Abstract: An arrangement for monitoring a centrifugal pump is provided. receiving the residual axial thrust of a centrifugal pump. The arrangement includes a load-relieving device configured to receive the residual axial thrust developed during pump operation, an axial bearing, and a sensor ring is associated with the axial bearing. The ring (10) is divided into segments having sensors at the segment dividing regions.

Abstract: A pump assembly includes at least one rotatingly driven impeller (14) and at least one valve element (18) which is rotatable about a rotation axis (X) between at least two switching positions. The valve element (18) includes a first face side (22) which extends transversely to the rotation axis of the valve element. A suction opening (24), which is engaged with a suction port (26) of the impeller (14), is formed in this first face side in a central region. The first face side (22) includes a pressure surface which surrounds the suction opening (24) and is adjacent to a delivery chamber (28) which surrounds the impeller (14).

Abstract: An example high-performance system includes an example high-performance component including a substrate and a multilayer abradable track adjacent to the substrate. The abradable track includes a plurality of alternating layers along a thickness of the abradable track. The plurality of alternating layers includes at least one relatively porous abradable layer and at least one relatively dense layer. A porosity of the relatively dense layer is lower than that of the at least one relatively porous abradable layer. The example high-performance system may include a rotating component configured to contact and abrade the multilayer abradable track. An example technique for forming the multilayer abradable track includes thermal spraying a first precursor composition toward the substrate to form a relatively porous abradable layer of a layer pair of a plurality of layer pairs of the multilayer abradable track, and a second precursor composition to form a relatively dense layer of the pair.

Abstract: A vacuum pump and a damper for the vacuum pump are provided so as to increase vibration isolation in a twisting direction with a simple structure and prevent rupture of an O-ring and an elastic member by regulating a misalignment of flanges facing each other. Provided are a first flange and a second flange, each having a central opening, the flanges being shaped like rings opposed to each other; an O-ring and an intermediate ring that are disposed between the first flange and the second flange; O-rings disposed between the first flange and the intermediate flange and between the intermediate ring and the second flange; a plurality of elastic members that are disposed between the first flange and the second flange and are spread in the circumferential direction of central openings; and airtightness keeping means including positioning pins inserted into positioning holes sequentially provided on the first flange, the intermediate ring, and the second flange.

Abstract: Provided is a heating blower, comprising an air duct, a motor and a wind wheel arranged in the air duct, and a heating device arranged at a first air outlet of the air duct; the wind wheel is fixed to a rotating shaft of the motor; the heating device comprises a housing, an electric heater, a rotary assembly and an air deflector; the housing is sleeved on the first air outlet, forming an inner chamber, which comprises a first area facing directly to the first air outlet and a second area not facing directly to the first air outlet; the electric heater is arranged in one of the first area and the second area; one end of the air deflector is fixedly arranged on the rotary assembly, and the other end of the air deflector rotates with the rotary assembly between the first area and the second area, separating the first area and the second area, so that the first air outlet is communicated with one of the first area and the second area.

Abstract: A method for controlling a gas turbine engine includes receiving, by a signal processor from a sensor, an operating condition of the gas turbine engine and determining, by the signal processor, whether the operating condition is within an acceptable threshold. In response to the operating condition being outside the acceptable threshold, the method includes restricting, by the signal processor, a subsequent engine restart of the gas turbine engine. Restricting the subsequent engine restart of the gas turbine engine may comprise preventing the subsequent restart. In various embodiments, restricting the subsequent engine restart of the gas turbine engine comprises limiting a subsequent operating state of the gas turbine engine after the subsequent restart.

Abstract: A propeller fan includes a shaft portion disposed on a rotation axis, and a blade disposed on an outer peripheral side of the shaft portion and including a leading edge and a trailing edge. The blade includes a negative pressure surface in which a plurality of recesses are formed, and the plurality of recesses include a first recess and a second recess disposed on the trailing edge side than the first recess in a circumferential direction about the rotation axis as a center. The first recess has a depth larger than a depth of the second recess.

Abstract: A compressor housing for a turbocharger dividably composed of a plurality of pieces including a scroll piece, and a shroud piece. The scroll piece and the shroud piece are assembled to each other by press-fitting a press-fitting portion of the shroud piece into a press-fitted portion of the scroll piece. Pressure-contacting portions that are provided on either one of the scroll piece and the shroud piece are pressure-contacted with pressure-contacted portions that are provided on the other one of the scroll piece and the shroud piece, respectively. As a result, the pressure-contacting portions plastically flow to form seal parts for sealing the scroll piece and the shroud piece, respectively.

Abstract: 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.

Abstract: A head-mounted heat dissipation device includes a fan assembly and a wearing assembly. The wearing assembly is connected to the fan assembly to fix the fan assembly onto a head of a user. The fan assembly includes a casing and fans arranged in the casing. Air inlets and air outlets are defined in the casing. The air outlets are located on an inner side of the bottom surface of the casing, so that the air from the air outlets can be blown to the user's face. In addition, air guide strips are arranged side by side on a side of the air outlet within the casing for concealing the operation of the fans.

Abstract: A component for a gas turbine engine. The component includes a body. The body has an exterior surface abutting a flowpath for the flow of a hot combustion gas through the gas turbine engine. Further, the body defines a cooling passageway within the body to supply cool air to the component. The component includes a leading face and a trailing face defining a trench therebetween on the exterior surface. The body defines a plurality of cooling holes extending between the cooling passageway and a plurality of outlets defined in the trench such that the trench is fluidly coupled to the cooling passageway. Additionally, the leading face and trailing face are each tangent to at least one of the plurality of outlets. The trench directs the cool air along a contour of the component.

Abstract: Centrifugal compressors can incorporate a side stream flow of intermediate pressure vapor between stages of that compressor. The side stream flow can be controlled by a side stream injection port controlled by a capacity control valve that has a curved surface facing a flow of refrigerant from the first stage to the second stage. The capacity control valve can allow or obstruct flow through the side stream injection port. The capacity control valve can extend and retract in a direction substantially perpendicular to the direction of flow from the first stage impeller to the second stage impeller. The side stream injection port and the capacity control valve can be ring-shaped. The side stream injection port and the capacity control valve can allow at least some of the side stream to be introduced on a side of the capacity control valve opposite the curved surface.

Abstract: A fan assembly includes a radial blower unit configured to exhaust air radially from an inlet axis of the radial blower unit. The fan assembly also includes baffles each partially surrounding the radial blower unit. The baffles are rotatable between an open position and a closed position around respective pivot axes, and the baffles have respective centers of mass aligned with the respective pivot axes.

Abstract: A containment shell for a magnetic pump, the shell comprising: a body section having a continuous side wall defining a chamber, and an end wall closing the chamber at one end, the chamber being open at the other end, wherein the body section and the end wall are integrally formed from a matrix material in which chopped carbon fibre material is distributed.

Abstract: There is disclosed a compressor comprising a case comprising a discharging part provided one side and configured to discharge a refrigerant, the case defining a predetermined space for storing oil; a drive part comprising a rotor coupled to an inner circumferential surface of the case and having coils wound there around and configured to generate a rotation magnetic field, and a rotor mounted in the rotor and configured to be rotatable by the rotation magnetic field; a shaft extending in a state of being coupled to the rotor; a compression part lubricated by the oil in a state of being coupled to the shaft and configured to compress and discharge the refrigerant; and a sealing part extending from the stator towards the compression part and configured to induce the winding of the coil.

Abstract: A centrifugal compressor includes: an impeller; a main flow passage which receives the impeller and extends in a rotation axis direction of the impeller; an auxiliary flow passage which includes an upstream communication portion communicating to the main flow passage and a downstream communication portion communicating to the main flow passage at closer to the impeller than the upstream communication portion, and extends in a rotation direction of the impeller; a plurality of opening/closing portions which each have an opening portion and are arranged in the auxiliary flow passage; and a drive unit configured to move at least one of the plurality of opening/closing portions in the rotation direction.

Abstract: Component for gas turbine engines are described. The components include an airfoil body having leading and trailing edges and pressure and suction sides. The airfoil has a leading edge cavity located proximate the leading edge defined between the leading edge and a separator rib and between the pressure side and the suction side. An insert member is installed within the leading edge cavity. The insert member has one or more metering flow apertures at an aft end and one or more impingement apertures at a forward end and at least one axially extending rib along an exterior surface thereof. At least one axial extending flow channel passage is defined along the axial extending rib between an exterior of the insert member and an interior of the airfoil body. Air flow through the metering flow apertures flows into the axial extending flow channel passage and flows forward toward the leading edge.

Abstract: A grey water treatment system includes a first tank configured to receive grey water via a grey water supply conduit and that comprises an overflow, a second tank configured to store grey water, and at least one transfer conduit configured to at least transfer grey water between the first tank and the second tank. A control is configured to maintain a water level in said first tank sufficiently close to the overflow to allow floating contaminants to pass over the overflow. A method of treating grey water includes: receiving grey water in a first tank of a grey water treatment system; transferring grey water via at least one transfer conduit between the first tank and a second tank of said treatment system; and controlling a water level in said first tank sufficiently close to an overflow of said first tank to allow floating contaminants to pass over the overflow.

Abstract: An impeller for use in an aquarium filter pump includes a shaft and a plurality of impeller blades radially extending from the shaft. Each of the impeller blades includes opposite blade faces. A depression is in each of the blade faces and aids in pushing the water. The depression can be a variety of shapes and can have its deepest portion along one of the edges of the blade.

Abstract: A platform for a gas turbine engine according to an example of the present disclosure includes, among other things, a platform body that extends in a circumferential direction between first and second sidewalls to define a gas path surface, and opposed rows of flexible retention tabs that extend from the platform body and are dimensioned to wedge the platform between adjacent airfoils.