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).

A vibration detection device for detecting vibration of a cartridge including a bearing housing that accommodates a rotor coupling a wheel and a rotor shaft, and a bearing rotatably supporting the rotor, the bearing housing including a lubricant-oil passage port for allowing lubricant oil to pass through an interior of the bearing housing, includes: a sensor mount attached to an oil-flow-passage forming member configured to be capable of connecting to and separating from the bearing housing, the oil-flow-passage forming member including, inside thereof, an oil flow passage through which one of lubricant oil to be supplied to the interior of the bearing housing via the lubricant-oil passage port or lubricant oil discharged from the interior of the bearing housing via the lubricant-oil passage port flows; a vibration sensor disposed on the sensor mount; and a vibration transmission leg portion connected to the sensor mount and configured to be in contact with the bearing housing in a state where the oil-flow-passage forming member is connected to the bearing housing.

The invention relates to an assembly for monitoring and/or controlling a wind turbine. The assembly includes a first strain sensor for measuring a first blade bending moment of a rotor blade of a wind turbine in a first spatial direction; a second strain sensor for measuring a second blade bending moment of a rotor blade of a wind turbine in a second spatial direction, which differs from the first spatial direction; an arrangement for determining constant components of forces and moments of the rotor blades provided in the wind turbine; and a controller for combining the first blade bending moment, the second blade bending moment and the constant components.

Systems and methods for starting an engine on an aircraft are provided. One example aspect of the present disclosure is directed to an integrated starter for starting an engine on an aircraft. The integrated starter includes an air turbine starter. The integrated starter includes a starter air valve integrated with the air turbine starter. The integrated starter includes a controller configured to control the starter air valve. The starter air valve can be movable between a first position and at least a second position to regulate the flow of fluid into the air turbine starter. An output torque of the air turbine starter can be dependent at least in part on the flow of fluid into the air turbine starter.

A turbocharger is used within a vehicle and includes an electronic actuator assembly. The electronic actuator assembly includes an actuator housing coupled to at least one of the turbine housing, the compressor housing, and the bearing housing, and an accelerometer coupled to the actuator housing. The accelerometer is adapted to detect vibration of at least one of the turbine housing, the compressor housing, the bearing housing, and the actuator housing thereby obtaining acceleration data of at least one of the turbine housing, the compressor housing, the bearing housing, and the actuator housing to determine rotational speed of the turbocharger shaft. Another embodiment includes a vibration detection assembly having an accelerometer coupled to a vehicle component and the vehicle component is one or more of a turbocharger, a valve assembly, an electronically driven compressor, and a turbocharger having an integral electric motor.

An anti-ice arrangement for a gas turbine engine may comprise an engine static structure, a fan blade housed for rotation within the engine static structure, and a magnetic field source mounted in close proximity to the fan blade and configured for inducing eddy currents in the fan blade to increase a surface temperature of the fan blade.

A system for compensating for a relative motion between a probe and an apparatus. The system includes a probe assembly, a sensor, and a computer. The probe assembly includes an actuator pack positioned exterior to the apparatus and a probe insertable into the apparatus. The probe includes a first end coupled to the actuator pack, a second end, and an elongated body extending therebetween. The sensor senses data indicative of a relative motion between the apparatus and the probe assembly. The computer is operably coupled with the sensor and the probe assembly to move the probe of the probe assembly in response to the sensor sensing the data indicative of the relative motion between the apparatus and the probe assembly.

A power generation system includes: a prime mover; a magnetic gear generator configured to be driven by an input from the prime mover to generate power; a power converter connected to the magnetic gear generator; an operation mode switch unit configured to switch an operation mode of the magnetic gear generator to a step-out avoidance mode in response to that a step-out parameter indicating a risk of step-out of the magnetic gear generator exceeds a prescribed allowable range; and a reduction command unit configured to give the prime mover an input reduction command to reduce the input from the prime mover and configured to give the power converter a torque reduction command to reduce a generator torque of the magnetic gear generator, in the step-out avoidance mode.

A sensor signal produced by a sensor as a feedback device rotates with a propeller about an axis and moves along the axis with adjustment of a blade angle of the propeller is received, the sensor signal indicative of a rotational speed and of the blade angle of the propeller. From the sensor signal, it is determined whether the rotational speed is within a predetermined range of a reference speed and an expected change in the blade angle has occurred in response to a command to adjust the blade angle to maintain the rotational speed at the reference speed. In response to determining that the rotational speed is within the predetermined range of the reference speed and the expected change in the blade angle has failed to occur in response to the command, inoperable movement of the feedback device along the axis is determined and an alert is output.

A system for determining eccentricity of a turbine shell and a turbine rotor of a gas turbine includes a laser module with a microprocessor having coupled thereto a wireless network chip, a laser sensor, an inclination sensor, and a power supply. The laser sensor transmits a laser toward the turbine shell as the rotor spins at slow speed and to receive a reflected laser from the turbine shell, thereby defining a path length indicative of a distance between the laser module and the turbine shell for each of a series of points disposed circumferentially around the turbine shell. The system further includes a bracket configured to hold the laser module proximate to a turbine blade; a base station that produces a wireless network near the turbine shell and that receives distance measurements from the laser module for each of the series of points; and a server for processing the distance measurements into an eccentricity plot.