A ferrite core coil device as a sensing element for a sensor device determining a rotational speed of a metallic rotatable object includes a coil having a first sector and a second sector and a ferrite core holding the coil. The ferrite core has a shape of a disk lacking a disk sector and defined by a contour of the disk and a chord of the disk. The chord forms a bending edge of the ferrite core. The first sector of the coil is not arranged on a bed of the ferrite core and the second sector of the coil is arranged on the bed. The first sector is bent around the bending edge at a bending angle with respect to the second sector.

A pumping system including a pumping chamber with a fluid sensor having a cylindrical shaft extending into the priming chamber. The sensor has a sensing dome on an end of a cylindrical shaft extending into the priming chamber, with the dome having a vertical base having a diameter less than the cylindrical shaft diameter. The sensor signals a controller whether liquid is present based on an algorithm with settings for dampening of the electromagnetic field, conductance of the electric field, and/or permittivity of the magnetic field using settings which correlate to the fluid environment. The controller controls operation of the pump and primer based on the sensor signal.

There is provided a blade angle feedback system for an aircraft-bladed rotor rotatable about a longitudinal axis and having an adjustable blade pitch angle. A feedback device is coupled to rotate with the rotor and to move along the axis with adjustment of the blade pitch angle. The feedback device comprises a body having position marker(s) embedded therein, the body made of a first material having a first magnetic permeability and the position marker(s) comprising a second material having a second magnetic permeability greater than the first. Sensor(s) are positioned adjacent the feedback device and configured for producing, as the feedback device rotates about the axis, sensor signal(s) in response to detecting passage of the position marker(s). A control unit is communicatively coupled to the sensor(s) and configured to generate a feedback signal indicative of the blade pitch angle in response to the sensor signal(s) received from the sensor(s).

The present disclosure can provide a vacuum pump capable of obtaining a rotation direction and correcting the rotation direction without adding a dedicated rotation direction sensor even in a state of low-speed rotation. The control device is capable of obtaining at least a first state in which a rotor shaft rotates at relatively high speed, and a second state in which the rotor shaft deviates within a gap between the rotor shaft and a protective bearing and rotates at relatively low speed while revolving, acquires output information of a radial displacement sensor, obtains a rotation direction of the rotor shaft in the second state on the basis of the output information, determines whether the rotation direction is normal or not, and when the rotation direction is not normal, stops the rotation and increases rotation speed to achieve a normal rotation direction.

Apparatus and associated methods relate to health-monitoring of a magnetic speed probe. An inductive coil of the magnetic speed probe is used for two purposes: i) to sense a changing magnetic field caused by rotation of a rotating member; and ii) to radiatively transmit radio-frequency signals for determining the health of the magnetic speed probe. A signal generator coupled to the inductive coil of the magnetic speed probe generates the radio-frequency signals that, when conducted by the inductive coil, causes an inductive coil to act as a radio transmitter by radiatively transmitting the radio-frequency signals. The radio-frequency signals transmitted by the inductive coil are detected by a radio receiver. The radio-frequency signals received are indicative of health of the magnetic speed probe.

A gas turbine engine has a fan case exit and an inner core housing exit. At least one of the exits is provided with a fiber optic sensing unit. The fiber optic sensing unit includes a fiber optic sensing member surrounding a circumference of the at least one of the exits. A control is programmed to calculate a nozzle area at the at least one of the exits based upon the displacement of the fiber optic sensing member. The calculated nozzle area is utilized to update nozzle area information at an electronic engine controller for the engine, and the electronic engine controller is programmed to control at least one associated component on a gas turbine engine based upon the updated nozzle area. A method is also disclosed.

A feedback device for use in a gas turbine engine, and methods and systems for controlling a pitch for an aircraft-bladed rotor, are provided. The feedback device is composed of a circular disk and a plurality of position markers. The circular disk is coupled to rotate with a rotor of the gas turbine engine, to move along a longitudinal axis of the rotor, and has first and second opposing faces defining a root surface that extends between and circumscribes the first and second faces. The plurality of position markers extend radially from the root surface and are circumferentially spaced around the circular disk. The position markers have a top surface elevated with respect to the root surface and opposing first and second side surfaces. The side surfaces of the position markers have a curved concave profile extending toward the root surface.

A method for controlling the bending deformation of a turbomachine shaft at rest subjected to the residual heat of operation of the turbomachine, wherein the shaft is rotated at a rotation speed between 0.1 and 50 revolutions per minute depending on the bending deformation deflection of the shaft when the turbomachine is at rest.

Apparatus for measuring alignment of two shafts. Two magnetic bases each have two linear contact edges designed to engage with a circumferential surface of the two shafts and to ensure alignment between the base and an axis of rotation of the shaft to within a tolerance compatible with alignment tolerances of the shaft. Brackets attached to the bases are designed to attach laser photoelectric devices, the photoelectric devices designed to measure shaft misalignment.

There is provided a blade angle feedback system for an aircraft-bladed rotor rotatable about a longitudinal axis and having an adjustable blade pitch angle. A feedback device is coupled to rotate with the rotor and to move along the axis with adjustment of the blade pitch angle. The feedback device comprises a body having position marker(s) embedded therein, the body made of a first material having a first magnetic permeability and the position marker(s) comprising a second material having a second magnetic permeability greater than the first. Sensor(s) are positioned adjacent the feedback device and configured for producing, as the feedback device rotates about the axis, sensor signal(s) in response to detecting passage of the position marker(s). A control unit is communicatively coupled to the sensor(s) and configured to generate a feedback signal indicative of the blade pitch angle in response to the sensor signal(s) received from the sensor(s).