Abstract: A turbine blade includes an airfoil body, and a plurality of cooling passages extending along a blade height direction inside the airfoil body and being in communication with each other to define a serpentine flow passage. The plurality of cooling passages include first turbulators on an inner wall surface of an upstream cooling passage of the plurality of cooling passages, and second turbulators on an inner wall surface of a downstream cooling passage of the plurality of cooling passages. A second angle formed by the second turbulators with respect to a flow direction of a cooling fluid in the downstream cooling passage is smaller than a first angle formed by the first turbulators with respect to the flow direction of the cooling fluid in the upstream cooling passage.

Abstract: A vertical axis turbine includes a rotatable hub assembly that is configured to be connected to an energy sink and rotatable about an axis of rotation. At least two blades are mounted on the hub assembly, each blade including a leading edge and a trailing edge, the blades being oriented so that the respective leading edges face in a common rotational direction. Each blade further includes a straight section that is substantially parallel to the axis of rotation and two helical sections, the straight section being interposed between the helical sections, and the helical sections extending at least partially around the axis of rotation.

Abstract: A rotor assembly for a gas turbine engine includes a turbine shaft disposed about a longitudinal axis, a first rotor and a second rotor configured for rotation about the longitudinal axis, and an intermediate shaft positioned radially between the turbine shaft and the second rotor. The second rotor is mounted to and axially adjacent the first rotor. The intermediate shaft is mounted to the turbine shaft on an inner radial side of the intermediate shaft. The intermediate shaft is mounted to the second rotor on an outer radial side of the intermediate shaft.

Abstract: An airfoil includes a root and a tip, which define a span of the airfoil therebetween. The airfoil also includes a leading edge and a trailing edge downstream of the leading edge along a flow direction. The leading edge and the trailing edge each extend across the span of the airfoil from the root to the tip. The airfoil further includes a pressure side surface and a suction side surface. The airfoil also includes a thermal barrier coating on the pressure side surface and the suction side surface. The thermal barrier coating includes a base layer and a top coat. A thickness of the base layer varies across each of the pressure side surface and the suction side surface with a maximum thickness of the base layer at the leading edge.

Abstract: A structure for assembling turbine blade seals, a gas turbine including the same, and a method of assembling turbine blade seals are provided. The structure for assembling turbine blade seals includes a turbine blade including an airfoil, a platform, and a root, a turbine rotor disk to which the root of the turbine blade is mounted, a seal plate mounted between the platform and one side of the turbine rotor disk to seal a cooling channel defined within the root and the platform, an insertion pin inserted through the turbine rotor disk and the seal plate to fix the seal plate to the turbine rotor disk, and a retainer configured to fix the insertion pin and to prevent the insertion pin from falling out.

Abstract: Impingement insert for an airfoil of a blade/vane of a gas turbine is provided. The impingement insert includes a double-walled section having an outer and an inner walls, that define—an inner channel at an inner surface of the inner wall, an outer channel at an outer surface of the outer wall and a middle channel between the outer and the inner walls. Impingement cooling holes are provided in the outer wall that use the cooling air of the middle channel to eject impingement jets into the outer channel. The impingement insert includes at least one extraction duct that extends between the outer and the inner walls across the middle channel, and has an inlet at the outer channel, and an outlet at the inner channel, for flowing the cooling air, after impingement, from the outer channel into the inner channel.

Abstract: An exhaust turbocharger turbine wheel can include a hub that includes a nose, a backdisk with a shaft joint portion, and a rotational axis; blades that extend from the hub to define exhaust flow channels where each of the blades includes a leading edge, a trailing edge, a hub profile, a shroud profile, a pressure side, and a suction side; where the backdisk includes an outer perimeter radius measured from the rotational axis of the hub, an intermediate radius at the shaft joint portion measured from the rotational axis of the hub, and an annular recess disposed between the intermediate radius and the outer perimeter radius and defined in part by three-dimensional bolster regions, where each of the three-dimensional bolster regions includes a footprint and a height measured at least in part in a direction of the rotational axis of the hub.

Abstract: A compressor bleed port apparatus includes: a compressor shroud which defines a boundary between a primary flowpath and a plenum; a bleed port including one or more apertures passing through the compressor shroud, each of the one or more apertures having an inlet communicating with the primary flowpath and an outlet communicating with the plenum, and extending along a respective centerline. Each of the one or more apertures is bounded by sidewalls, and includes a diffuser section in which the sidewalls diverge from each other in a downstream direction; A diffusing angle between the sidewalls varies over the length of the diffuser section.

Abstract: A turbine blade for a gas turbine engine has an airfoil including leading and trailing edges joined by spaced-apart pressure and suction sides to provide an external airfoil surface extending from a platform in a spanwise direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil defined by a set of Cartesian coordinates set forth in Table 1, the Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by a local axial chord, and a span location.

Abstract: A rotor assembly for a gas turbine engine includes a turbine shaft disposed about a longitudinal axis, a first rotor and a second rotor configured for rotation about the longitudinal axis, and an intermediate shaft positioned radially between the turbine shaft and the second rotor. The second rotor is mounted to and axially adjacent the first rotor. The intermediate shaft is mounted to the turbine shaft on an inner radial side of the intermediate shaft. The intermediate shaft is mounted to the second rotor on an outer radial side of the intermediate shaft.

Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a first drain tube, a second drain tube, a container and a gas tube. The container fluidly couples the first drain tube to the second drain tube. The container is configured to receive fluid from the first drain tube. The gas tube is fluidly coupled with the container. The gas tube is configured to direct gas into the container for propelling the fluid received within the container into the second drain tube.

Abstract: A ceiling fan assembly or similar air-moving device can include a motor for rotating one or more blades to drive a volume of air about a space. The ceiling fan assembly can further include a hanger ball with an indexing pin. The ball hanger can be received by a mounting bracket so that, via an alignment guide, the indexing pin of the hanger ball aligns with an indexing groove on the mounting bracket.

Abstract: A centrifugal fan includes a housing and an impeller. The housing includes a sidewall, and the sidewall includes a tongue portion. The impeller includes a fan hub and a plurality of blades. The fan hub is rotatably disposed in the housing, and the tongue portion has an inner contour line on a reference plane. The blades connect to the fan hub. Each one of the blades has an end surface facing the sidewall. The end surface has an outer contour line on the section of the blade. Any two adjacent blades have different outer contour lines. The outer contour line of at least one first blade of the plurality of blades is parallel to the inner contour line. The outer contour line of at least one second blade of the plurality of blades is not parallel to the inner contour line.

Abstract: A wicket gate for a hydraulic turbine or pump contains a blade being defined by a pressure surface, an oppositely facing suction surface, a leading edge and a spaced apart trailing edge, a first trunnion, a second trunnion, an air inlet aperture, an air passage and at least one air outlet aperture. The profile of the suctions side surface of the blade along a cross section through a point P1 and a point P2 is concave. Whereas point P1 is located on the suction side surface of the trailing edge where an air outlet aperture is located and point P2 is spaced apart from point P1 by less than 10% of the wicket gate length D and point P2 is located upstream of point P1 on a line perpendicular to the trailing edge starting at point P1.

Abstract: A return geometry fluidically connects a first and a second compressor stage of the turbocompressor. The return geometry has multiple partial helices that are evenly or unevenly distributed in the circumferential direction. The multiple partial helices extend at least in part in the circumferential direction. They form flow channels that extend at least in some sections, separately from each other, to fluidically connect the first and second compressor stages.

Abstract: A gas turbine engine component includes a tubular body section including a plurality of fiber wraps encompassed within a matrix composition and one or more integrally-formed stiffeners extending from an outer surface of the body section and in a component circumferential direction around the body section. The stiffener includes one or more fiber wraps extending radially outwardly from the body section over a form and to the body section from the form.

Abstract: A vacuum pump generally comprises a low pressure portion and a high pressure portion separated by a gas impermeable partition. Gas molecules exit the low pressure portion through an opening in the partition and passively impinge on a featureless rotatable surface in the high pressure portion. A drive rotates the rotatable surface with tangential velocity in the supersonic range at multiple times the most probable velocity of the impinging gas molecules. Impinging gas molecules are ejected outwardly from the periphery of the rotatable surface generating a substantial net outward flow of gas and reducing the pressure in the low pressure portion. The vacuum pump is effective to reduce the pressure in the low pressure portion to a target minimum pressure without using seals to prevent gas molecules from leaking back to the low pressure portion and without using blades or vanes to actively impact the gas molecules.

Abstract: Provided is a rotor for a wind turbine, including: a blade, a hub, a pitch bearing being configured to support the blade rotatably about a longitudinal axis of the blade and relative to the hub, and one or more metal arcs for conducting a lightning current from the blade to the hub, the one or more metal arcs including: a first arc portion electrically and mechanically connected to the blade, a second arc portion electrically and mechanically connected to the hub, and a bent portion connecting the first and second arc portions. The metal arcs being configured such that, when the blade rotates relative to the hub, the first arc portion is shifted relative to the second arc portion and a length of the first arc portion is reduced or increased at the expense of an increase or decrease of a length of the second arc portion.

Abstract: A method may include: in a used metal turbomachine blade including a root including a shank, a platform coupled to the shank and an airfoil coupled to the platform, removing the airfoil, leaving a remaining base including the platform, the shank and the root. The method may also form a radially extending opening through the platform into the shank, and insert a ceramic shank nub extending from a ceramic airfoil into the radially extending opening of the remaining base. The ceramic airfoil is fixedly attached to the remaining base. The method allows reuse of the metal shank while providing the lower cooling requirements of a ceramic airfoil.

Abstract: A mainframe mounts the drivetrain of a wind turbine, and to an arrangement comprising such a mainframe, and to a wind turbine having a corresponding arrangement. For the purpose of mounting the drivetrain of a wind turbine, the mainframe is realized with two bearing points that are spaced apart from each other, a partial flange, having a fastening region shaped as a circular ring segment, being provided at at least one bearing point. The arrangement comprises, besides the mainframe, at least one ring element configured to radially encompass the drivetrain. At least one ring element is fastened to the fastening region, shaped as a circular ring segment, of a bearing point of the mainframe. In the case of the wind turbine, the drivetrain is mounted by means of the described arrangement.