The invention relates to a twisting torque sensor, comprising a transmission shaft (12) subjected to the torque to be measured, a reference shaft (14), and a device for measuring an angular deformation representing the torque to be measured between the two shafts. The torque sensor is characterised in that the transmission shaft (12) comprises a bore (24) extending from one end of the transmission shaft (12), referred to as input (28) of the shaft, to an opposite end, and in that the torque sensor comprises an enclosure (22) for confining the temperature of the two shafts, and a fluid circulation circuit including a portion made up of said bore (24), an injector (32) for injecting the fluid into the bore (24) at said input (28) of the shaft, and a fluid temperature sensor (34) in the fluid circulation circuit, the measured temperature being intended for correcting the torque measurement.

The invention relates to a twisting torque sensor, comprising a transmission shaft (12) subjected to the torque to be measured, a reference shaft (14), and a device for measuring an angular deformation representing the torque to be measured between the two shafts. The torque sensor is characterised in that the transmission shaft (12) comprises a bore (24) extending from one end of the transmission shaft (12), referred to as input (28) of the shaft, to an opposite end, and in that the torque sensor comprises an enclosure (22) for confining the temperature of the two shafts, and a fluid circulation circuit including a portion made up of said bore (24), an injector (32) for injecting the fluid into the bore (24) at said input (28) of the shaft, and a fluid temperature sensor (34) in the fluid circulation circuit, the measured temperature being intended for correcting the torque measurement.

A method for operating a machine plant having a shaft train, including: a) determining the harmonic frequency of a torsional vibration mode of the shaft train and determining mechanical stresses arising during a vibration period of the torsional vibration mode; b) determining a correlation for each torsional vibration mode between a first stress amplitude, at a position of the shaft train that carries risk of stress damage, and a second stress amplitude, at a measurement location of the shaft train, using stresses determined for the respective torsional vibration mode; c) establishing a maximum first stress amplitude for the position; d) establishing a maximum second stress amplitude, corresponding to the maximum first stress amplitude, for the measurement location; e) measuring the stress of the shaft train while rotating; f) determining a stress amplitude at each harmonic frequency; g) emitting a signal when the stress amplitude reaches the maximum second stress amplitude.

A method for operating a machine plant having a shaft train, including: a) determining the harmonic frequency of a torsional vibration mode of the shaft train and determining mechanical stresses arising during a vibration period of the torsional vibration mode; b) determining a correlation for each torsional vibration mode between a first stress amplitude, at a position of the shaft train that carries risk of stress damage, and a second stress amplitude, at a measurement location of the shaft train, using stresses determined for the respective torsional vibration mode; c) establishing a maximum first stress amplitude for the position; d) establishing a maximum second stress amplitude, corresponding to the maximum first stress amplitude, for the measurement location; e) measuring the stress of the shaft train while rotating; f) determining a stress amplitude at each harmonic frequency; g) emitting a signal when the stress amplitude reaches the maximum second stress amplitude.

An apparatus measuring thrust of an aircraft gas turbine engine includes a core shaft connecting a turbine and compressor, a fan and gearbox with a sun gear driven by the core shaft, a plurality of planet gears, an annulus gear mounted in a static structure, and a planet carrier driven by the fan via fan shaft. The apparatus includes a sensor to measure force applied by the annulus gear on the static structure and first and second sensors to measure rotational speed of the core and fan shafts. A processor determines restoring torque on the annulus gear from measurement of force applied by the gear on the static structure, torque applied to the fan by the planet carrier using rotational speeds of core and fan shafts and restoring torque on the annulus gear, and thrust of the fan from torque applied to the fan and the fan's rotational speed.

A propulsion system for a vehicle (10) includes a propulsor (102) for generating a thrust for the vehicle, a motor (104) operable with the propulsor for driving the propulsor, a motor mount (164) for mounting the motor in or to the vehicle, and a thrust measuring device (172). The thrust measuring device (172) includes a strain sensor (174) mounted to a structural component of at least one of the propulsor (102), the motor (104), or the motor (164) mount for directly measuring a strain on the structural component caused by the thrust generated by the propulsor during operation of the propulsion system.

A tool for a slot in a gas turbine engine, according to an example of the present disclosure, includes a head configured to be received in the slot, a first pad removably bonded to the head with an adhesive, and a second pad removably bonded to the head with an adhesive and disposed opposite from the first pad.

An axial thrust load sensor for an axial thrust foil bearing used in a small gas turbine engine, the axial thrust load sensor having a axial thrust foil bearing plate and an intermediate washer plate and a load sensor plate arranged face to face to form the load sensor. The load sensor plate has three pedestals on a front side and three pedestals on a back side so that all six pedestals alternate at equal spacing. Next to each pedestal is a strain gauge connected to a controller. The controller regulates a supply of cooling air to the axial thrust bearing in order to control a thrust balance.

The present invention relates to an adjusting device for adjusting guide vanes of a guide vane cascade of a turbomachine, in particular of a turbine stage or a compressor stage of a gas turbine, wherein the adjusting device comprises a coupling ring for coupling the guide vanes and at least two actuators for rotating the coupling ring, said actuators being connected to the coupling ring, wherein at least one of these actuators has a disconnection coupling.

The present invention relates to an adjusting device for adjusting guide vanes of a guide vane cascade of a turbomachine, in particular of a turbine stage or a compressor stage of a gas turbine, wherein the adjusting device comprises a coupling ring for coupling the guide vanes and at least two actuators for rotating the coupling ring, said actuators being connected to the coupling ring, wherein at least one of these actuators has a disconnection coupling.