A method (400) of measuring rotor blade tip deflections of turbomachine rotor blades (R.sub.1, R.sub.2) during operation using Blade Tip Timing (BTT) includes measuring (402), by a proximity sensor (202), a proximity signal caused by a moving rotor blade (R.sub.1, R.sub.2) and determining (412), by a control module (212), a Time-of-Arrival (ToA). The method (400) includes measuring a time that the shaft starts to rotate a measurable angular distance and a time the shaft has completed its rotation of the measurable distance and storing (406) timing data indicative of a plurality of ToA measurements of the rotor blade (R.sub.1, R.sub.2) and the zero crossing times. The method (400) includes determining the shaft Instantaneous Angular Position (IAP) between at least two zero crossing times, which determination comprises expressing the shaft IAP between at least two zero crossing times as a continuous, non-constant IAP mathematical function of time, with unknown function coefficients and calculating the unknown function coefficients of the IAP mathematical function.

The method can include: monitoring a current value of a rate of reduction of torque of the shaft; providing a threshold value for the rate of reduction of torque of the shaft; and generating a signal indicative of the shaft shear event when the current value exceeds the threshold value.

An architecture for controlling and/or monitoring at least one actuator of a mobile cowl of a thrust reverser equipping a nacelle, the actuator being driven by at least one engine, includes at least one engine sensor to provide its control according to instructions, the architecture including an electronic control system to process at least one piece of information generated by the engine sensor and to calculate, using at least this same piece of information, the position of the mobile cowl of the thrust reverser.

A computer-implemented method comprising: receiving an operability determination for a compressor of a gas turbine engine, the operability determination being determined using an output from a machine learning algorithm trained using data quantifying damage received by compressor blades of a compressor; determining one or more actions to be performed using the received operability determination; and generating control data using the determined one or more actions.

A system and computer-implemented method of determining an acceleration of an engine are provided. The system comprises a processor and a memory comprising instructions stored thereon which when executed by the processor cause the system to perform a method of determining an acceleration of an engine. The method comprises obtaining and storing zero-crossing timestamps in a buffer, determining angular displacement times of the shaft based on the timestamps, applying a conversion factor to the angular displacement times, determining an acceleration of a shaft based on the angular displacement, and causing a fuel flow to the engine to be adjusted as a function of the acceleration as determined. The zero-crossing timestamps correspond to an angular displacement of a shaft associated with the engine. The zero-crossing timestamps are obtained using an angular displacement measurement device. The conversion factor corresponds to an angular displacement of the shaft.

An architecture for controlling and/or monitoring at least one actuator of a mobile cowl of a thrust reverser equipping a nacelle, the actuator being driven by at least one engine, includes at least one engine sensor to provide its control according to instructions, the architecture including an electronic control system to process at least one piece of information generated by the engine sensor and to calculate, using at least this same piece of information, the position of the mobile cowl of the thrust reverser.

A method (400) of measuring rotor blade tip deflections of turbomachine rotor blades (R.sub.1, R.sub.2) during operation using Blade Tip Timing (BTT) includes measuring (402), by a proximity sensor (202), a proximity signal caused by a moving rotor blade (R.sub.1, R.sub.2) and determining (412), by a control module (212), a Time-of-Arrival (ToA). The method (400) includes measuring a time that the shaft starts to rotate a measurable angular distance and a time the shaft has completed its rotation of the measurable distance and storing (406) timing data indicative of a plurality of ToA measurements of the rotor blade (R.sub.1, R.sub.2) and the zero crossing times. The method (400) includes determining the shaft Instantaneous Angular Position (IAP) between at least two zero crossing times, which determination comprises expressing the shaft IAP between at least two zero crossing times as a continuous, non-constant IAP mathematical function of time, with unknown function coefficients and calculating the unknown function coefficients of the IAP mathematical function.

A turbomachine train with two shaft parts which each have a fixedly attached grooved wheel, with a first overrunning clutch, with two rotational speed sensors and with a control device. The clutch is designed to couple and decouple the first shaft part to and from the second shaft part. The first rotational speed sensor measures the rotational speed of the first grooved wheel. The second rotational speed sensor measures the rotational speed of the second grooved wheel. The control device determines the differential angle between the first shaft part and the second shaft part and accelerates the turbomachines, with an acceleration value determined on the basis of the measured rotational speeds and on the basis of the differential angle, such that the two shaft parts couple together at a predetermined target coupling angle.

Various embodiments of the present application provide one or more of: (1) auxiliary wheel that (a) enables accurate speed detection of a turbine disc and/or (b) presents a machining surface for balance correction; and/or (2) techniques for mounting an auxiliary wheel to a rotor, such as a turbine disc.

An assembly is provided for a turbine engine. This turbine engine assembly includes a rotating assembly and a sensor. The rotating assembly is configured to rotate about an axis. The rotating assembly includes an engine shaft and a stack nut threaded onto the engine shaft. The stack nut includes a castellated periphery. The sensor is configured to measure fluctuations in a magnetic field induced by the castellated periphery during rotation of the rotating assembly about the axis.