Abstract: A compressor moves a fluid from an inlet to an outlet and provides a pressure differential there between due to respective pistons moving in and out of a plurality of piston chambers via a piston rod. A rotating shaft extends through a grooved end plate, and the rotating shaft is connected to either the grooved end plate or the piston rod. The grooved end plate defines an off center or eccentric groove. A bearing extends from the piston rod and fits within the groove such that when the rotational motion of the shaft rotates either the piston rod or the grooved end plate, the piston rod slides back and forth relative to the rotating shaft. Each position of the bearing within the groove determines a corresponding position of the piston rod relative to the rotating shaft. Each pair of pistons may extend from a single, continuous piston rod.

Abstract: A diffuser for a radial compressor of a turbomachine is provided. The diffuser has a plurality of diffuser channels, wherein the diffuser channels extend across a radial area of the diffuser across a bent area into an axial area of the diffuser, wherein, in the radial area of the diffuser, the diffuser channels have diffuser walls in particular at v-shaped blades that are bent in the movement direction of the radial compressor or are straight.

Abstract: A turbine system including a sealing component is presented. The sealing component is positioned in a gap between adjacent turbine components of the turbine system. The sealing component includes a metallic shim including a high-temperature-resistant alloy in a single crystal form. A turbine shroud assembly including the sealing component is also presented.

Abstract: A rotor blade for a wind turbine is provided. The rotor blade includes a pressure side, a suction side, a leading edge section with a leading edge, and a trailing edge section with a trailing edge. An airflow flows along the surface of the rotor blade from the leading edge section to the trailing edge section and builds up a boundary layer in close proximity to the surface of the rotor blade. The rotor blade includes a noise reduction device for reducing noise which is generated by interaction of the airflow and the rotor blade. The noise reduction device is located within the boundary layer of the rotor blade. The noise reduction device includes a cover and connection device for connecting the cover to the surface of the rotor blade. The cover spans at least over a part of the surface of the rotor blade.

Abstract: A control arrangement for a coolant pump of an internal combustion engine includes a control slide which controls a throughflow cross-section of an annular gap arranged between an outlet of a coolant pump impeller and a surrounding delivery duct. A control pump adapts a hydraulic pressure generated in a flow duct. An electromagnetic valve includes a first and second valve seat, a first, second and third flow connection, a closing member and an armature. The first flow connection is fluidically connected to an outlet of the control pump. The second flow connection is fluidically connected to a first pressure chamber of the control slide. The third flow connection is fluidically connected to an inlet of the coolant pump. The first valve seat is arranged between the first flow connection and the second flow connection. The second valve seat is arranged between the second flow connection and the third flow connection.

Abstract: A rotor blade for a compressor of a gas turbine engine includes an airfoil extending from a root to a tip and having a leading edge and a trailing edge. The airfoil has a span that extends from 0% at the root to 100% at the tip and a mean camber line that extends from the leading edge to the trailing edge. The airfoil has a total camber distribution that increases from the root to a maximum value of total camber between 5% of the span and 20% of the span.

Abstract: A centrifugal pump for delivering a medium comprising solid admixtures includes a blade-free space arranged in front of an impeller. The centrifugal pump has a suction-side arrangement that permits variable sizing of the blade-free space. The suction-side arrangement permits the efficiency of the centrifugal pump to be increased while avoiding blockages.

Abstract: An impeller that rotates about a central axis extending vertically includes a base portion and blades. The base portion spreads perpendicularly to the central axis. The blades are on an upper surface of the base portion at intervals in a circumferential direction. The base portion includes an irregular portion that is radially outward and in which irregularities are repeated in the circumferential direction. The irregular portion includes one or more first irregular regions and a second irregular region. The first irregular regions include first recesses with a same shape and first projections with a same shape, the first recesses and projections being alternately arranged one by one. The second irregular region is positioned between the first irregular regions and includes at least one among a second recess with a different shape from the first recesses and a second projection with a different shape from the first projections.

Abstract: An axial-flow fan includes an impeller including plural blades fixed to an outer peripheral portion of the hub and each surrounded by an inner peripheral edge, an outer peripheral edge, a leading edge, and a trailing edge. The leading edge is forward-curved in a rotational direction with an angle increasing to outer periphery of the impeller and runs toward an outer periphery up to point A, the trailing edge is forward-curved in the rotational direction and runs toward the outer periphery up to point D, recedes in the rotational direction of the impeller as the trailing edge runs toward the outer periphery up to point A? located closer to the outer periphery than point D is to the outer periphery, advances in the rotational direction of the impeller in a region between point A? and point B?, and reflexed at point D and point A?.

Abstract: A turbine vane assembly adapted for use in a gas turbine engine includes a support strut and a vane. The support strut is made of metallic materials. The vane is made of composite materials and is arranged around the support strut to insulate the metallic materials of the support strut during use of the turbine vane assembly.

Abstract: A lead-lag damper arranged inside a blade of a rotor of a rotary wing aircraft. The lead-lag damper comprises an inner strength member provided with a cage in which a ball-joint connection is arranged, an outer strength member for securing to the blade, and an elastomer material member arranged between the two strength members. The two strength members and the elastomer material member extending beyond the zone around the cage so that the relative movements between two strength members resulting from the movements of the blade are damped by deformations of the elastomer material member, at least a portion of the lead-lag damper being designed to occupy a portion of the inside of the blade that is conventionally filled with foam.

Abstract: A multi-film oil damper has an annular damper cavity defined within a housing between a radially outward wall, a first radially extending side wall and a second radially extending side wall. Nested damper rings are disposed within the annular damper cavity for defining squeeze film annuli therebetween. The squeeze film annuli are fluidly connected in parallel to an inlet gallery.

Abstract: A fan includes an impeller including a boss serving as a center of rotation and a plurality of blades provided on an outer circumferential surface of the boss, and a structure member installed on an upstream side of the impeller in an airflow direction. The plurality of blades each have a plurality of recesses disposed only on a side of a suction surface of a leading edge. The plurality of recesses each have a rectangular shape having two longitudinal sides. Consequently, it is possible to reduce fluctuations of lift on the plurality of blades and thereby reduce discrete frequency noise.

Abstract: An inducer includes a hub and a blade which radially protrudes from the hub and is helically provided. The inducer has a thick portion in which a first distance and a second distance coincides with each other in a region outside a position at which a height ratio of the blade is 0.5 while the first distance is shorter than the second distance in a region inside the position at which the height ratio of the blade is 0.5, in which the height ratio is a ratio of a distance from a connection portion between the hub and a root portion of the blade with respect to a height of the blade which is a distance from the connection portion between the hub and the root portion of the blade to a tip portion of the blade in the radial direction of the blade.

Abstract: A clearance control system for a gas turbine engine may comprise a rotor blade, an outer structure disposed radially outward from the rotor blade, and a heating element configured to cause the outer structure to be heated in response to electric current being supplied to the heating element, wherein a gap between the rotor blade and the outer structure is at least one of increased, decreased, and maintained in response to the outer structure being heated.

Abstract: An air moving device according to the present disclosure can include a housing and an installation hub. The housing can be connected to the installation hub via one or more adjustable supports. An impeller can be installed at least partially in the housing and configured to direct air out of the housing. In some embodiments, the adjustable supports can be adjusted to move the housing with respect to the installation hub. For example, the adjustable supports can be configured to modify the tilt of the housing and/or the overall distance between the housing and the installation hub. The installation hub can be installed on a ceiling, wall, or other mounting surface. Adjustment of the adjustable supports can permit vertical alignment of the air moving device housing, even when the installation hub is mounted to a slanted or sloped (e.g., non-horizontal) ceiling or wall.

Abstract: A gas turbine engine article includes a substrate and a bond coating that covers at least a portion of the substrate with a step formed in at least one of the substrate and the bond coating. A thermally insulating topcoat is disposed on the bond coating. The thermally insulating topcoat includes a first topcoat portion separated by at least one fault that extends through the thermally insulating topcoat from a second topcoat portion.

Abstract: A rotor assembly for a gas turbine engine includes, among other things, a rotatable hub that has a metallic main body that extends along a longitudinal axis, and that has an array of annular flanges that extend about an outer periphery of the main body to define an array of annular channels along the longitudinal axis. Each of the annular channels receives a composite reinforcement member that extends about the outer periphery of the hub.

Abstract: A variable geometry turbocharger includes: a turbine rotor; and a variable nozzle mechanism for adjusting a flow of exhaust gas to the turbine rotor from a scroll flow passage formed on a radially outer side of the turbine rotor. The variable nozzle mechanism includes: a nozzle vane disposed in an exhaust gas flow passage for guiding the exhaust gas to the turbine rotor from the scroll flow passage; a support wall forming a flow passage wall on a first side of the exhaust gas flow passage with respect to an axial direction of the turbine rotor and supporting the nozzle vane rotatably in a cantilever fashion; and a non-support wall forming a flow passage wall on a second side of the exhaust gas flow passage with respect to the axial direction. Of an end surface of the nozzle vane on a side of the non-support wall, an edge portion on a side of a pressure surface includes a non-support-wall side linear portion formed to have a linear shape.

Abstract: A seal and bearing assembly having a bearing received within a housing. The bearing is disposed radially outwardly of a shaft and having an inner portion and an outer portion. The outer portion has a protrusion extending at least in an axial direction. An outer diameter of the outer portion is sized to provide a radial gap between the outer diameter and the housing section. The gap receives a film of lubricant for damping movements of the bearing relative to the housing section. A sealing member has a rotating portion configured for rotation with the shaft radially spaced apart from a static portion defined by the protrusion of the bearing outer portion. There is also disclosed a method of operating such an assembly.