Abstract: Various embodiments of the invention include turbine buckets and systems employing such buckets. Various particular embodiments include a turbine bucket having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge, the base including a non-axisymmetric contour proximate a junction between the base and the airfoil.

Abstract: A turbine rotor blade includes a tip portion having a pressure tip wall and a suction tip wall, a tip leading edge and a tip trailing edge. Also included is a squealer cavity at least partially defined by the pressure tip wall and the suction tip wall. Further included is at least one hole defined by the suction tip wall, the at least one hole configured to bleed a cooling flow out of the squealer cavity into a hot gas path to reduce pressure within the squealer cavity. Yet further included is a main body having a suction side wall and a pressure side wall each extending from a root portion of the turbine rotor blade to the tip portion.

Abstract: A soft composite actuator is described, including a first elastomeric layer; a strain limiting layer; and a first radially constraining layer, wherein the first elastomeric layer is disposed between the first radially constraining layer and the strain limiting layer; and the elastomeric layer, the strain limiting layer, and the radially constraining layer are bonded together to form at least one bladder for holding pressurized fluid. Methods of using and making of the soft composite actuator are described.

Abstract: An exhaust-gas turbocharger (1) with 2-channel turbine inflow, including a housing (2), a shaft (6) mounted in the housing (2), a compressor wheel (8) arranged on the shaft (6) and a turbine wheel (7) arranged on the shaft (6), and a first and a second inflow duct (11, 12) formed in the housing (2). Both inflow ducts (11, 12) open in the direction of the turbine wheel (7). A partition (9) separates the two inflow ducts (11, 12) from one another. At least one water-cooling duct (10) is provided in the interior of the partition (9).

Abstract: A turbine wheel (1) of an exhaust-gas turbocharger (2), formed from a titanium aluminide material, having a wheel back (7) which is of closed configuration as viewed from an axial direction (A) and which has an outer contour (17), a hub (3) which extends from the wheel back (7) and which tapers along the axial direction (A), and a multiplicity of turbine blades (4) which extend from the wheel back (7) and from the hub (3) and which blades extend outward in a radial direction (R), as far as a connection region outer diameter (DAB) at least in a connection region (5). The wheel back (7) has, in an outer region (11) adjoining the connection region (5), a wheel back outer diameter (DRR) which is greater than or equal to the connection region outer diameter (DAB).

Abstract: A hydrostatic axial piston machine (1) utilizing a bent-axis construction has a driveshaft (4) with a drive flange (3) rotatable around an axis of rotation (Rt) inside a housing (2). A cylinder barrel (7) has pistons (10) fastened in an articulated manner to the drive flange (3). The drive flange (3) is supported on a housing-side slide face (101) by an axial bearing (100) in the form of a hydrostatically relieved sliding bearing (102) having a plurality of slippers (105). Each of the slippers (105) is mounted in an articulated manner in the drive flange (3) so that when the drive flange (3) rotates, a compensating force (FFR) acts on the slipper (105) which is in the opposite direction to the centrifugal force (FF) acting on the slipper (105). The point of application (AP) of the compensating force (FFR) on the slipper (105) is selected so that there is no tipping moment on the slipper (105) or to compensate for some or all of any tipping moment that does occur.

Abstract: A cross-flow fan includes an impeller and a shaft. The impeller includes a plurality of support plates and a plurality of blades. The blades are different in a blade cross section orthogonal to an impeller rotational axis, and each have a plurality of regions arranged in a direction of the impeller rotational axis and a coupling portion formed so as to couple the plurality of regions to each other. A rib is formed on the coupling portion, or formed in a region adjacent to the coupling portion within a range separated away from the coupling portion by up to 20% of a length of the region adjacent to the coupling portion in the rotational axis direction.

Abstract: A turbine nozzle includes an airfoil that extends in span from an inner band to an outer band where the inner band and the outer band define inner and outer flow boundaries of the turbine nozzle. At least one of the inner band and the outer band defines a plurality of cooling channels formed and a coolant discharge plenum beneath a gas side surface of the corresponding inner or outer band that is in fluid communication with the cooling channels. The coolant discharge plenum is formed within the inner band or the outer band downstream from the cooling channels and upstream from a plurality of coolant discharge ports.

Abstract: A drive system, in particular for a self-propelled construction machine, in particular a soil compactor, comprises a drive unit, at least one hydraulic circuit with a hydraulic pump driven by the drive unit, a hydraulic drive support unit with a hydraulic pump/motor assembly, and at least one pressure fluid reservoir, wherein the hydraulic pump/motor assembly is, or can be, drivingly coupled with the drive unit and/or at least one hydraulic circuit, wherein the hydraulic pump/motor assembly can be operated in a charging operating mode by the drive unit and/or at least one hydraulic circuit as a pump to charge at least one pressure fluid reservoir, and be driven in a drive support operating mode as a motor to provide a drive support torque for the hydraulic pump of at least one hydraulic circuit, characterized in that the hydraulic pump/motor assembly is operated in a recirculation operating mode as a pump to convey fluid out of a fluid reservoir and into a fluid reservoir.

Abstract: A drive unit of a fluid-actuated linear drive includes a piston rod, an annular drive piston seated coaxially on the piston rod and a buffer sleeve which is likewise seated coaxially on the piston rod. These components are secured to one another by one and the same common welded joint. Furthermore, a method for the manufacture of such a drive unit and a fluid-actuated linear drive equipped with such a drive unit is proposed.

Abstract: A nacelle for a turbofan propulsion system that extends along a centerline includes a forward cowling and an aft cowling. To improve the fit of a turbofan propulsion system in the space between the wing and ground of a fixed-wing aircraft, the aft cowling of the nacelle is modified. The aft cowling has a non-circular cross-sectional geometry disposed in a plane substantially perpendicular to the centerline. The non-circular cross-sectional geometry includes a radially recessed section disposed between first and second curved sections. The first and the second curved sections each have a radius that is greater than a radial distance between the centerline and a center point of the radially recessed section.

Abstract: Embodiments of the present disclosure provide a cooling structure for a stationary blade, including: an endwall coupled to a radial end of an airfoil; a chamber positioned within the endwall and radially displaced from a radially outer end of the trailing edge of the airfoil, wherein the chamber includes a pair of opposing chamber walls, one of the pair of opposing chamber walls being positioned proximal to the pressure side surface of the airfoil and the other of the pair of opposing chamber walls being positioned proximal to the suction side surface and the trailing edge of the airfoil, and wherein the cooling fluid in the chamber is in thermal communication with least a portion of the endwall positioned proximal to the pressure side surface and the trailing edge of the airfoil; and a plurality of thermally conductive fixtures positioned within the chamber.

Abstract: A cylinder has first and second coupling partners. The first coupling partner is a cylindrical tube. The second coupling partner is a closing element. One coupling partner is inserted axially into the other coupling partner. Each of the coupling partners has an annular groove. The groove of the inserted coupling partner is an external groove. The groove of the remaining coupling partner is an internal groove and the grooves of the coupling partners lie opposite one another. The working cylinder includes a spring-loaded coupling ring, and which when deformed in a tensioning direction, can be fully accommodated by the groove of one coupling partner and which, when deformed in the release direction, engages in the grooves of both coupling partners. The inserted coupling partner is oversized in relation to the remaining coupling partner and provides a additional frictional connection.

Abstract: A housing for a gas turbine is disclosed. At least one wall element is housed on the housing so as to move, which limits a flow channel of the housing in the radial direction from a rotational axis of a rotor of the gas turbine toward the exterior. The housing includes at least one variably adjustable guide blade which extends through the wall element into the flow channel. The wall element can be moved between a sealing setting, in which the wall element makes contact at least in a partial area of a side of a blade leaf of the guide blade facing toward the wall element, and an open setting, in which the blade leaf and the wall element are spaced some distance apart from one another. A gas turbine as well as a process for operating a gas turbine is also disclosed.

Abstract: A turbocharger (10) includes a shaft (26) rotatably supported within a bearing housing (28), a turbine wheel (22) connected to the shaft (26), and a heat shield (150, 250) disposed between the turbine wheel (22) and the bearing housing (28). The heat shield (150, 250) includes surface features (80, 180) formed on at least one of a sidewall (57) portion thereof and a flange (63) portion thereof that locate the heat shield (150, 250) relative to the bearing housing (28) such that the heat shield (150, 250) is coaxial with the rotational axis of the shaft (26).

Abstract: Provided is a body reservoir assembly whose height can be reduced. In the body reservoir assembly, the reservoir comprises: a recessed portion formed on a bottom surface of the reservoir; and a reservoir side connecting portion formed in the recessed portion and connected to a cylinder portion.

Abstract: The present disclosure includes gas turbine engine components which are cooled internally through the inclusion of lattice structures. Such structures may comprise a network of branches and nodes. Further, the branches may vary in size, shape, and configuration.

Abstract: A fan comprising: (a) an impeller, (b) a motor connected to the impeller so that during operation the motor drives the impeller to move a fluid; (c) an instrumentation assembly that includes one or more components for controlling one or more operations of the fan; (d) an interface in communication with the instrumentation assembly; wherein the interface is configured so that one or more programs, one or more signals, or both can be input into the fan after a final assembly of the fan so that the fan can be configured to perform a desired function at the time of installation into a final product, reconfigured for a different purpose than originally programmed, or both.

Abstract: A system for sealing an oil chamber from an adjoining exterior volume, and a turbo-machine including a sealing system. The system for sealing the oil chamber from the adjoining exterior volume, both of which are delimited by a mobile rotor in rotation about an axis and a part, fixed or mobile, includes: a first seal arranged between the rotor and the part; a second seal that is mounted between the rotor and the part and which is offset longitudinally relative to the first seal, to form with the first seal a sealing chamber delimited by the rotor, the part, and the two seals; and a mechanism for supplying gas to the sealing chamber, such that the gas can be compressed when the rotor begins to rotate, the chamber communicating with the oil chamber and/or the adjoining exterior volume via the first and second seals alone, respectively.

Abstract: A turbine engine case defines a centerline and a gaspath within the engine case. A fan is coupled to a fan shaft. A transmission couples the shaft to the fan shaft to drive the fan and comprises a gear system. A gutter system is positioned to capture lubricating fluid slung from the gear system. The gutter system includes a gutter extending partially circumferentially about the centerline having a first circumferential end edge. An inlet channel has an inlet at the gutter first circumferential end edge and locally radially outboard of the gutter. At least one vane is spaced apart from the gutter first circumferential end edge.