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 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 for detecting resonance in a rotor shaft of a turbine engine, in which a resonance frequency (Fr) of the rotor shaft belonging to a resonance band is centered on an estimated resonance frequency (Frest), is disclosed. The method including: measuring a parameter (P) for regulating the fuel of the turbine engine is measured to obtain an excitation signal; forming a spectrum of the excitation signal; comparing an amplitude of the excitation signal is compared with a resonance threshold (S) on the resonance band of the spectrum; and emitting a resonance detection alarm if the resonance threshold (S) is exceeded.

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 method for operating a debris monitoring system comprises continuously sensing the passage of particulates through a gas turbine engine to produce a time-domain sensor signal. The time-domain sensor signal is Fourier transformed to produce a frequency domain sensor signal. The frequency domain sensor signal is partitioned into bins corresponding to particulate composition categories. At least one feature is identified within each bin, and is used to determine the amount of particulate flow in each particulate composition category.

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: A method for determining a total mechanical load of a wind turbine is provided. A present load signal indicative of a present load of a wind turbine base structure is obtained, wherein the present load acts in a present angular direction. A first present load and a second present load are derived based upon the present load signal and the present angular direction, wherein the first present load is associated with a first angular sector of the turbine and the second present load is associated with a second angular sector of the turbine. Further, a total mechanical load is derived based upon the first present load and the second present load.

Abstract: A device monitors an obstruction of two fluid filters of a fluid circulation system of a gas turbine engine of an aircraft. A first obstruction sensor sends a first detection signal of an obstruction of a first filter. A second obstruction sensor sends a second detection signal of an obstruction of a second filter. A processor includes a monitoring input to measure the first and second detection signals. The first obstruction sensor includes a Wheatstone bridge including a strain gauge resistor. The second obstruction sensor is connected in parallel with the strain gauge resistor. The first detection signal is sent over a first predetermined variation range. The second detection signal is sent over a second predetermined variation range, distinct from the first variation range. The processor identifies the obstruction of one of the fluid filters as a function of one of the variation ranges of the detection signals.

Abstract: A fluid testing apparatus for performing fluid flow analysis on a gas turbine engine component having a plurality of fluid cooling circuits each defining one or more openings in the component includes a first sealing insert configured to create a seal at an interface of the first sealing insert to the component to seal off one or more openings of a first fluid cooling circuit of the component and a generic insert separable from the first sealing insert. The first sealing insert is configured as a substantially flat sheet having a shaped perimeter, and the component is clampable to the generic insert to hold the first sealing insert against the component.

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 system may detect a flame about a fuel nozzle of a gas turbine. The gas turbine may have a compressor and a combustor. The system may include a first pressure sensor, a second pressure sensor, and a transducer. The first pressure sensor may detect a first pressure upstream of the fuel nozzle. The second pressure sensor may detect a second pressure downstream of the fuel nozzle. The transducer may be operable to detect a pressure difference between the first pressure sensor and the second pressure sensor.

Abstract: A system for sensing at least one physical characteristic associated with an engine including a turbine having a plurality of blades turning inside a casing, the system including: a pressure sensor coupled substantially adjacent to the casing and including at least one output; a port in the turbine casing for communicating a pressure indicative of a clearance between the blades and casing to the pressure sensor; a cooling cavity substantially surrounding the pressure sensor; and, an inlet for receiving fluid from the engine and feeding the fluid to the cooling cavity to cool the pressure sensor; wherein, the pressure sensor output is indicative of the clearance between the blades and casing.

Abstract: A method for identifying a defect such as a crack on a turbine rotor blade while the blade is in operation within a gas turbine engine, the method includes scanning the blade using an IR camera, identifying a leading edge or other line on the blade for a reference point, identifying a potential defect candidate on the blade by comparing the potential defect to a surrounding neighborhood in order to determine if the potential defect is an anomaly, and if the potential defect is an anomaly determine the structure of the anomaly in order to determine if the defect is a crack or a hole or a TBC spallation. The method computes a probability density for sub-regions in an image of the blade, conditioned upon the areas surrounding the sub-regions.

Abstract: A sensor for measuring gas pressure in a gas turbine engine. The sensor is positioned to receive pressurized gas and measure the pressure. A thermally insulating material mounts the sensor spaced from conductive portions of the engine. A heater is mounted on a plurality of sides of the sensor to provide heat thereto. A thermal blanket covers the heater to prevent loss of sensor heat.

Abstract: A power plant analyzer for analyzing a plurality of power plants, comprising: analyzing means 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 alert generation means, responsive to the analyzing means, for generating an alert for the first or the second power plant.

Abstract: A sensor element for use in a backing sensor to monitor a gas turbine shaft. The sensor includes an oscillator circuit 30 having an oscillator and a resonance circuit 42, and a frequency detector 31 for monitoring the frequency of the ossilation circuit. Abnormal movement of the shaft cuts the circuit in the sensor along a cutting line (15). The cutting of the sensor changes the capacitance and/or inductance of the resonance circuit and thereby changes the frequency of oscillation.

Abstract: A system and method of monitoring oil consumption in a gas turbine engine system are provided. When the gas turbine engine is not running the reservoir oil level, reservoir oil temperature, and reservoir attitude are sensed. The current gas turbine engine system oil quantity is determined based on at least the sensed reservoir oil level, the sensed reservoir oil temperature, and the sensed reservoir attitude. When a predetermined event has occurred, an average gas turbine engine system oil quantity is automatically calculated. The gas turbine engine system oil consumption rate is determined from a plurality of the average oil quantities.

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: A fluid testing apparatus for performing fluid flow analysis on a gas turbine engine component having a plurality of fluid cooling circuits each defining one or more openings in the component includes a first sealing insert configured to create a seal at an interface of the first sealing insert to the component to seal off one or more openings of a first fluid cooling circuit of the component and a generic insert separable from the first sealing insert. The first sealing insert is configured as a substantially flat sheet having a shaped perimeter, and the component is clampable to the generic insert to hold the first sealing insert against the component.

Abstract: An apparatus and method for inducing waves within a container arranged to permit a through-flow of fluid flowing generally from an inlet of the container to an exit of the container, wherein the container has wave inducing means located at the exit of the container, the wave inducing means being operable to vary the area of the exit thereby inducing waves within the container. The apparatus may form part of a combustor test rig.

Abstract: A method for determining a mass change at a rotating blade of a wind turbine is provided. The method includes measuring a vibration quantity representative of a vibration of the wind turbine, measuring an azimuthal quantity representative of a rotation angle of the blade, determining a frequency quantity representative of a vibration frequency of the blade from the vibration quantity and the azimuthal quantity, and determining the mass change at the blade based on the frequency quantity.

Abstract: Embodiments of the present invention have the technical effect of automatically testing an overspeed protection system of a powerplant machine comprising a shaft and integrated with a safety control system. An embodiment of the present invention may automatically test the overspeed protection system while the powerplant machine is in the process of shutting down. Another embodiment of the present invention may automatically test the overspeed protection system of the powerplant machine by adjusting the speed of a shaft while operating at full-speed-no-load.

Abstract: A system for monitoring a gas turbine includes a memory containing information from comparable gas turbines and an input device that generates a unit data signal and a risk signal. A processor in communication with the memory and the input device incorporates the unit data signal into the database, projects information for the gas turbine, and calculates a conditional risk that the gas turbine will reach a limit. An output signal includes repair or maintenance schedules. A method for monitoring a gas turbine includes receiving information from comparable gas turbines, adding information from the gas turbine to the information from comparable gas turbines, and projecting information for the gas turbine. The method further includes calculating a conditional risk that the gas turbine will reach a limit and generating an output signal containing repair or maintenance schedules.

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 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: An apparatus is provided for inspecting a component of a turbomachine in-situ. The apparatus includes an end effector having a frame defining a stable platform with a curved surface of the component, a spring loaded suspension attached to the frame, and a probe connected to a wedge member, where the probe and wedge member are connected to the spring loaded suspension. The probe is configured to inspect the component by passing signals through the wedge.

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: The present application discloses a method for detecting performance of an APU, comprising: obtaining EGT (Exhaust Gas Temperature), LCIT (Load Compressor Inlet Temperature), STA (Starting Time), TSR and PT, comparing respectively a difference of EGT and LCIT (i.e., EGT-LCIT), STA, TSR and PT with respective threshold value; assigning a weights to comparison results between the EGT-LCIT, STA, TSR and PT and the respective threshold value; and determining the performance of the APU based on the comparison results considering the weight between the EGT-LCIT, STA, TSR and PT and the respective threshold value.

Abstract: A sensor is provided and includes a body disposed at a point of measurement interest on a rotor at a radial distance from a centerline thereof and having a substantially cylindrical shape and first and second opposing ends and a sensing end coupled to one of the first and second opposing ends, the other of the first and second opposing ends being coupled to a communication system, the sensing end including a sensing device configured to generate a signal reflective of a detected condition at the point of measurement interest, and at least one of the first and the second opposing ends being formed to define a shoulder portion for absorbing gravitational loading.

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 method for operating a debris monitoring system comprises continuously sensing the passage of particulates through a gas turbine engine to produce a time-domain sensor signal. The time-domain sensor signal is Fourier transformed to produce a frequency domain sensor signal. The frequency domain sensor signal is partitioned into bins corresponding to particulate composition categories. At least one feature is identified within each bin, and is used to determine the amount of particulate flow in each particulate composition category.

Abstract: The invention relates to a method for inspecting especially a gas turbine installation or steam turbine installation. An actual condition of a component of the turbine installation is determined using a suitable system, the determined actual condition is compared with a predetermined desired condition of the component, and the result of comparison between the actual condition and the desired condition is used to determine whether an overall inspection of the turbine installation is required. The component is a guide vane whose angular position in relation to the direction of influx is the actual condition to be determined. The actual condition is determined by an imaging device. The invention also relates to a turbine inspection system for carrying out the method.

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 method for assembling a gas turbine engine to prevent rotor over-speeding is described. The method includes serially coupling a first fuel system interface to a second fuel system interface, such that at least one of the first fuel system interface and the second fuel system interface is coupled to the gas turbine engine. The method also includes coupling a control system to the first fuel system interface and to the second fuel system interface. The control system is configured to identify an occurrence of an over-speed condition. The method also includes programming the control system to discontinue fuel flow to the engine when both the first fuel system interface and the second fuel system interface indicate an over-speed condition has occurred.

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: A method of checking a wind turbine in a wind farm with a number of wind turbines for a yaw misalignment is provided. In this method, the yaw angles of at least a subset of wind turbines of the wind farm are ascertained, an average yaw angle is established from the ascertained yaw angles, and a yaw misalignment of the wind turbine to be checked is identified by a deviation of its yaw angle from the average yaw angle by more than a threshold value.

Abstract: A transducer assembly for connecting a transducer to a device, the transducer assembly having a transducer mount adapted to receive the transducer, and a clamp having first and second jaws, the first and second jaws being adapted to selectively clamp to a flange portion of the device. The transducer mount may include a housing, a resilient member, and first and second end walls. The first end wall may be operatively connected to the device. The transducer may be held within the housing and adjacent to the first end wall. The resilient member may be disposed between the transducer and the second end wall.

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: 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: A method of detecting a fault of a frequency sensor having a bias resistor and associated with a rotary member. The following steps are performed while the rotary member is stationary: injecting into the bias resistor of the sensor inverted alternating signals (S1, S2) comprising at least one first alternation (A1) and at least one second alternation (A2), the first alternation being of amplitude greater than the amplitude of the second alternation; and detecting a frequency of an output signal (S?) from the sensor. A measurement circuit implementing the method is also provided.

Abstract: The present invention provides a method of controlling engine performance that includes obtaining at least one optical wavelength-dependent measurement from at least one combustion event in at least one combustion chamber. The method further includes analyzing the optical wavelength-dependent measurement for determining adjustments to the at least one combustion event. Additionally, the method includes adjusting the at least one combustion event or at least a next combustion event by changing at least one physical parameter, at least one constituent parameter, or at least one physical parameter and at least one constituent parameter to control the engine performance. The engine can include steady-flow engines or periodic flow engines, and the engine performance can be selected by an engine user.

Abstract: A method for testing rotors is disclosed, wherein a rotor to be tested is coupled in a torque-transmitting manner to an activating motor and is set in rotation. Vibrations of the rotor to be tested are measured, wherein the activating motor is operated such that torsional excitations are generated in the rotor.

Abstract: A method and a system for analyzing turbomachinery is provided. In one embodiment, a system for analyzing turbomachinery is provided. The system includes an intelligent turbomachinery tracking filter (ITTF) system configured to determine one or more performance shifts for one or more components of the turbomachinery based on a plurality of turbomachinery parameters. The system further includes a root cause analyzer configured to determine a root cause of the turbomachinery performance based on the one or more performance shifts. The one or more performance shifts include trended data.

Abstract: An example method of controlling gas turbine engine debris monitoring sensors includes detecting debris carried by air moving through an engine using at least first and second debris sensors, and processing signals from both the first and second debris sensors using a common signal conditioning unit. Another example method of monitoring gas turbine engine debris includes configuring at least one first debris sensor to detect debris carried by airflow moving through a first portion of an engine and configuring at least one second debris sensor to detect debris carried by airflow moving though a second portion of the engine. The method alternates between using the first debris sensor to detect debris and using the second debris sensor to detect debris.

Abstract: A system, including, a boundary layer rake, including a rake body, a coolant path extending through the rake body, and a first probe coupled to the rake body, wherein the first probe is configured to measure a first parameter of a first boundary layer flow along a first wall.

Abstract: A measuring assembly for use in a gas turbine engine includes an indicia portion that extends radially inwardly from an inner surface of a ring seal structure to a location radially inwardly from tips of blades mounted on a rotor. The indicia portion of the measuring assembly comprises a section that is abraded by the blades during rotational movement of the rotor to provide a visual indication of a distance between the tips of the blades and the inner surface.

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: 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: The present application provides a shaft speed monitoring system for a pulse detonation combustor with a number of combustion tubes and positioned about a shaft of a pulse detonation turbine engine. The shaft speed monitoring system may include one or more shaft sensors positioned about the shaft and a control in communication with the shaft sensors to determine a number of shaft speed fluctuations related to each of the combustion tubes.

Abstract: A method of calculating the tip clearance during operation of a combustion turbine engine that includes the steps of: measuring a cold tip clearance and a cold shell-to-shell distance; while the combustion turbine engine is operating, measuring an operating parameter and measuring a shell-to-shell distance with a proximity sensor; calculating the tip clearance based on the cold tip clearance measurement and the operating parameter measurement; calculating the shell-to-shell distance based on the cold shell-to-shell distance measurement and the operating parameter measurement; comparing the shell-to-shell distance measurement of the proximity sensor with the shell-to-shell distance calculation; and calibrating the calculated tip clearance calculation based on the comparison.