Abstract: A method for measuring a thrust margin of a turbomachine, in which data are acquired including the thrust margin which is determined as a function of a specified thrust and a measured thrust, the measured thrust being determined on a measuring bench which includes a bench equipment and on which the turbomachine is, wherein a time evolution of the thrust margin is modelled by at least one linear or affine function which is calculated for at least one determined time interval of the thrust margin, at least one bias of the bench equipment is calculated relative to at least one linear or affine function having been calculated, the thrust margin is corrected by subtracting from it at least one bias of the bench equipment in at least one determined time interval.

Abstract: A turbine analysis device includes a state quantity acquiring unit configured to acquire a state quantity of a turbine, the state quantity including at least a temperature of the turbine. A load specifying unit is configured to calculate a history of a load of the turbine, based on the state quantity. A load and time calculating unit is configured to derive a relationship between the load of the turbine and an operable time when the turbine is operated at the load, based on a designed service life of the turbine and the history of the load that has been calculated by the load specifying unit.

Abstract: A method and system for establishing sets of blade frequency values for each rotating blade of a rotor assembly at two or more different points in time and determining an indication of blade health from the change in the blade frequency values is provided. Blade frequency values are determined by receiving measurements of vibratory responses from blade monitoring equipment (20) and processing via a processing device (30) vibration data as a system of rotating blades to extract a frequency of each blade. Sets of blade frequency values are compared to determine a change in the blade frequency values for each rotating blade to provide the indication of blade health.

Abstract: The present invention relates to a method and device for monitoring performance of an auxiliary power unit (APU) turbine efficiency of an aircraft. The method comprises: obtaining APU messages at multiple time points within a period; obtaining APU startup parameters including at least a rotation speed at a peak of EGT according to the APU messages; calculating a percentage NPA of the rotation speed when the exhausting gas temperature EGT reaches its peak at the APU startup stage relative to the rotation speed in the APU normal operation; calculating the average of the NPA within the period; and determining which of the stable, decline and failure phases the APU turbine efficiency is in according to the average of the NPA.

Abstract: Systems and methods for implementing engine cycle counts are disclosed. One method may include determining, by at least one processor, a plurality of cycles associated with an engine; determining a category, by at least one processor, for each of the plurality of cycles based at least in part on an acceleration value associated with each of the plurality of cycles; and predicting, by at least one processor, a life cycle associated with the engine based at least in part on the determined category.

Abstract: Method for verification of age-depth relationships of rocks in sedimentary basins by reconstructing the subsistence rate of samples, in which, by determining the precipitation depth and precipitation temperature of a carbonate precipitation, wherein by determining the precipitation depth and the precipitation temperature of the carbonate precipitation in the geological-history-determining sedimentary rocks, from which a sample is taken, a set point is fixed.

Abstract: A system and methods for the condition based lifing of a gas turbine engine component is disclosed. The system and methods determine the stress and caused by fatigue and creep for each load cycle of the gas turbine engine, and use a ductility exhaustion method to combine the fatigue and creep strain rates determined from the fatigue and creep stresses to determine the remaining useful of the gas turbine engine component.

Abstract: A method of initializing speed sensors in a rotational system is used determine a sensor spacing. An indexing feature is identified at each of two locations on an outer circumference of a wheel path corresponding to two speed sensors, as well as the speed of the wheel. The spacing of the sensors is then determined.

Abstract: A method tracking positive displacement efficiency of a high pressure positive displacement pump in a hydraulic regulator system of a turbomachine delivering a flow rate based on an engine speed of the turbomachine, the flow rate delivered to an actuator actuating variable geometry vanes of the turbomachine and to a bypass valve feeding engines of the turbomachine, the method including: starting engines of the turbomachine at a low engine speed, the valve being closed; using a computer to order a movement of the actuator; progressively increasing the engine speed until the flow rate reaches a predetermined value sufficient for opening the valve; storing in the computer a position of the actuator and the engine speed corresponding to opening of the valve; repeating the preceding operations at successive instants during a lifetime of the engines; and replacing the high pressure positive displacement pump when the engine speed exceeds a predetermined value.

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

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

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

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

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

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

Abstract: A method of more accurately measuring steam turbine efficiency is disclosed in which the sealing steam in the steam turbine is re-routed so that a more accurate measure of steam turbine efficiency can be made. Some of the steam entering a turbine goes into the turbine's end pack and then mixes with the steam that goes through the turbine. Piping is added from one of the end pack line's to the condenser. This added line has a valve, pressure, temperature and flow measuring devices. As the valve is opened, the amount of flow going to the end pack line allowing the end pack steam mix with the steam that goes through the turbine is reduced. As the flow in this line is reduced the measured temperature at the turbine exhaust will also decrease. The amount that the valve is opened is increased until either the exhaust temperature has reached a minimum, or the enthalpy in the pipe changes from the initial enthalpy.

Abstract: A solution for measuring steam quality in a steam turbine is disclosed. A steam quality measurement (SQM) device and an ejector are coupled to a steam turbine through an appropriate piping configuration to draw steam emitted from the turbine through the SQM device for measurement of the steam quality, for example, continuously, during operation of the turbine.

Abstract: A method comprises the step of quantifying an improvement in a gas turbine engine operation after a cleaning of the engine. A computer-readable medium, and a system for performing the method are also disclosed.

Abstract: A method for determining a suction mass flow of a gas turbine is provided. A turbine inlet pressure, a combustion chamber pressure loss and a pressure loss between an environment and a compressor inlet are determined as input parameters. For each input parameter a provisional value for the suction mass flow is ascertained and for each provisional value a validated value by cross-balancing with the other provisional values is ascertained. A characteristic quantity of the suction mass flow of the gas turbine is generated as an average value from the validated values. The suction mass flow is determined without solving energy balances, without information relating to a fuel calorific value, and without information relating to a fuel mass flow.

Abstract: Disclosed is a method and system for determining composition of a fuel entering a combustor. The method includes determining a temperature of the fuel entering the combustor, calculating a first estimated total fuel flow utilizing fuel properties and fuel nozzle effective area (Ae), and calculating a second estimated total fuel flow utilizing an aero-thermal cycle model analysis. The first estimated total fuel flow is compared to the second estimated total fuel flow and a lower heating value of the fuel is determined from a difference between the first estimated total fuel flow and the second estimated total fuel flow. A method and system for controlling a gas turbine includes calculating effects of the fuel composition on performance of the gas turbine and comparing one or more performance parameters to one or more parameter limits. One or more machine controls of the gas turbine are changed based on the results of the comparison.

Abstract: A method and system for recreating a two-dimensional distribution of temperatures in an exhaust plane of a gas turbine engine. Light transmission and detection pairs may be arranged in the annulus of the exhaust of the turbine engine in such a way that the individual rays form a two-dimensional mesh of beams across a sector of the exhaust. Based on the absorption of the rays, the temperature of the sector of the exhaust thru which the ray passes may be determined. Based on these determinations, an image that corresponds to the operation of the turbine engine may be generated.

Abstract: A method and system is described that estimates gas turbine engine module performance changes from gas path measurement data using a linear predictor-corrector estimation process. A measurement configuration matrix MC and a fault configuration FC matrix are assembled. The configuration matrices MC and FC are used to adapt a typical linear predictor-corrector type of performance estimation process to a given measurement suite and are ideally suited for linear estimation systems such as those using a Kalman filter.