Abstract: The rotor of a hybrid aerodyne for producing lift by rotating during a stage of vertical flight and then for being held stationary and stored longitudinally during a stage of cruising flight has at least one single-blade with a counterweight. The length of the active blade that generates lift of the rotor while rotating is significantly shorter than the length of the radius of the rotor. The portion that carries the active blade that makes the connection between the active blade and rotor mast is structurally rigid. The rigid portion that carries the active blade presents a cross-section optimized to provide zero or almost zero lift and very little aerodynamic drag while the rotor is rotating. The assembly is hinged about a transverse axis perpendicular to the vertical axis of the rotor and substantially on the vertical axis of the rotor mast.

Abstract: A liquid pump comprising a motor housing, a motor, a volute housing joined to the motor housing, and upper and lower seals contained in the volute housing. The motor housing has a motor housing side wall including a distal end joined to the volute housing. The motor includes a rotatable shaft that extends into the volute housing. The volute housing includes an upper volute wall having a major portion in direct fluid communication with the motor housing volume, thereby enabling a high rate of heat transfer from the motor to the fluid in the volute that is being pumped. In that manner, the pump has dual seal capability that reduces the risk of motor damage due to a seal failure, while also having a high rate of heat transfer out of the motor housing, which reduces the risk of failure of the motor from operating at a high temperature.

Abstract: A compressor housing (12) for a turbocharger includes a recirculation cavity (4) formed in a portion of the compressor housing (12). The recirculation cavity (4) is defined by an inner cavity wall (2) and an outer cavity wall (5). In addition, an inlet groove (1) and an outlet (7) are formed in the recirculation cavity (4) for circulating airflow from the compressor housing (12) through the recirculation cavity (4), and at least one recirculation noise obstruction (6) is fixedly secured within the recirculation cavity (4) to disrupt air flow through the cavity and reduce noise in the compressor housing (12).

Abstract: The present invention belongs to the technical field of fluid machinery, and proposes a rotating guide vane module for hydraulic working condition adjustment and a method of assembling in a turbopump. The rotating guide vane module comprises a rotating guide vane back cover plate, a rotating guide vane front cover plate, a rotating guide vane drive gear, and rotating guide vanes. Each rotating guide vane is an integrally-formed independent component and comprises a rotating guide vane back seat, a blade, a rotating guide vane front seat, and a shaft. When the rotating guide vane module for hydraulic working condition adjustment of the present invention is used for adjusting the hydraulic working condition, a center gear rotates to drive the rotating guide vane drive gear, and then the rotating guide vanes rotate to change their opening degrees.

Abstract: A sheet having a fan-mounting part for mounting a fan is provided. The fan includes a fan body including a cylinder part and a protrusion which is disposed on the cylinder part protruding in a direction substantially perpendicular to a side face of the cylinder part and an engaging member which is fitted on an outer side of the cylinder part and is thus attached to the fan body so as to be opposite the protrusion. The sheet having the fan-mounting part includes a sheet member and a non-stretchable flat ring-shaped reinforcing section. The sheet member has an open hole for receiving the cylinder part of the fan. The reinforcing section has an opening with substantially the same shape as an outer edge of the cylinder part of the fan.

Abstract: A centrifugal pump including an outer case; an inner case; a first unit and a second unit placed in fluid communication with each other, each unit including a plurality of impellers; the inner case includes two half-parts joined along a connection plane containing the axis of rotation; a connecting element is placed between the first unit and the second unit, the connecting element is engaged with a last impeller of the first unit and with a last impeller of the second unit.

Abstract: A blower unit, particularly for an apparatus for assisting respiration, comprises a housing (2), an impeller (1) accommodated in an impeller chamber (3) in the housing (2), and a motor (12), connected to the impeller (1) via a shaft (15), which is accommodated in a motor chamber (13) in the housing (2). The motor (12) is fixed between walls (14, 18) of the motor chamber (13) by means of buffers, with at least one of the buffers being a sealing ring (16) which separates the shaft (15) from a passage for cooling air (33) which, in radial section, extends annularly around the motor (12).

Abstract: A rotor blade assembly for a wind turbine is presented. The rotor blade assembly includes a rotor blade having a surface, where the surface of the rotor blade includes an inclined groove. The rotor blade assembly further includes at least one add-on element mounted on the surface of the rotor blade via a bonding interface downstream of the inclined groove such that particulate matter in an airflow upstream of the at least one add-on element is deflected away from the bonding interface between the surface of the rotor blade and the at least one add-on element. The wind turbine having the rotor blade assembly is also presented.

Abstract: A convertible ducted fan engine and mounting system. The convertible ducted fan engine has a shroud encircling a mechanical fan. The convertible ducted fan engine includes a fluid-propulsion configuration in which the mechanical fan rotates freely with respect to the shroud to produce thrust through fluid flow, and a drive-wheel configuration in which the shroud rotates about the rotational axis. The mounting system includes at least one gimbal ring and may include a circular track system thereby enabling the convertible engine to be oriented in any direction.

Abstract: The present disclosure is directed to a turbomachine that includes a hot gas path component having an inner surface and defining a hot gas path component cavity. An impingement insert is positioned within the hot gas path component cavity. The impingement insert includes an inner surface and an outer surface and defines an impingement insert cavity and a plurality of impingement apertures fluidly coupling the impingement insert cavity and the hot gas path component cavity. A plurality of pins extends from the outer surface of the impingement insert to the inner surface of the hot gas path component.

Abstract: A pump features a trimmed impeller having a trimmed impeller diameter that is less than a standard full-sized diameter of a standard full-sized impeller for a standard full-sized casing, and having a circumferential outer edge; and a modified standard full-sized casing having dimensions corresponding to the standard full-sized casing and configured to house the trimmed impeller for pumping a fluid, having an outer peripheral wall, and having an inner annular volute portion between the circumferential outer edge of the trimmed impeller and the outer peripheral wall configured with a volume of material deposited using an additive manufacturing process so as to fill in vacant space otherwise caused by the trimmed impeller diameter being less than the standard full-sized impeller diameter. The additive manufacturing process is a directed energy deposition.

Abstract: A component according to the disclosure may include a body having an aperture therein for receiving one of a turbomachine shaft or a lathe chuck, wherein in response to the body being coupled to the lathe chuck, the aperture is oriented substantially axially relative to an axis of rotation of the body with the lathe chuck; and a flange coupled to and in direct axial contact with the body, the flange including a surface that extends axially relative to the axis of rotation of the body, wherein the surface of the flange comprises a matingly engageable face configured to contact an axially aligned surface during operation of the component and having a sanding indentation thereon, wherein a surface roughness of the surface of the flange is less than a surface roughness of a remainder of the component.

Abstract: A turbocharger includes a center housing that includes a through bore and a stepped locating pin socket that includes a stop surface; a bearing disposed in the through bore where the bearing includes an opening; and a stepped locating pin where the stepped locating pin includes a pin portion received in part by the opening of the bearing and a seating portion secured via an interference fit in the stepped locating pin socket where a maximum radius of the seating portion exceeds a maximum radius of the pin portion and where the stepped locating pin includes a stop surface that contacts the stop surface of the stepped locating pin socket to axially position the stepped locating pin in the stepped locating pin socket.

Abstract: A fan includes a central hub defining an inlet, a motor positioned within the central hub, and an impeller positioned within the central hub. The impeller is operable to be rotated by the motor to generate air movement. The fan also includes a nozzle defining a channel that receives the airflow from the central hub. The nozzle also defines an outlet in communication with the channel to direct air out of the nozzle. The fan further includes a plurality of conduits connecting the nozzle to the central hub to direct air from the central hub to the channel and through the outlet of the nozzle. The nozzle defines a projection aligned with each conduit to divide air movement through the nozzle.

Abstract: A gas turbine engine includes a compressor section and a turbine section. A first spool is rotatable with a first turbine of the turbine section and a first compressor of the compressor section. Additionally, a second spool is rotatable with a second turbine of the turbine section and a second compressor of the compressor section. An electric machine is positioned at least partially inward of the core air flowpath of the gas turbine engine along a radial direction of the gas turbine engine. Additionally, the exemplary gas turbine engine includes a gear assembly mechanically coupled to both the first spool and the second spool, such that the first and second spools may each drive the electric machine.

Abstract: A nozzle including a vane and a band, each having defined therein interlocking features. The vane and the band are each formed of a ceramic matrix composite (CMC) including reinforcing fibers embedded in a matrix. The vane and the band include one or more interlocking features. The nozzle further including an interlocking mechanical joint joining the vane and the band to one another. Methods are also provided for joining the vane and the band at the interlocking features to form an interlocking mechanical joint.

Abstract: A convertible ducted fan engine having a shroud, a drive shaft connected to a mechanical fan, and a rotational drive motor configured to rotate the mechanical fan. An embodiment includes a linear drive motor configured to translate the drive shaft and mechanical fan in a direction parallel to a longitudinal axis of the shroud. The convertible ducted fan engine includes a fluid-propulsion configuration in which the mechanical fan rotates freely with respect to the shroud to produce thrust through fluid flow, and a drive-wheel configuration in which the shroud rotates about the rotational axis.

Abstract: A wind turbine blade (10) for a horizontal axis wind turbine (2), wherein the wind turbine blade (10) extends in a longitudinal direction parallel to a longitudinal axis and having a tip end (14) and a root end (16), and wherein the wind turbine blade (2) further includes a shell body is disclosed. The wind turbine blade (10) further includes a root end flange (55, 155, 255) at the root end (16) of the blade (10) and which includes a ring-shaped body that extends circumferentially along the entire root end (16), the root end flange (55, 155, 255) preferably made from a metal, such as stainless steel. The root end flange (55, 155, 255) includes an inwardly extending protrusion (70, 170) with a distal plate part (72, 172, 272, 372, 472, 572, 672, 772) arranged in a distance from the ring body.

Abstract: A stator configuration for a gas turbine engine including a splitter segment. Also included is a first stator extending radially outwardly from the splitter segment. Further included is a second stator extending radially inwardly from the splitter segment, the splitter segment, the first stator and the second stator being a single, integrally formed structure.

Abstract: The invention relates to a wind turbine that includes a rotor rotating about a horizontal axis of rotation substantially parallel to the direction of the wind, the rotor having a front face facing into the wind and substantially perpendicular to the axis of the wind, and a rear face situated toward a support of the rotor. At least two distinct families of blades are distributed on the rotor, each family of blades including at least two blades having a free end and a blade root end connected to said rotor. Each family of blades includes a catching blade guiding the wind toward a force blade having a surface arranged substantially perpendicular to the axis of the wind, the blade root ends of each family of blades are successively offset on an exterior surface of the rotor along the axis of rotation thereof.