A system and method for generating input signals for an electronic engine control module includes a first waveform generator that is configured to generate a simulated first speed signal that is representative of a first speed and a vibration modulating signal that is representative of the first speed, a second waveform generator that is synchronized with the first waveform generator is configured to receive the vibration modulating signal and to generate a simulated second speed signal that is representative of a second speed and a simulated composite vibration voltage signal, and a voltage-to-charge converter that is configured to receive the simulated composite vibration voltage signal from the second waveform generator and to generate a simulated composite vibration charge signal that simulates a speed/vibration composite signal from an accelerometer.

A method of controlling a gas turbine engine includes the steps of: detecting a shaft break event in a shaft connecting a compressor of the gas turbine engine to a turbine of the gas turbine engine; and in response to this detection, activating a shaft break mitigation system which introduces a fluid into a gas flow of the gas turbine engine downstream of the turbine, or increases an amount of a fluid being provided into the gas flow of the gas turbine engine downstream of the turbine, whereby the fluid reduces an effective area of a nozzle for the gas flow so as to reduce the mass flow rate of the gas flow through the turbine.

The invention relates to a monitoring system for a gas turbine, in particular for an aircraft engine. The monitoring system comprises at least one borescope device that is able to be mounted in a borescope opening of a gas turbine housing and has a housing, in which at least one optical sensor device for acquiring images of at least one inner region of the gas turbine is arranged, and an evaluation device that is able to be connected to the at least one borescope device in order to exchange data and is designed to inspect the at least one inner region for the presence of a fault on the basis of the at least one image acquired by way of the sensor device. The invention furthermore relates to a borescope device to an evaluation device and to a gas turbine.

A system and method for determining performance of an engine is provided. The system includes two or more sensors configured in operable arrangement at two or more respective positions at a flowpath. The system includes one or more computing devices configured to perform operations, the operations include acquiring, via the two or more sensors, parameter sets each corresponding to two or more engine conditions different from one another, wherein each parameter set indicates a health condition at a respective location at the engine; comparing, via the computing device, the parameter sets to determine the respective health condition corresponding to the respective location at the engine; and generating, via the computing device, a health condition prediction based on the compared parameter sets.

A system and method for predicting a remaining oil life of oil in a gearbox of an air turbine starter of a vehicle. The method includes generating a temperature data, generating an environmental data set by an environmental sensor, predicting a remaining oil life based on the temperature data set and the environmental data set and scheduling a maintenance event in response to the prediction of the remaining oil life.

A method and controller for operating a pumping station. The method includes receiving (1102), by at least one controller (910, 952), sensor data (712) of a first pumping station (900) corresponding to a liquid being transported from the first pumping station (900). The method includes predicting (1104) arrival of the liquid, by the at least one controller (910, 952), at a second pumping station (900). The method includes executing (1106) one or more pump models (720), by the at least one controller (910, 952), according to the sensor data (712) to determine an optimal pumping configuration. The method includes operating (1108) one more pumps of the second pumping station (900), by the at least one controller (910, 952), according to the optimal pumping configuration.

A method for designing and/or controlling a filter assembly for the air supply to a turbomachine includes: calculating a current and/or an expected concentration of particles in air present at an inlet of at least one filter stage of the filter assembly as a function of a mean size of the particles; calculating a sensitivity spectrum that, depending on the mean size of the particles, indicates an extent to which a predetermined concentration of such particles has a negative effect on performance and/or on service life of the turbomachine; calculating, for at least one filter candidate usable in the filter stage and/or switchable on or off, a concentration of particles to be expected at an outlet of the filter from a concentration and filter properties of the at least one filter candidate; and calculating a quality rating from the concentration and a sensitivity spectrum.

Variable geometry turbines having new configurations of vanes are disclosed. New methods for designing new configurations of vanes for geometry turbines having are also disclosed.

A method of evaluating compliance of a component of an aircraft engine with flow requirements has: obtaining experimental data from experimental testing on a prototype of the component; obtaining a digitized model of a production model of the component, the digitized model including digitized apertures having geometrical data corresponding to that of apertures defined in the production model; computing a nominal mass flow rate through the digitized apertures using the geometrical data and flow parameters from the experimental data; correcting the nominal mass flow rate of the digitized model to obtain a computed mass flow rate of the production model; and assigning at least one parameter to the production model, the at least one parameter indicative of installation approval of the production model of the component for installation on the aircraft engine when the computed mass flow rate is determined to be within a prescribed range of the flow requirements.

Provided is a startup control device for adjusting a startup schedule during startup of a power generation plant. This startup control device is provided with: a determining unit which, for a prescribed physical quantity that restricts the startup of the power generation plant, determines, on the basis of a predicted value of a physical quantity corresponding to the elapsed time from startup when the power generation plant has started up on the basis of a prescribed optimal startup schedule, and an observed value of the physical quantity acquired during the startup of the power generation plant, whether the observed value will exceed the predicted value; a speed adjusting unit which, if the determining unit determines that the observed value will exceed the predicted value, issues an instruction to decelerate the speed of progress of elapsed time from the startup in the optimal startup schedule; and a startup timer which progresses the elapsed time from the startup at a speed based on the instruction.