTEM AND METHOD FOR SIMULATING A GAS TURBINE COMPRESSOR - A method for simulating a compressor of a gas turbine is disclosed. The method may generally include determining a predicted pressure ratio and a predicted mass flow of the compressor based on a model of the gas turbine, monitoring an actual pressure ratio and an actual mass flow of the compressor, determining difference values between at least one of the predicted pressure ratio and the actual pressure ratio and the predicted mass flow and the actual mass flow, modifying the difference values using an error correction system to generate a compressor flow modifier and using the compressor flow modifier to adjust the predicted pressure ratio and the predicted mass flow. | 03-21-2013 |
| 20130073171 | METHOD AND DEVICE FOR DETECTION OF CONTAMINATION BY FUEL OF THE OIL CIRCUIT OF A TURBINE - A method for detection of contamination, by another fluid, of the oil circuit of a turbomachine fitted on an aircraft, the oil circuit including a tank provided with a device for measuring its oil level, piping which connects the tank to the various units of the turbomachine to be lubricated, and a device for putting the oil into circulation between the tank and the units, the turbomachine including a device for measuring its engine speed and a device for measuring the temperature of the oil at one point at least of the oil circuit. The oil level in the tank is monitored, an alert is triggered if the decrease in the oil level, measured over a given interval of time, becomes lower than a set minimum decrease. The decrease can be replaced by a simple increase in the oil level, without taking a duration of the monitoring into account. | 03-21-2013 |
| 20130096800 | HYBRID INTERNAL COMBUSTION ENGINE AND AIR MOTOR SYSTEM AND METHOD - A hybrid internal combustion engine and air motor system is provided and includes at least one chamber having a drivable member and at least one intake valve and at least one exhaust valve, and a reservoir connected to the chamber through at least one of the intake valve and the exhaust valve. The system further comprises a computer configured to calculate air compressor efficiency during an air compressor mode of operation and select an intake and exhaust valve opening and closing timing sequence for maximizing air compressor efficiency and/or a computer configured to calculate air motor efficiency during an air motor mode of operation and select an intake and exhaust valve opening and closing timing sequence for maximizing air motor efficiency. | 04-18-2013 |
| 20130131951 | SYSTEM AND METHOD OF MONITORING TURBINE ENGINES - A monitoring system for use with a turbine engine is described herein. The turbine engine includes a compressor and at least one compressor bleed valve coupled to the compressor. The monitoring system includes at least one sensor that is for sensing an operational parameter of the compressor bleed valve, and a controller that is coupled to the sensor and the compressor bleed valve. The controller is configured to determine an operating mode of the turbine engine and receive a monitoring signal indicative of the sensed operational parameter. The controller is also configured to calculate at least one operational value of the compressor bleed valve based at least in part on the sensed operational parameter. The controller is further configured to determine a condition of the turbine engine based at least in part on the calculated compressor bleed valve operational value. | 05-23-2013 |
| 20130138322 | FULL AUTHORITY DIGITAL ENGINE CONTROL SYSTEM FOR AIRCRAFT ENGINE - In one aspect, a digital engine control system for an aircraft engine is provided. The control system includes a selection unit, the selection unit including a monitoring module configured to determine a measurement of the speed of rotation of the engine from the output signal from one or more protection sensors and to compare the or each speed measurement determined by the selection unit with speed measurements supplied by electronic control units to determine an operating state of each electronic control unit. | 05-30-2013 |
| 20130151112 | METHOD FOR OPTIMIZING THE CONTROL OF A FREE TURBINE POWER PACKAGE FOR AN AIRCRAFT, AND CONTROL FOR IMPLEMENTING SAME - A method optimizing fuel-injection control with driving speeds of apparatuses adjusted by controlling a turbine speed according to power, and optimizing control of a free turbine power package of an aircraft, including a low-pressure body, supplying power to apparatuses and linked to a high-pressure body. The method varies the low-pressure body speed to obtain a minimum speed for the high-pressure body, so power supplied by the apparatuses remains constant. Power supplied by the apparatuses is dependent upon the apparatuses driven speed by the low-pressure body, and a speed set point of the low-pressure body is dependent upon a maximum value of minimum speeds of the apparatuses, enabling required power to be optimized, upon a positive or zero incrementation added to the speed set point of the low-pressure body to minimize speed of the high-pressure body to the apparatuses power supply. | 06-13-2013 |
| 20130158831 | DETECTION OF THE INGRESS OF WATER OR HAIL INTO A TURBINE ENGINE - A detection method for detecting ingestion of water or hail in a gas turbine engine, the engine including at least a compressor, a combustion chamber, and a turbine, the method including: estimating a value of a first indicator representative of water or hail being ingested; estimating a value of a second indicator representative of water or hail being ingested, the second indicator being different from the first indicator; and calculating a value of a global indicator by summing at least the first indicator and the second indicator. | 06-20-2013 |
| 20130173135 | METHODS AND SYSTEMS FOR TURBINE LINE REPLACEABLE UNIT FAULT DETECTION AND ISOLATION DURING ENGINE STARTUP - Systems and methods for isolating a performance anomaly within one or more line replaceable units (LRUs) on a gas turbine engine by monitoring the start up transient are presented. The system comprises a set of sensors, an anomaly detector and a fault isolation reasoner. Each sensor of the set monitors at least one operating parameter of at least one engine component. The anomaly detector is configured to detect an anomaly in a component by comparing a particular value of an operating parameter to a base line value of that parameter. The specific cause of the startup anomaly is isolated utilizing a set of component reasoners that is based on the nature of the detected anomaly. The key events during the engine startup are identified by the combination of monitoring physically relevant phases of a startup and monitoring the engine control schedule. The values at these key events are used for comparing at the anomaly detector. | 07-04-2013 |
| 20130184961 | METHODS AND SYSTEMS FOR MANAGING POWER OF AN ENGINE - A method and system for online power management of a turbine engine is provided. The method includes operating an engine control system on a first bandwidth, filtering at least one data input from the engine control system to a second bandwidth, and receiving, by a power management system operating on the second bandwidth, the at least one filtered data input. The method also includes predicting an engine operating condition using the at least one filtered data input using a closed-loop engine model, determining an optimal engine power management based on the prediction, solving a constrained optimization for a desired optimization objective, and outputting the optimal engine power management to the engine control system. | 07-18-2013 |
| 20130191004 | GAS TURBINE ENGINE CONTROL - A gas turbine engine control apparatus comprises a controller | 07-25-2013 |
| 20130204506 | ENGINE SYSTEMS WITH EFFICIENT START CONTROL LOGIC - An engine system for starting a gas turbine engine is provided. The system includes a starter generator coupled to the gas turbine engine and configured to provide torque to the gas turbine engine and a controller coupled to the starter generator and configured to provide a command signal to the starter generator. The starter generator provides the torque to the gas turbine engine based on the command signal, and the controller is configured to command the starter generator at a dwell speed until ignition. | 08-08-2013 |
| 20130204507 | METHOD AND A DEVICE FOR MONITORING AN ENGINE - A method of monitoring at least one limited-lifetime part. During an identification step (STP | 08-08-2013 |
| 20130211690 | Detection System and Method to Detect Flame Holding Event - A turbine to detect a flame holding event includes a combustion section to receive a fluid from a compressor, to heat the fluid by combusting a fuel to generate heat, and to output the heated fluid to a turbine section. The combustion section includes a combustor having a combustion chamber in which the fuel is combusted, and the combustion section having a sensor to sense a static pressure within the combustion chamber. A combustion control device detects a flame holding event in the combustion chamber based only on the sensed static pressure. | 08-15-2013 |
| 20130211691 | SYSTEM FOR REAL TIME SIMULATION OF THE ENVIRONMENT OF AN AEROENGINE - A system for real time simulation of the environment of an aeroengine includes a digital computer having its inputs switched by a selection module included in the computer either to a respective sensor or else to a substitution digital bus configured to convey substitution digital data generated by a real time simulator. | 08-15-2013 |
| 20130218437 | GAS TURBINE SEQUENCING METHOD AND SYSTEM - A method to develop a software based sequencer for a turbine including: selecting a general purpose sequencer software module having standardized software for sequencing turbines through defined states of operation; selecting options from predefined settings presented by the sequencer software module, wherein the selected options define operational events of the turbine which trigger the sequencer to transition the turbine from one of the defined states to the next defined state, and using the general purpose sequencer software configured with the selected options for the settings. | 08-22-2013 |
| 20130238215 | MONITORING OF A FILTER OF THE FUEL-SUPPLY SYSTEM OF AN AIRCRAFT ENGINE - A monitoring method for monitoring a filter of a feed circuit for feeding an aircraft engine with fuel, the method including: detecting clogging of the filter; issuing an indication message; determining a current stage from among a plurality of successive stages of a mission of the aircraft, including at least a stage during which clogging of the filter is not capable of being caused by ice, and a stage during which clogging of the filter might be caused by ice; and in response to detecting clogging, determining the type of clogging as a function of the current stage; wherein during the issuing an indication message, the message that is issued depends on the type of clogging. | 09-12-2013 |
| 20130311060 | ENGINE WASH OPTIMISATION - The present invention provides a method of optimising engine wash event scheduling. An underlying deterioration gradient and a total deterioration gradient are determined. A number of engine wash events, x, are set. Engine deterioration for x engine wash events is calculated. The washed engine cost of engine deterioration for x engine wash events is calculated. The calculation of engine deterioration is iterated for different x to optimise the number of engine wash events with respect to the cost of engine deterioration. Advantageously the method systematically optimises scheduling of wash events taking into account the underlying deterioration of the engine which cannot be recovered by engine washing and the cost of the engine wash events. | 11-21-2013 |
| 20130325287 | FLYWHEEL ENERGY STORAGE FOR VEHICLE PROPULSION - A propulsion system includes a prime mover for providing primary power to propel a vehicle; a flywheel energy storage device for providing secondary power to propel the vehicle when primary power is not being provided, wherein the flywheel energy storage device stores power provided by the prime mover; and a controller for commanding the prime mover on and off. | 12-05-2013 |
| 20130338898 | METHOD AND A DEVICE FOR MONITORING A SERVO-CONTROL LOOP OF AN ACTUATOR SYSTEM FOR ACTUATING VARIABLE-GEOMETRY COMPONENTS OF A TURBOJET - A method monitoring a servo-control loop, including: estimating monitoring parameters from operating data of the servo-control loop; obtaining indicators from the monitoring parameters; determining at least one signature from values of at least some of the indicators; and detecting and locating a degradation affecting the servo-control loop as a function of the at least one determined signature. | 12-19-2013 |
| 20140005909 | REAL TIME LINEARIZATION OF A COMPONENT-LEVEL GAS TURBINE ENGINE MODEL FOR MODEL-BASED CONTROL | 01-02-2014 |
| 20140005910 | SCHEDULING OF VARIABLE AREA FAN NOZZLE TO OPTIMIZE ENGINE PERFORMANCE | 01-02-2014 |
| 20140012481 | AIRCRAFT ENGINE CONTROL DURING ICING OF TEMPERATURE PROBE - Methods for controlling an aircraft turbofan engine during icing of a temperature probe and devices for carrying out such methods are described. The methods may comprise: using one or more signals representative of temperature received from a heated temperature probe to generate one or more control signals for use in controlling the engine; determining that an icing condition associated with the probe exists; and using data representing one or more substitute signals in place of signals representative of temperature received from the heated temperature probe to generate the one or more control signals for use in controlling the engine. | 01-09-2014 |
| 20140039775 | SYSTEM AND METHOD FOR CONTOLLING A SINGLE-SPOOL TURBOSHAFT ENGINE - One of a controllable load and a fuel flow to a single-spool turboshaft engine is controlled so that a rotational speed of a single-spool turboshaft engine is substantially regulated to a level corresponding to a corrected rotational speed command, and the other of the fuel flow and the controllable load is controlled so that a torque transmitted from the single-spool turboshaft engine to the controllable load is substantially regulated to a level corresponding to a corrected torque command. Under at least one operating condition, the corrected rotational speed command is determined so as to minimize or nearly minimize a measure of fuel consumption by the single-spool turboshaft engine when operated so that the torque transmitted to the controllable load corresponds to the corrected torque command. | 02-06-2014 |
| 20140058644 | METHOD, SYSTEM, AND APPARATUS FOR REDUCING A TURBINE CLEARANCE - A method for reducing a turbine clearance between a plurality of rotor blades of a turbine engine and a shroud of the turbine engine is provided. Said method includes determining, with a flight operation controller, that an airplane is in a first flight condition, wherein the first flight condition is associated with a first turbine clearance and a first engine responsiveness level, determining, with the flight operation controller, that the airplane is in a second flight condition, adjusting an engine responsiveness level from the first engine responsiveness level to a second engine responsiveness level based on determining the airplane is in the second flight condition, and adjusting the turbine clearance from the first turbine clearance to a second turbine clearance based on the engine responsiveness level. | 02-27-2014 |
| 20140081547 | CLOSED LOOP PROPULSION SYSTEM TRANSIENT RESPONSE PREDICTOR - An electronic engine controller includes a commanded rotor speed input, an altitude input, and a current rotor speed input, a computer processor, and a memory storing a prediction logic. The prediction logic is operable to cause the processor to determine a predictive value representative of a closed loop transient response of a propulsion system's actual corrected low rotor speed in response to a commanded change in low rotor speed. | 03-20-2014 |
| 20140114549 | WIRELESS ENGINE MONITORING SYSTEM WITH MULTIPLE HOP AIRCRAFT COMMUNICATIONS CAPABILITY AND ON-BOARD PROCESSING OF ENGINE DATA - An engine monitoring module includes a housing configured to be mounted at the aircraft engine and a first wireless transmitter carried by the housing. A memory is carried by the housing and a processor is carried by the housing and coupled to the memory and the first wireless transmitter and configured to collect and store in the memory engine data relating to at least one engine parameter sensed during operation of the aircraft engine by a plurality of engine sensors that transmit the engine data via the first wireless transmitter. A wireless receiver is located within the aircraft and configured to receive the engine data transmitted from the first wireless transmitter. A second wireless transmitter is located within the aircraft and operatively connected to the wireless receiver and configured to receive and transmit the engine data. | 04-24-2014 |
| 20140121934 | SYSTEM FOR DETECTING SHAFT SHEAR EVENT - Systems and methods for detecting a shaft shear event in a turbine engine. An accelerometer coupled to the engine detects an axial acceleration indicative of a shaft shear event in the engine. A control system is configured to, in response to the detected axial acceleration, transmit a signal to initiate a shut down of a fuel system of the engine. | 05-01-2014 |
| 20140121935 | Model Based Control Tuning Process for Gas Turbines - Systems and methods for model based control tuning for gas turbine systems. In one embodiment, a nonlinear optimization process with multiple nonlinear constraints can create a set of control schedules that can work across an ambient range based on specific unit characteristics derived from a single test ambient. As part of model based control for a gas turbine system, all of the control schedules can be defined based on a nominal unit. Multiple control loops may be active across the ambient range with each control loop being active at a different ambient condition. This tuning process can provide a set of control schedules to provide improved performance for a specific gas turbine system or unit over a wide operation range. | 05-01-2014 |
| 20140129111 | SYSTEM AND METHOD OF PROTECTING AN ENGINE AND OTHER AIRCRAFT COMPONENTS FROM DAMAGE THAT MAY OTHERWISE OCCUR FROM A FUEL CONTROL UNIT FAILURE - The system for mitigating an overspeeding condition of a turbine engine can include a sensor for measuring an actual speed of a gas generator turbine of the turbine engine and a processor for deriving a delta, the delta being a comparison between the actual speed of the gas generator turbine and a predicted gas generator turbine speed. The system is configured for detecting the overspeeding condition when delta is higher than a predetermined threshold. A method of detecting an overspeeding condition during operation of a turbine engine can include measuring an actual speed of a gas generator turbine, then evaluating a delta between the actual speed of the gas generator turbine and a predicted speed of the gas generator turbine, then comparing the delta to a threshold value. | 05-08-2014 |
| 20140156165 | SYSTEM AND METHOD FOR GAS TURBINE OPERATION - A system includes a controller configured to control one or more parameters of a gas turbine engine based on a feedback and a predicted lifespan of one or more components of the gas turbine engine to substantially maintain at least one of power output or heat rate above a threshold level in response to degradation or fouling of the gas turbine engine. | 06-05-2014 |
| 20140163838 | OPERATIONS SUPPORT SYSTEMS AND METHODS FOR CALCULATING AND EVALUATING TURBINE TEMPERATURES AND HEALTH - An operations support system is provided for an engine with a turbine having a turbine inlet. The system includes a diagnostic engine model unit configured to receive engine data from the engine and to generate diagnostics data based on the engine data, the diagnostics data including scalars. The system further includes an engine-specific model unit coupled to the diagnostic engine model unit and configured to receive the scalars from the diagnostic engine model unit and configured to generate turbine inlet temperature information for the engine using a thermodynamic model. The thermodynamic model is based on component maps associated with the engine. The system further includes a storage unit coupled to the engine-specific model unit and configured to store the turbine inlet temperature information. | 06-12-2014 |
| 20140236450 | DETERMINING THE DETERIORATION OF A GAS TURBINE ENGINE IN USE - This invention relates to the operation of gas turbine engines, and in particular to determining deterioration of components during operation. In a specific embodiment, the invention is concerned with determining the actions to be taken when a foreign body impact has been detected, for example on a fan blade. | 08-21-2014 |
| 20140236451 | AVIONICS METHOD AND DEVICE FOR MONITORING A TURBOMACHINE AT STARTUP - A method of characterizing a turbine engine, the method comprising:
| 08-21-2014 |
| 20140244132 | SYSTEM AND METHOD FOR 0N-WING ENGINE TRIM VERIFICATION - Devices and methods relating to gas turbine engines and engine temperature trim verification are disclosed. An exemplary method comprises acquiring signals representing a plurality of engine parameters measured while the engine is operating and determining a recommended trim thermocouple resistance based at least partly on the measured parameters. The engine parameters may comprise at least an engine inlet temperature and an exhaust temperature. | 08-28-2014 |
| 20140244133 | AIRCRAFT ENGINE SYSTEMS AND METHODS FOR OPERATING SAME - A device and a method for determining a residual life expectancy of a rotor of a gas turbine. The method includes receiving at a computer operating conditions of the gas turbine, receiving a gas turbine rotor inspection result, updating, based on the operating conditions of the gas turbine and the gas turbine rotor inspection result, a database for a fleet corresponding to the gas turbine, and calculating the residual life expectancy of the rotor of the gas turbine. | 08-28-2014 |
| 20140257666 | Online Enhancement for Improved Gas Turbine Performance - A system is provided that includes a memory storing a turbomachinery degradation model configured to model degradation of a turbomachinery over time. The system also includes a controller communicatively coupled to the memory and configured to control the turbomachinery based on a feedback signal and the turbomachinery degradation model. Moreover, the turbomachinery degradation model is configured to use a target power to derive a control parameter by estimating a modeled power of the turbomachinery, and the controller is configured to use the control parameter to control the turbomachinery. | 09-11-2014 |
| 20140257667 | METHOD OF SYNCHRONISING THE ENGINES OF AN AIRCRAFT - A method of synchronizing engines of an airplane in accordance with at least one activation logic ( | 09-11-2014 |
| 20140277991 | PROGNOSTIC HEALTH MANAGEMENT APPROACHES FOR PROPULSION CONTROL SYSTEMS - A real-time gas turbine management system includes a controller system coupled to a gas turbine engine. The controller system is configured to control demand on a first and second component of a gas turbine engine. The controller system is configured to identify a set point reference of the first component, identify a set point reference of the second component, and identify a data set indicative of a level of deterioration of the gas turbine engine. The controller system is also configured to change the set point reference of the first component to extend a lifespan of the gas turbine engine and/or change the set point reference of the second component to extend the lifespan of the gas turbine engine. | 09-18-2014 |
| 20140277992 | INTEGRATED HEALTH MANAGEMENT APPROACH TO PROPULSION CONTROL SYSTEM PROTECTION LIMITING - A real-time engine management system having a controller system configured to control demand on a first component of an engine. The controller system is also configured to access a first set of prognostic data about the first component, where the first set of prognostic data includes a remaining lifespan approximation of the first component operating at a present operating condition. The controller system is also configured to identify a temporal length of an engine procedure operating at the present operating condition, alter a current limit constant associated with the first component to increase the remaining lifespan approximation of the first component beyond the temporal length, and implement the current limit constant associated with the first component so that the first component does not fault during the engine procedure. | 09-18-2014 |
| 20140297155 | AIRCRAFT POWER OUTTAKE MANAGEMENT - A system and method for controlling the operation of a gas turbine engine supplying power to an aircraft. The engine is controlled according to a reading of an amount of power drawn from the supplied power. The reading is fed directly to a control system, which issues commands for controlling engine parameters comprising an acceleration reference signal, load shedding, variable geometry positioning, and fuel flow. The control system may further issue commands for controlling the amount of power drawn. The control system may further use the reading to monitor the engine's condition. | 10-02-2014 |
| 20140303871 | METHOD AND SYSTEM FOR REGULATING POWER IN THE EVENT OF AT LEAST ONE AIRCRAFT ENGINE FAILURE - A method to optimize resources needed to continue flight if at least one main engine is lost, by relieving a propulsion system that has remained operative of all or some of non-propulsive energy demands, by additional generation of non-propulsive power, operating continuously. The method uses a GPP unit that operates constantly in flight while taking up some of nominal total non-propulsive power of the aircraft, to supply increased non-propulsive power almost instantaneously, based on at least three respective emergency regimes at a time of engine failure. A control and monitoring function of the GPP calculates elapsed time for each emergency regime, and informs a data processing unit thereof, while emitting an alarm if operating periods allocated to each emergency regime are exceeded, and the emergency function adjusts non-propulsive power demands made by the aircraft between main engines and the unit GPP either automatically or on orders of a pilot. | 10-09-2014 |
| 20140358398 | Use of SS Data Trends in Fault Resolution Process - An automated method for resolving fault in an engine is disclosed. The method may include providing a reasoner module for recommending a set of maintenance actions to resolve fault in the engine, inputting steady state performance data from the engine into the reasoner module, and using the reasoner module to recommend a set of maintenance actions based at least in part on the steady state performance data. A fault resolution system for a gas turbine engine is also disclosed. The fault resolution system may include at least one computer processor operatively configured to receive steady state performance data from the gas turbine engine, and recommend a set of maintenance actions to resolve fault in the gas turbine engine based at least in part on the steady state performance data. | 12-04-2014 |
| 20150019104 | GAS TURBINE ENGINE CONTROLLER WITH EVENT TRIGGER - A feedback control system is provided and includes a controller to control an operation of a motive element in accordance with current and previous measured states. The controller includes a servo, a processor and an event trigger controller. The event trigger controller is configured to cause the processor to command the servo to perform model based control (MBC) executions in an event a difference between the current and previous measured states exceeds a threshold based on the previous measured state or the current measured state exceeds a limit, and skip the MBC executions in an event the difference does not exceed the threshold and the current measured state does not exceed the limit. | 01-15-2015 |
| 20150046061 | SHAFT DISPLACEMENT CONTROL - An aircraft powerplant having a shaft is disclosed in one embodiment in which a squeeze-film damper is used. The squeeze-film damper includes a plurality of sectors having a working fluid. A pressure can be controlled in the working fluid to the sectors to discourage changes in the sectors as a result of vehicle maneuvering. A controller is used to operate upon sensed aircraft motion and regulate pressure in the sectors. | 02-12-2015 |
| 20150081193 | ADAPTIVE REMAINING USEFUL LIFE BALANCING CONTROL SYSTEM AND METHOD FOR MULTI-ENGINE SYSTEMS - A system and method of adaptively managing a plurality of engines in a multi-engine system, where each engine comprises hot gas components and non-hot gas components, and each engine exhibits a performance margin and a remaining useful life, includes continuously, and in real-time, determining a plurality of different degradation mechanisms for each of the plurality of engines, and continuously, and in real-time, determining which of the determined degradation mechanisms is most limiting. The engines are controlled, based on the most limiting degradation mechanism, in a manner that the remaining useful lives of each engine are substantially equal. The plurality of different degradation mechanisms of each engine are determined based on the engine performance margin, modeled failure predictions of the hot gas components, and modeled failure predictions of the non-hot gas components. | 03-19-2015 |
| 20150100219 | FUEL DELIVERY SYSTEM - This invention concerns a fuel delivery system for an engine, in which two or more discrete fuel compositions are made available to the engine. The system has a vapour trail detection sensor configured to generate a detection signal indicative of a characteristic of a vapour trail. A regulator is configured to regulate a percentage of a first and a second fuel composition delivered to the engine as resultant fuel composition. A controller is arranged to undertake a search of trial fuel compositions by controlling the regulator to deliver to the engine a plurality of trial fuel compositions having different ratios of the first and second fuel compositions. The controller controls delivery of a resultant fuel composition to the engine in response to the vapour trail characteristic detection signals for said plurality of trial fuel compositions. | 04-09-2015 |
| 20150100220 | AIRCRAFT ENGINE FUEL SYSTEM - This invention concerns a method of delivering fuel to an aircraft engine | 04-09-2015 |
| 20150291286 | MULTIPLE AIRCRAFT ENGINE CONTROL SYSTEM AND METHOD OF COMMUNICATING DATA THEREIN - The multiple aircraft engine control system having a corresponding engine controller associated with each one of the engines, each one of the engine controllers having at least two independent channels, each one of the at least two independent channels having at least two communication buses, each one of the at least two communicating buses of each channel being connected to a respective one of the at least two communicating buses of each one of the other channels. The method can time-interweave originating data of the channels. | 10-15-2015 |
| 20150330310 | METHODS AND APPARATUS TO DETERMINE AIRFLOW CONDITIONS AT AN INLET OF AN ENGINE - Methods and apparatus to determine airflow conditions at an inlet of an engine are disclosed herein. An example apparatus disclosed herein includes a sensor disposed at an inlet of an engine to measure a pressure characteristic, a temperature characteristic and a velocity characteristic of an airflow moving through the inlet and a processor to determine an air mass flow rate based on the pressure characteristic, the temperature characteristic and the velocity characteristic measured at the engine inlet. | 11-19-2015 |
| 20150345403 | Model-Based Optimal Control For Stall Margin Limit Protection in an Aircraft Engine - A control system for a gas turbine engine, a method for controlling a gas turbine engine, and a gas turbine engine are disclosed. The control system may include a hybrid model predictive control (HMPC) module, the HMPC module receiving power goals and operability limits and determining a multi-variable control command for the gas turbine engine, the multi-variable control command determined using the power goals, the operability limits, actuator goals, sensor signals, and synthesis signals. The control system may further include system sensors for determining the sensor signals and a non-linear engine model for estimating corrected speed signals and synthesis signals using the sensor signals, the synthesis signals including an estimated stall margin remaining. The control system may further include a goal generation module for determining actuator goals for the HMPC module using the corrected speed signals and an actuator for controlling the gas turbine engine based on the multivariable control command. | 12-03-2015 |
| 20150346059 | VEHICLE MISSION CAPABILITY PREDICTION SYSTEM AND METHOD - A system method for predicting vehicle mission capability for a vehicle that is propelled by an engine includes collecting engine degradation data for the engine. Location independent engine degradation data are generated from the collected engine degradation data. The location independent engine degradation data are representative of engine degradation that is independent of locations associated with the mission. Predictions of location dependent engine degradation are calculated from the collected engine degradation data and the location independent engine degradation data. The location dependent engine degradation is representative of engine degradation due to movement through locations associated with the mission. | 12-03-2015 |
| 20150369138 | ENGINE HEALTH MONITORING AND POWER ALLOCATION CONTROL FOR A TURBINE ENGINE USING ELECTRIC GENERATORS - A control for a turbine engine using electrical machines monitors engine health and allocates power extraction between the electrical machines. | 12-24-2015 |
| 20160010495 | METHOD FOR THE CONTROL AND PROTECTION OF A GAS TURBINE AND GAS TURBINE USING SUCH METHOD | 01-14-2016 |
| 20160130974 | COMPRESSOR MONITORING METHOD - A method of predicting the condition of a compressor with respect to rotating stall is disclosed. The method comprises the steps of:
| 05-12-2016 |
| 20160138481 | DEGRADED GAS TURBINE TUNING AND CONTROL SYSTEMS, COMPUTER PROGRAM PRODUCTS AND RELATED METHODS - Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective output to match a nominal mega-watt power output value, and subsequently measuring an actual emissions value for each GT; adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual emissions value and a nominal emissions value at the ambient condition; and calculating a degradation for each GT in the set of GTs over a period. | 05-19-2016 |
| 20160146116 | METHOD FOR OPTIMIZING THE CONTROL OF A FREE TURBINE POWER PACKAGE FOR AN AIRCRAFT, AND CONTROL FOR IMPLEMENTING SAME - A method optimizing fuel-injection control with driving speeds of apparatuses adjusted by controlling a turbine speed according to power, and optimizing control of a free turbine power package of an aircraft, including a low-pressure body, supplying power to apparatuses and linked to a high-pressure body. The method varies the low-pressure body speed to obtain a minimum speed for the high-pressure body, so power supplied by the apparatuses remains constant. Power supplied by the apparatuses is dependent upon the apparatuses driven speed by the low-pressure body, and a speed set point of the low-pressure body is dependent upon a maximum value of minimum speeds of the apparatuses, enabling required power to be optimized, upon a positive or zero incrementation added to the speed set point of the low-pressure body to minimize speed of the high-pressure body to the apparatuses power supply. | 05-26-2016 |
| 20160146117 | AIRCRAFT ENGINE FUEL SYSTEM - This invention concerns fuel delivery system for an aircraft engine ( | 05-26-2016 |
| 20160146118 | METHODS AND SYSTEMS FOR ENHANCING CONTROL OF POWER PLANT GENERATING UNITS - A control method for optimizing an operation of a power plant having generating units during a selected operating period subdivided so to include regular intervals within which each of the generating units comprises one of an on-condition and an off-condition. The control method may include: determining a preferred case for each of the competing operating modes for the intervals; based upon the preferred cases, selecting proposed turndown operating sequences for the selected operating period; determining a shutdown operation for each of the generating units comprising the off-condition for one or more intervals during the selected operating period and, therefrom, calculating a shutdown economic outcome; determining a turndown operation for each of the generating units comprising the on-condition for one or more intervals during the selected operating period and, therefrom, calculating a turndown economic outcome; calculating a sequence economic outcome for each of the proposed turndown operating sequences; and comparing the sequence economic outcomes. | 05-26-2016 |
| 20160146119 | GAS TURBINE ENGINE OPTIMIZATION CONTROL DEVICE - A gas turbine engine optimization control device estimates a specific fuel consumption using a given control parameter of a variable mechanism, determines a change between a specific fuel consumption estimation value by the control parameter of the variable mechanism in a previous operation period and a specific fuel consumption estimation value by the control parameter of the variable mechanism in this operation period, determines a new control parameter of the variable mechanism with which the specific fuel consumption estimation value approaches a minimum, adds the new control parameter of the variable mechanism to a preset control parameter initial value, and sets the addition value to be a control parameter command value of the variable mechanism in a next operation period. | 05-26-2016 |
| 20160160762 | SYSTEM AND METHOD FOR PREDICTING AND MANAGING LIFE CONSUMPTION OF GAS TURBINE PARTS - A method for estimating and managing life of a gas turbine is provided. The method includes estimating a remaining useful life of a component of a gas turbine, obtaining parameters of the gas turbine, at least one of which comprises the estimate of the remaining useful life of a component of the gas turbine, assigning operating weightages to the gas turbine parameters based a plant objective, generating a set point for operating the gas turbine based on the weighted gas turbine parameters, and adjusting an operating characteristic of the gas turbine to meet the set point. | 06-09-2016 |
| 20160169103 | CONTROL UNIT FOR GASIFICATION POWER GENERATION PLANT, GASIFICATION POWER GENERATION PLANT, AND CONTROL METHOD FOR GASIFICATION POWER GENERATION PLANT | 06-16-2016 |
| 20160169129 | ENERGY STORAGE ADVISEMENT CONTROLLER FOR A VEHICLE | 06-16-2016 |
| 20160169154 | MODEL-BASED COMBINED CYCLE POWER PLANT LOAD CONTROL | 06-16-2016 |
| 20160177777 | OVER TIP LEAKAGE MEASUREMENT | 06-23-2016 |
| 20160186669 | METHOD AND MODULE FOR FILTERING A RAW SETPOINT - This module ( | 06-30-2016 |
| 20160195024 | FUEL SYSTEM FOR TONE CONTROL AND OPERABILITY | 07-07-2016 |
| 20160195026 | SYSTEMS AND METHODS FOR GENERATING VARIABLE RAMP RATES FOR TURBOMACHINERY | 07-07-2016 |
| 20160201573 | AUTOMATED TUNING OF GAS TURBINE COMBUSTION SYSTEMS | 07-14-2016 |
| 20160201919 | METHOD AND SYSTEM FOR INJECTING FUEL INTO AN ENGINE COMBUSTION CHAMBER | 07-14-2016 |
| 20170233103 | MODIFIED START SEQUENCE OF A GAS TURBINE ENGINE | 08-17-2017 |
| 20180022464 | CROSS ENGINE COORDINATION DURING GAS TURBINE ENGINE MOTORING | 01-25-2018 |
| 20180023484 | SPEED CONTROL DURING MOTORING OF A GAS TURBINE ENGINE | 01-25-2018 |
| 20190144136 | METHODS FOR EFFLUENT BASED CONDITION ASSESSMENT | 05-16-2019 |
