Abstract: Various embodiments of the invention include a system having: at least one computing device connected with an array of ultrasonic probes on a gas turbomachine component, the at least one computing device configured to: instruct a first probe in the array of ultrasonic probes to transmit an ultrasonic beam to at least one additional probe in the array of ultrasonic probes; and determine a property of a medium between the first probe and the at least one additional probe based upon a time between transmission of the ultrasonic beam from the first probe and reception of the ultrasonic beam at the at least one additional probe.

Abstract: Systems and devices configured to determine misalignment of targets of a rotating shaft by monitoring axial and radial aspects of targets and the shaft. In one embodiment, a target monitoring system includes a first horizontal probe communicatively connected to at least one first horizontal target connected to the shaft, and a first axial probe located adjacent to the first horizontal probe and communicatively connected to the first horizontal target. The system also includes a second horizontal probe communicatively connected to at least one second horizontal target connected to the shaft, and a second axial probe located adjacent to the second horizontal probe and communicatively connected to the second horizontal target. The system may further include an end probe disposed proximate a first end of the shaft for monitoring axial movement of the shaft, and a computing device communicatively connected to the end probe and each horizontal and axial probe.

Abstract: In a testing overspeed protection system: a) on receiving an order to start a turbomachine, an electronic regulation system (ERS) of the turbomachine sends an order to a control circuit of a fuel cutoff member to close the fuel cutoff member or to keep it in the closed position; b) the closed state of the FCM is verified on the basis of information transmitted to the ERS and representative of the position of the FCM; c) if the result of the verification in b) is positive, the ERS sends an order to the FCM control circuit to authorize opening of the FCM and enable the starting procedure to continue; and d) if the result of the verification in b) is negative, the ERS issues fault information concerning the overspeed protection system.

Abstract: A method for checking cooling holes of a gas turbine blade, including in sequence: step 1: injecting a liquid plastic material into a cooling hole of a gas turbine blade; step 2: stopping the flow of the liquid plastic material, and curing the liquid plastic material to form a model; step 3: separating the model from the gas turbine blade; step 4: scanning the model. By scanning the model, the cooling holes of the gas turbine blade can be checked, so as to obtain more data about the position, dimensions and shape thereof, while improving the accuracy and efficiency of measurement.

Abstract: A system for optically monitoring a gas turbine engine includes an optical multiplexer configured to receive multiple images from respective viewports into the gas turbine engine. The optical multiplexer includes a movable reflective device configured to selectively direct at least a portion of each image toward a detector array, and the detector array is directed toward a fixed location on the optical multiplexer.

Abstract: A probe assembly for a gas turbine engine is disclosed. The probe assembly may include a probe, and a fastener to retain the probe within a case of the gas turbine engine, the fastener including a sealing arrangement with a heat shield of the gas turbine engine.

Abstract: The invention concerns an asset monitoring system (10) having a monitoring unit 8 and a plurality of sensors (4) onboard the asset. The sensors (4) are arranged to measure a plurality of operational variables for the asset in use and the monitoring unit (8) is arranged to receive operational variable measurements output from the sensors. The monitoring unit is also arranged to determine a current value of a sensor characteristic (ZA1; ZB1) for each sensor and to compare the current sensor characteristic value with a predetermined sensor characteristic value in order to determine automatically whether a change of one or more sensors has occurred between instances of operation.

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: When it is determined that a blade is rotating, a control device operates a braking device, and acquires a rotation angle (first rotation angle) from a rotation angle sensor. Then, the control device reverses a nacelle and acquires again a rotation angle (second rotation angle) from the rotation angle sensor. Then, the control device determines whether or not the difference between the first rotation angle and the second rotation angle is greater than a threshold value. When it is determined that the rotation angle difference is greater than the threshold value, the control device determines that a gear or a bearing of a gearbox is worn out.

Abstract: An apparatus and method for a more time efficient measurement of backlash in one or more variable guide vanes of a gas turbine system are provided. A mounting structure, with an indicator attached thereto, may be provided. Further, a guide structure may be provided to allow the mounting structure to be moved adjacent to two or more variable guide vanes without moving the guide structure.

Abstract: A vehicle is provided that has a rigid dressing raft 200. The rigid dressing raft 200 provides a part of a fluid and/or electrical system to the vehicle. The rigid dressing raft comprises elongate fibres 232, which may provide strength to the raft. The fibres 232 are electrically conductive, and a voltage source may be applied to at least one of the fibres. The fibre 232 may form a part of an electrical measurement circuit 400, such as a wheatstone bridge, which may be used to determine the electrical resistance of the fibre 232. The electrical resistance of the fibre 232 may then be used to determine the temperature to and/or stress/strain of the raft 200.

Abstract: A method for determining total damage to at least one rotating component of a drive train in a system, in particular a wind or wave energy system, includes determining over time during operation of the system a variable characterizing a rotational speed of the component and a variable characterizing a torque transmitted by the component. A load collective is determined in a calculator unit from the temporal progression of the variables, and the total damage is determined from a comparison of the determined load collective and a reference load collective.

Abstract: A device and method for monitoring a high-pressure pump in a turbomachine fuel supply circuit by detecting opening of a pressurizing and shut-off valve mounted on an outlet side of a fuel flow regulating valve, by measuring rotational speed of the turbomachine corresponding to the opening of the pressurizing and cut-off valve, and by monitoring change in a value of the rotational speed to propose replacement of the high-pressure pump when the measure value rotational speed reaches a predetermined threshold.

Abstract: A working fluid sensor system adapted to analyze operation of a power generation system is disclosed. In one embodiment, a working fluid sensor system includes: a set of sensors adapted to be disposed within a turbine, the set of sensors including probe portions which extend into a flowpath of the turbine for exposure to a working fluid, the probe portions adapted to react to a force exerted by the working fluid on the probe portions and indicate a moisture content of the working fluid.

Abstract: Monitoring of transient operation of a turbine includes identifying a start condition and a stop condition for the transient operation and defining a path from the start condition to the stop condition wherein the path comprises a plurality of sequentially arranged sub-segments. Also, a respective value is obtained of each of a plurality of operating parameters for each respective sub-segment of the path and, then, for each of the respective sub-segments, a determination is made if the respective value of each of the plurality of operating parameters matches a respective predetermined allowable value for that particular operating parameter.

Abstract: A station probe employed in a gas turbine engine includes a rake portion having a plurality of sensors for sensing conditions in the gas turbine engine. An environmental container attached to the rake portion includes signal conditioning circuitry that locally analyzes sensor signals received from the plurality of sensors to generate measured values, and a communication module for communicating the measured values to a control room.

Abstract: A sensor housing is provided. The sensor housing includes an elongated body having an open end and a closed end. An opening is disposed axially within the elongated body through the open end and is configured to receive a sensor secured therein. A support section is connected to the closed end of the elongated body and coupled to a receiving port disposed on the gas turbine engine system. The elongated body has an axial dimension determined according to a vibration characteristic of the gas turbine engine system during operation.

Abstract: An apparatus and method for a more time efficient measurement of backlash in one or more variable guide vanes of a gas turbine system are provided. A mounting structure, with an indicator attached thereto, may be provided. Further, a guide structure may be provided to allow the mounting structure to be moved adjacent to two or more variable guide vanes without moving the guide structure.

Abstract: A device and method for monitoring a gas turbine is disclosed. The device includes a receiver for receiving condition values of the gas turbine and an analytical device. The analytical device is designed to determine condition information from the condition values of the gas turbine using Bayes' Prediction.

Abstract: One embodiment of the invention relates to a method for controlling a wind turbine, having the steps of detecting an internal fault signal which is generated in the first wind turbine and which indicates a disruption of the first wind turbine; receiving at least one external fault signal which is generated outside of the first wind turbine and which indicates a disruption of another wind turbine; and evaluating the internal fault signal dependent on the at least one external fault signal.

Abstract: A functional access port in a machine casing, a machine having a functional access port, and a method of monitoring a machine via a functional access port are disclosed herein. In an embodiment, an access port is provided in the external casing of an industrial machine. The access port comprises a passageway through the external casing of the machine, providing access to an interior of the machine. The access port further includes a removable passageway cover for removably occluding the passageway. A location, a size, a shape, and an orientation of the passageway relative to the external casing are strategically selected in accordance with engineering and design requirements to provide access through the passageway to a desired location on the interior of the machine while the external casing is in place, with minimal to no disassembly of the casing.

Abstract: Method for spectral evaluation of oscillation signals which have been obtained on a rotor blade of a wind power installation with an accelerations sensor. In doing so, instead of the otherwise conventional Fourier transform calculation, the spectral power density is computed. In the evaluation, also signal portions are considered which are not detected in the Fourier transform because they do not go back to oscillations which have been excited in the rotor blade.

Abstract: An engine simulator for wind tunnel models exhibits a turbine with an inlet for a pressurized fluid and an outlet for a relieved fluid, a flow-type body arranged downstream from the turbine, a jacket that at least partially envelops the flow-type body with the formation of a gap, and at least two electrodes. A downstream end of the flow-type body is provided with a heater coating comprised of a matrix material that contains a conductivity additive and is connected with the electrodes for applying an electrical voltage. This may make it possible to prevent ice formation on the trailing edge of the flow-type body.

Abstract: A sealing head for an installation configured to perform fluid tests on an aircraft turbine engine part. The sealing head includes a sealing element crossed by a passage for flowing of a gas flow, the sealing element including a sealing surface configured to come into contact with a part to be tested, at an aperture of the part to be tested configured to be fed with the gas flow. The sealing head includes a mechanism centering the sealing element relatively to the aperture of the part, the centering mechanism being firmly attached to the sealing element and protruding towards the front of the surface having an outer portion surrounding the centering mechanism.

Abstract: An impact load monitoring system for a wind turbine for wind power generation is provided with: an acceleration sensor 28 attached to a step-up gear 18 connected to a main shaft 20; a frequency filter 30 for extracting a monitoring-object component contained in a target frequency domain from vibration data representing a temporal change of amplitude of the acceleration obtained by the acceleration sensor 28; and a determination unit 32 for determining whether or not amplitude of acceleration of the monitoring-object component exceeds a reference value which is set in advance, by comparing the amplitude of the acceleration with the reference value.

Abstract: A method and system for measuring a mass flow rate in a portion of a flow path in an inlet duct of a gas turbine engine is provided. The system includes a sensor assembly attached to the inlet duct. The sensor assembly includes a tube with a longitudinal axis disposed in a substantially laminar flow region of the inlet duct, and a flow conditioner disposed in the tube. A hot wire sensor disposed in the tube is also provided.

Abstract: A method of observing an airflow passage within a gas turbine engine includes locating a support in view of an airflow passage and housing an optical fiber within the support.

Abstract: Embodiments of the disclosure relate to systems and methods for holding target turbomachine compressor pressure ratio constant while varying the shaft speed. In order to characterize a load compressor and validate the compressor design, the speed of the load compressor can be changed while controlling the compressor operating line and holding the inlet guide vanes at a constant angle. Discharge control valves can be dynamically adjusted to maintain the pressure ratio equal to the operating line over a range of speeds.

Abstract: A pressure-measuring device and a pressure-measuring method for measuring a pressure in a combustion chamber of a turbomachine are provided. The pressure-measuring device includes at least one sensor device for measuring an ion current at at least one point inside the combustion chamber.

Abstract: An Ignitor Plug Isolation Chamber (IPIC) includes a first end cap mountable to a cylinder, the first end cap includes an igniter aperture to receive an ignitor plug. A second end cap mountable to the cylinder, the second end cap includes a ground aperture. The ground connection mounted to the ground aperture.

Abstract: Embodiments of the present invention have the technical effect of automatically testing an overspeed protection system of a powerplant machine comprising at least one shaft. An embodiment of the present invention may automatically test the overspeed protection system while the powerplant machine is decelerating from full-speed-no-load (FSNL). Another embodiment of the present invention may automatically test the overspeed protection system of the powerplant machine while the powerplant machine is accelerating to FSNL.

Abstract: A multi-stage gear box (122) of a wind power plant, wherein the gear box (122) includes a gear box housing (125). The gear box (122) includes at least one access opening for the insertion of a work instrument into the gear box housing (125) or respectively into the interior of the gear box housing (125) is provided on the outside of the gear box housing (125) and in that at least one guiding device (201, 202, 203, 204, 205) is provided for the work instrument inside the gear box housing (125) so that the work instrument is moveable and/or positionable within the guiding device (201, 202, 203, 204, 205). Parts of the gear box (122) in the gear box housing (125) are checked and/or worked by a work instrument inserted or arranged or arrangeable in the guiding device (201, 202, 203, 204, 205).

Abstract: A gage tool (700) for inspecting tolerances of a gas turbine engine seal plate (430) includes a base plate (710) arid a top plate (720). The base plate (710) includes abase opening (712) and a slot (711) with an annular shape sized to receive a seal plate (430). The top plate (720) Includes a top opening (723). The base opening (712) and top opening (723) each provide access to a portion of a seal plate (430) within the gage tool (700). The gage tool (700) also includes a first gage (750) with a probe tip for measuring a variation in an outer interlacing surface (433) of a seal plate (430) and a seal slide gage (740) for measuring a force required to rotate Ore seal plate (430) within the gage tool.

Abstract: A state detection device according to the invention includes a strain gauge that detects a physical state of a tapered roller, and a processing portion that obtains a detection signal that is output from the strain gauge, performs processing on the detection signal, and transmits detection data obtained by performing the processing on the detection signal, to an outside. The strain gauge and the processing portion are accommodated in a through-hole formed at an axis center of the tapered roller.

Abstract: A creep indication system and a method for determining a creep amount are disclosed. The system includes a first creep indicating member on a first rotating component and a second creep indicating member on a second rotating component. The second creep indicating member has at least one different creep characteristic from the first creep indicating member. The system further includes at least one measurement device configured to measure a change in radial position of at least one of the first creep indicating member or the second creep indicating member. The method includes measuring a first creep amount of a first creep indicating member and measuring a second creep amount of a second creep indicating member. The method further includes estimating a temperature of a rotating component using the first creep amount and the second creep amount.

Abstract: A component for use in a gas turbine engine comprises an indicator operable to provide a visual indication when strain over a threshold value has been experienced by the component by transitioning from a rest state to an indication state on occurrence of strain above the threshold value. Also disclosed is a method of detecting foreign object damage in a component of a gas turbine engine, comprising: identifying at least one of a component or a region of a component that is subject to increased strain during a foreign object impact; and mounting an indicator on the identified component or region of a component, the indicator providing a visual indication when increased strain has been experienced.

Abstract: A wind turbine blade used in a wind power generator that receives wind and rotates a rotating shaft of a generator includes at least two layers on a surface of a blade body, one of the layers being colored with a coating material different in color from the blade body and the rest of the layers. The layers are provided at least on a tip, particularly at a front edge of the wind turbine blade. A wind turbine blade monitoring system that monitors the wind turbine blade includes: an imaging unit that images the wind turbine blade in a predetermined position over a predetermined period at timing when the wind turbine blade passes through the predetermined position; and an indication unit that chronologically indicates imaging results of the wind turbine blade imaged by the imaging means.

Abstract: A gas turbine engine component such as a laminate airfoil having a static pressure transducer and having a plurality of structural fiber layers bonded with a polymer matrix composite. The transducer includes a lattice formed from a plurality of hypotubes aligned in a first direction and a plurality of reinforcing wires aligned substantially perpendicular to the hypotubes. The lattice is placed between at least some of the structural fiber layers prior to thermally processing into a cured polymer matrix laminate composite.

Abstract: The present invention discloses an eddy current probe and an eddy current inspection device including the eddy current probe for inspection of surface defect of a rotor wheel including a dovetail coupling part in which a hook is formed. The eddy current probe in accordance with an embodiment of the present invention includes: a main body, a contact part coupled to the main body and having a convex part and a concave part formed thereon corresponding to the hook, and an eddy current sensor being coupled to an end part of the convex part of the contact part. Accordingly, the detectability of a defect and the permeation depth can be enhanced, and the inspection procedures can be simplified.

Abstract: A gas turbine engine inlet sensor fault detection and accommodation system comprises an engine model, an engine parameter comparison block, an inlet condition estimator, control laws, and a fault detection and accommodation system. The engine model is configured to produce a real-time model-based estimate of engine parameters. The engine parameter comparison block is configured to produce residuals indicating the difference between the real-time model-based estimate of engine parameters and sensed values of the engine parameters. The inlet condition estimator is configured to iteratively adjust an estimate of inlet conditions based on the residuals. The control laws are configured to produce engine control parameters for control of gas turbine engine actuators based on the inlet conditions.

Abstract: An exemplary device for testing a gas turbine engine component includes a shaft that is configured to be rotated. A first hub is selectively fixed to the shaft near a first end of the first hub with an opposite, second end spaced from the shaft. A second hub is selectively fixed to the shaft near a first end of the second hub with an opposite, second end spaced from the shaft. The second ends of the hubs each have a feature for supporting the component between the first and second hubs at a location spaced from the shaft for introducing a load on the component near the location.

Abstract: A method for detecting defects in a combustion duct in a combustion system of a turbine engine while the turbine engine operates, wherein the combustion duct comprises an inner surface, which, during operation, is exposed to the hot-gas flowpath, the method comprising the steps of: providing a first electrode that is electrically connected to the combustion duct; providing a second electrode that resides within the hot-gas flowpath; applying a voltage across the first electrode and the second electrode; and detecting current flowing between the first electrode and the second electrode.

Abstract: Internal components of power generation machinery, such as gas and steam turbines are inspected with an optical camera inspection system that is capable of automatically positioning the camera field of view (FOV) to an area of interest within the machinery along a pre-designated navigation path and capturing images without human intervention. Automatic camera positioning and image capture can be initiated automatically or after receipt of operator permission. The pre-designated navigation path can be defined by operator manual positioning of an inspection scope within the power machine or a similar one of the same type and recording of positioning steps for future replication. The navigation path can also be defined by virtual simulation. The inspection system includes a multi-axis inspection scope suitable for inspection within the turbine section of a gas turbine.

Abstract: A method for monitoring the health of one or more blades is presented. The method includes the steps of generating a signal representative of delta times of arrival corresponding to the rotating blade, generating a reconstructed signal by decomposing the signal representative of the delta times of arrival utilizing a multi-resolution analysis technique, wherein the reconstructed signal is representative of at least one of static deflection and dynamic deflection in the rotating blade.

Abstract: A health index (124) can be determined from vibration signatures (108, 110, 112, 114) arising out of an analysis of vibration data (102, 104, 106) by using a combination of frequency analysis (e.g. crest factor, side-band factor) and analyses done in time domain. The health index (124) can thus be calculated by summing a product of one or more of these vibration signatures (108, 110, 112, 114) and a corresponding weighting factor (116, 118, 120, 122).

Abstract: A test rig for testing a component in a wind turbine is proposed. The test rig has an adjustable radial weight arrangement mounted on a rotatable shaft; a driving means for rotating the shaft at a shaft rotational velocity; and an adjusting means for adjusting the centre of mass of the adjustable radial weight arrangement relative to the shaft while the shaft is rotating. A wind turbine test setup for testing components of a wind turbine has a test rig mounted to a component such that centrifugal forces generated by the rotating radial weights during operation of the test rig are transferred as lateral forces to the wind turbine component under test.

Abstract: Methods for testing turbine blades. One method for testing turbine blades includes measuring dimensions of each of a first set of turbine blades. The method also includes testing airflow through first openings in each of the first set of turbine blades to determine airflow properties of each of the first set of turbine blades. The method includes determining a relationship between the dimensions and the airflow properties of each of the first set of turbine blades. The method includes measuring dimensions of each of a second set of turbine blades. The method also includes determining airflow properties for each of the second set of turbine blades based at least partially on the dimensions of the second set of turbine blades and the relationship.

Abstract: A power plant analyzer for analyzing a plurality of power plants, comprising: an analyzing apparatus for analyzing a first parameter indicative of fuel flow to a first power plant, a second parameter indicative of fuel burned in the first power plant, a third parameter indicative of fuel flow to a second power plant and a fourth parameter indicative of fuel burned in the second power plant; and an alert generation apparatus, responsive to the analyzing apparatus, for generating an alert for the first or the second power plant, and wherein analyzing the first, second, third and fourth parameters comprises carrying out a differential analysis between the first and third parameters to produce a first result, and to carry out a differential analysis between the second and fourth parameters to produce a second result, and comparing the first and second results.

Abstract: A wear-indicating system includes a wear-indicating mark applied to a portion of a surface edge margin of an internal component of a turbine. The wear-indicating mark is visually discernible from the surface edge margin through boroscopic inspection. An inner extent of the wear-indicating mark is spaced a pre-selected distance from the surface edge.

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.