Abstract: A method for positioning a rotor of a gas turbine automatically is provided that includes gathering data with a control unit, and processing this data to bring the rotor to a desired position which is set according a Human Machine Interface (HMI). The indication of the lay of the rotor to the control unit is done by a key phasor, which includes a sensor which gets a digital pulse for each revolution of a phasor cam wheel. This digital pulse is used to give the information of the lay of the rotor to the control unit.

Abstract: A method of testing a gas turbine is provided. The gas turbine includes a first compressor and an expansion turbine coupled by a drive shaft. The method includes operating the gas turbine and a second compressor at a first steady load and a first steady drive shaft speed. The second compressor is rigidly coupled to the drive shaft. The method also includes changing a load of the second compressor by a known amount, and measuring a time required for the gas turbine to stabilize at a second steady load and a second steady drive shaft speed in response to the changed load of the second compressor.

Abstract: A method of generating a comprehensive image (87) of interior surfaces (78, 80) of machine components such as a gas turbine combustor basket (59) and transition duct (34) by digitally stitching together multiple photographs (82) thereof, and analyzing the comprehensive image by contouring (91, 95A-B) of colors and shadings thereon, and quantifying and tracking aspects of the contours (A, B, C) over time for indications of degradation (89) of the interior surfaces. A scope (58) may be inserted into a port (56) in the combustor with a camera (72, 74) in a rotatable end (70) of the scope for obtaining a circumferential set (84) of photos at each axial position along a length of the combustor and transition duct. A 3D surface scanning device (76) in the scope may define the geometry of the interior surface for 3D photographic modeling thereof providing a virtual walk-through inspection.

Abstract: A method of resolving a balanced condition that generates control parameters for start-up and steady state operating points and various component and cycle performances for a closed split flow recompression cycle system. The method provides for improved control of a Brayton cycle thermal to electrical power conversion system. The method may also be used for system design, operational simulation and/or parameter prediction.

Abstract: 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.

Abstract: A device for measuring vibration amplitudes of the blade tips in a turbomachine is provided. The device includes a support mounted in an orifice of a casing of a turbomachine, in which are housed two optical guides for the emission and reception of a light signal exiting inside the casing across from the tips of the blades of a turbine wheel Each optical guide includes an optical fiber connected by a mechanical connector to a needle of which the core is made of a material able to transmit a light signal and which is resistant to temperatures less than or equal to 1100° C. and which exits at its distal end in the casing across from the blade tips.

Abstract: The state of a flame in a gas turbine combustor is acoustically monitored using a single dynamic pressure sensor within the combustor. A dynamic pressure sensor output signal is received from the single sensor and is processed to determine a flame status. The signal is processed by performing an autocorrelation operation to identify time-separated portions of the signal and to determine that the time-separated portions of the signal include portions indicative of acoustic oscillations emitted by the flame in the gas turbine engine combustor and received directly by the single acoustic sensor, and portions indicative of reflections.

Abstract: A method of imaging a test subject includes providing one or more moveable sensors to sense an attribute of the test subject (e.g., acoustic pressure), wherein the attribute has a tonal noise component and a broadband noise component. A rotational sensor is provided to sense a rotational velocity of a rotational element of the test subject. Each of the moveable sensors are moved along a path while continuously acquiring test data that is indicative of the rotational velocity of the rotational element, the sensed attribute, the position, and the orientation of each of the moveable sensors. A set of transfer functions corresponding to points in space that have been visited by the moveable sensors are constructed, each of the transfer functions relating the test data of the moveable sensors to the test data of the rotational sensor. A visual representation of the tonal noise component of the attribute in a region adjacent the test subject is produced using the set of transfer functions.

Abstract: A temperature sensor circuit is disclosed. In one embodiment, the temperature sensor comprises an input circuit with a current mirror for forcing a current down a reference stage and an output stage. The reference stage and the output stage include P-N junctions (e.g., using bipolar transistors) with differing junction potentials. By tailoring the resistances in the reference and output stages, the input circuit produces two output voltages, one of which varies predictably with temperature, and one which is stable with temperature. The input circuit is preferably used in conjunction with an amplifier stage which preferably receives both the temperature-sensitive and non-temperature sensitive outputs. Through various resistor configurations in the amplifier stage, the output of the temperature sensor can be made to vary at a higher sensitivity than produced by the temperature-sensitive output of the input circuit.

Abstract: An image forming apparatus that forms a toner image on a recording medium includes a fixing unit configured to fix the unfixed toner image on the recording medium while conveying the recording medium bearing the unfixed toner image at a nip portion. The fixing unit includes a fixing rotating member and a pressure member forming the nip portion with the fixing rotating member. The apparatus also includes: a counting portion configured to count the cumulative rotation time of the fixing rotating member and the cumulative number of startups of the fixing unit; and a notifying portion configured to performing notification of information about at least one of the lifetime expiration of the fixing unit and the necessity of replacing the fixing unit. The notifying portion performs the notification in accordance with the cumulative rotation time and the cumulative number of startups of the fixing unit.

Abstract: Methods for verifying satisfaction of prognostic algorithm requirements for a component of a certain device of interest are provided. A method according to an example of an embodiment of the invention can include providing a prognostic algorithm requirements statement for a preselected component contained in each of a plurality of a certain type device, receiving field data indicating a number of premature component failures and a total number of replacements including both due to premature failures and scheduled maintenance, determining a probability density function providing a probability of failing to replace the prematurely failed components, determining a confidence value indicating a level of confidence that failure avoidance requirements provided in the prognostic algorithm statement are being met, and verifying whether or not the prognostic algorithm requirements provided in the prognostic algorithm requirements statement are being satisfied according to a preselected minimum level of confidence.

Abstract: A method for detecting rotating stall in a compressor is disclosed herein. The method comprises measuring radial vibration of the rotor relative to the stator and generating a vibration measurement signal, calculating a frequency spectrum of the vibration measurement signal, identifying a plurality of frequency bandwidths of the frequency spectrum, neglecting one first frequency bandwidth of the plurality of frequency bandwidths if the rotation frequency of the rotor falls within the first frequency bandwidth, neglecting at least one second frequency bandwidth of the plurality of frequency bandwidths if the rotation frequency of the rotor falls below the second frequency bandwidth, determining the maximum magnitude of the spectrum in each of the non-neglected frequency bandwidths, and comparing each determined maximum magnitude and a predetermined value.

Abstract: A computing device for use in performing a redundancy test on a turbine assembly and a turbine control system including a plurality of controllers each configured to independently control operation of the turbine assembly is provided. The computing device configured to be coupled to the turbine control system and configured to determine whether a plurality of test conditions are satisfied, display to a user an indication of which test conditions are satisfied, and test, in response to a user input, the plurality of controllers.

Abstract: The system is configured for automation of rotorcraft entry into autorotation. The system can provide a means to assist the flight crew of a rotorcraft in maintaining rotor speed following loss of engine power. The system can automatically adjust control positions, actuator positions or both to prevent excessive loss of rotor speed upon initial loss of engine power before the flight crew is able to react. The system uses model matching to provide axis decoupling and yaw anticipation; it includes pitch control initially to assist in preventing rotor deceleration; and it makes use of collective, pitch, roll and yaw trim functions to provide tactile cueing to the pilot to assist when the pilot is in the loop. The system can reduce workload by assisting the crew with controlling rotor speed and forward speed during stabilized autorotation.

Abstract: Internal components of gas and steam turbines are inspected with an optical camera inspection system that is capable of automatically and/or manually positioning the camera field of view (FOV) to an area of interest within the turbine along a pre-designated navigation path and capturing images with or without human intervention. Camera positioning and image capture can be initiated automatically or after receipt of operator permission. The inspection system includes an articulated multi-axis inspection scope with an optical camera that is inserted through a combustor nozzle access port, combustor and transition, so that the camera FOV captures the leading edge of Row 1 rotating turbine blades while the rotor is spinning at up to 1000 RPM. An illumination system strobe light and the camera image capture are synchronized with the blade rotation speed so that images of multiple or all blades may be obtained from a single inspection scope insertion point.

Abstract: A thermal erosion tester, comprising a rotating heated element, which is adapted to contact a sand specimen placed in the thermal erosion tester, a heating element to heat the rotating heated element, and a motor to drive rotation of the rotating heated element, wherein the rotating heated element is adapted to contact the sand specimen while the rotating heated element is rotating, causing erosion of the sand specimen, and a method of testing thermal erosion, and a method of testing erosion of a sand specimen when it is in contact with a heated element.

Abstract: A vacuum system diagnostic is disclosed. In one example, vacuum system leaks are diagnosed via a pressure reading of a vacuum reservoir. The approach may reduce the number of sensors used to diagnose vacuum system degradation.

Abstract: A thermal distortion tester for testing thermal distortion of a sand specimen, comprising a gimbal to support the sand specimen, an actuator to raise and lower the sand specimen, and a hot surface, wherein the sand specimen is brought into contact with the hot surface at a pre-determined pressure or pressure profile. The temperature of the hot surface is maintained at a pre-determined temperature or temperature profile. The distortion of the sand specimen while applied to the hot surface is directly measured through measurement of the longitudinal movement of the gimbal, and radial distortion is measured by a micrometer camera. The temperature gradient of the sand specimen is also measured throughout the duration of the test. A method of using the same is also described herein.

Abstract: A method for monitoring a control device of a fuel metering valve of an aircraft turbojet engine, the control device supplying a control current to a servo valve in order to modify the position of the fuel metering valve. The method includes determining the position of the fuel metering valve during a flight of the aircraft, determining the travelling speed of the fuel metering valve, and determining the control current when the travelling speed of the fuel metering valve is zero. A mean control current is calculated when the travelling speed of the fuel metering valve is zero, the mean control current forming an indicator of deterioration of the control device. The deterioration indicator is compared with a reference base of indicators with deterioration so as to infer the type of deterioration from it, and an abnormality score is calculated for the deterioration indicator.

Abstract: In a gas turbine engine that includes a compressor and a combustor, wherein the combustor includes a primary fuel injector within a fuel nozzle and a secondary fuel injector that is upstream of the fuel nozzle and configured to inject fuel into a flow annulus of the combustor, a method for detecting a flame holding condition about a fuel injector. The method may include the steps of: detecting an upstream pressure upstream of the secondary fuel injector; detecting a downstream pressure downstream of the secondary fuel injector; determining a measured pressure difference between the upstream pressure and the downstream pressure; and comparing the measured pressure difference to an expected pressure difference.

Abstract: A system and method of measuring a residence time in a gas-turbine engine is provided, whereby the method includes placing pressure sensors at a combustor entrance and at a turbine exit of the gas-turbine engine and measuring a combustor pressure at the combustor entrance and a turbine exit pressure at the turbine exit. The method further includes computing cross-spectrum functions between a combustor pressure sensor signal from the measured combustor pressure and a turbine exit pressure sensor signal from the measured turbine exit pressure, applying a linear curve fit to the cross-spectrum functions, and computing a post-combustion residence time from the linear curve fit.

Abstract: A multi-hole probe has a kernel that includes a forward surface that includes at least a first, second, and third pressure sensing ports. The multi-hole probe kernel further includes an upper surface, generally orthogonal to the forward surface, and including at least a first, second, and third stem ports. Still further, the multi-hole probe kernel includes first, second, and third tubes running between and providing a fluid connection with the first, second, and third pressure sensing ports and the first, second, and third stem ports, respectively.

Abstract: A method for monitoring a system for actuating variable geometries of a turbojet engine, the actuation system including a control device, a servovalve, and an actuator controlled by the servovalve, the control device configured to determine a control current according to a set position value and to a measured position of the actuator and to provide the control current to the servovalve. The monitoring method includes: detecting a stabilized condition; determining an average value of the control current during the detecting the stabilized condition; and comparing the average value with a predetermined threshold.

Abstract: The principal object of the invention is a method for managing the operation of a metering unit of a turbomachine fuel injection system, characterized in that a channel of the metering unit is selected according to the reliability of the injection system's flowmeter, determined by reliability conditions of the flowmeter providing information as to whether or not there is confidence in the flowmeter.

Abstract: A system for locating at least one surface feature, such as a cooling aperture, on a turbine component is provided. The system includes at least one feature marker configured for placement adjacent to the at least one surface feature. The system also includes at least one sensor configured for non-visual detection of the at least one feature marker. The system also includes a control device coupled to the at least one sensor for receiving signals from the at least one sensor, wherein the signals represent data indicative of one of a presence of the at least one feature marker and an absence of the at least one feature marker.

Abstract: A system includes a first unitary measurement strip configured to be secured about a rotational component at a first axial location. The first unitary measurement strip includes a first set of one or more windows, each window of the first set of one or more windows is configured to correspond to a first respective tangential location of the rotational component at the first axial location, and each window of the first set of one or more windows is configured to be detectable via a first sensor.

Abstract: A method for detecting a state of change of an installation includes rotating at least one first component around a rotatable connection using a drive such that at least part of the at least one first component carries out an oscillation. The at least one first component is mechanically connected to a second component via the rotatable connection. The method further includes recording the oscillation using a third component. The method includes investigating the recorded oscillation for changes based on a reference value. The method further includes detecting the state of change of the installation in reference to the changes to based on the reference value.

Abstract: Disclosed are methods and systems to determine a reliability forecast for a wind turbine. In an embodiment, a method may comprise obtaining an environmental factor of a wind turbine based on geospatial data of a first area and location data of a second area, obtaining an operating factor of the wind turbine, and determining a reliability forecast based on the environmental factor and the operating factor.

Abstract: A method of predicting an auxiliary power unit fault in an aircraft having an auxiliary power unit and multiple sensors related to the auxiliary power unit, components thereof, and systems related thereto, including receiving a sensor signal from at least one of the multiple sensors to define a sensor output, comparing the sensor output to a reference value and predicting a fault in the auxiliary power unit based on the comparison.

Abstract: Embodiments of the present disclosure are directed towards a turbine combustor probe having a combustion dynamics monitoring probe configured to monitor combustion dynamics within a turbine combustor. The turbine combustor probe also has a gas sampling sleeve configured to collect a gas sample from an airflow path between a liner and a flow sleeve of the turbine combustor.

Abstract: Turbine blade tip clearance is measured in a fully assembled turbine casing by mounting a contact or non-contact displacement probe on a turbine blade that generates data indicative of probe distance from the turbine casing that circumferentially surrounds the blade. Variations in probe distance data are recorded as the blade circumferentially sweeps the turbine casing when the turbine is operated in turning gear mode. Blade rotational position data are collected by a rotational position sensor. A data processing system correlates the distance and rotational position data with localized blade tip gap at angular positions about the turbine casing circumference. An optical camera inspection system may be coupled to a turbine blade to obtain visual inspection information within the turbine casing. This method and apparatus provide an accurate and cost effective solution for accessing turbine casing deformation impact on blade tip clearance and rotor/casing alignment.

Abstract: Turbine blade tip clearance is measured in a fully assembled turbine casing by mounting a non-contact displacement probe or sensor on a turbine blade that generates data indicative of sensor distance from the turbine casing that circumferentially surrounds the blade. The sensor is mounted on the blade with a sensor fixture, which includes a clamping mechanism and a sensor retention mechanism that retains and calibrates the sensor by selective movement of the sensor relative to the retention mechanism. Variations in sensor distance data are recorded when the turbine is operated in turning gear mode. Blade rotational position data are collected by a rotational position sensor. A data processing system correlates the distance and rotational position data with localized blade tip gap at angular positions about the turbine casing circumference. This method and apparatus facilitate assessment of turbine casing deformation impact on blade tip clearance and rotor/casing alignment.

Abstract: Various embodiments of the invention include methods for monitoring a gas turbine component. In some cases, a method includes: analyzing a gas turbomachine component to detect at least one of a void or a porosity of the gas turbomachine component while maintaining a structural integrity of the gas turbomachine component during the analyzing; and providing instructions to perform a hot isostatic pressing (HIP) process on the gas turbomachine component in response to at least one of detecting the void or detecting that the porosity exceeds a threshold.

Abstract: Measurement devices and methods for evaluating clearances between adjacent components in turbomachines are provided. A measurement device may include a tool and a controller. The tool and controller may determine the clearance by measuring the distance between the adjacent components. The controller may compare the clearance to a predetermined engineering clearance limit and/or a previously measured clearance. A method may include measuring the clearance with a device which includes a controller. The method may further include comparing the clearance in the controller to a predetermined engineering clearance limit and/or a previously measured clearance.

Abstract: Systems and methods for operating a gas turbine combustion system by generating a flame detection signal are provided. A set of modeled parameters expected when there is a flame in a secondary combustion zone is calculated. A set of measured gas turbine parameters is measured. A flame validation signal based on the set of measured parameters and the set of modeled parameters is generated. The systems include a subsystem that calculates a set of modeled parameters expected when there is a flame in the secondary combustion zone and a subsystem that measures a set of measured parameters. A subsystem generates a flame validation signal based on the set of measured parameters and the set of modeled parameters.

Abstract: A method for positioning sensors about a sensor ring includes the steps of assigning each sensor in a plurality of sensors a sensor number selected from a set of sensor numbers, where the set of sensor numbers is a whole number in the range of 0 to N, and where N is the total number of sensors in said plurality of sensors minus one, disposing a first sensor at a circumferential angular position zero on the sensor ring, and disposing each sensor in the plurality of sensors at a circumferential angular position about the sensor ring, wherein the circumferential angular position is defined by an offset from a circumferential angular position zero and the offset is equal to a base arc length between sensors multiplied by the sensor number of the sensor plus a base offset arc length multiplied by the sensor number of the sensor.

Abstract: The state of a flame in a subject combustor of a gas turbine engine is acoustically monitored using a dynamic pressure sensor within the subject combustor and one or more additional sensors in nearby combustors. Dynamic pressure sensor output signals from the sensors are cross correlated to identify acoustic oscillations generated by a flame in the subject combustor and received by the sensors. The cross correlation may be constrained by a maximum time delay between correlated components of the signals, based on physical characteristics.

Abstract: The present invention relates to a method and device for monitoring APU turbine vane fracture and rotor shaft jam. The method for monitoring APU turbine vane fracture and rotor shaft jam comprises: acquiring APU messages at multiple time points within a period; obtaining the operation parameters of the APU according to the APU messages, the operation parameters including at least the start time STA; calculating the average value AVG and the deviation index ? of the start time STA within the period; and determining the circumstance of the turbine vane fracture and rotation shaft jam of APU is in stable phase, decline phase or malfunction phase according to the deviation index ?.

Abstract: A device for measuring a part in a turbine engine, including a rod including a portion with a profile that corresponds to a profile of a portion of a calibration part of a same type as a part under examination, the portion of the rod further including visible marks for remote measurement arranged along its length.

Abstract: The invention relates to a data acquisition system configured for acquiring operational data from one or more wind turbine components of a wind turbine, the data acquisition system comprising: a setup arrangement configured for establishing one or more data acquisition tasks, a user interface configured for allowing a user to access said setup arrangement, a wind turbine interface configured so that the setup arrangement can communicate with the wind turbine, wherein said user interface is configured for enabling the user to establish the one or more data acquisition tasks wherein the setup arrangement is configured for communicating one or more of the one or more data acquisition tasks to the wind turbine, and wherein said data set to be acquired is configured for being acquired from said data storage arrangement.

Abstract: A method for monitoring a state of a drive train of a wind power plant. The drive train including at least one component which is mechanically connected to a rotating element of the drive train and at least one acceleration sensor connected to the rotating element and located at a distance from a rotational axis of the drive train. The at least one acceleration sensor is configured to rotate about the rotational axis of the drive train at the distance. A signal of the at least one acceleration sensor is sensed in terms of its timing at least one rotational speed of the rotating element and is examined for interference frequencies which correspond to damage in the drive train.

Abstract: The invention relates to a method for the self-calibration of electric jacks (6a, 6b) capable of actuating a mobile member (2) of a turbojet nacelle (1) and connected to at least one position measuring member, characterized in that it comprises the steps of: moving the jack(s) into a retracted position corresponding to a first position of the mobile member, storing one or more position values fed back by the position measuring member for the jack(s) in said retracted position; moving the jack(s) into an extended position corresponding to a second position of the mobile member; storing one or mom position values fed back by the position measuring member for the jack(s) in said extended position.

Abstract: The invention relates to a method for controlling a plurality of actuators (9a, 9b, 9c) for a movable thrust reverser cowl (1), characterized remarkable in that the position deviation between adjacent actuators is measured in real time, and in that the speed profile of the actuator or actuators in question is adjusted by a position deviation exceeding a predetermined threshold.

Abstract: Embodiments of the invention relate generally to turbomachines and, more particularly, to the positioning of airfoils to reduce pressure variations entering a diffuser. One embodiment includes a turbomachine comprising a diffuser, a plurality of airfoil rows, including a first airfoil row adjacent the diffuser, the first airfoil row being of a first type selected from a group consisting of stationary vanes and rotating blades, a second airfoil row adjacent the first airfoil row, the second airfoil row being of a second type different from the first type, and a third airfoil row of the first type adjacent the second airfoil row, wherein at least one of the plurality of airfoil rows is clocked, relative to another airfoil row of the turbomachine, reducing variations in airflow circumferential pressure at at least one spanwise location in the diffuser adjacent the first airfoil row in an operative state of the turbomachine.

Abstract: A device for detecting anomalies in an aircraft turbine engine by acoustic analysis, the device not an onboard device and including: a mobile module including a directional system for acquiring acoustic signals from the turbine engine; a processor for processing the signals, which is suitable for generating a damage report; a transmitter for transmitting the damage report; a server capable of exchanging data with the mobile module, the server including a receiver for receiving the damage report; and a storage device suitable for storing the damage report.

Abstract: Methods and apparatus for inspecting cooling holes in a wall of a combustor of a gas turbine engine are disclosed. An exemplary method disclosed may comprise: heating the wall of the combustor; directing a flow of cooling fluid through the one or more cooling holes in the wall of the combustor while the wall is being heated; acquiring a first measurement indicative of a flow rate of the cooling fluid through the one or more cooling holes; and acquiring a second measurement indicative of a cooling effectiveness provided by the cooling fluid flowing through the one or more cooling holes at the flow rate.

Abstract: A shaft break detection system and a method of detecting shaft break for a gas turbine engine. A first indication is calculated from measured rotational speed of a shaft. A second indication is calculated from the rotational speed. A shaft break signal is generated if both indications are true.

Abstract: An apparatus is provided for measuring a depth of a groove defined between adjacent steeples of a rotor of a turbine. The groove is adapted to receive a root of a blade. The apparatus may comprise: a measuring tool comprising: a fixture; and first and second depth measuring devices associated with the fixture for measuring the depth of the groove at two spaced apart locations.

Abstract: The state of a flame in a gas turbine engine combustor is acoustically monitored using a dynamic pressure sensor within the combustor. A spectral pattern of a dynamic pressure sensor output signal from the sensor is compared with a characteristic frequency pattern that includes information about an acoustic pattern of the flame and information about acoustic signal canceling due to reflections within the combustor. The spectral pattern may also be compared with a characteristic frequency pattern including information about a flame-out condition in the combustor.

Abstract: A method for monitoring and diagnosing anomalies in auxiliary systems of a gas turbine implemented using a computer device coupled to a user interface and a memory device, the method including storing a plurality rule sets in the memory device, the rule sets relative to the auxiliary systems of the gas turbine, the rule sets including at least one rule expressed as a relational expression of a real-time data output relative to a real-time data input, the relational expression being specific to parameters associated with the auxiliary systems of the gas turbine, receiving real-time and historical data inputs from a condition monitoring system associated with the gas turbine, the data inputs relating to process parameters associated with the auxiliary systems of the gas turbine, and estimating values for at least some of the parameters associated with the auxiliary systems of the gas turbine using the received inputs.