Abstract: A failure diagnostic apparatus is provided with an offset power source for offsetting a ground-side voltage of an air-fuel ratio sensor, an activation state judging unit for judging whether the air-fuel ratio sensor is active, a failure diagnosing unit for judging for a failure from an offset-added output signal of the air-fuel ratio sensor in a period when the activation state judging unit judges that the air-fuel ratio sensor is active, an input resistance switching unit for switching the level of an input signal from the air-fuel ratio sensor when the failure diagnosing unit has detected a failure in the air-fuel ratio sensor, and a failure state judging unit for determining a type of failure of the air-fuel ratio sensor on the basis of a voltage level obtained when the input resistance switching unit has switched the input signal level.

Abstract: 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.

Abstract: 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.

Abstract: 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 25 performs a frequency analysis of combustion oscillation of a combustor and splits a result of the analysis into respective frequency bands. Then, a state grasping unit 22 checks an operating state of the gas turbine on the basis of the result of the analysis of the combustion oscillation and process value of the gas turbine, and corrects the checked operating state on the basis of a fuel composition or a heat capacity of fuel gas measured by a fuel characteristic measuring unit 200. A countermeasure determining unit 23 conducts a countermeasure for controlling an operating action of the gas turbine on the basis of the operating state thus checked.

Abstract: In a control system for a gas turbine engine, a degradation level of the gas turbine engine is estimated according to a deviation of an output of an internal temperature sensor when the engine is producing a target output at a target rotational speed from a prescribed reference temperature, and a correction value for correcting the engine operation map is computed according to the degradation level of the gas turbine engine. Thereby, even when the degradation of the engine has progressed to a certain extent typically owing to the aging of various component parts, the engine operation map can be corrected in such a manner that the level of fuel supply is optimally selected and the acceleration, efficiency and other items of performance of the engine can be improved.

Abstract: 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.

Abstract: A gas turbine engine having at least a rotor shaft operatively connecting a compressor apparatus and a turbine apparatus, comprises an auxiliary gear box and a phonic wheel apparatus. The auxiliary gear box is drivingly connected to the rotor shaft and the phonic wheel apparatus includes an oil pump having toothed gear and a sensor mounted to the oil pump for sensing a rotational speed of the toothed gear.

Abstract: There is provided a control apparatus for a gas-turbine engine which is configured in such a manner that a portion of compressed air from a compressor is supplied to a combustion chamber and the other portion of the compressed air is sent to the outside of the engine to be used as source of energy, and a turbine is rotated by combustion gas produced in the combustion chamber. The control apparatus executes the optimum combustion control in an extraction engine. The control apparatus calculates the physical quantity related to the air in the gas-turbine engine using the turbine flow-rate coefficient in the range in which the turbine chokes.

Abstract: 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.

Abstract: A system and method are provided for effectively removing ice that may have formed on gas turbine engine compressor inlet guide vanes and/or preventing, or at least inhibiting, reformation of ice on gas turbine engine compressor inlet guide vanes after the ice has been removed. A determination is made as to whether flow through the compressor is below a predetermined flow value. If the flow through the compressor is below the predetermined flow value, then the inlet guide vanes are repeatedly moved between at least two predetermined positions to remove ice and/or prevent, or at least inhibit, reformation of ice on the inlet guide vanes.

Abstract: A monitoring system of components of a gas turbine (1) comprising: a acquisition device (3) of signals proportional to functioning parameters characteristic of the functioning state of a gas turbine (1), a first electronic processing unit (4) comprising a first data base, a second electronic processing unit (6), a data transfer device, capable of electronically conveying the contents of said first data base to a second electronic processing unit (6), a monitoring program associated with said second electronic processing unit (6) comprising a library of algorithms, which allow the performances of the gas turbine (1) and its components to be determined by comparing data coming from subsequent recordings of said functioning parameters, a display device associated with said second electronic processing unit (6) whereby it is possible to gain access to the functionality of said monitoring program by means of a graphic interface.

Abstract: A system and method is provided for startup characterization in a turbine engine that provides the ability to accurately characterize engine startup. The startup characterization system and method uses engine temperature sensor data and engine speed sensor data to accurately characterize the startup of the turbine engine by determining when several key engine startup conditions are reached. By storing and analyzing engine sensor data taken during these key conditions of engine startup, the system and method is able to accurately characterize the performance of the engine during startup. This information can be used as part of a trending system to determine when faults in the start transient regime are occurring or likely to occur. Additionally, this information can be used in real time by control systems to better control the startup and operation of the turbine engine.

Abstract: A method for determining how well configurations for a gas turbine propulsion system attain selected acoustic wave energy emissions criteria based on acquiring a plurality of acoustic frequency spectra representations of a noise representation therefor over an operating duration. Relative peaks in the acoustic frequency spectra representations are then located and the forms of at least one of those peaks is altered with respect to acoustic frequency in manners substantially matching acoustic wave energy emissions changes corresponding to configuration changes in gas turbine propulsion systems which are then evaluated to provide an operating parameter noise value. One of those operating parameter noise values that best meets the selected acoustic wave energy emissions criteria is used to aid in determining corresponding configurations changes to thereby better meet those criteria.

Abstract: A method of estimating quality parameters for a plurality of engine components of a gas turbine engine is provided. The engine components have at least one sensor responsive to the engine component operation. The method includes providing an engine model having virtual sensor values and quality parameters corresponding to the plurality of sensors of the engine components; comparing the virtual sensor values to actual sensor values of the plurality of sensors of the engine components to determine the difference between the actual and virtual sensor values; amplifying the difference by a predetermined gain; generating a plurality of quality parameter deltas in response to the sensed difference; iteratively updating the embedded engine model by inputting a predetermined portion of the generated quality parameter deltas into the embedded engine model; adjusting the embedded engine model for engine operating conditions; and recalculating the virtual sensor values.

Abstract: Interruption in supervisory position control signals can cause problems with respect to actuators which upon loss of such control signals for the actuator will generally slew to a fixed idle position. In such circumstances a machine such as a gas turbine engine in which an actuator is associated will not sustain performance even though there is continued local power supply to the actuator. By utilising a local controller which stores actuator response profiles for certain machine status stages through perturbation or marginal activation of the actuator an appropriate actuator response profile can be chosen and therefore sustaining control signals presented to the actuator to maintain machine operation.

Abstract: 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.

Abstract: A method and controller for identifying lean blowout conditions in a Dry Low NOx (DLN) combustor during a premix mode. An effective approach to quickly and reliably identify a blowout during operation in the premix mode is by the effect on fuel normalized power (FNP). FNP is a useful signal, in that a power reduction from a blowout may be distinguished much slower changes in power resulting from global fuel demand (changing load request). A difference between the FNP and a filtered FNP parameter may be compared against a predetermined threshold. If the difference exceeds the threshold, a lean blowout is identified and a signal may be transmitted to the turbine controller to reposition combustor operation away from blowout conditions.

Abstract: 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.

Abstract: Methods and systems for reducing a flow of ambient air into a bearing lubricating oil system are provided. The system includes a lubricating oil bearing cover that is stationary with respect to the bearing wherein the bearing is configured to support a portion of a rotatable machine shaft. The cover includes a first end cap extending radially inwardly towards the shaft such that a cavity surrounding the bearing is formed by the cover and the first end cap and a set of seal rings positioned substantially concentric with the shaft and forming a seal against lubricating oil flow. The seal rings include a plurality of wire bristles extending radially inwardly from the end cap wherein the wire bristles are configured to extend to a surface of the shaft when assembled and the bristles are configured to present a tortuous flow path to gas infiltrating the cavity.

Abstract: 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.

Abstract: Systems and methods for prediction of gas turbine trips due to component failures such as electro-hydraulic valve (gas control valve) system failures. Exemplary embodiments include prediction of gas turbine trips due to component failures, the method 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 gas control valves.

Abstract: A system, method and apparatus for monitoring the performance of a gas turbine engine. A counter value Indicative of the comparison between the engine condition and the threshold condition is adjusted. The aircraft operator is warned of an impending maintenance condition based on the counter value and determines an appropriate course of action.

Abstract: 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.

Abstract: A gas turbine engine includes a combustor having a fuel nozzle assembly for delivering fuel to a combustion chamber. A sensor is at least partially housed within the fuel nozzle assembly for sensing a parameter associated with the delivery of fuel to the combustion chamber. In one example, the sensor is an optical sensor coupled to an optical decoder for ascertaining the parameter. A trim valve is in communication with the fuel nozzle assembly. A controller is in communication with the sensor and is programmed to actuate the trim valve to adjust the amount of fuel delivered through the fuel nozzle assembly in response to the parameter. In one example, an end of the optical sensor is arranged near a fuel exit of the fuel nozzle assembly. The controller actuates the trim valve for the fuel nozzle assembly to achieve a desired air/fuel ratio and/or balance the fuel delivery of the fuel nozzle assembly relative to another fuel nozzle assembly within the gas turbine engine's combustor system.

Abstract: 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.

Abstract: A method of detecting rubs during operation of a turbomachine comprising at least one rotating object having a tip and a shelf is provided. The method includes generating signals representative of a sensed parameter and processing the signals to generate height versus time data for the tip. The height of the tip corresponds to the distance between the tip and the shelf. The method further includes monitoring the height versus time data, in order to determine whether a change in the height data exceeds a threshold value, and detecting a rub of the rotating object(s) on a second object, when the change in the height data exceeds the threshold value. A rub detection system for a turbomachine and a turbine engine system with rub detection are also provided.

Abstract: 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.

Abstract: The present invention relates to a method and to apparatus (9) for controlling and regulating a rotorcraft turbine engine (1) provided with an electronic control and regulation computer (3) that receives signals relating to monitored parameters of said turbine engine (1). The apparatus is remarkable in that it is provided alarm means (4) controlled by said electronic computer (3) via an analog connection (8) to operate whenever an event occurs that might diminish the safety of said rotorcraft.

Abstract: The invention is a method for controlling blade tip clearance in a turbine engine having a flowpath extending therethrough, and a system for carrying out the method. The method includes acquiring a first nonpulsating pressure signal PC representative of tip clearance, sensing a second pressure PB substantially unaffected by tip clearance, forming an actual ratio of the acquired pressure and the sensed pressure, determining an error E having an actual component and a desired component, the actual component being a function of the actual ratio; and commanding a clearance control system to reduce the error.

Abstract: 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 (30) situated in correspondence with the combustion chamber (14) of the turbine, the amplitude of the pressure oscillations inside the combustion chamber (14) and the persistence time or cycle of the same oscillations, evaluating the behaviour under fatigue conditions of the combustion chamber (14), by constructing the Wohler curve for a certain material which forms the combustion chamber (14) for a predefined combustion frequency and for the amplitude and cycle values of the pressure oscillations measured, measuring the cumulative damage (D) to the combustion chamber (14) during functioning under fatigue conditions of the turbine by means of the Palmgren-Miner hypothesis and exerting protection actions of the turbine if the cumulative damage value (D) measured is exceeded.

Abstract: The present invention comprises methods for detecting and controlling flame blowout in combustors. The blowout precursor detection system comprises a combustor, a blowout precursor detection unit, a pressure measuring device and/or an optical measuring device. The methods of the present invention comprise receiving optical data measured by an optical measuring device, performing one or a combination of raw data analysis, spectral analysis, statistical analysis, and wavelet analysis on received optical data, and determining the existence of a blowout precursor based on such analyses. The present invention further comprises closed-loop control methods for controlling a combustor to prevent blowout.

Abstract: A system and method for determining thermal growth of motor or engine parts to thereupon control the clearance of motor or engine fan blades is disclosed herein. In addition, a system and method for monitoring the health of a turbine engine, its components and sub-components is also described herein. The system(s) and method(s) described herein permit continuous monitoring during the life of the engine for radial clearances and blade and rotor vibration problems, which will assist in correcting and retaining performance for a longer on-wing time in operation. In addition, inconsistent engine-to-engine performance variations due to component tolerances, engine operation characteristics, and operation during extremes in ambient temperatures can be eliminated or significantly minimized when employing the system(s) and method(s) described herein.

Abstract: A method of emergency operation of an aircraft turbofan engine during an aircraft flight is provided. The engine includes a fan shaft with a fan, and an electric motor/generator mounted for rotation therewith. The method includes shutting down the engine while allowing the engine to windmill, operating the electric motor/generator to rotate the shaft at a determined windmilling speed which is desired for the fan shaft, and operating the engine at the desired windmilling speed for substantially a remainder of the aircraft flight.

Abstract: 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.

Abstract: The present invention relates to a method and to an associated fuel metering system for balancing the power delivered by two aircraft turboshaft engines by determining first and second limiting margins of the engines (M1, M2) which are transformed into first and second power margins. Thereafter, the values of the first and second power margins are compared in order to determine a primary difference between said first and second power margins. Finally, the engine having the greater power margin is accelerated in order to balance the first and second engines in power by minimizing the primary difference to as great as extent as possible.

Abstract: 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.

Abstract: 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.

Abstract: A vehicle communication system is provided to facilitate meeting our people in nearby or neighboring cars with similar interests, desires or wants. The vehicle communication system has a host vehicle two way communication device, a host vehicle personal data storage component and a host vehicle personal data matching component. The host vehicle two way communication device conducts direct short range communications in a host vehicle broadcast area surrounding a host vehicle. The host vehicle personal data storage component broadcasts at least some of a host vehicle user's personal data and receives nearby user's desired profile requirement via the host vehicle two way communication device. The host vehicle personal data matching component compares host vehicle user's desired profile requirement that is based on the host vehicle user's personal data with the nearby user's desired profile requirement.

Abstract: Means for cooling a bearing assembly supporting a rotor stage of a gas turbine engine after engine shutdown. The engine comprises a combustion section, a compressor for the delivery of air to the combustion section, and a bearing assembly supporting a rotor stage. The means for cooling a bearing assembly comprises a means operable to generate a signal representative of turbine duct temperature immediately prior to engine shutdown, a means for determining the duration for cooling after engine shutdown as a function of the signal representative of turbine duct temperature, and the compressor operable as a cooling means to deliver cooling air to the rotor stage after engine shutdown. Thereby the amount of heat conducted to the bearing assembly is limited such that the temperature of the bearing assembly is limited to below a predetermined temperature.

Abstract: A vehicle on-board unit comprises a short range wireless broadcasting section, a vehicle identifier receiving section, a vehicle identifier counting section and a communication congestion determining section. The short range wireless broadcasting section is configured to broadcast a host vehicle identifier of a host vehicle equipped with the vehicle on-board unit. The vehicle identifier receiving section is configured to receive neighboring vehicle identifiers relating to neighboring vehicles located within a prescribed communication region around the host vehicle. The vehicle identifier counting section is configured to determine a number of the neighboring vehicle identifiers received by the vehicle identifier receiving section within a prescribed period of time.

Abstract: 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.

Abstract: A method of analyzing variations in an indicator of the behavior of a mechanism, in which noise is extracted, and any discontinuities from an indicator in order to obtain a trend, variations in the trend are compared with one or more reference values; and a fault of the mechanism is indicated as a function of the result of the comparison. Any outlier data in the indicated data are search for and subtracted, and any edge data are extracted from the data obtained from the search operation.

Abstract: An exemplary controller includes a control valve that includes an electric actuator operatively coupled to a valve stem, a piston operatively coupled to one or more hydraulic fluid paths controlled by the control valve and including a piston shaft, a rotatable shaft operatively coupled to the piston shaft and mechanically isolated from the valve stem and capable of adjusting geometry of the variable geometry turbine, and an electronic sensor capable of sensing an angular position of the rotatable shaft. Various other exemplary systems, methods, devices, etc., are also disclosed.

Abstract: 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.

Abstract: A system and method for narrowing an assessment of root cause to a single stage within a gas turbine engine module using coupling factors and known instrumentation non-repeatability. Embodiments examine certain root cause (RC) effects that manifest themselves as coupling levels, or ratios (CR), between an engine module's efficiency change ?? and its flow parameter change ?FP.

Abstract: 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.

Abstract: A turbine overspeed control system for use with a gas turbine engine of a gas turbine electrical powerplant. The overspeed control system preferably comprises a first and second overspeed control subsystem. When an overspeed condition of the gas turbine engine is detected, the first overspeed control subsystem acts to remove air from a combustion section of the engine, while the second overspeed control subsystem operates to alter the angle at which an incoming flow of air is supplied to a compressor turbine located therein. The result of operating the first and/or second overspeed control subsystem is a reduction in the speed of the gas turbine engine that is much more rapid than can be accomplished by simply shutting off a fuel supply thereto.

Abstract: This present specification provides, amongst other things, an electro-optical monitoring system for obtaining a once-per-revolution signal based on the surface reflection of a rotating device that mandates non-contacting sensor input in potentially hostile environments. The system can use optical and electronic sections to illuminate and detect surface reflections from the rotating surface using existing mounting locations on the periphery of the machine to be measured. The electronic portion is configured to determine a unique mark as the once-per-revolution marker or allow an attending operator to assign a specific marker based on the observed reflected pattern. The optical portion consists of a light source, receiver, and optics will allow for focused and directed light paths to properly position relevant to key reflective surfaces.

Abstract: 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.

Abstract: Method for detecting faults in a device comprising the steps of receiving a plurality of performance parameters, applying the plurality of performance parameters to a first model to produce a plurality of estimated performance parameters, applying the plurality of performance parameters to a second model to produce a plurality of estimated device parameters, computing a plurality of residuals from the plurality of estimated device parameters, computing a plurality of distance measuring from the plurality of residuals, detecting at least one parameter deviation using the plurality of residuals and the plurality of estimated performance parameters, and setting at least one detection flag if the detected at least one parameter deviation is persistent.