Abstract: A vacuum pump comprises: a rotor; a stator; a rolling bearing configured to support a rotor shaft provided at the rotor; and a vibration sensor configured to detect vibration of the rolling bearing.

Abstract: A waste water pump includes an impeller (12) and a surrounding pump housing (4), wherein an impeller side chamber (20) is formed between the impeller (12) and the pump housing (4). The impeller side chamber (20) has a first seal (16) between the impeller (12) and the pump housing (4), towards the intake side (32) of the impeller (12), and a second seal (18) between the impeller (12) and the pump housing (4), towards the pressure side (14) of the impeller (12). The first seal (16) is provided with a conveying device (28, 30) configured to convey debris from the impeller side chamber (20) to the intake side (32) of the impeller (12). The second seal (18) is provided with conveying device (38, 40) configured to convey debris from the side chamber (20) to the pressure side (14) of the impeller (12).

Abstract: A pitch varying device, a pitch varying method and a pitch varying control device for a wind turbine blade and a wind turbine are provided. The blade pitch varying device includes: a disc-type driving structure perpendicular to an axis of a pitch bearing, a track surrounding the axis of the pitch bearing being provided on the disc-type driving structure; a first linear telescopic driving mechanism connected to the track through a first clamping member capable of clamping the track, and the first linear telescopic driving mechanism and the first clamping member being connected through a hinge connection; and a second linear telescopic driving mechanism connected to the track through a second clamping member capable of clamping the track, and the second linear telescopic driving mechanism and the second clamping member being connected through a hinge connection.

Abstract: A rotor assembly is provided for a piece of rotational equipment. This rotor assembly includes a rotor disk, a rotor blade and a seal element. The rotor disk is configured to rotate about a rotational axis. The rotor disk extends axially along the rotational axis to a rotor disk end face. The rotor blade includes an attachment. The attachment attaches the rotor blade to the rotor disk. The seal element is configured to seal a gap between the rotor disk and the attachment. The seal element has a longitudinal centerline that extends along an interface between the rotor disk and the attachment at the rotor disk end face.

Abstract: A gas turbine engine component according to an example of the present disclosure includes a wall extending in a thickness direction between first and second wall surfaces. The first wall surface bounds an internal cavity. The wall includes a plurality of cooling passages. Each of the cooling passages extend in a first direction between an inlet port and an outlet port coupled to a respective diffuser, and the inlet port coupled to the internal cavity along the first wall surface. Sidewalls of adjacent diffusers are conjoined to establish a common diffuser region interconnecting the diffusers and a common outlet along the second wall surface. A method of cooling a gas turbine engine component is also disclosed.

Abstract: A system and method in at least one embodiment for separating fluids including liquids and gases into subcomponents by passing the fluid through a vortex chamber into an expansion chamber and then through at least a portion of a waveform pattern present between at least two rotors and/or disks. In further embodiments, a system and method is offered for harnessing fields created by a system having rotating rotors and/or disks having waveform patterns on at least one side to produce current within a plurality of coils. In at least one embodiment, the waveform patterns include a plurality of hyperbolic waveforms axially aligned around a horizontal center of the system.

Abstract: A scroll shape of a compressor forms into a spiral shape a flow path of fluid discharged from a diffuser provided on a downstream side of the compressor in a fluid flow direction. The scroll shape has a scroll outer diameter that is not constant in a circumferential direction. An increase degree of a ratio A/R is set to be increased in a range from a winding start position to a winding end position of a scroll portion where A is a passage cross-sectional area of the scroll portion and R is a radius from a center of the compressor to a center of a passage cross section of the scroll portion.

Abstract: Disclosed is an acoustic liner for a gas turbine engine, having: a face sheet; a first plurality of resonator chamber cavities, distributed non-uniformly against the face sheet, the first plurality of resonator chamber cavities defining a first aggregated volume that is configured to target noise attenuation at a first frequency, the first plurality of resonator chamber cavities include first and second resonator chamber cavities fluidly coupled to each other, which have different configurations with respect to each other; and a second plurality of resonator chamber cavities, distributed non-uniformly against the face sheet, the second plurality of resonator chamber cavities define a second aggregated volume that differs from the first aggregated volume and is configured to target noise attenuation at a second frequency, the second plurality of resonator chamber cavities include third and fourth resonator chamber cavities fluidly coupled to each other, which have different configurations with respect to each

Abstract: A turbocharger device for an internal combustion engine and a method for mounting a turbocharger device are described. The turbocharger device has a housing with a locating hole, in which a turbocharger shaft is mounted by two rolling element bearings. A rolling element bearing sleeve is situated between the two rolling element bearings. The rolling element bearing sleeve and hence the two rolling element bearings are fixed with the turbocharger shaft in the axial direction with the aid of two pins, which are introduced through a hole in the housing and are pressed into a groove in the rolling element bearing sleeve. During this process, the beveled tips of the pins slide along the chamfered outer edges of the groove as far as an end position, which fixes the axial position of the rolling element bearing sleeve.

Abstract: A blade for a gas turbine engine comprises an aerofoil body having a suction side, a pressure side, and a trailing edge. An internal cooling passageway is provided in the aerofoil body, and an ejection slot in fluid communication with the cooling passage and provided at the trailing edge of the aerofoil body. The ejection slot is defined between a pressure side wall and a suction side wall. Both the suction side wall and the pressure side wall include a mid-section and a trailing edge section adjacent the mid-section, and the thickness of the suction side wall and the pressure side wall reduces to define a taper with a wedge angle less than or equal to 20 degrees.

Abstract: A turbomachinery component of a gas turbine engine is disclosed having a number of techniques of reducing the effects of a gap flow between an airfoil member of the gas turbine engine and a wall of the gas turbine engine. The airfoil member can be variable and in one form is a variable turbine vane. In one embodiment a brush seal is included between the vane and the wall. In another form a wear surface is disposed between the vane and the wall. In yet another form a moveable member capable of being actuated to change position can be disposed between the vane and the wall to alter the size of a gap between the two.

Abstract: A component includes a component body. The component further includes a first passage disposed in the component body. The first passage includes a first end and a second end opposite the first end. The component further includes a second passage. The second passage extends from the second end of the first passage. The second passage includes a turn. The component further includes a third passage. The third passage extends from the second end of the first passage. The component further includes a first projection extending from a passage surface of the component body within the first passage. The first projection is disposed between the first and the second end of the first passage and is configured to direct debris transiting the first passage away from the second passage and into the third passage.

Abstract: The invention relates to a turbine housing, in particular for a turbo charging assembly (2) within a combustion engine, wherein the turbine housing (10) accommodates a shaft (8) with a turbine wheel (6) which is adapted to deliver fluid from a volute (26) as a fluid intake through an inlet channel to an fluid outlet (24), wherein the volute (26) and the fluid outlet (24) are separated along an axial direction (12) by a hollow area (30), the hollow area (30) being formed between an inner wall section (32) and an out wall section (34) around the fluid outlet (24) and being located in the axial direction (12) from a cover plate (36) covering the inlet channel next to the turbine wheel (6) within the turbine housing (10).

Abstract: A disc able to support platforms and blades of a fan, and including an external surface having a succession of grooves for receiving the fan blades and teeth interposed between the grooves to support the fan platforms, an upstream face of the disc, and a plurality of radial protrusions disposed radially around the axis of the disc on the upstream face of the disc, and able to be fastened to a fan platform retaining flange, the protrusions being offset radially toward the interior of the disc relative to the grooves of the disc, and being disposed circumferentially between two teeth of the disc.

Abstract: A propeller blade comprises a root, a tip distal from the root, a trailing edge extending from the root to the tip, a trailing edge, e.g. foam, insert, a shell forming an outer surface of the propeller blade and a plurality of stitches of yarn extending through two parts of the shell adjacent the trailing edge, wherein the yarns do not extend through the trailing edge insert.

Abstract: Provided is a pitch apparatus of a wind turbine. The wind turbine includes a wheel hub and multiple blades. The pitch apparatus includes a pitch bearing, a transmission element and a driving mechanism for driving the transmission element. The pitch bearing includes a bearing inner race and a bearing outer race. The bearing inner race is fixedly connected to the blade; the bearing outer race is fixedly connected to the wheel hub. The transmission element is driven by the driving mechanism, and drives the blade and the bearing inner race to rotate relative to the wheel hub. A load level of ultimate bending moment for a blade root and a safety factor of the pitch apparatus increase, failure risks of the pitch bearing, bolts and the transmission belt are reduced. A wind turbine having pitch apparatus is provided.

Abstract: An axial flow impeller includes a hub and a blade at the hub. A blade edge of the blade includes a blade root edge, a front blade edge, a blade top edge, and a rear blade edge connected sequentially. The blade includes a divider strip arranged between the front blade edge and the rear blade edge and connecting the blade root edge and the blade top edge. At a same circumference, a ratio between a circumferential span from the divider to the front blade edge and a circumferential span from the front blade edge to the rear blade edge is equal to or greater than 0.2 and equal to or smaller than 0.4, a thickness of the divider strip is greater than thicknesses of other portions of the blade, and a thickness of the rear blade edge is smaller than a thickness of the front blade edge.

Abstract: A cross flow fan includes a fan frame and a rotor having a hub, a shaft connected with the hub at its rotation center, a plurality of blades, and a disk structure connected with the blades and hub within the fan frame. The fan frame has a frame wall having a lateral flow inlet to the rotor and a lateral flow outlet from the rotor, a base carrying the rotor and frame wall, a cover on one side of the frame wall opposite to the base, and a partition structure disposed between the blades and an inner wall surface of the frame wall. A normal line of the lateral flow inlet and a normal line of the lateral flow outlet are not parallel to an extension direction of the shaft. The blades directly face the lateral flow inlet and the lateral flow outlet along radial directions of the shaft.

Abstract: A turbine nozzle includes an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.

Abstract: A bladed rotor system includes a circumferential row of blades mounted on a rotor disc. Each blade includes an airfoil and a shroud attached to the airfoil at a span-wise height of the airfoil. The row of blades includes a first set of blades and a second set of blades. The airfoils in the first and second set of blades have substantially identical cross-sectional geometry about a rotation axis. The blades of the second set are distinguished from the blades of the first set by a geometry of the shroud that is unique to the respective set, whereby the natural frequency of a blades in the first and second sets differ by a predetermined amount. Blades of the first set and the second set alternate in a periodic fashion in said circumferential row, to provide a frequency mistuning to stabilize flutter of the blades.