Abstract: The invention relates to a helico-axial pump (1) for pumping a multi-phase mixture (M), said helico-axial pump (1) including a rotor (2) rotatably journalled in a pump housing (6) about a longitudinal axis (A), wherein the rotor (2) includes a compression stage (K) with a helico-axial impeller (3) and a stator (4) for the compression of the multi-phase mixture (M). In accordance with the invention a hydrodynamic stabilization element (7, 71, 72, 73) having a stabilization surface (700) is provided in the pump housing (6) and designed such that a stabilization gap (8) is formed upstream of the stabilization medium, so that in the operating state a hydrodynamic stabilization layer (S) can be formed from a stabilization medium in the stabilization gap (S). The invention further relates to a rotor (2) for a helico-axial pump (1), a method for the hydrodynamic journaling of a rotor (2) of a helico-axial pump (1) as well as to a hybrid pump with a rotor (2) for a helico-axial pump 1.

Abstract: A number of variations may include a product for use with a turbocharger system may include a housing with a rotor wheel rotatable relative to the housing. The rotor wheel may have a front face with blades disposed in a gas stream and a back wall facing the housing. The rotor wheel may generate thrust loads. A thrust bearing may be positioned on the housing and may face the back wall. The thrust bearing may be configured to directly absorb the thrust loads from the rotor wheel.

Abstract: The invention relates to a runner for a direct-connected low-speed small mixed flow type water turbine applied in a hydrodynamic energy-saving cooling tower, which comprises an upper crown (1), a lower ring (3) and curved surface blades (2) mounted between the upper crown (1) and the lower ring (3), and is characterized in that the ratio of the height h of water inlet edge (4) of each blade (2) to the diameter D1 corresponding to the water inlet edge (4) is 0.18-0.22, the ratio of the overall height H of the blades (2) to the diameter D1 is 0.35-0.42, the ratio of the diameter D2 corresponding to the intersection point A of each water outlet edge (4) and the lower ring (3) to the diameter D1 is 0.4-0.6, the ratio of the diameter D3 corresponding to the intersection point B of each water outlet edge (4) and the upper crown to the diameter D1 is 0.3-0.45, the ratio of the diameter D4 in the position of a water drain round platform on the upper crown (1) to the diameter D1 is 0.1-0.

Abstract: An air induction system for a power source including a first compressor and a second compressor is disclosed. The air induction system includes an air feed passageway that directs compressed air from the second compressor to an area between a compressor wheel and a center housing in the first compressor to reduce oil consumption in the first compressor.

Abstract: Turbine and compressor casing abradable component embodiments for turbine engines, with composite grooves and vertically projecting asymmetric non-parallel walls or trapezoidal cross section ridges that reduce, redirect and/or block blade tip airflow leakage downstream into the grooves rather than from turbine blade airfoil high to low pressure sides. In some embodiments at least one angularly oriented first groove formed in the ridge plateau is adapted for angular orientation upstream a turbine blade rotation direction to resist blade tip airflow leakage and the ridges are separated by second grooves that are skewed relative to the respective ridge plateaus and the substrate that are also adapted for orientation upstream the turbine blade rotation direction to resist blade tip airflow leakage.

Abstract: A wind turbine condition monitoring system and method are disclosed where the wind turbines include a tower, a gearbox coupled to the tower, and turbine blades coupled to the gearbox. The monitoring system includes blade sensors coupled to the blades, a hub node coupled to the gearbox and a controller. The controller is in communication with the hub node and blade sensors, and determines blade positions based on blade sensor readings. The blade sensors and hub node can include multi-axis accelerometers. The controller can wirelessly communicate with the blade sensors directly or through the hub node. Using position information, shadowing areas with obstructed communication can be avoided, node separation can be accounted for to reduce power requirements and/or interference from multiple transmitters can be avoided during node communications.

Abstract: A platform cooling arrangement for a turbine rotor blade having a platform at an interface between an airfoil and a root, the root including attachment means and a shank, wherein the platform comprises a suction side that includes a topside extending from an airfoil base to a suction side slashface, and wherein the platform overhangs a shank cavity. The platform cooling arrangement may include: a pocket formed in an underside region of the platform, the pocket comprising a mouth that fluidly communicates with the shank cavity; a manifold extending from the suction side slashface to a pressure side slashface, the manifold including a connection to the pocket; and cooling apertures that extend from connections made with the pocket and manifold to ports.

Abstract: A platform cooling arrangement in a turbine rotor blade having a platform positioned between an airfoil and a root. The rotor blade, along a side that coincides with a pressure side of the airfoil, includes a pressure side of the platform includes a topside extending from an airfoil base to a pressure side slashface. The platform cooling arrangement includes: a main plenum residing just inboard of the topside in the pressure side of the platform, the main plenum extending through the platform from an upstream end having an aft position to a downstream end having a forward position; and cooling apertures. Near the upstream end, the main plenum includes an aft switchback, and, between the aft switchback and the downstream end, a forward arc. Each of the cooling apertures extends from the main plenum to a port formed on the pressure side slashface.

Abstract: A turbomachine includes a housing and a rotatable shaft, where at least a portion of the rotatable shaft is located in the housing. The turbomachine also includes a magnetic thrust bearing that axially positions the rotatable shaft and a radial bearing that centers the rotatable shaft. The turbomachine includes a flexure including a first portion secured to the housing and a second portion axially moveable relative to the first portion. The second portion of the flexure is connected to the radial bearing, and the second portion moves axially to eliminate thrust loads on the radial bearing and allow the magnetic thrust bearing to carry axial loads.

Abstract: The invention relates to a helico-axial pump (1) for conveying a multiphase mixture (M), which helico-axial pump (1) includes a rotor (2) rotatably journalled about a longitudinal axis (A) in a pump housing (6) and having a first part rotor (21) and a second part rotor (22), wherein the first part rotor (21) and the second part rotor (22) include a compression stage (K, K1E, K1A, K2E K2A) having a helico-axial impeller (3) and a stator (4) for the compression of the multiphase mixture (M). In accordance with the invention, a hydrodynamic stabilization bush (70) having a stabilization surface (700) is provided and formed between the first part rotor (21) and the second part rotor (22) such that a stabilization gap (8) is formed before the stabilization surface (700) so that a hydrodynamic stabilization layer (S) is formed from a stabilization medium (M) in the stabilization gap (8) in the operating state.

Abstract: Disclosed is a low-cost composite-type vacuum pump having a strength capable of withstanding high loads and using a cylindrical rotor formed from a fiber-reinforced plastic material. Having a turbo-molecular pump section (14) and a thread groove pump section (15), the composite vacuum pump is formed by press-fitting a joint portion (20a) of a rotor (17) of the turbo-molecular pump section (14) into the upper end section of a cylindrical rotor (21) formed from the fiber-reinforced plastic material of the thread groove pump section (15).

Abstract: A turbine engine comprises compressor and turbine sections. An epicyclic gear train includes a carrier, a sun gear and intermediate gears arranged about and intermeshing with the sun gear. The intermediate gears are supported by the carrier. A baffle includes a lubrication passage near at least one of the sun gear and intermediate gears for directing a lubricant on at least one of the sun gear and intermediate gears. A method of designing a turbine engine is also disclosed.

Abstract: The present invention relates to an aircraft gas turbine having a fan rotatable about an engine axis in the inflow region of the aircraft gas turbine, with the fan having several fan blades, with each fan blade being moveably mounted on a hub rotatable about the engine axis by means of its blade root on an area which is at the front in the flow direction, and with each fan blade being moveably mounted on an area at the rear in the flow direction, on an adjusting disk axially displaceable relative to the engine axis and non-rotatable with the hub, with the pitch angle of the fan blades being variable by the axial movement of the adjusting disk.

Abstract: A driveshaft for an aircraft ram air turbine includes a substantially cylindrical elongate portion, a first end extending from the elongate portion, and a second end extending from the elongate portion opposite the first end. The first and second ends each include a substantially frusto-conical section having a curved generatrix, such that distal portions of each of the first and second ends have smaller outer diameters than an outer diameter of the elongate portion. The elongate portion provides relatively high lateral stiffness and the first and second ends provide relatively low torsional stiffness, such that the driveshaft has a lateral natural frequency higher than an operating range of the driveshaft and has a torsional natural frequency below the operating range of the driveshaft.

Abstract: A seal assembly between a disc cavity and a hot gas path in a gas turbine engine includes a stationary vane assembly and a rotating blade assembly axially upstream from the vane assembly. A platform of the blade assembly has a radially outwardly facing first surface, an axially downstream facing second surface defining an aft plane, and a plurality of grooves extending into the second surface such that the grooves are recessed from the aft plane The grooves are arranged such that a circumferential space is defined between adjacent grooves During operation of the engine, the grooves impart a circumferential velocity component to purge air flowing out of a disc cavity through the grooves to guide the purge air toward a hot gas path such that the purge air flows in a desired direction with reference to a direction of hot gas flow through the hot gas path.

Abstract: A shaped rim cavity wing includes an upper surface and a lower surface. The lower surface has a geometric shape to control the separation of airflow as it passes around the lower surface to the top surface. A point of maximum extent defines the boundary between the upper surface and the lower surface, wherein the point of maximum extent defines a corner that that separates airflow from the shaped rim cavity rim and creates a flow re-circulation adjacent to the top surface of the shaped rim cavity wing.

Abstract: An airfoil platform comprises a leading edge portion and a trailing edge portion. The trailing edge portion comprises a first region having a convex flowpath contour, a second region having an intermediate flowpath contour extending downstream from the convex flowpath contour, and a third region having a concave or linear flowpath contour extending downstream from the intermediate flowpath contour to a downstream end of the trailing edge portion of the platform.

Abstract: An abrasive coating on a rotor shaft interacts with cantilevered vanes to form an abradable air seal in a turbine engine. The abrasive coating includes a metal bond coat, and an abrasive layer containing a plurality of abrasive CBN grit particles in a ceramic matrix.

Abstract: A system to cool the air inside a nacelle and the heat generating components housed in the nacelle of an offshore wind turbine is presented. An upper cooling circuit is disposed in the nacelle. A reservoir is disposed below the upper cooling circuit and has a lid that freely rotates about a vertical axis of the reservoir along with an inlet and an outlet pipe of the upper cooling circuit as the nacelle yaws, the vertical axis of the reservoir being coincident with a yaw axis of the nacelle. A lower cooling circuit is disposed below the reservoir. Coolant is circulated through the upper cooling circuit using a cooling pump disposed between the nacelle and the upper cooling circuit. The upper cooling circuit carries heat from the heat generating components and from the air inside the nacelle to the reservoir. The lower cooling circuit carries heat from the reservoir to the bottom of the tower and dissipates the heat to the sea water through a heat exchanger that is cooled by the sea water.

Abstract: The present application provides a variable stator vane control system. The variable stator vane control system may include a variable stator vane positioned by an actuator and a trimmer motor, a resolver to determine a position of the variable stator vane, and a controller in communication with the resolver, the actuator, and the trimmer motor to prevent over travel of the variable stator vane.