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: The device comprises first means for determining a pressure value relative to the pressure at the outlet of a precooler of an air bleed system and second means for calculating the air bleed level using this pressure value, said first means comprising means for calculating a first pressure value at the outlet of the precooler, using the pressure measured by a sensor, means for receiving a pressure measured by a second sensor, which represents a second pressure value at the outlet of the precooler and means for selecting one of said first and second pressure values, which is then transmitted to said second means for calculating said air bleed level.

Abstract: A pressure probe includes an elongated cable provided with a sensing tip, a portion of the elongated cable and sensing tip enclosed within a ceramic shroud, the ceramic shroud at least partially formed of a metalized ceramic material.

Abstract: A strategically located device and a machine including such a device are disclosed herein. In an embodiment, the device comprises a tool removably affixed to an external casing of the machine. The external casing of the machine includes an access port therethrough for providing access to an interior of the machine; and the tool is inserted into a desired location in the interior of the machine through the access port.

Abstract: Monitoring method of a variable speed wind turbine (11) comprising control means for a pitch regulation tracking a power vs. generator speed curve (21) in function of the wind speed expressed by a transfer function (TF) applied to the wind speed measured by a wind sensor placed in a location where the wind flow is disturbed, that comprises the following steps: a) providing an optimum relationship function (F1) between a wind speed dependant variable (V) such as the blade pitch angle, and a wind turbine performance variable (P) such as the generator speed; b) measuring continuously said variables (V, P) and obtaining a relationship function (F2) between them; c) obtaining continuously a parameter (D) indicative of the differences between said relationship functions (F1, F2); d) generating a warning message when the value of said parameter (D) is greater than a predetermined value.

Abstract: A method and a system for identifying failures in an aeroengine. The system includes: a mechanism defining a set of standardized indicators representative of operation of the aeroengine; a mechanism constructing an anomaly vector representative of a behavior of the engine as a function of the set of standardized indicators; a mechanism selecting in an event of an anomaly being revealed by the anomaly vector a subset of reference vectors having directions belonging to a determined neighborhood of a direction of the anomaly vector, the subset of reference vectors being selected from a set of reference vectors associated with failures of the aeroengine and determined using criteria established by experts; and a mechanism identifying failures associated with the subset of reference vectors.

Abstract: A capacitance based clearance probe has a partial sensor housing mounted on a surface and a sensor rod anchored in the partial sensor housing. The sensor rod extends into a sensor opening in the surface such that the partial sensor housing and the surface combine to operate as a complete sensor housing.

Abstract: A method for checking a blade contour of a turbomachine, in particular a gas turbine, wherein an actual contour (1; 1?) of a blade is detected, wherein a target contour of the blade is scaled and the actual contour is compared with said scaled contour (2).

Abstract: A measuring rod capable of receiving a plurality of instrumentation cables transmitting data to a data processing device, includes a section of epicycloidal shape.

Abstract: There is provided a wind power installation having a component to be monitored and a crack detection unit. In that case the crack detection unit has at least one thread or fiber which is fastened directly on the component to be monitored. The crack detection unit further has a crack detector which serves to detect whether the thread or fiber is or is not cracked.

Abstract: A two piece measurement rake has a first split tubular section with at least one hollow support member disposed therethrough the measurement rake includes at least one sensor probe mounted on the hollow support member and coupled to a transducer. A second split tubular section is attached to the first split tubular section, and forms an interior cavity on which the at least one transducer tube is disposed.

Abstract: A clearance probe includes a sensor component with a sensor face. A housing is arranged about the sensor component and includes multiple gas passage exit holes that are arranged about the sensor face and are operable to create a gas curtain circumferentially surrounding the sensor face. This gas curtain displaces a portion of the particles in the area between the probe and the blade tip, thereby improving the accuracy of the clearance measurement.

Abstract: Embodiments of the present invention have the technical effect of automatically testing an overspeed protection system associated with multiple powerplant machines of a powerplant. An embodiment of the present invention may automatically test the overspeed protection system while at least one of the powerplant machines is in the process of shutting down. Another embodiment of the present invention may automatically test the overspeed protection system by adjusting the speed of a shaft while at least one of the powerplant machines operates at full-speed-no-load.

Abstract: A hub unit adapted for use in a monitoring system that monitors engine performance parameters of a gas turbine engine. The hub unit includes a housing, at least one signal conditioning circuit board within the housing and adapted to receive the analog sensor outputs from the sensors, and a control circuit board within the housing, connected to the signal conditioning circuit board, and adapted to produce digital data corresponding to analog sensor outputs. The control circuit board and the signal conditioning circuit board each comprise electrical circuit components that define an analog signal processing path and have accuracy and precision characteristics that drift in response to component aging and to changes in the temperature to which the hub unit is subjected. The hub unit performs a continuous calibration scheme to determine and remove errors in the analog signal processing path resulting from the drifts of the electrical circuit components.

Abstract: A system and a process for testing a gas turbine engine or component thereof, especially for a large aero gas turbine engine, and for a process for testing a large industrial gas turbine engine that requires large flow capacity and pressure ratios. The system and process may include the use of a large compressed air storage reservoir to provide compressed air to the testing system. Further, the system and process may also include the use of a pre-heating system, which may include a heater and a heat exchange device, to warm the compressed air from the compressed air storage reservoir to a temperature suitable to simulate normal operating conditions of the gas turbine engine or component thereof.

Abstract: Isolation circuits, turbine data acquisition systems, and related methods are disclosed. One example isolation circuit includes a voltage divider circuit for coupling to an operational sensor, a clamping circuit connected to said voltage divider circuit and a gain circuit connected to said clamping circuit. The voltage divider circuit is configured to divide an amplitude of a signal received from the sensor. The clamping circuit is configured to limit voltage from said voltage divider circuit. The gain circuit includes an output. The isolation circuit provides a single-ended output signal to the output of the gain circuit as a function of the sensor signal and independent of ground.

Abstract: A master component is provided for use in checking for any variation in the performance of a gas turbine test facility. The master component replaces a standard component, which is typically a turbine blade, vane or segment in the test facility. The master component is attached to the test facility in the same manner as the standard component. The flow rate through the master component is substantially the same as the flow rate through the standard component for a given inlet and outlet temperature and pressure. The flow through the master component is simpler than the flow through the standard component. This means that the flow through the master component is less likely to vary over time. As such, the master component is more suitable for use in checking for any variation in the performance of a test facility.

Abstract: A condition measurement apparatus is provided and includes a gas turbine engine combustor having an end cover, a liner defining a liner interior and a fuel nozzle communicative with the liner interior, the end cover being formed to separate a cold side thereof, which is a relatively low temperature environment, from a hot side thereof, which is a relatively high temperature environment in which the liner and the fuel nozzle are disposed, the combustor being formed to define a fuel flow path extending through piping disposed at the cold side of the end cover by which fuel is deliverable to the fuel nozzle, and a condition sensing device operably mounted on the piping.

Abstract: Systems and methods for inspecting turbine components are disclosed. In one embodiment, an apparatus includes: a base frame adapted to position an inspection device relative a turbine component; and a set of mounts connected to the base frame, the set of mounts adapted to connect the base frame to at least one other point of the turbine component and to pivotally connect the base frame to a pivot point of the turbine component.

Abstract: The invention relates to a method for detecting rubbing and/or contact points on machines with rotating parts. The rotating parts form an electrical coaxial system with respect to the stationary parts of such a machine, in which system electrical voltage pulses are propagated at a characteristic speed because of the small distance between the rotating and the stationary part. Short electrical voltage pulses and/or continuous alternating voltage signals are applied between the rotating part and the stationary part, an electrical connection occurring between the rotating and the stationary part at a rubbing and/or contact point. In order to locate this rubbing and/or contact point as a point of electrical discontinuity, the period of time until the reflected pulses arrive is measured along the path of propagation of the electrical voltage pulses and/or of the continuous alternating voltage signals.

Abstract: The invention relates to a test tool for testing an overspeed protection system of a wind turbine. The system includes a sensor for sensing a first physical signal having a physical nature and representing a speed of rotation of a rotor of the wind turbine, and for providing a corresponding output signal; means for receiving the output signal from the sensor and for determining, based on the output signal, if the speed of rotation exceeds a threshold of speed of rotation; and means for initiating, if the speed of rotation exceeds the threshold of speed of rotation, an action reducing the speed of rotation. The test tool provides a second physical signal of the same physical nature as the first physical signal, is suitable for supplying the second physical signal to the sensor so as to simulate the rotation of the wind turbine.

Abstract: Redundant detection of a rotational direction of a body having a rotary axis, in particular of a drive shaft of a turbine, is performed using at least one evaluation unit designed for evaluating at least three signals from three sensors arranged offset around the rotary axis. One period of a flank signal of a signal used as the primary signal is evaluated with the applied signal of one (Digital2) of the two signals not used as the primary signal for detecting the rotational direction. An error detection unit is designed for detecting the number of flanks of the signal initially used for detecting the rotational direction during the period. In the event of an error detection, the further rotational direction is detected in the evaluation unit on the basis of the other (Digital3) of the two signals.

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: In the course of a method for the function testing of turbo-machines, preferably exhaust gas turbochargers (1, 2, 3), the test object is subjected to one or a plurality of gas pressure pulses and is operated thereby. For a simple, economic and still informative testing, the test object (1, 2, 3) is integrated in a testing device and, by means of this testing device, is subjected to at least one gas pressure pulse, preferably at least one compressed air pulse, wherein from the dynamic behavior of the test object (1, 2, 3) resulting therefrom, potential failures are determined.

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: A method for monitoring the change in state of a valve in a start up circuit of a turbo-engine following a command to change the state of the valve includes measuring the air pressure under a fan cowl of the turbo-engine before the change state command, measuring the air pressure under the fan cowl after the change state command, comparing the measured values of the air pressure, and determining whether or not the valve has actually changed state. An aircraft turbo-engine includes a unit that monitors the change in the valve using such a method.

Abstract: A method is provided for determining the diameter of a rotor of a turbomachine, rotor being equipped with rotor blades. The method involves setting the rotor with the rotor blade ring in rotation, arranging a clearance measuring device assigned to the rotor blade ring outside the region of the latter, measuring the distance to the rotor blades of the rotor blade ring which are rotating past the clearance measuring device, and using the measured distance for determining the diameter of the rotor. During measuring, the rotational speed is identical to, almost identical to or higher than the setpoint rotational speed of the rotor.

Abstract: Systems and methods of determining a flame state within a combustor of a turbine engine make use of characteristics of an output pressure of a compressor of the turbine engine and a temperature of exhaust gases of the turbine engine to make a determination. If the first and/or second derivatives of the output pressure of the compressor and the first and/or second derivatives of the exhaust gas temperature of the turbine engine are all positive during at least portions of a predetermined period of time, one can determine that a flame has ignited in the combustor. If those values are negative during at least portions of a predetermined period of time, one can determine that a flame has been extinguished in the combustor.

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 inspection vehicle structured to inspect a portion of the turbine disk, preferably the blade attachment hubs, while the turbine disk is disposed within a turbine housing assembly is provided. A turbine disk is generally planar but includes a inner hub and an outer blade attachment hub. The inner hub is coupled to a shaft and the blade attachment hub provides a surface to which removable blades are attached. The area between the inner hub and outer blade attachment hub is substantially planar. The inner and blade attachment hubs are the “inspection areas” that the inspection vehicle is structured to inspect. The inspection vehicle travels over, and is magnetically coupled to the planar surface between the two hubs.

Abstract: Apparatus and methods for testing a turbomachine, with the apparatus including a loading device housing, a disk, and a non-contacting seal. The loading device housing has an inner surface and a fluid inlet configured to receive a pressurized gas. The disk is located outside of a turbomachine housing in which the turbomachine is disposed and is coupled to a shaft of the turbomachine, proximal an axial end of the shaft. The disk is received in the loading device housing and is axially moveable in the loading device housing while the shaft is rotating. The non-contacting seal is disposed between the inner surface and the disk.

Abstract: A method of monitoring operation of a fuel system includes urging a fuel flow from a fuel source toward a pressure regulating valve via a fuel pump. A pressure of the fuel flow is detected at the pressure regulating valve, and a pump speed required to produce a selected pressure at the pressure regulating valve is detected. The pump speed is compared to a range of acceptable pump speeds, and an operational status of the fuel pump is determined based on a result of the comparison.

Abstract: A test rig that reproduces high temperature and high pressure conditions found in a gas turbine engine for testing materials under these conditions. The test rig includes a combustor surrounded by an upper plenum chamber and an exhaust plenum that receives a hot gas stream from the combustor. A transparent channeling vessel guides the hot gas stream from the combustor over a test specimen on which a material to be tested is mounted. The hot gas stream exits the clear channeling vessel and into the exhaust plenum where the stream is cooled by diluting the stream with cooling air. A viewing portal is located in the exhaust plenum so that the material can be observed through the clear vessel.

Abstract: A method of determining emission values of a gas turbine, includes the following steps: a test run is performed on the gas turbine; operational parameters of the gas turbine are determined during the test run; first emission values are determined during the test run; an association between the operational parameters and the first emission values is stored; and during operation, operational parameters of the gas turbine are determined; and second emission values are determined in accordance with the stored association between the operational parameters and the first emission values.

Abstract: Systems and methods for inspecting turbine components are disclosed. In one embodiment, an apparatus includes: a base frame adapted to position an inspection device relative a turbine component; and a set of mounts connected to the base frame, the set of mounts adapted to connect the base frame to at least one other point of the turbine component and to pivotally connect the base frame to a pivot point of the turbine component.

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 method for performing condition monitoring on a plurality of wind turbines arranged in a wind farm is disclosed. The method comprises the steps of: for each wind turbine, obtaining at least one vibration signal, each vibration signal representing vibrations of one or more monitored components of the wind turbine, e.g. moving gear parts or bearings; generating a plurality of faulty frequency indexes, each faulty frequency index corresponding to a monitored component, each faulty frequency index being generated on the basis of one or more of the obtained vibration signals, and each faulty frequency index being generated in such a manner that variations in the vibration signals introduced by variations in rotational speed of one or more rotating shafts of the wind turbine are filtered out; comparing faulty frequency indexes originating from different wind turbines of the wind farm; and based on the comparing step, evaluating the condition of each of the monitored components of the plurality of wind turbines.

Abstract: In a first aspect, the present invention provides a method for detecting a wake situation in a wind farm comprising a plurality of wind turbines theoretically distributed according to a theoretical layout, one or more of the wind turbines having one or more load sensors. The method comprises obtaining, for one or more of the wind turbines with load sensors, load measurements from the load sensors during a predefined time interval. The method further comprises obtaining a qualified layout by qualifying in the layout each wind turbine for which load measurements have been obtained as overloaded or non-overloaded according to its load measurements. Finally, the obtained qualified layout is used to detect the wake situation.

Abstract: A fuel injector for a gas turbine engine is disclosed which includes a nozzle body for issuing fuel and air into a combustor, and an on-axis optical probe located within the nozzle body for observing combustor flame radiation, wherein the optical probe includes a plurality of optical fiber bundles extending to a distal end of the probe, and a shaped lens is supported at the distal end of the probe to provide a multi-directional field of view of combustion characteristics and properties in an operating gas turbine engine combustor.

Abstract: A system for airflow testing a turbine engine component having multiple cavities has a test fixture with a module for supporting a turbine engine component to be tested and a sliding element for sequentially allowing a pressurized fluid to flow through each of the multiple cavities in the turbine engine component. A method for performing the airflow testing is also described.

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: An exemplary debris detection method according to one example embodiment of the present disclosure includes, among other things, monitoring turbomachine performance, and initiating a debris warning when an actual rate of change in turbomachine performance varies from a predicted rate of change in the performance.

Abstract: Embodiments of the invention can provide systems and methods for modifying the operation and/or performance of a gas turbine. According to one embodiment, a method for modifying the performance of a gas turbine comprising one or more combustors can be provided. The method can include measuring a gas exhaust temperature for the gas turbine and estimating a heat transfer rate for the gas turbine based at least in part on the gas exhaust temperature. After estimating the heat transfer rate, the method can continue by estimating a transiently accurate combustion reference temperature and using this parameter to control the one or more combustors of the gas turbine. In doing so, the performance of the gas turbine can be modified to ensure reliable and consistent operation.

Abstract: A method for testing a component for determining a maximum period of use for renewed use of the component is proposed. The component was in use and is subjected to a refurbishment for reuse. Core drilling of the used component enables a simultaneous refurbishment of the component. The state of the component is analyzed.

Abstract: A system for use in monitoring operation of a rotor assembly is provided. The system includes a plurality of clearance sensors including at least a first clearance sensor configured to measure a distance between the first sensor and a surface of a lockwire tab, and a monitoring unit coupled to the plurality of clearance sensors, the monitoring unit configured to receive measurements from the plurality of clearance sensors, and determine whether a crack exists in the rotor assembly based on the received measurements.

Abstract: A probe may be used to inspect objects. The probe may be configured with a flexible eddy current array mounted in a flexible film such that the flexible eddy current array conforms to a shape of an object when applied to the object, a probe body connected to at least one section of the flexible eddy current array, and a communications component configured to receive and output from the flexible eddy current array.

Abstract: A device for non-destructive in situ inspection of parts of a turbine engine, the device including a stick carrying at its distal end a pivoting finger carrying at one of its ends a blade for supporting an inspection probe, and at its opposite end a skid for bearing against and/or catching on an element of the engine, the skid being movable in a direction parallel to the longitudinal axis of the finger.

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: It is described an arrangement for determining a target value of an operational variable of a wind turbine, the arrangement comprising: at least one input terminal for receiving at least one operational parameter of the wind turbine; a determining unit adapted to determine a target value of an operational variable of the wind turbine based on the operational parameter. Further, a corresponding method and a wind turbine are described.

Abstract: A system for detecting defects in a combustion duct of a combustion system of a combustion turbine engine while the combustion turbine engine operates, wherein the combustion duct comprises a hot side, which is exposed to combustion gases and, opposing the hot side, a cold side. The system may include: an indicator coating disposed on an outer surface of the combustion duct, the indicator coating comprising a detectable substance; and a gas sensor positioned downstream of the combustor, the gas sensor configured to take a measurement of the amount of the detectable substance in the combustion products of the combustion turbine engine.