Flow restricting arrangements and rotor assemblies are provided. A flow restricting arrangement includes a stationary component and a rotating component. The rotating component is radially spaced apart from the stationary component such that a clearance is defined between the stationary component and the rotating component. A first magnet is embedded within the stationary component. A second magnet embedded within the rotating component. A plurality of magnetically responsive particles is contained within the clearance by a magnetic field produced by the first magnet and the second magnet. The plurality of magnetically responsive particles at least partially span the clearance.

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 gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a compressor section, a combustor section, a turbine section, and at least one rotatable shaft. The engine further includes a seal assembly including a seal plate mounted for rotation with the rotatable shaft and a face seal in contact with the seal plate at a contact area. The seal assembly further includes an abradable coating adjacent the contact area. The abradable coating includes magnetic particles embedded in a polymer material.

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 centrifugal pump with adaptive pump stages includes an impeller configured to provide kinetic energy to fluid flow through the pump. The impeller has multiple geometric dimensions. The pump includes a diffuser connected to the impeller that is configured to convert the kinetic energy provided by the impeller into static pressure energy to flow the fluid through the pump. The pump includes an adaptive material attached to the impeller that is configured to modify, during operation of the pump, a geometric dimension to modify fluid flow through the pump.

A centrifugal pump with adaptive pump stages includes an impeller configured to provide kinetic energy to fluid flow through the pump. The impeller has multiple geometric dimensions. The pump includes a diffuser connected to the impeller that is configured to convert the kinetic energy provided by the impeller into static pressure energy to flow the fluid through the pump. The pump includes an adaptive material attached to the impeller that is configured to modify, during operation of the pump, a geometric dimension to modify fluid flow through the pump.

A vacuum pump and a sensor target are provided that are inexpensive and widen the linearity range of the sensor sensitivity as compared to a configuration in which a ferromagnetic material is used for the sensor target of a displacement sensor, and also reduce the possibility of touch down even when a disturbance occurs. An axial displacement sensor 109 includes a shaft 109A, which is extended through and fixed to the central section of a holder 5 holding an axial electromagnet 106, and a bobbin 109B, which is coupled to the upper end of the shaft 109A and around which a coil 7 is wound. A shaft end portion 113B, which has the shape of a small-diameter column, projects from the lower end of a rotor shaft 113 and is separated from the coil 7 by a gap 2. An external thread is formed on the outer circumference of the shaft end portion 113B so that a nut 19, which has an internal thread on the inner side, is engaged with the shaft end portion 113B. The area where the internal thread is formed does not extend over the entire thickness of the nut 19 and extends only partially. That is, the nut 19 has a threaded hole 19A opening only at the upper end. The nut 19 is made of a single material of low-carbon steel.

A gas turbine engine comprises a compressor having a plurality of blades mounted to a hollow, annular compressor drum. The compressor comprises an electric storage device mounted within the hollow compressor drum.

A gas turbine engine can have a magnetic chip detector system with a first conductor member and a second conductor member both exposed to a lubricant flow path of the gas turbine engine, at least a first one of the conductor members including an electromagnet including a coil wrapped around a ferromagnetic core. As part of an engine shutdown procedure, an intrinsic magnetic field strength within the ferromagnetic core can be increased by circulating electrical current in the coil, and the electrical current circulation can then be interrupted for the magnetic field to remain active during engine shutdown.

A vibration suppression device for a rotary machine according to at least one embodiment of the present disclosure is a vibration suppression device for a rotor of a rotary machine including a damper pin movably provided inside a gap of the rotor, the damper pin including a magnet, and a magnetic force generation portion provided in the rotor at a periphery of the gap. The magnetic force generation portion is configured to exert, against the magnet, a magnetic force in a direction pushing the damper pin away from a stick region of the damper pin located on a radially outward side of the rotor in the gap.