A sensing system and method for an engine rotor are provided. The rotor is rotatable about a longitudinal axis and at least one rotating member is coupled to rotate with the rotor about the axis. The rotating member comprises at least one marker affixed to a core. The core is made of a first material having a first magnetic permeability and the marker comprises a second material having a second magnetic permeability greater than the first magnetic permeability. At least one sensor is mounted adjacent the rotating member and configured to produce at least one first signal in response to detecting passage of the marker as the rotating member rotates about the axis. A control unit is communicatively coupled to the sensor and configured to generate, in response to the first signal received from the sensor, a second signal indicative of at least a rotational speed of the rotor.

A controllable magneto-rheological device includes an annular cylinder formed by inner and outer walls connected at first and second opposing ends and forming an inner shaft configured to receive an operational component of an engine, generator or other device including one or more rotating structures. A magneto-rheological fluid is provided to fill a volume between the inner and outer walls of the annular cylinder. A plurality of electro-magnetic coils are positioned around the outer wall of the annular cylinder. One or more current controllers are coupled to the plurality of electro-magnetic coils for introducing a current through each of the electro-magnetic coils and corresponding magnetic flux through the magneto-rheological fluid. A level of current provided to each of the plurality of electro-magnetic coils directly affects the viscosity of the magneto-rheological fluid and thus the stiffness and damping levels of the controllable magneto-rheological device.

A gas turbine rotor having a combination of proximal embedded permanent magnets in the blended turbine(s) trunnion structure to which blades are integral to and through these distal trunnion channels attach to which turbine blades are integral to as a single component is provided. Permanent magnets or warm conducting coils or cold superconducting coils can be used. The structure rotates around a superconducting power shaft core (SPSC), running axially in relation to the turbine blade permanent magnets, for example, and embedded distal trunnion rings.

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).

A system and method for providing feedback for an aircraft-bladed rotor about a longitudinal axis and having an adjustable blade pitch angle. At least one position marker is provided at the rotor, extends along an axial direction, from a first end to a second end, and has varying magnetic permeability from the first end to the second end. At least one sensor is coupled to the rotor and configured for producing, as the rotor rotates about the longitudinal axis, at least one sensor signal in response to detecting passage of the at least one position marker. A control unit is communicatively coupled to the at least one sensor and configured to generate a feedback signal indicative of the blade pitch angle in response to the at least one sensor signal received from the at least one sensor.

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 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, are circumferentially spaced around the circular disk, and extending along the longitudinal axis from a first end portion to a second end portion. At least part of the first end portion and/or of the second end portion comprises a material having higher magnetic permeability than that of a remainder of the position markers.

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.

An apparatus for an aircraft engine that is configured for actively adjusting physical characteristics of an airfoil. The apparatus includes an airfoil that has a body and a filler that is embedded within the body. A source for electromagnetic energy is positioned in a portion of the engine and configured to generate electromagnetic energy having a predetermined range which encompasses the airfoil. A physical property of the filler is configured to change between a first state in the absence of electromagnetic energy and a second state in the presence of electromagnetic energy. The airfoil has a first airfoil characteristic when the filler is in the first state and the airfoil has a second airfoil characteristic when the filler is in the second state.

One embodiment relates to a pump device with an impeller; a pump housing, including a wall surrounding an interior having an inlet and an outlet. The impeller is provided in the interior of the pump housing. The pump housing includes at least one first part-region, at least two further part-regions and at least one third part-region. The at least one first part-region includes, to an extent of at least 60% by weight at least one nonmagnetic material. The at least two further part-regions comprise, to an extent of at least 25% by weight at least one ferromagnetic material metal. The at least one third part-region comprises a metal content in a range from 40% to 90% by weight. The at least two further part-regions of the pump housing at least partially project into the substantially tubular outer surface defined by the at least one first part-region.