| Entries |
| Document | Title | Date |
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| 20080236261 | Power turbine test apparatus - The invention provides a power turbine test apparatus able to significantly reduce the equipment cost and testing cost required for an independent operation test of a test object power turbine. The power turbine test apparatus for independently operating and testing a power turbine that drives a driven machinery using combustion gas or steam, comprises: an air compressor that supplies compressed outside air to a combustor positioned on a downstream side; a first air duct that guides the outside air compressed by the air compressor into the combustor; a combustor which combusts the compressed outside air and fuel to generate combustion gas; and a second air duct that guides the combustion gas generated by the combustor to the power turbine installed on the downstream side; wherein a rotating shaft of the power turbine and a rotating shaft of the air compressor are joined to each other, and power of the power turbine is recovered by the air compressor. | 10-02-2008 |
| 20090049894 | Monitoring of a flame existence and a flame temperature - A method for monitoring a flame in a combustion chamber comprising a wall with an outer side is provided, wherein the radiation which is emitted from a part of the outer side of the wall is optically detected by a sensor. Furthermore, a burner is provided, especially for use in a gas turbine. The burner comprises a wall section with an inner side, which shows towards a combustion zone, and an outer side. The burner further comprises a sensor for optically detecting the radiation emitted from the outer side of said wall section. | 02-26-2009 |
| 20090064773 | Systems and Methods for Determining Airflow Parameters of Gas Turbine Engine Components - Systems and methods for determining airflow parameters of gas turbine engine components are provided. In this regard, a representative method includes: receiving information from multiple test systems regarding a first airflow parameter of a gas turbine engine component; and using the information to establish a desired performance parameter that is to be exhibited by a repaired component. | 03-12-2009 |
| 20090084170 | Systems and Methods for Performing Cooling Airflow Analysis of Gas Turbine Engine Components - Systems and methods for performing cooling airflow analysis of gas turbine engine components are provided. In this regard, a representative system includes an airflow insert operative to form a seal with a component, the airflow insert having a main portion and a removable sacrificial portion, the sacrificial portion being sized and shaped to engage the component, the main portion having a cavity sized and shaped to removably receive the sacrificial portion, the main portion being sized and shaped to form a seal about the sacrificial portion and a corresponding portion of the component. | 04-02-2009 |
| 20090100918 | Systems and Methods for Testing Gas Turbine Engines - Systems and methods for testing gas turbine engines are provided. In this regard, a representative system for testing a gas turbine engine having an inlet includes an inflatable seal having an interior chamber operative to receive pressurized gas such that the seal inflates to engage circumferentially about the exterior of an inlet of a gas turbine engine. | 04-23-2009 |
| 20090165540 | METHOD FOR MEASURING BLADE TIP CLEARANCE - A method for measuring blade tip clearance for a gas turbine engine having a fan case assembly and a rotor having a plurality of blades may include the steps of removably attaching a measurement tool to the fan case assembly, the measurement tool having a sensor, rotating the rotor, and measuring blade tip clearance for the plurality of blades during the rotation of the rotor. | 07-02-2009 |
| 20090266150 | SENSOR CRITICALITY DETERMINATION PROCESS - A method and system of evaluating the criticality of parameters by evaluating consequences of a loss of capability to determine a desired operating parameter, identification of alternate means of obtaining the parameter, and assigning an importance value to the capability of determining the operating parameter. The resulting evaluation and identification is utilized to direct design and mitigation efforts. | 10-29-2009 |
| 20100005869 | METHOD OF ANALYSIS OF SECONDARY-AIR CIRCUITS IN GAS-TURBINE PLANTS - A method of analysis of secondary-air circuits in gas-turbine plants includes defining an equivalent fluid-dynamic network of a secondary-air circuit of a gas-turbine plant. The equivalent fluid-dynamic network includes a plurality of elements, organized in branches and connected to nodes. For at least one element of the secondary-air circuit a principal component of flow and at least one auxiliary component of flow are calculated. | 01-14-2010 |
| 20100024536 | METHODS AND SYSTEMS FOR ESTIMATING OPERATING PARAMETERS OF AN ENGINE - A method for estimating an operating parameter of a turbine engine is provided. The method includes receiving at least one sensor input, calculating the operating parameter using at least the one sensor input, and determining whether an anomaly is present in the calculated operating parameter using a redundancy system. An estimated operating parameter is output. | 02-04-2010 |
| 20100043540 | Method for detecting overpressure inside a compartment associated with a gas turbine nacelle - A method for detecting overpressure inside a compartment associated with a gas turbine nacelle, the method comprising: a) measuring one or more predetermined operating conditions nominally affecting the temperature inside the compartment; b) determining a reference temperature for the compartment, corresponding to a nominal reference zone pressure, on the basis of the measured operating condition or conditions; c) measuring the actual temperature inside the compartment, corresponding to the actual compartment pressure; and d) using the measured actual temperature in the compartment and the determined reference temperature for the compartment to assess the gas pressure inside the compartment. In one embodiment, there is disclosed a system for assessing the gas pressure inside the compartment caused by an associated pressure system failure, comprising using a quantified mass leakage flow to assess gas pressure inside the compartment. The quantified mass leakage flow may also be used to detect excessive mass leakage flow by comparing the quantified mass leakage flow with a predetermined mass flow leakage. | 02-25-2010 |
| 20100050752 | METHOD AND DEVICE TO MEASURE, TEST AND/OR MONITOR TURBINE PERFORMANCE - A set of data is measured reliably and accurately to test, operate and/or monitor the performance of turbines. It is proposed to determine the performance parameters of a turbine applicable to its entire operating envelope and for a condition when it is producing net output power, by measuring its characteristic performance parameters in the mode of no net output-power production. | 03-04-2010 |
| 20100089136 | Method For Testing Rotors - 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. | 04-15-2010 |
| 20100180674 | Systems and Methods of Monitoring Acoustic Pressure to Detect a Flame Condition in a Gas Turbine - A method may detect a flashback condition in a fuel nozzle of a combustor. The method may include obtaining a current acoustic pressure signal from the combustor, analyzing the current acoustic pressure signal to determine current operating frequency information for the combustor, and indicating that the flashback condition exists based at least in part on the current operating frequency information. | 07-22-2010 |
| 20100212413 | Method for Determining Emission Values Of A Gas Turbine, And Apparatus For Carrying Out Said Method - A method for determining emission values of a gas turbine comprises the following steps: performing a test run of the gas turbine; determining operating parameters (T0, T4, T4*, NGG, output) of the gas turbine during the test run; determining first emission values (NOx) during the test run; storing a correlation (NOx(T4*)) between the operating parameters and the first emission values; and, during operation, determining operating parameters (T0, T4, T4*, NGG) of the gas turbine; and determining second emission values (NOx 15% O2 dry exhaust) corresponding to the stored correlation (NOx(T4*)) between the operating parameters and the first emission values. | 08-26-2010 |
| 20100288034 | SYSTEM AND METHOD OF ASSESSING THERMAL ENERGY LEVELS OF A GAS TURBINE ENGINE COMPONENT - An example method of assessing a component of a gas turbine engine includes monitoring debris in at least a portion of an engine and establishing an estimated thermal energy level for a component of the engine based on the monitoring. The method may use gas path parameters to establish the estimated thermal energy level. An example gas turbine engine component assessment system includes a debris monitoring system configured to monitor debris moving through a portion of an engine and a controller programmed to execute an engine deterioration model that assesses a thermal energy level of at least one component of the engine based on information from the debris monitoring system. | 11-18-2010 |
| 20100313639 | GAS TURBINE ENGINE DEBRIS MONITORING ARRANGEMENT - 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. | 12-16-2010 |
| 20110000287 | VALVE FAILURE DETECTION - A method and arrangement for detecting failure of an actuated component, particularly a valve. The method comprises determining a calibration step response and an in-use step response for the actuated component, determining any difference between the responses and comparing the difference to a pre-determined threshold indicating failure. | 01-06-2011 |
| 20110048116 | APPARATUS FOR EXPERIMENTAL INVESTIGATION OF AXIAL SEAL SYSTEMS OF GAS TURBINES - An apparatus for experimental investigation of axial seal systems of gas turbines includes a test structure having a test chamber, which is delimited by a first seal portion and by a second seal portion and extends along an axis. At least one of the first seal portion and the second seal portion is provided with a series of ribs transverse to the axis The first seal portion and the second seal portion are arranged facing each other so as to form an axial seal system according to the axis. Furthermore, the first seal portion and the second seal portion are at least partially made of a transparent material. | 03-03-2011 |
| 20110048117 | INSPECTION OF HOLES - A method of inspecting a hole in a component situated within an engine. The engine comprises a chamber configured to receive fluid from a fluid supply, and the component is in flow communication with the fluid supply via the chamber. The method comprises the steps of (i) delivering a test fluid via the chamber to the component to induce flow of the test fluid through the hole; (ii) deploying a sensor panel adjacent the component in the path of test fluid issuing from the hole, the sensor panel being sensitive to the impingement of the test fluid; and (iii) assessing the condition of the hole in dependence on the response of the sensor panel at the location corresponding to the hole. | 03-03-2011 |
| 20110138896 | TRANSDUCER ASSEMBLY - A transducer assembly ( | 06-16-2011 |
| 20110138897 | METHOD FOR TESTING GAS TURBINE ENGINES - A method for testing a cooling system for use in a gas turbine engine control system is provided. The method includes connecting an inlet of the cooling system to a differential pressure sensor, connecting an outlet of the cooling system to the differential pressure sensor, and determining whether or not a difference in pressure exists between the inlet and outlet, wherein such a pressure difference is indicative of whether cooling fluid is flowing through the cooling system. | 06-16-2011 |
| 20110259093 | METHOD FOR DETECTING RESONANCE IN A ROTOR SHAFT OF A TURBINE ENGINE - A method for detecting resonance in a rotor shaft of a turbine engine, the resonance frequency (Fr) of the said rotor shaft belonging to a resonance band centred on an estimated resonance frequency (Fr | 10-27-2011 |
| 20110308306 | DEVICE FOR MONITORING THE OBSTRUCTION OF AT LEAST TWO FILTERS OF A FLUID CIRCULATION SYSTEM OF AN AIRCRAFT GAS TURBINE ENGINE - A device for monitoring the obstruction of at least two fluid filters of a fluid circulation system of a gas turbine engine of an aircraft, the device comprising a first obstruction sensor, intended to monitor a first fluid filter, set up to send a first detection signal of an obstruction of the first filter and a processor comprising a monitoring input linked to said first sensor to measure the first detection signal. The device also comprises a second obstruction sensor, intended to monitor a second fluid filter, set up to send a second detection signal of an obstruction of the second filter, the monitoring input of the processor being connected to the first obstruction sensor to measure said second detection signal over a single monitoring input. | 12-22-2011 |
| 20120031177 | SEALING HEAD FOR AN INSTALLATION FOR FLUID TESTS ON AN AIRCRAFT TURBINE ENGINE PART - 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. | 02-09-2012 |
| 20120060594 | STRAIN INDICATOR FOR A GAS TURBINE ENGINE COMPONENT - 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. | 03-15-2012 |
| 20120085156 | DEVICE FOR CHECKING A TURBOMACHINE ENGINE - 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. | 04-12-2012 |
| 20120096933 | SENSOR WITH G-LOAD ABSORBING SHOULDER - 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. | 04-26-2012 |
| 20120096934 | COMMUNICATION SYSTEM FOR TURBINE ENGINE - A communication system is provided and includes a sensor to measure a condition at a point of measurement interest defined on a rotor of a turbine at a radial distance from a centerline about which the rotor is rotatable, wiring disposed on the rotor at a radial distance from the centerline, the wiring including a first wiring section coupled to the sensor, a second wiring section and a first connection by which the first and second wiring sections are connectable, a second connection by which the second wiring section transmits a signal reflective of the detected condition to a non-rotating recording element and a temperature compensation module disposed on the second wiring section to adjust the signal. | 04-26-2012 |
| 20120152007 | TESTING PERFORMANCE OF A MATERIAL FOR USE IN A JET ENGINE - An apparatus for testing failure of a material used in a jet engine, and more particularly to an apparatus that uses one or more miniature jet engine components made from a material used in a full-size jet engine and desired to be tested. The apparatus permits easy removal and disassembly of a jet engine mounted thereon as well as real-time measurements of run-time parameters. The methods and apparatus provide for predicting and analyzing failure by a number of fatigue-related mechanisms including creep, fatigue, crack growth, foreign object damage, fretting, erosion, and stress corrosion. The apparatus also permits testing of a component placed in the exhaust gases of a jet engine mounted therein. | 06-21-2012 |
| 20120192630 | Pulse Detonation Turbine Engine Using Turbine Shaft Speed for Monitoring Combustor Tube Operation - 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. | 08-02-2012 |
| 20120192631 | AXIAL LOADING DEVICE AND METHOD FOR MAGNETICALLY-SUPPORTED ROTOR SYSTEMS - 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. | 08-02-2012 |
| 20120216608 | SYSTEM FOR MEASURING PARAMETERS OF FLUID FLOW IN TURBOMACHINERY - 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. | 08-30-2012 |
| 20120240667 | METHOD FOR DETECTING THE FAILURE OF A FREQUENCY SENSOR, AND CIRCUIT FOR IMPLEMENTING SAID METHOD - 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 (S | 09-27-2012 |
| 20120279288 | Method of checking a wind turbine in a wind farm for a yaw misalignment, method of monitoring a wind turbine in a wind farm and monitoring apparatus - 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. | 11-08-2012 |
| 20120279289 | Method for Determining Emission Values Of A Gas Turbine, And Apparatus For Carrying Out Said Method - 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. | 11-08-2012 |
| 20120297864 | SYSTEMS AND METHODS FOR USE IN PROVIDING A SENSOR SIGNAL INDEPENDENT OF GROUND - 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. | 11-29-2012 |
| 20120324987 | IDMS SIGNAL PROCESSING TO DISTINGUISH INLET PARTICULATES - 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. | 12-27-2012 |
| 20120324988 | STATION PROBE FOR GAS TURBINE ENGINES - 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. | 12-27-2012 |
| 20130008242 | ABRASION SENSING DEVICE, WIND TURBINE GENERATION APPARATUS INCLUDING THE SAME, AND ABRASION SENSING METHOD - 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. | 01-10-2013 |
| 20130025351 | MASTER COMPONENT FOR FLOW CALIBRATION - 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. | 01-31-2013 |
| 20130025352 | METHODS FOR MONITORING WIND TURBINES - Monitoring method of a variable speed wind turbine ( | 01-31-2013 |
| 20130031966 | METHOD AND SYSTEM FOR DETERMINING A MASS CHANGE AT A ROTATING BLADE OF A WIND TURBINE - 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. | 02-07-2013 |
| 20130047714 | INSERT ASSEMBLY AND METHOD FOR FLUID FLOW REVERSE ENGINEERING - 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. | 02-28-2013 |
| 20130061664 | INSPECTION VEHICLE FOR A TURBINE DISK - 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. | 03-14-2013 |
| 20130074588 | POWER PLANT ANALYZER FOR ANALYZING A PLURALITY OF POWER PLANTS - A power plant analyzer for analyzing a plurality of power plants, comprising:
| 03-28-2013 |
| 20130091940 | Method and System for Determining Gas Turbine Tip Clearance - 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. | 04-18-2013 |
| 20130111982 | Systems and Methods For Use In Monitoring Operation Of A Rotating Component - 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. | 05-09-2013 |
| 20130125632 | DETERMINING AN ACCUMULATED LOAD OF A WIND TURBINE IN ANGULAR SECTORS - 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. | 05-23-2013 |
| 20130139578 | PRESSURE-MEASURING DEVICE AND PRESSURE-MEASURING METHOD FOR A TURBOMACHINE - 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. | 06-06-2013 |
| 20130160535 | Airflow Testing Method and System for Multiple Cavity Blades and Vanes - 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. | 06-27-2013 |
| 20130167624 | IMPACT LOAD MONITORING SYSTEM AND IMPACT LOAD MONITORING METHOD FOR WIND TURBINE FOR WIND POWER GENERATION - An impact load monitoring system for a wind turbine for wind power generation is provided with: an acceleration sensor | 07-04-2013 |
| 20130167625 | METHOD FOR OSCILLATION MEASURMENT ON ROTOR BLADES OR WIND POWER INSTALLATIONS - 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. | 07-04-2013 |
| 20130192353 | SYSTEM AND METHOD FOR AUTOMATED OPTICAL INSPECTION OF INDUSTRIAL GAS TURBINES AND OTHER POWER GENERATION MACHINERY WITH MULTI-AXIS INSPECTION SCOPE - 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. | 08-01-2013 |
| 20130199279 | GAS TURBINE DISC INSPECTION USING FLEXIBLE EDDY CURRENT ARRAY PROBE - 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. | 08-08-2013 |
| 20130213122 | COMPONENT TESTING AND METHOD FOR OPERATING A MACHINE - 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. | 08-22-2013 |
| 20130220004 | DEBRIS DETECTION IN TURBOMACHINERY AND GAS TURBINE ENGINES - 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. | 08-29-2013 |
| 20130220005 | WIND TURBINE BLADE, METHOD FOR MANUFACTURING WIND TURBINE BLADE, AND WIND POWER GENERATOR AND WIND TURBINE BLADE MONITORING SYSTEM INCLUDING WIND TURBINE BLADE - 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. | 08-29-2013 |
| 20130255363 | Detecting a Wake Situation in a Wind Farm - 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. | 10-03-2013 |
| 20130263651 | DETECTION AND CLASSIFICATION OF FAILURES OF POWER GENERATING EQUIPMENT DURING TRANSIENT CONDITIONS - 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. | 10-10-2013 |
| 20130269426 | TURBINE INSPECTION SYSTEM AND RELATED METHOD OF OPERATION - 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. | 10-17-2013 |
| 20130319092 | SHAFT BREAK DETECTION - 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. | 12-05-2013 |
| 20140000352 | METHOD AND DEVICE FOR MONITORING A SERVOVALVE ACTUATION SYSTEM | 01-02-2014 |
| 20140013836 | PMC LAMINATE EMBEDDED HYPOTUBE LATTICE - 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. | 01-16-2014 |
| 20140020458 | Method and Apparatus for Redundant Detection of a Rotational Direction - 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 (Digital | 01-23-2014 |
| 20140020459 | TESTING AN OVERSPEED PROTECTION SYSTEM OF A WIND TURBINE - 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. | 01-23-2014 |
| 20140053641 | APPARATUS AND PROCESS FOR TESTING AN INDUSTRIAL GAS TURBINE ENGINE AND COMPONENTS THEREOF - 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. | 02-27-2014 |
| 20140069177 | EPICYCLOIDAL MEASUREMENT SHAFT - A measuring rod capable of receiving a plurality of instrumentation cables transmitting data to a data processing device, includes a section of epicycloidal shape. | 03-13-2014 |
| 20140076037 | CAPACITANCE PROBE - 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. | 03-20-2014 |
| 20140076038 | CHECKING A BLADE CONTOUR OF A TURBOMACHINE - 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). | 03-20-2014 |
| 20140090456 | MODEL BASED ENGINE INLET CONDITION ESTIMATION - 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. The fault detection and accommodation system is configured to detect faults in inlet condition sensors, select sensed inlet conditions for use by the control laws in the event of no fault, and select estimated inlet conditions for use by the control laws in the event of inlet condition sensor fault. | 04-03-2014 |
| 20140090457 | METALIZED CERAMIC LEADING EDGE NOZZLE KIELS FOR HIGH-TEMPERATURE TURBINE APPLICATIONS - 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. | 04-03-2014 |
| 20140090458 | METHOD AND DEVICE FOR DETERMINING THE AIR BLEED ON AN AIRCRAFT TURBOJET ENGINE - 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. | 04-03-2014 |
| 20140096601 | METHOD AND DEVICE FOR MEASURING A PART IN A TURBINE ENGINE - 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. | 04-10-2014 |
| 20140116123 | TEST RIG - 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. | 05-01-2014 |
| 20140116124 | VIBRATION MONITORING - A health index ( | 05-01-2014 |
| 20140157880 | STATE DETECTION DEVICE FOR BEARING ROLLER, ROLLER BEARING DEVICE WITH SENSOR, AND WIND TURBINE GENERATOR - 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. | 06-12-2014 |
| 20140174162 | IGNITOR PLUG ISOLATION CHAMBER (IPIC) FOR A GAS TURBINE ENGINE - 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. | 06-26-2014 |
| 20140208837 | GAS TURBINE ENGINE VANE EMBEDDED BEAM INTERRUPT OPTICAL TIP-TIMING PROBE SYSTEM - 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. | 07-31-2014 |
| 20140260572 | Sensor Housing - 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. | 09-18-2014 |
| 20140260573 | VARIABLE GUIDE VANE DIGITAL BACKLASH MEASUREMENT - 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. | 09-18-2014 |
| 20140318226 | METHOD AND CALCULATOR UNIT FOR DETERMINING TOTAL DAMAGE TO AT LEAST ONE ROTATING COMPONENT OF A DRIVE TRAIN - 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. | 10-30-2014 |
| 20140326058 | ENGINE HEALTH MONITORING - A vehicle is provided that has a rigid dressing raft | 11-06-2014 |
| 20140331750 | MULTI-HOLE PROBES AND METHODS FOR MANUFACTURING MULTI-HOLE PROBES - 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. | 11-13-2014 |
| 20140331751 | EQUIPMENT MONITORING SYSTEM - The invention concerns an asset monitoring system ( | 11-13-2014 |
| 20140366613 | Probe Retention-Sealing Feature - 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. | 12-18-2014 |
| 20140373609 | OPTICAL MONITORING SYSTEM FOR A GAS TURBINE ENGINE - 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. | 12-25-2014 |
| 20150007641 | PHASED ARRAY TURBOMACHINE MONITORING SYSTEM - 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. | 01-08-2015 |
| 20150013440 | METHOD AND SYSTEM FOR DIAGNOSTIC RULES FOR HEAVY DUTY GAS TURBINES - 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. | 01-15-2015 |
| 20150027210 | APPARATUS AND PROCESS FOR MEASURING THE DEPTH OF A GROOVE IN A ROTOR OF A GAS TURBINE ENGINE - 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. | 01-29-2015 |
| 20150027211 | FLAME MONITORING OF A GAS TURBINE COMBUSTOR USING A CHARACTERISTIC SPECTRAL PATTERN FROM A DYNAMIC PRESSURE SENSOR IN THE COMBUSTOR - 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. | 01-29-2015 |
| 20150033836 | METHODS AND APPARATUS FOR INSPECTING COOLING HOLES - 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. | 02-05-2015 |
| 20150040650 | DEVICE FOR DETECTING ANOMALIES IN AN AIRCRAFT TURBINE ENGINE BY ACOUSTIC ANALYSIS - 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. | 02-12-2015 |
| 20150052985 | Method, Computing Unit and Device for Monitoring a Drive Train - 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. | 02-26-2015 |
| 20150068293 | METHOD AND DEVICE FOR MONITORING THE MALFUNCTION OF APU TURBINE VANE FRACTURE AND ROTOR SHAFT JAM - 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 δ 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 δ. | 03-12-2015 |
| 20150068294 | FLAME MONITORING OF A GAS TURBINE COMBUSTOR USING MULTIPLE DYNAMIC PRESSURE SENSORS IN MULTIPLE COMBUSTORS - 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. | 03-12-2015 |
| 20150075265 | MEASUREMENT DEVICE AND METHOD FOR EVALUATING TURBOMACHINE CLEARANCES - 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. | 03-19-2015 |
| 20150090017 | TURBINE BLADE-MOUNTED SENSOR FIXTURE FOR TIP GAP MEASUREMENT - 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. | 04-02-2015 |
| 20150096359 | METHOD FOR PREDICTING AN AUXILIARY POWER UNIT FAULT - 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. | 04-09-2015 |
| 20150101401 | Method And System For Determining Wind Turbine Reliability - 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. | 04-16-2015 |
| 20150107341 | METHOD AND SYSTEM FOR DETECTING SURFACE FEATURES ON TURBINE COMPONENTS - 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. | 04-23-2015 |
| 20150107342 | SYSTEMS AND METHODS FOR MONITORING ROTARY EQUIPMENT - 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. | 04-23-2015 |
| 20150107343 | METHOD FOR DETECTING A STATE CHANGE OF AN INSTALLATION - 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. | 04-23-2015 |
| 20150300324 | ELECTROMAGNETIC SHIELDING OF A STRAIN GAUGE IN A WIND POWER INSTALLATION - The present subject matter relates to a wind power installation having a strain gauge ( | 10-22-2015 |
| 20150308285 | WIND TURBINE DIAGNOSTIC DEVICE FOR GENERATOR COMPONENTS - A wind turbine diagnostic device for diagnosing mechanical damage to generator components of at least one wind turbine, comprising at least one speed sensor for determining a variation over time of the rotational speed of a generator of a wind turbine, the speed sensor having at least one speed signal output for outputting the determined variation over time of the rotational speed, a frequency analysis module and a frequency spectrum signal output for outputting a frequency spectrum, the frequency analysis module determining a frequency spectrum from the determined variation over time of the rotational speed, and a comparator element for comparing a frequency spectrum with a prescribed standard frequency spectrum and for diagnosing mechanical damage to generator components on the basis of the comparison. This increases the possibility of predicting mechanical damage to generator components caused by vibrations. | 10-29-2015 |
| 20150322863 | Localized Ignition Diagnostics - A system for a gas turbine engine includes an igniter event conductor. The igniter event conductor has a first portion adjacent an igniter of the engine and in a combustion chamber of the engine and a second portion apart from the igniter and apart from the combustion chamber. The conductor is adapted to conduct an aspect of an igniter event at the igniter from the first portion to the second portion. A sensor is coupled to the second portion of the conductor to sense the aspect of the igniter event. | 11-12-2015 |
| 20150346058 | METHODS FOR PRODUCING STRAIN SENSORS ON TURBINE COMPONENTS - Methods for manufacturing strain sensors on turbine components include providing a turbine component comprising an exterior surface, depositing a ceramic material onto a portion of the exterior surface, and ablating at least a portion of the ceramic material to form a strain sensor comprising at least two reference points. | 12-03-2015 |
| 20150355055 | IN-SITU SYSTEM AND METHOD OF DETERMINING COATING INTEGRITY OF TURBOMACHINERY COMPONENTS - The present disclosure relates generally to a method of operating an inspection system, including a sensor and heating element operably coupled to a control module, to determine in-situ a coating integrity for a turbomachinery component within a turbomachinery system, the method comprising the steps of: placing the sensor and heating element at a distance from the desired turbomachinery component to be examine, operating the heating element for a predetermined amount of time, operating the sensor to detect an output from a surface of the turbomachinery component, and operating the control module to compare the output with at least one integrity parameter. | 12-10-2015 |
| 20150377669 | METHOD AND SYSTEM FOR DETERMINING DISTRIBUTION OF TEMPERATURE AND VELOCITY IN A GAS TURBINE ENGINE - Techniques for determining temperature and velocity in a space inside a gas turbine engine ( | 12-31-2015 |
| 20160010505 | SYSTEM AND METHOD FOR INSPECTING TURBOMACHINES | 01-14-2016 |
| 20160010506 | SYSTEM AND METHOD FOR INSPECTING TURBOMACHINES | 01-14-2016 |
| 20160011078 | LINEAR ARRAY TO IMAGE ROTATING TURBINE COMPONENTS | 01-14-2016 |
| 20160011079 | SYSTEM AND METHOD FOR INSPECTING TURBOMACHINES | 01-14-2016 |
| 20160011080 | SYSTEM AND METHOD FOR INSPECTING TURBOMACHINES | 01-14-2016 |
| 20160018292 | GAS TURBINE INSPECTION APPARATUS AND METHOD AND SYSTEM FOR INSPECTING A GAS TURBINE - A method and a system for inspection of gas turbine are presented. An inspection tool is attached on a track which is permanently positioned on site with respect to the gas turbine. The inspection tool includes an extendible shaft with a proximal end attached on the track and a distal end carrying a sensor. The inspection tool moves along the track for accessing an inspection port of the gas turbine by the shaft. A control system is coupled to the inspection tool for controlling the inspection tool for the inspection of the gas turbine. The method and system enable an automated engine inspection which allows for the engine to have been inspected and reviewed by an engineer without having to send the engineer on site. | 01-21-2016 |
| 20160032898 | GENERATOR TEST BENCHES AND BACK-TO-BACK TESTING SYSTEMS AND METHODS - Generator test benches and back-to-back testing systems and methods are disclosed. A test bench ( | 02-04-2016 |
| 20160084233 | SYSTEMS AND METHODS FOR VALIDATING WIND FARM PERFORMANCE MEASUREMENTS - The present disclosure is directed to systems and methods for validating and/or identifying wind farm performance measurements so as to optimize wind farm performance. The method includes measuring operating data from one or more wind turbines of the farm. Another step includes generating a plurality of baseline models of performance of the wind farm from at least a portion of the operating data. Thus, each of the baseline models of performance is developed from a different portion of operating data so as to provide comparable models. The method also includes selecting an optimal baseline model and comparing the optimal baseline model with actual performance of the wind farm. In a particular embodiment, the actual performance of the wind farm is determined after one or more wind turbines of the wind farm is modified by one or more upgrades. | 03-24-2016 |
| 20160084736 | SYSTEMS AND METHODS FOR ATTACHING A PROBE TO A CASING OF A GAS TURBINE ENGINE - A system for attaching a probe to a casing of a gas turbine engine is disclosed. The system may include a probe receptacle attachable to the casing. The probe receptacle may include an internal bore, a bayonet slot, a spring disposed within the internal bore adjacent to the bayonet slot, and a sealing surface within the internal bore. The system also may include a probe attachment assembly disposed about the probe and configured to engage the probe receptacle. The probe attachment assembly may include at least one bayonet positionable within the bayonet slot and a seal positionable adjacent to the sealing surface within the internal bore. | 03-24-2016 |
| 20160103032 | ANOMALY DETERMINATION SYSTEM AND ANOMALY DETERMINATION METHOD - An anomaly determination system includes inlet and outlet pressure sensors for a pressure loss portion, an outside pressure sensor, and an anomaly determination section for determining an anomaly of the pressure loss portion. The anomaly determination section determines that the pressure loss portion is anomalous if the following two conditions are both met: a difference between the inlet pressure and the outlet pressure, a difference between the outlet pressure and the outside pressure, and a difference between the outside pressure and the inlet pressure which differences are detected when the flow rate is less than the minimum flow rate are all included in an allowable range; and a pressure difference between the inlet pressure and the outlet pressure when the flow rate is greater than or equal to the minimum flow rate is included in the first pressure loss range. | 04-14-2016 |
| 20160123307 | SYSTEM AND METHOD FOR WIND TURBINE OPERATION - A method for determining a flow condition includes disposing a plurality of sensors on a surface and receiving a first sensor signal and a second sensor signal from the plurality of sensors. The method further includes determining at least one correlation parameter based on the first sensor signal and the second sensor signal. The method also includes receiving a plurality of stored parameters from a database, wherein each of the plurality of stored parameters is representative of a corresponding flow condition. The method also includes comparing the at least one correlation parameter with the plurality of stored parameters and selecting at least one matching stored parameter and determining a matching flow condition based on the at least one matching stored parameter. | 05-05-2016 |
| 20160123729 | SENSOR ASSEMBLY FOR DETECTING POSITION OF SPRING-LOADED TARGET SURFACE AND METHOD OF DETECTING POSITION THROUGH MULTIPLE STRUCTURES - A sensor assembly includes a first structure and a second structure disposed radially outwardly of the first structure. Also included is a sensor body extending through the first and second structures, the sensor body having first and second ends, the first end disposed proximate a first environment defined by the first structure and the second end located radially outwardly of the second structure. Further included is a first sealing assembly configured to operatively couple the sensor body to the second structure and to accommodate movement of the sensor body. Yet further included is a position sensor operatively coupled to the sensor body, the position sensor configured to determine a position of a target located within the first interior volume. Also included is at least one biasing member in contact with the target to bias the target into constant operative contact with the sensor body. | 05-05-2016 |
| 20160123731 | ROTARY-TO-LINEAR CONVERSION FOR SENSOR ASSEMBLY AND METHOD OF DETECTING ANGULAR POSITION OF A TARGET THROUGH MULTIPLE STRUCTURES - A sensor assembly includes a first structure and a second structure disposed radially outwardly of the first structure. Also included is a sensor body extending through the first and second structures, the sensor body having first and second ends, the second end located radially outwardly of the second structure. Further included is a first sealing assembly configured to couple the sensor body to the second structure and to accommodate movement of the sensor body due to relative movement between the first and second structures. Yet further included is an interior cavity of the sensor body, a linear position sensor operatively coupled to the sensor body, and a rotary linkage assembly located within the interior cavity and coupled to a target. Also included is a rotary-to-linear interface disposed between the rotary linkage assembly and the sensor and configured to convert rotational motion of the rotary linkage assembly to linear motion. | 05-05-2016 |
| 20160123843 | SENSOR ASSEMBLY AND METHOD OF DETECTING POSITION OF A TARGET THROUGH MULTIPLE STRUCTURES - A sensor assembly includes a first structure and a second structure disposed radially outwardly of the first structure. Also included is a sensor body extending through the first and second structures, the sensor body having first and second ends, the second end disposed in an ambient environment. Further included is a sensor mounted to the sensor body proximate the second end, the sensor configured to detect a characteristic of a target disposed within the first structure. Yet further included is a first sealing assembly configured to operatively couple the sensor body to the second structure and to accommodate movement of the sensor body. The first sealing assembly includes a mounting body, a radial seal, a slider plate and a slider plate retainer disposed in a recess of the mounting body and in abutment with the slider plate. | 05-05-2016 |
| 20160123844 | VANE POSITION SENSOR INSTALLATION WITHIN A TURBINE CASE - A measuring system for sensing vane positions that comprises a turbine, a target, and a sensor. The turbine includes a plurality of articulating vanes, with each vane being coupled to a sync ring that is configured to position the plurality of articulating vanes in accordance with a degree of rotation by the sync ring. The target is coupled to a first position of the turbine within a first region that is associated with a first vane of the plurality of articulating vanes. The sensor is coupled via a bracket to a second position of the turbine within the first region. The sensor is configured to detect an orientation of the target that corresponds to a vane position of the first vane. | 05-05-2016 |
| 20160135279 | INSTRUMENTED ARTICLE HAVING COMPLIANT LAYER BETWEEN CONFORMAL ELECTRONIC DEVICE AND SUBSTRATE - An instrumented article includes a ceramic-based substrate and at least one conformal electronic device deposited on a surface of the ceramic-based substrate. A compliant layer is located between the ceramic-based substrate and the one or more conformal electronic devices. The compliant layer has a thermal expansion that is intermediate of the thermal expansions of, respectively, the ceramic-based substrate and the one or more conformal electronic devices. | 05-12-2016 |
| 20160146705 | STATE HOLDING AND AUTONOMOUS INDUSTRIAL SENSING DEVICE - A passive sensor is configured to detect one or more operational parameters of a gas turbine. The passive sensor is coupled to the gas turbine. The passive sensor is also configured to extract a portion of energy from the one or more operational parameters to utilize for operation, store an indication of a value of the one or more operational parameters, transition from a first mechanical state to a second mechanical state according to the value of the one or more operational parameters, and to provide a signal in response to receiving an interrogation signal. The signal comprises the indication of the value of the one or more operational parameters. | 05-26-2016 |
| 20160153865 | GAS TURBINE ENGINE AIRFOIL GROWTH INSPECTION METHOD | 06-02-2016 |
| 20160177776 | OPTICAL MEASUREMENT SYSTEM FOR DETECTING TURBINE BLADE LOCKUP | 06-23-2016 |
| 20160178464 | TORQUE SENSOR MONITORING FOR GAS TURBINE ENGINE | 06-23-2016 |
| 20160194977 | TURBINE ENGINE SHAFT BREAK DETECTION | 07-07-2016 |
| 20160376949 | LUBRICANT VALVE MONITORING METHOD AND ASSEMBLY - An exemplary method of monitoring a position of a lubricant valve in a gas turbine engine includes monitoring a position of a lubricant valve using a first auxiliary pressure reading and a second auxiliary pressure reading. The first auxiliary pressure reading is taken when a primary lubrication circuit is at a first pressure. The second auxiliary pressure reading is taken when the primary lubrication circuit is at a second pressure. An exemplary assembly that detects transitions of a lubricant valve in a gas turbine engine includes a controller that uses readings of the primary pressure and readings of the auxiliary pressure to detect a position of a lubricant valve. | 12-29-2016 |
| 20170234304 | CONDITION MONITORING SYSTEM AND WIND POWER GENERATION SYSTEM COMPRISING THE SAME | 08-17-2017 |
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