The present invention relates to the field of drive technology and provides a space-saving possibility for determining forces or torques transmitted by a drive shaft with a journal cross of a universal joint with four journals projecting from a base, to which a strain sensor is attached for this purpose.

A method of calibrating a gas turbine engine having a propulsive fan, and an engine core, the method including: measuring a total thrust generated by the engine; measuring the thrust generated by the engine core; measuring first and second engine performance parameters; based on the total thrust and engine core thrust, determining a thrust generated by the propulsive fan; providing a first power setting parameter associating the fan thrust with the first engine performance parameter; and providing a second power setting parameter associating the engine core thrust with the second engine performance parameter.

A tunnel boring machine includes: a cutter head; a cutter support; a cutter driving unit; a rotational position sensing unit; a strain sensor; and a data processing unit configured to calculate a force acting on the cutter head in association with the position of the cutter head in the rotational direction, based on sensing results of the strain sensor and the rotational position sensing unit.

A tunnel boring machine includes: a cutter head; a cutter support; a cutter driving unit; a rotational position sensing unit; a strain sensor; and a data processing unit configured to calculate a force acting on the cutter head in association with the position of the cutter head in the rotational direction, based on sensing results of the strain sensor and the rotational position sensing unit.

An aircraft powerplant and a method for measuring thrust are described herein. A gas turbine engine has a turbine section for extracting energy from combustion gases and has a shaft mounted to the turbine section for converting the energy into rotary motion. A load cell is coupled to an end of the shaft and positioned to rotate with the shaft. The load cell is configured for generating a measurement indicative of propeller thrust. A propeller is coupled to the load cell and is configured for converting the rotary motion from the shaft and the load cell into the propeller thrust. The propeller thrust can be measured from the load cell as the propeller rotates.

An aircraft powerplant and a method for measuring thrust are described herein. A gas turbine engine has a turbine section for extracting energy from combustion gases and has a shaft mounted to the turbine section for converting the energy into rotary motion. A load cell is coupled to an end of the shaft and positioned to rotate with the shaft. The load cell is configured for generating a measurement indicative of propeller thrust. A propeller is coupled to the load cell and is configured for converting the rotary motion from the shaft and the load cell into the propeller thrust. The propeller thrust can be measured from the load cell as the propeller rotates.

A sensor system for a wind turbine blade, the system comprising: a blade load sensor providing a load measurement; a processing unit interfaced with the blade load sensor and configured to provide a corrected load parameter as an output. The processing unit includes: an axial force estimation module that determines an estimated axial force on the wind turbine blade in a direction along the length of the blade; and a load calculation module that 10 determines the corrected load parameter based on the estimated axial force and the load measurement of the blade load sensor.

A sensor system for a wind turbine blade, the system comprising: a blade load sensor providing a load measurement; a processing unit interfaced with the blade load sensor and configured to provide a corrected load parameter as an output. The processing unit includes: an axial force estimation module that determines an estimated axial force on the wind turbine blade in a direction along the length of the blade; and a load calculation module that 10 determines the corrected load parameter based on the estimated axial force and the load measurement of the blade load sensor.

A system for torque measurement is generally provided. The system includes a sensor disposed between an outer bearing race and a static structure of a bearing assembly. The sensor is disposed adjacent along a thrust load direction to the outer bearing race. The system further includes a rotor assembly rotatably coupled to the bearing assembly, and a controller communicatively coupled to the sensor. The controller is configured to store and execute operations. The operations include determining a torque measurement from the rotor assembly based at least on an axial thrust load from the rotor assembly.

A system for torque measurement is generally provided. The system includes a sensor disposed between an outer bearing race and a static structure of a bearing assembly. The sensor is disposed adjacent along a thrust load direction to the outer bearing race. The system further includes a rotor assembly rotatably coupled to the bearing assembly, and a controller communicatively coupled to the sensor. The controller is configured to store and execute operations. The operations include determining a torque measurement from the rotor assembly based at least on an axial thrust load from the rotor assembly.