Abstract: A method, as applied to a program-controlled measuring instrument, determines an observable property of an object. The program-controlled measuring instrument has a diagnostic measurement program that is executed by a user. The diagnostic measurement program stores data related to the execution of the diagnostic measurement program and maintains the data for remote transmission to a remote service entity.

Abstract: An ECM executes a catalyst early activation control at the cold start of an engine such that the activation of a catalyzer is promoted by opening a WGV. Further, the ECM performs a diagnosis process of diagnosing whether or not the WGV is stuck closed, based on the amplitude of the output fluctuation in an air-fuel-ratio sensor during execution of the catalyst early activation control.

Abstract: A system for predicting a surge of a centrifugal refrigeration compressor including a signal capturing module for capturing at least two signals relevant to the centrifugal refrigeration compressor; a feature extracting module defining a window period for extracting data of the at least two signals, and defining at least two feature functions respectively acting on the data in the window period of the at least two signals; and, a feature analyzing and deducing module calculating a feature value for each of the signals to map a probability value of surge prediction for each of the signals, and concluding, based on the probability value of the surge prediction of each of the signals, a final probability value to determine whether or not the surge will occur to the centrifugal refrigeration compressor.

Abstract: Systems and method for filling a fuel manifold comprising at least a primary and a second manifold of a gas turbine engine are described. The method comprises providing fuel flow to the secondary manifold of the gas turbine engine, the secondary manifold being partly or completely empty; monitoring at least one engine operational parameter of the gas turbine engine as fuel fills the secondary manifold; and accelerating the engine when a transition threshold is reached, the transition threshold being associated with the engine operational parameter and indicative that fuel has reached the combustor.

Abstract: A method for in-flight monitoring of the health of an aero gas turbine engine including in flow series a compressor system, a core gas generator including a combustor, and a turbine, and further including a shaft system connecting the turbine to the compressor system and forming a torque path there between. The method includes: measuring a first rotational speed of a forward portion of the shaft system; measuring a second rotational speed of a rear portion of the shaft system; measuring other operational parameters of the engine; calculating from the measured rotational speeds the power delivered by the torque path from the turbine to the compressor system; calculating from the other measured operational parameters the power delivered to the turbine by the core gas generator; correlating the power delivered by the torque path at a given time with the power delivered to the turbine at that time.

Abstract: In one example embodiment, a gas turbine system includes a gas turbine, a compressor bleed valve, various sensors, and a valve health assessment system. The compressor bleed valve bleeds a portion of air received by the compressor during certain operating modes. The valve health assessment system includes a processor that uses a neural network model to generate a first failure mode predictor of the compressor bleed valve by processing operational data provided by the various sensors. The processor also generates a second failure mode predictor of the compressor bleed valve by using empirical data and a valve transfer function. The processor further generates a third failure mode predictor of the compressor bleed valve by using predictive data and a prediction model. The processor then applies a holistic procedure to the three failure mode predictors to derive a probability of occurrence of a failure in the compressor bleed valve.

Abstract: Based on entry/exit pressures of compressor 2a detected by atmospheric/boost pressure sensors 13 and 14, pressure ratio of compressor is calculated. Based on mass flow rate and entry temperature of intake air 4 detected by intake air flow-rate/temperature sensors 15 and 16 and entry pressure, volumetric flow rate of intake air is calculated in environmental condition at detection time using gas state equation, and is corrected into volumetric flow rate under standard environmental condition thorough multiplication by corrective coefficient based on entry temperature of intake air. Based on corrected value and calculated pressure ratio, rotational frequency of compressor under standard environmental condition is read out in light of operating characteristic diagram for compressor.

Abstract: Systems and methods for continuous pressure change monitoring in turbine compressors. In one embodiment, a system can be provided. The system can include a dynamic pressure sensing device mounted to the turbine compressor. The dynamic pressure sensing device may be configured to provide continuous dynamic pressure data, which may be associated with one or more pressure change events. The system may further include a memory configured to store the continuous dynamic pressure data, and a processor configured to correlate the one or more pressure change events with one or more component failures of the turbine compressor, and, based at least in part on the correlation, diagnose the one or more component failures.

Abstract: A system and method for monitoring and diagnosing anomalies in an output of a gas turbine, the method including storing a plurality rule sets specific to a performance of the gas turbine. The method further including receiving real-time and historical data inputs relating to parameters affecting the performance of the gas turbine, periodically determining current values of the parameters, comparing the initial values to respective ones of the current values, determining a degradation over time of the at least one of the performance of the compressor, the power output, the heat rate, and the fuel consumption based on the comparison, recommending to an operator of the gas turbine a set of corrective actions to correct the degradation.

Abstract: Systems and methods for measuring fouling in a gas turbine compressor include a conductivity resistance sensor disposed in a compressor inlet mouth. The degree of compressor fouling is correlated to changes in resistance measured by the conductivity resistance sensor. Measurements of resistance changes are converted to an indicia of fouling and used to trigger cleaning of the compressor.

Abstract: An inspection arrangement including an inspection element and a positioning tool for positioning the inspection element, the inspection element being attachable to the positioning tool by an attachment arrangement, and having a fixing element to present the inspection element in use, the fixing element including a plurality of radially extending resilient elements.

Abstract: A turbomachine includes a fan having a housing and a plurality of vanes rotatable within the housing. Each of the plurality of vanes includes a pressure side and a suction side. A pressure sensing system includes at least one pressure sensor mounted to one of the pressure side and the suction side of one or more of the plurality of vanes, and a pressure sensor receiver mounted to the housing. The at least one pressure sensor is configured and disposed to communicate pressure data to the pressure sensor receiver.

Abstract: Systems and methods for continuous pressure change monitoring in turbine compressors. In one embodiment, a system can be provided. The system can include a dynamic pressure sensing device mounted to the turbine compressor. The dynamic pressure sensing device may be configured to provide continuous dynamic pressure data, which may be associated with one or more pressure change events. The system may further include a memory configured to store the continuous dynamic pressure data, and a processor configured to correlate the one or more pressure change events with one or more component failures of the turbine compressor, and, based at least in part on the correlation, diagnose the one or more component failures.

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

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

Abstract: A method for similitude testing of a turbomachine, the method comprising selecting a test gas having a molecular weight between 40 g/gmol and 150 g/gmol, a global warming potential (GWP) of less than 700, and a gas specific heat ratio of between 1 and 1.5; operating the turbomachine using the selected test gas; identifying at least one parameter while operating the turbomachine; establishing at least one test parameter associated with the at least one parameter; and comparing the at least one test parameter with a corresponding at least one specified parameter to determine whether the turbomachine has passed the similitude test.

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: A test device for a compressor has a valve and ducting connected to the valve. A flow nozzle connected to the ducting has a corresponding coefficient of flow. A pressure sensor connected to the flow nozzle measures a pressure of a working fluid, and a flow rate of the working fluid is calculated using the pressure and the coefficient of flow. A method for testing a compressor includes operating the compressor at a first power level, measuring a flow rate of a working fluid at the first power level, adjusting a pressure of the working fluid to equal a first predetermined pressure, and measuring operating parameters of the compressor at the first power level. The method also includes adjusting the pressure of the working fluid to equal a second predetermined pressure and measuring operating parameters of the compressor at the first power level with the pressure of the working fluid at the second predetermined pressure.

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: 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: A method (and corresponding apparatus) for monitoring gas turbine blades. The output from an eddy current sensor monitoring the movement of turbine blades past the sensor is processed to determine when the signal train from the sensor omits a signal or pulse corresponding to one of the shaft's full complement of blades. The signal processor compares sensed blade periods with average blade periods.

Abstract: A method for similitude testing of a turbomachine, the method comprising selecting a test gas having a molecular weight between 40 g/gmol and 150 g/gmol, a global warming potential (GWP) of less than 700, and a gas specific heat ratio of between 1 and 1.5; operating the turbomachine using the selected test gas; identifying at least one parameter while operating the turbomachine; establishing at least one test parameter associated with the at least one parameter; and comparing the at least one test parameter with a corresponding at least one specified parameter to determine whether the turbomachine has passed the similitude test.

Abstract: An apparatus includes an operating conditions module that interprets a number of compressor operating parameters; a compressor flow module that determines a compressor inlet flow in response to the number of compressor operating parameters; and a fresh air flow module that provides a fresh air flow value in response to the compressor inlet flow. The operating conditions module further interprets a current mass air flow value, and the apparatus further includes a mass air flow sensor trimming module that adjusts a mass air flow sensor drift value in response to the current mass air flow value and the fresh air flow value. The apparatus includes a diagnostics module that determines a mass air flow sensor is failed in response to the current mass air flow value and the fresh air flow value.

Abstract: The present application provides a method of monitoring a compressor. The method may include the steps of determining a blade passing frequency, determining a power indication for a number of frequencies above and below the blade passing frequency, determining a ratio between a maximum power indication and a minimum power indication for the frequencies for a number of predetermined time intervals, and analyzing the ratio for each predetermined time interval to predict a surge condition of the compressor.

Abstract: A mechanical drive train for testing a full scale compressor rig is disclosed. The drive train can include an electric motor, a gear box, and a gas turbine. The compressor rig is coupled to the drive train between the gear box and gas turbine. The drive train can further include a torque converter for transferring torque from the electric motor to the compressor rig. The drive train is configured to test a full scale compressor rig over the entire speed and load operating range, allowing for full compressor mapping from choke to stall at full load, part load (power turn down) and partial speed conditions. The drive train can also be used to test a compressor rig or gas turbine over the full range of operability for the compressor rig or gas turbine without having to connect the gas turbine to the power grid at the power generation site.

Abstract: Certain embodiments of the invention may include systems and methods for compensating fuel composition variations in a gas turbine. According to an example embodiment of the invention, a method is provided for compensating for fuel composition variations in a turbine. The method can include: monitoring at least one fuel parameter associated with a turbine combustor; monitoring one or more combustion dynamics characteristics associated with the turbine combustor; monitoring one or more performance and emissions characteristics associated with the turbine; estimating fuel composition based at least in part on the at least one fuel parameter, the one or more combustion dynamics characteristics, and the one or more performance and emissions characteristics, and adjusting at least one fuel parameter based at least in part on the estimated fuel composition.

Abstract: An inner bleed structure of the 2-shaft gas turbine includes a slit for leading part of compressed air to a cavity is formed between a wall surface of a rotor wheel of the compressor equipped with a last stage rotor of the compressor which is connected to a first rotating shaft and end of an inner casing, and a bleed hole for leading part of compressed air after flowing down the last stage of the compressor to a cavity formed in the inner side of the inner casing at the downstream side of the last stage of the compressor.

Abstract: In one embodiment, a blade monitoring system includes: at least one computing device configured to monitor a compressor during a load change by performing actions comprising: extracting a dynamic component of a blade time-of-arrival (TOA) deviation signal in response to the load change on the compressor; calculating, using the dynamic component, at least one of: a natural frequency of the GT compressor blade during the load change, an overshoot of the GT compressor blade during the load change, a rise time of the compressor blade during the load change, a damping factor of the compressor blade during the load change, or a settling time of the GT compressor blade after the load change; and determining whether the GT compressor blade is damaged based upon the at least one of: the natural frequency, the overshoot, the rise time, the damping factor, or the settling time.

Abstract: An example method of estimating gas turbine engine performance deterioration includes monitoring debris in at least a portion of an engine and estimating performance deterioration of at least one component of the engine using information from the monitoring. The method may use gas path parameters, such as pressures, temperatures, and speeds to establish the estimated performance deterioration. An example gas turbine engine performance assessment system includes a debris monitoring system configured to monitor debris moving through a portion of an engine and a controller programmed to estimate performance deterioration of at least one component of the engine based on information from the debris monitoring system.

Abstract: A method and apparatus for conducting dynamic characterization of a gas turbine engine which involves generating exciting pressure pulses and measuring responses in the engine, and, in one aspect, then analyzing the measured response for engine dynamic characteristics.

Abstract: A method for monitoring a compressor comprising a rotor is presented. The method comprises obtaining a dynamic pressure signal of the rotor, obtaining a blade passing frequency of the rotor, using the blade passing frequency signal for filtering the dynamic pressure signal, buffering the filtered dynamic pressure signal over a moving window time period, and analyzing the buffered dynamic pressure signal to predict a stall condition of the compressor.

Abstract: A method (and corresponding apparatus) for monitoring gas turbine blades. The output from an eddy current sensor monitoring the movement of turbine blades past the sensor is processed to determine when the signal train from the sensor omits a signal or pulse corresponding to one of the shaft's full complement of blades. The signal processor compares sensed blade periods with average blade periods.

Abstract: A method (and corresponding apparatus) for monitoring the rotational speed of the shaft of a gas turbine having a number of spaced blades on or rotating with the shaft. The invention compensates for the errors which arise from the relative movement of turbine blade tips by deriving a correction factor for each blade and continually updating that correction factor.

Abstract: A method and apparatus for conducting dynamic characterization of a gas turbine engine which involves generating exciting pressure pulses and measuring responses in the engine, and, in one aspect then analyzing the measured response for engine dynamic characteristics.