A pump assembly method and computer program are disclosed. The pump assembly comprises: a pump, an associated motor controller and an accelerometer mounted on the pump. The motor controller is configured to control power supplied to drive the pump and to receive data output from the accelerometer, the motor controller comprising processing circuitry configured to process the data received from the accelerometer to determine accelerations experienced at the pump due to the pump operation. These accelerations can be used to determine a condition of the pump.

Systems and methods for measuring a clearance between a rotating machine component and a sensor unit are disclosed. In some aspects, a system includes a sensor unit oriented to detect the rotating machine component as the rotating machine component rotates past the sensor unit, the sensor unit including at least a first sensing element and a second sensing element spaced apart from the first sensing element. The system includes a sensor processing unit in electrical communication with the sensor unit. The sensor processing unit is configured for receiving a first waveform from the first sensing element; receiving a second waveform from the second sensing element; and determining, based on a comparison between the first waveform and the second waveform, a distance between the blade tip and the sensor unit.

A cryogenic-rated vibration sensor generally includes a cryogenic-rated accelerometer mounted to a top planar surface of an insulation block, wherein the insulation block includes a threaded opening on a bottom planar surface thereof for attachment to an object. Also disclosed are cryogenic pumps including the cryogenic-rated vibration sensor.

Systems and methods for detecting an issue with a starter are provided. One example aspect of the present disclosure is directed to a method for detecting an anomaly with an air turbine starter. The method includes receiving, by one or more controllers, data indicative of a frequency associated with an integrated air turbine starter from one or more sensors located on a stationary portion of the air turbine starter to monitor a rotating portion of the air turbine starter. The method includes determining, by the one or more controllers, an anomaly associated with the integrated air turbine starter based at least in part on the data indicative of the frequency. The method includes providing, by the one or more controllers, a notification indicative of the anomaly associated with the integrated air turbine starter.

A gearbox monitoring system can include a fan, compressor, combustor, and turbine in axial flow arrangement, with corresponding rotating components mounted to a shaft, and a gearbox assembly operably coupled to the shaft and connecting the turbine and the fan. The gearbox assembly can include a carrier, a sun gear, at least one planet gear, and a ring gear. An oil feed tube is coupled to the gearbox for lubricating at least one of the sun, ring or planet gears. A plurality of bearings rotationally supports at least one of the sun gear, ring gear, or planet gear relative to the carrier. In addition, at least one vibration sensor is carried by one of the carrier or ring gear and is in wireless communication with an engine control unit or health monitoring unit.

A gas turbine engine is provided with a controller configured to detect a spool shaft failure and to initiate an engine shut-down in response to the shaft failure. The controller evaluates the compressor speed probe, the speed probe continuity, P30 pressure and compressor surge to determine whether a shaft failure has occurred.

A cryogenic-rated vibration sensor generally includes a cryogenic-rated accelerometer mounted to a top planar surface of an insulation block, wherein the insulation block includes a threaded opening on a bottom planar surface thereof for attachment to an object. Also disclosed are cryogenic pumps including the cryogenic-rated vibration sensor.

A regulation system for controlling the vibratory behavior in twisting and/or the twisting stability of a drivetrain of a rotorcraft, the regulation system comprising two regulation loops that are interleaved one in the other, the two regulation loops being arranged in cascade relative to each other to regulate firstly a first speed of rotation NG of a gas generator of at least one turboshaft engine driving said drivetrain in rotation, and secondly a second speed of rotation NTL of a free turbine of the engine(s).

Systems and methods for measuring a clearance between a rotating machine component and a sensor unit are disclosed. In some aspects, a system includes a sensor unit oriented to detect the rotating machine component as the rotating machine component rotates past the sensor unit, the sensor unit including at least a first sensing element and a second sensing element spaced apart from the first sensing element. The system includes a sensor processing unit in electrical communication with the sensor unit. The sensor processing unit is configured for receiving a first waveform from the first sensing element; receiving a second waveform from the second sensing element; and determining, based on a comparison between the first waveform and the second waveform, a distance between the blade tip and the sensor unit.

In one embodiment, a turbine system includes a number of sensors, each of the number of sensors disposed in a respective location of the turbine system, and a controller including a memory storing one or more processor-executable routines and a processor. The processor configured to access and execute the one or more routines encoded by the memory wherein the one or more routines, when executed cause the processor to receive one or more signals from the number of sensors during any stage of operation of the turbine system, and convert the one or more signals to audio output.