Abstract: A control arrangement (1) of an exhaust-gas turbocharger having a bearing bushing (3); a control shaft (4) which is connected at a first end (5) to a first adjustment lever (6) and which is guided in the bearing bushing (3); and a second adjustment lever (9) which is connected to a second end (8) of the control shaft (4) and which, on a free end region (10), bears a control device (11), wherein the free end region (10) is designed to be cranked in the direction of the first adjustment lever (6).

Abstract: A turbomachine blade is disclosed including an airfoil including a cooling fluid plenum extending therein and a trailing edge cooling opening extending from the cooling fluid plenum through a trailing edge of the airfoil. A platform may couple the airfoil to a shank, the platform including a trailing edge extending downstream relative to the shank. At least one cooling conduit delivers a cooling fluid radially inward from at least one of the cooling fluid plenum and the trailing edge cooling opening to a wheel space that is adjacent the shank and radially inward from the trailing edge of the platform. A related turbomachine is also disclosed.

Abstract: A bearing load sharing system comprising: first and second rotors extending in an axial direction; a first thrust bearing having an inner race and an outer race, the inner race connected to the first rotor; a second thrust bearing having an inner race and an outer race, the inner race connected to the second rotor; and an inter-rotor bearing having an inner race and an outer race, the inner race connected to one of the first and second rotor and the outer race connected to the other of the first and second rotor; wherein the outer race of the first bearing and/or the outer race of the second bearing is movable to vary the axial spacing between the outer races.

Abstract: A guide vane (300) for a turbomachine, having a sealing device (27, 27?) at the radially inner end region of the guide vane (300) for sealing leakage flows (25) between the guide vane (300) and an inner ring (7) joined thereto. The sealing device (27, 27?) is movably configured relative to the guide vane (300). The sealing device (27, 27?) is positionable in at least one open or in a closed configuration for sealing the leakage flows (25). Also, a guide vane (100), as well as a turbomachine.

Abstract: A hydraulic actuating device is provided for a positive-locking shifting element of a transmission with a cylinder, in which a piston is arranged in a manner displaceable between a first end position and a second end position. The piston is a stepped piston and, with the cylinder, bounds an additional pressure chamber, which is connected to a first pressure chamber and/or a second pressure chamber through at least one hydraulic line. The volume of the additional pressure chamber decreases during an actuating movement of the piston in the direction of the first end position and increases during an actuating movement of the piston in the direction of the second end position. The degree of locking of the connection between the additional pressure chamber and the first pressure chamber and/or the second pressure chamber increases through the cylinder from a defined actuating path of the piston prior to reaching the first end position up to the first end position.

Abstract: An airfoil (10) is disclosed for a gas turbine engine in which the airfoil (10) includes an internal cooling system (14) with one or more converging-diverging exit slots (20) configured to increase the effectiveness of the cooling system (14) at the trailing edge (34) of the airfoil (10) by increasing the contact of cooling fluids with internal surfaces (24, 30) of the pressure and suction sides (36, 38) of the airfoil (10). In at least one embodiment, the trailing edge cooling channel (18) may include one or more converging-diverging exit slots (20) to further pressurize the trailing edge cooling channel (18) and may be formed by a first and second ribs (80, 82) extending between an outer walls (13, 12) forming the pressure and suction sides (36, 38).

Abstract: A progressive vortex pump comprises an inlet housing in contact with the pumped fluid, a pump housing connected to the inlet housing, and an outlet housing connected to the pump housing and connected to a pumping pipe. The pump housing comprises a disc-shaped rotor having a central bore and a rim with vanes. Each rotor comprises at least one through hole along the axial direction, the through hole being positioned between the central bore and the rotor rim. Advantageously, the presence of a through hole on the rotor enables, under operating conditions, fluid exchange from the posterior fluid film to the anterior fluid film, thus promoting a pressure balance between the posterior and anterior fluid films, therefore enabling the rotor to work evenly, preventing rubbing on adjacent diffusers.

Abstract: A fan, in particular an axial fan, comprising a support element with a wall ring and an electric fan motor which is mounted in the wall ring and comprises a fan rotor. The wall ring has on its outer periphery a hinge consisting of a first hinge part that is connected to the wall ring and a second hinge part that can be pivoted about a hinge axis relative to the first hinge part, wherein the second hinge part is designed as a terminal box for receiving electrical connectors. The invention further relates to a support element for such a fan.

Abstract: A turbine blade includes a platform that has a platform leading edge and trailing edge joined by two platform circumferential sides. An airfoil extends radially outwardly from the platform to a free tip end. The airfoil includes an airfoil leading edge and trailing edge joined by opposed pressure and suction sides. A root extends radially inwardly from the platform. The platform and the airfoil include film cooling holes that have external breakout points that are located in substantial conformance with the Cartesian coordinates set forth in Table 1. The Cartesian coordinates provided by an axial coordinate, a circumferential coordinate, and a radial coordinate, relative to a zero-coordinate, and the cooling holes have a diametrical surface tolerance relative to the specified coordinates of 0.200 inches (5.0 mm).

Abstract: One embodiment is an apparatus comprising a first rotational component including an elongated connecting element fixed thereto and extending axially therefrom through a second rotational component to an end structure. The connecting element is connected to the end structure to compress the second rotational component between the end structure and the first rotational component.

Abstract: The cooling effectiveness of a turbine blade that a gas turbine engine or the like is provided with is further increased by providing a convex portion that is arranged in the inner portion of a cooling air hole and that is provided projecting out from the inner wall surface of the cooling air hole.

Abstract: A drivetrain for a horizontal axis wind turbine includes a main shaft, and a main bearing housing having a main body at least partly enclosing the main shaft and extending from a first end to a second end, a distance from the second end to the rotor attachment flange being larger than a distance from the first end to the rotor attachment flange. The main bearing housing: carries the main shaft via a first bearing and a second bearing, a distance between the second bearing and the rotor attachment flange being larger than a distance between the first bearing and the rotor attachment flange; has a first seat for the first bearing, and a second seat for the second bearing; and includes a seat flange extending from the main body at least partly radially inwards, the second seat being located on a distal end of the seat flange.

Abstract: A gearbox for driving equipment of a turbomachine, including a substantially V-shaped box having two arms joined together by a joining part, the arms containing gear trains joined together at the joining part, and an attachment to the turbomachine. The attachment include a mechanism for insetting and/or for attaching the joining part and a suspension device of the arms.

Abstract: A method for making blade unit with divided shaft facilitating drastically the productivity and assembling compared to a method fixing blade to a shaft using many connecting parts. The method for making blade unit includes steps for making a blade with divided shaft comprising a blade and a divided shaft that is attached integrally to a root portion of the blade and divided into a plurality of portions in a direction of length of the shaft, and combining a plurality of made blades with divided shaft together with one another through the divided shaft.

Abstract: A check seat assembly includes a check valve seat with a by-pass passage in parallel with a check valve passage of the check seat assembly to meter flow and maintain stability of a hydraulic system, such as a hydraulic cylinder. The check valve may include an o-ring seated in a V-shaped groove. The check seat assembly may allow flow from a pump to a hydraulic cylinder to freely pass through the check valve to pressurize one side of a piston of the hydraulic cylinder, such as a front side of the piston to retract a corresponding rod connected to the piston.

Abstract: A seal configuration (100) for a turbo machine having a rotor (5), wherein the seal configuration (100) has a sealing element (300) to create a seal with respect to the rotor (5) in an installed position and a supporting device (200). The supporting device (200) has, in at least one section of the supporting device, a material (9) that melts when it comes into contact with the rotating rotor (5) in the installed position. A turbo machine having a seal configuration (100) is also provided.

Abstract: A diffuser for a gas turbine including a support structure and a liner connected by holders. The liner includes a plurality of adjacent segments with overlapping borders. The overlapping borders are clamped to one another and slidingly rest one above the other.

Abstract: The present invention provides an apparatus for providing a balancing weight in a groove on a rotor disk in a gas turbine engine. The apparatus comprises an elongate reservoir for housing a hardenable material and an inflatable balloon in fluid communication with the distal end of the elongate reservoir. An actuator is provided for forcing the hardenable material from the elongate reservoir to inflate the inflatable balloon with hardenable material within the groove on the rotor disk. A sealing device for sealing the inflated inflatable element to form the balancing weight is also provided.

Abstract: An assembly can include a turbine housing that defines a bore, a wastegate opening, a wastegate passage to one side of the wastegate opening and a chamber to another side of the wastegate opening and that includes a wastegate seat disposed about the wastegate opening; a rotatable wastegate shaft configured for receipt by the bore; a wastegate arm that extends from the wastegate shaft; and a wastegate plug that extends from the wastegate arm where the wastegate plug includes a seal surface that includes a toe end and a back end where the back end includes a radius of curvature that exceeds a radius of curvature of the toe end.

Abstract: An object of the present invention is to provide a natural energy extraction apparatus comprising a vertical rotating shaft and a float for supporting the vertical rotating shaft, wherein the internal structure of the float is simpler, the float and a mooring apparatus are more compact, and production cost is lower than in the conventional natural energy extraction apparatus. A natural energy extraction apparatus comprises a first float forming a swingable vertical rotating shaft, a second float moored to surround the first float, and a power transmission device attached to the second float to convert rotational kinetic energy of the first float to driving torque for driven equipment, and the natural energy extraction apparatus is installed on a body of water.