Abstract: A malfunction detection device for a resolver detects malfunction in a resolver with accuracy and stability even if a value of a square sum is varied between inside and outside of a normal range. When the resolver is in malfunction, a sine signal and a cosine signal are read. It is determined whether a malfunction determination of the resolver is prohibited, or not, from read values of the sine signal and the cosine signal, or square values thereof. When it is determined that the malfunction determination of the resolver is prohibited, the count value is accumulated and incremented every time the test value falls outside a normal range. When the count value arrives at a given value or higher, it is determined that the resolver is in malfunction.

Abstract: A system for optically monitoring a gas turbine engine includes a viewport having an opening disposed within a casing of the gas turbine engine. The opening extends from an interior side of the casing to an exterior side of the casing, and the viewport is configured to receive an image from inside the casing. The system also includes an optical connection positioned outside the casing and optically coupled to the viewport. The optical connection is configured to convey the image from the viewport to a detector array, and the optical connection includes multiple optical fibers fused to one another to form a unitary substantially rigid fiber bundle.

Abstract: One illustrative embodiment is a method comprising operating an engine and an aftertreatment system by controlling a plurality of charge constituents provided the engine, iteratively perturbating one or more combustion inputs effective to vary operation of the engine, and determining fuel consumption and emissions information at the operating points effective to seek a weighted optimization of multiple parameters including fuel consumption and reductant consumption while also meeting a predetermined NOx emissions criterion. Further embodiments, forms, objects, features, advantages, aspects, and benefits shall become apparent from the description and figures.

Abstract: 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.

Abstract: A system to performance tune a site system includes one or more controllers each controlling a subsystem of the site system by changing values of a set of parameters. The system also includes a site reference model configured to indicate a target performance of the site system, and a processor configured to instruct the one or more controllers based on the target performance for the site system.

Abstract: A method of optimizing the performance of a rotary wing aircraft having at least one turbine engine with a gas generator and a turbine assembly comprising at least one turbine. In a definition step (STP1), first and second performance levels are defined for the aircraft. During a health check step (STP2), a first power margin is determined as a function of a speed of rotation of said gas generator and a second power margin is determined as a function of a temperature in said turbine assembly. During an evaluation step (STP3), each power margin is compared with a first threshold in order to determine whether a target performance level is equal to the first performance level or to the second performance level. During a display step (STP4), the target performance level is displayed.

Abstract: 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.

Abstract: A hazard warning system can be utilized in an aircraft. The hazard warning system can include a processing system for determining an icing condition and causing an indication of the icing condition to be provided to an engine control, such as a full authority digital engine control (FADEC). The engine can be operated in a mode in response to the indication. The mode can be a lower efficiency mode.

Abstract: An adjustment test apparatus for AI module is disclosed, which includes a signal generator supplying analog electric quantity to a plurality of the same type of AI modules, and a maintenance PC connected to each AI module, the maintenance PC being connected to each AI module through a USB hub having a port corresponding to each AI module and a USB-RS232 converter connected to each port, the maintenance PC having a function of selecting a port to communicate with each AI module, and a function of monitoring a digital output value corresponding to an input signal provided by the signal generator to each AI module at the time of communication and setting each AI module to correct the output value to a proper value.

Abstract: A method and device for aiding the monitoring of a turbine engine of an aircraft, which displays on one and the same indicator of a of a display indication elements illustrating as a percentage the engine start progression or the current sub-idle state of the turbine engine, a margin to a limit temperature of the turbine engine, a margin to a maximum temperature of the turbine engine and a margin to a possible failure of the start that is generated by a too low speed increase of the turbine engine.

Abstract: Embodiments are directed to receiving, by a computing device comprising a processor, at least one control input associated with an aircraft, obtaining, by the computing device, a predicted response to the at least one control input by filtering on a trim position, wherein the predicted response is based on a model of the aircraft, obtaining, by the computing device, an actual response of the aircraft to the at least one control input, comparing, by the computing device, the predicted response and the actual response, and determining, by the computing device, at least one attribute based on the comparison.

Abstract: A control device of a compressor includes a valve control unit configured to control an anti-surge valve that returns fluid in a discharge side of the compressor to a suction side of the compressor in accordance with a control parameter, a simulation unit configured to simulate operational status of the compressor in a plant in accordance with a plant model and the control parameter of the plant to which the compressor is installed, and a control parameter adjusting unit configured to adjust the control parameter in accordance with a result of the simulation.

Abstract: Systems and methods for model based control optimization for gas turbine systems. In one embodiment, a nonlinear optimization process with multiple nonlinear constraints 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 are defined based on a nominal unit. Multiple control loops are active across the ambient range with each control loop being active at a different ambient condition. This optimization process provides a set of control schedules to provide optimized performance for a specific gas turbine system or unit over a wide operation range.

Abstract: A method of monitoring a device, the method comprising: measuring one or more device operating parameters and a device performance parameter during one or more device operational periods; recording a plurality of data points, each data point comprising the device operating parameters and the associated device performance parameter; identifying one or more steady state regions in the device performance parameter and selecting a plurality of the data points from the one or more steady state regions in the device performance parameter; selecting one or more groups (40) of the steady state data points in the device operating parameter space by virtue of a predetermined density of the steady state data points in the device operating parameter space; and comparing the device performance parameter within the groups so as to identify a change in the performance of the device.

Abstract: An operations support system is provided for an engine receiving fuel. 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 and the engine data. The engine-specific model unit includes a fuel flow calculation module configured to determine a current fuel flow for the engine and a set point module configured to generate set point information for the engine using a thermodynamic model that reduces the current fuel flow to the engine, the thermodynamic model being based on component maps associated with the engine. The system further includes a data storage unit coupled to the engine-specific model unit and configured to store the set point information.

Abstract: A condition assessment system for use in monitoring the operation of at least one of a plurality of units included within a fleet of substantially similar units is described. The system includes an input device configured to receive a selection of at least one source of data related to the operation of at least one of the plurality of units. The system also includes at least one sensor associated with the at least one source of data and configured to sense data related to the operation of at least one of the plurality of units. The system also includes a condition assessment device configured to receive data from the at least one sensor, sample data associated with at least one data parameter from the received data, and generate a baseline parametric curve from the data associated with the at least one sampled data parameter.

Abstract: A method of controlling a group (2) of engines developing a necessary power (Wnec) for driving a rotor (3), said group (2) of engines having at least one electrical member (4), electrical energy storage means (5), and a first number n of engines (6) that is greater than or equal to two. A processor unit (10) executes instructions for evaluating a main condition as to whether the group of engines can develop the necessary power while resting one engine, and if so for resting one engine and accelerating a second number engines not at rest, and for causing the electrical member to operate in motor mode, if necessary, the electrical member operating temporarily in electricity generator mode when the storage means are discharged.

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 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: 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. Accordingly, the invention provides a method to take one or more FOD detection apparatus, analyse the likely (probabilistic) outcome, and provide a system to determine subsequent action that assures safety whilst minimising operational disruption. This invention provides a method and apparatus to identify FOD or bird impact to gas turbine fan blades, assessing the damage that may have occurred whist still in flight and determining post impact actions, including replacement parts.

Abstract: 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.

Abstract: An apparatus is described comprising: at least one processor; and memory storing instructions that, when executed by the at least one processor, cause the apparatus to: regulate an operation of a motor based at least in part on a control imposed on an output torque of the motor and a rate of change of a speed of the motor.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: This invention concerns a method of delivering fuel to an aircraft engine 60, which involves providing a plurality of distinct fuel sources 20, 22, a first fuel source 20 comprising a first fuel having a first aromatic content and a second fuel source 22 comprising a second fuel having a second aromatic content. One or more ambient atmospheric condition is determined for at least a portion of a flight path of the aircraft, said condition being indicative of a likelihood of contrail 135 formation by the engine 60. A desirous fuel composition for combustion by the engine is determined based upon the one or more ambient atmospheric condition and a ratio of the first and second fuels from said respective fuel sources is selected according to said desirous fuel composition. The selected ratio of the first and second fuels is delivered to the aircraft engine 60.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: A gas turbine engine control apparatus comprises a controller 34, a memory 36 associated with the controller 34 and inputs 38 for measurement data from an engine. The controller 34 determines the start of a monitoring cycle at 73, receives measurement data at the inputs 38 during the monitoring cycle, manipulates the measurement data to provide an incremental deterioration value representing deterioration occurring within the engine and during the monitoring cycle, and uses the incremental deterioration value at 72 to update a deterioration value 74 stored in the memory 36, and determines the start of a further monitoring cycle.

Abstract: A system for controlling a machine includes a first model, a second model, a controller, and a comparator. During a first cycle, the first model generates a response signal to the controller while the second model generates a predicted parameter signal. During the first cycle, the comparator transmits a feedback signal to the second model if a predetermined threshold is not met. A method for controlling a machine includes transmitting a response signal from a first model to a controller, generating a control signal to the machine, and generating a predicted parameter value in a second model. The method further includes transmitting a feedback signal to the second model if a predetermined threshold is not met.

Abstract: 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.

Abstract: A system of speed control for a ram air turbine of an aircraft includes a power electronics controller, at least one routing device in communication with the power electronics controller, at least one secondary load in serial communication with the at least one routing device and the power electronics controller, and a ram air turbine (RAT) in communication with the power electronics controller, wherein the power electronics controller is configured to apply the secondary load to the RAT through the at least one routing device in response to a transient speed increase of the RAT.

Abstract: 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.

Abstract: 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.

Abstract: A turbofan engine control system and method includes a core nacelle housing (12), a compressor and a turbine. A turbofan is arranged upstream from the core nacelle and is surrounded by a fan nacelle (34). A bypass flow path (39) is arranged downstream from the turbofan between the core and fan nacelles. The bypass flow path includes a nozzle exit area (40). A controller (50) detects at least one of a take-off condition and a landing condition. The controller changes effectively the nozzle exit area to achieve a thrust vector in response to the take-off and landing conditions.

Abstract: The invention relates to a method for detecting a fuel leakage in the fuel distribution system between a fuel control valve and at least one burner of a gas turbine during the operation of the gas turbine. In order to detect a fuel leakage, the fuel consumption is approximated in accordance with the mechanical power of the gas turbine, the fuel amount fed to the fuel distribution system is determined, and the leakage flow is determined from the difference between the fed fuel amount and the fuel consumption. The invention further relates to a gas turbine for performing such a method.

Abstract: There is provided a system and method for conditioning a noisy signal. A sensing signal is received during each one of a plurality of successive control cycles, the sensing signal comprising a measurement component indicative of a measurement of at least one engine parameter and a noise component. A curve-fitting technique is applied to the received sensing signal for filtering thereof to attenuate the noise component, the filtering comprising, during a first one of the plurality of the control cycles, asymmetrically filtering the sensing signal received during the first control cycle, thereby generating filtered data, and, during a second control cycle subsequent to the first control cycle, symmetrically filtering the sensing signal received during the first control cycle, thereby generating corrected data.

Abstract: A method and device aids in monitoring at least one turbine engine in an aircraft. The method includes determining a value illustrating a thermomechanical state of the turbine engine, and comparing the determined value with at least one threshold. The method also includes displaying in the cockpit of the aircraft, at least one indication related to the operation of the turbine engine, according to this comparison. As a result, conditions that could result in mechanical degradation or failure of the turbine engine are identified for a crew of the aircraft.

Abstract: An operations support system is provided for an engine receiving fuel. 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 and the engine data. The engine-specific model unit includes a fuel flow calculation module configured to determine a current fuel flow for the engine and a set point module configured to generate set point information for the engine using a thermodynamic model that reduces the current fuel flow to the engine, the thermodynamic model being based on component maps associated with the engine. The system further includes a data storage unit coupled to the engine-specific model unit and configured to store the set point information.

Abstract: 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.

Abstract: 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.

Abstract: The vehicle power generation system includes: a power generation unit, a power supply unit, a clutch mechanism, and a control unit. The power generation unit includes generator, power input shaft, and a power output unit. The clutch mechanism includes a speed increasing unit and a motor controller for attaching the speed increasing unit to the crankshaft or detaching the speed increasing unit from the crankshaft. The control unit is electrically connected to the motor controller, and includes a power generation condition determining unit.

Abstract: A system and method are provided for estimating the operating speed of a turbocharger. A first pressure value corresponds to pressure at or near the air inlet of the compressor, and a second pressure value corresponds to pressure at or near the air outlet of the compressor. A temperature value corresponds to a temperature at or near the air inlet of the compressor, and a flow rate value corresponds to a flow rate of air entering the air inlet of the compressor. The operating speed of the turbocharger is estimated as a function of the first pressure value, the second pressure value, the temperature value and the flow rate value.

Abstract: A method of providing a volume-mass law for determination of a fuel flow rate of an engine, particularly providing a fuel flow rate to a helicopter turbine, comprising the steps of: determining a sample type of fuel and a start density ?o of said sample type of fuel in said fuel tank using an equation ?0=aT+b0, with a and b0 being known for said sample type of fuel and calculating real time offset parameters bn from an algorithm to determine real time densities ? of the fuel.

Abstract: 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.

Abstract: A method of managing a gas turbine engine operating line includes detecting an air speed and a fan speed. A data table is referenced that includes a desired variable area fan nozzle position based upon air speed and fan speed. The detected air speed and detected fan speed are compared to the data table to determine a target variable area fan nozzle position. An actual variable area fan nozzle position is adjusted to the target variable area fan nozzle position.

Abstract: A method for controlling the combustion in a gas turbine including measuring, with one or more probes situated adjacent to the combustion chamber of the turbine, the amplitude of the pressure oscillations inside the combustion chamber and the persistence time or cycle of the same oscillations, evaluating the behavior under fatigue conditions of the combustion chamber, by constructing the Wohler curve for a certain material which forms the combustion chamber for a predefined combustion frequency and for the amplitude and cycle values of the pressure oscillations measured, measuring the cumulative damage to the combustion chamber during functioning under fatigue conditions of the turbine using the Palmgren-Miner hypothesis and exerting protection actions of the turbine if the cumulative damage value measured is exceeded.

Abstract: 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.

Abstract: 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.