Abstract: Various embodiments include a turbine blade having an airfoil with a tip shroud having a forwardmost tip rail having one or more pressure side and suction side bevel surfaces and pressure side and suction side scallop surfaces. The surfaces have a nominal profile substantially in accordance Cartesian coordinate values of X, Y and Z set forth in various tables herein. The Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by a tip rail length expressed in units of distance. The X, Y and Z values are connected by smooth continuing arcs that are joined smoothly with one another to form the nominal profile that defines the suction side scallop surface, the pressure side scallop surface, the suction side bevel surface, or the pressure side bevel surface.

Abstract: A turbine engine with an outer rotor that circumscribes an inner rotor. The outer rotor includes circumferentially arranged components with a radial outer end and radial inner end. Inner ends of confronting sides of adjacent components include at least one damper element to dampen the relative motion of the components or to provide at least a partial seal between adjacent components.

Abstract: This blade repair method has: a first welding step in which overlay welding in which a first welding material is used is performed to form a notched part and a bury a first region positioned on a blade-body side with a first welding material; and a second welding step in which, after the first welding step, overlay welding in which a second welding material is used is performed to form a notched part and bury a second region positioned on a front-surface side of a platform with the second welding material. The high-temperature strength of the second welding material is higher than the high-temperature strength of the first welding material, the weldability of the first welding material is higher than the weldability of the second welding material, and the second region is located in a range from 1.0 mm to 3.0 mm (inclusive) from the front surface of the platform toward the blade body.

Abstract: A pump comprises: at least one rotor rotatable about an axis of rotation; a pump housing surrounding the rotor, wherein a pump channel is formed between a radially inner surface of the pump housing and a radially outer surface of the rotor; and a seal assembly that seals the pump channel to an end surface of the rotor. The seal assembly comprises: a sliding surface which is provided on one of the rotor and the pump housing and which extends perpendicular to the axial direction of the rotor; a static surface provided on the other of the rotor and the pump housing; and a first elastomer element attached to the static surface and pressed against the sliding surface in the axial direction.

Abstract: A dispensing pump for fuel vending systems, comprising a pump body which forms internally a pumping chamber, which rotatably accommodates an impeller, functionally connected to a motor, and provided with an intake connector and a delivery connector, which communicate with the pumping chamber and can be connected to a fuel dispensing line; the pump body has at least one coupling portion for at least one auxiliary device of the dispensing line.

Abstract: A process for producing compressed hydrogen gas, said process comprising electrolysing water to produce hydrogen gas and compressing said hydrogen gas in a multistage compression system to produce compressed hydrogen gas. The multistage compression system comprises at least one centrifugal compression stage, and the hydrogen gas is fed to the centrifugal compression stage at a pre-determined feed temperature and pressure and having a pre-determined relative humidity. The process further comprises adding water and heat to the hydrogen gas upstream of the centrifugal compression stage, as required, to humidify the hydrogen gas to the pre-determined relative humidity.

Abstract: Computer-implemented methods are disclosed for determining a flow rate of fluid flow at a target time through a pump, such as a centrifugal pump, the pump being driven by a pump motor. An illustrative method includes, in some aspects: receiving at least one set of previous parameter values including a first previous parameter value indicative of a first operational parameter of the pump motor at a previous time, earlier than the target time, and a second previous parameter value indicative of a second operational parameter of the pump motor at the previous time, and receiving a current set of parameter values including a first current parameter value indicative of the first operational parameter of the pump motor at the target time and a second current parameter value indicative of the second operational parameter of the pump motor at the target time.

Abstract: A blade assembly for a torque converter includes a shell defining an inner surface and a plurality of blades arranged around the inner surface of the shell. The plurality of blades each include a curved portion contacting the inner surface. The plurality of blades each further include a curved region axially spaced from the respective curved portion. The plurality of blades each further include an end extending from the respective curved portion to the respective curved region. Each end includes a notch arranged radially closer to the respective curved region than to the respective curved portion.

Abstract: A blade for a turbine engine with a wall separating a cooling fluid flow and a hot gas fluid flow and having a heated surface along which the hot gas fluid flow flows and a cooled surface facing the cooling fluid flow. A plurality of cooling holes each having a passage extending between an inlet at the cooled surface and an outlet at the heated surface. The outlet extending between an upstream end and a downstream end with respect to the hot gas fluid flow to define a distance, the passage defining a centerline forming a first angle (?) with the heated surface.

Abstract: Provided is a wind turbine and to a method and a device for controlling aerodynamic properties of a blade of the wind turbine, the blade including a predetermined number of add-on members which are actuated by a corresponding trim actuator to alter the aerodynamic properties of the blade, wherein each trim actuator is configured to hold the add-on member in a predetermined first position and a predetermined second position. The control device is configured to determine a first number of add-on members which are to be held at the predetermined first position, and to determine a second number of add-on members which are to be held at the predetermined second position.

Abstract: An impeller for use in an aquarium filter pump includes a shaft and a plurality of impeller blades radially extending from the shaft. Each of the impeller blades includes opposite blade faces. A depression is in each of the blade faces and aids in pushing the water. The depression can be a variety of shapes and can have its deepest portion along one of the edges of the blade.

Abstract: Fuel pump for an aircraft engine, comprising an inducer and a centrifugal impeller fixed together and having an axis of rotation, an annular space spacing axially the inducer and the impeller, and two contact portions between the inducer and the impeller disposed radially outside the annular space, a first plenum chamber and a second plenum chamber, in which the inducer and the impeller are spaced axially from each other, each being disposed between the two contact portions, the plenum chambers being symmetrical to each other with respect to the axis of rotation and in fluid communication with the annular space, the centrifugal impeller comprising a plurality of axial balancing holes distributed about the axis of rotation and opening out into the annular space at one end, and into a downstream space of the impeller at the other end.

Abstract: An airfoil for a turbine engine, the airfoil having an outer wall defining an interior and a camber line extending through the airfoil, and at least one cell located within the interior. The at least one cell can include a forward portion and an aft portion with respect to the camber line. The forward portion and the aft portions can be connected by side portions. A braided fabric can be provided on at least one of the forward or aft portions, while a braided fiber can be provided on at least one of the side portions.

Abstract: A neck fan includes: an inner shell, disposed near the neck; an outer shell, connected to the inner shell and disposed opposite to the inner shell and away from the neck. The outer shell and the inner shell cooperatively define a receiving space; a plurality of fan assemblies. Each fan assembly is received in the receiving space and connected to the inner shell and the outer shell. The inner shell defines a plurality of air inlets, located near and facing towards the neck. At least a part of the receiving space serves as an air duct communicating with the air inlets. Each fan assembly corresponds to the air inlets. Each fan assembly is configured to intake air from an outside of the neck fan through the air inlets and to further drive the air to flow into the air duct.

Abstract: A wind turbine blade includes a first blade portion and a second blade portion coupled together by a connection joint. A first spar cap is associated with an upper shell half and a second spar cap is associated with the lower shell half of each of the first and second blade portions. A shear web extends between the first spar cap and the second spar cap of each of the first and second blade portions. The shear web is terminated away from a joint interface at which the first and second blade portions meet, and there is no shear web extending in a longitudinal direction across the joint interface. The shear web extending between the first spar cap and the second spar cap is branched in the longitudinal direction toward the first and second blade interfaces of the first and second blade portions respectively.

Abstract: The invention relates to a movable turbomachine blade comprising at least one cooling circuit comprising at least one cavity extending radially between the root and the tip, at least one air intake opening at a radial end of the cavity, a plurality of first discharge slots arranged to open out along the trailing edge between the root and the tip, and a plurality of second discharge slots separate from the first discharge slots and arranged along the trailing edge between the root and the tip, the second discharge slots being offset axially upstream relative to the first discharge slots and each of the first discharge slots being radially offset relative to each of the second discharge slots, with no overlap between the first and second discharge slots.

Abstract: The disclosure provides a nozzle adapted for placement within a flowpath of a turbomachine. The nozzle includes an airfoil having a suction side; a pressure side opposing the suction side; a leading edge between the pressure side and the suction side; a trailing edge opposing the leading edge and between the pressure side and the suction side; a root region at a first radial end; a tip region at a second radial end opposite the first radial end; and a midspan region between the root region and the tip region. An endwall is connected with the root region or the tip region of the airfoil along the suction side, the pressure side, the trailing edge, and the leading edge. The trailing edge of the airfoil has an elliptical shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in TABLE I.

Abstract: A seal assembly for a pump comprises a gland housing mounted to the pump casing. A staging flow pathway is defined within the gland housing with multiple seal chambers. A seal stage is positioned in each seal chamber, each having a static sealing element and a rotating sealing element, the sealing elements engaging one another to form a fluid-tight seal. A rotor assembly pumps coolant through the gland housing. Fluid passing through the staging flow pathway is accelerated by an acceleration surface of the rotor assembly. An inlet passage feeds coolant fluid into the staging flow pathway and past the acceleration surface.

Abstract: An air guide arrangement, for a ventilation system, has a housing forming a flow channel with a fan arranged in the flow channel to generate an airflow through the housing. A flow guide device is arranged in the flow channels. The flow guide device is axially connected downstream of the fan on the outflow side and directly influences the airflow generated by the fan. The flow guide device has an axis-central through opening delimited by a tubular element extending parallel to the flow direction. Multiple separate flow segments are formed along the tubular element and are evenly distributed in the circumferential direction. The flow segments in the circumferential direction are each separated from one another in terms of flow by flow guide elements extending radially outward from the tubular element.

Abstract: A compressor system includes: a compressor having an upstream region into which a working fluid flows, a downstream region in which the pressure of the working fluid is greater than that in the upstream region, inlet guide vanes that are provided further upstream than the upstream region and capable of altering the flow rate of the inflowing working fluid, and an extraction part that is provided to a portion between the upstream region and the downstream region and capable of extracting at least a portion of the working fluid; detection devices, at least one of which is provided in each of the upstream region and the downstream region, for detecting the physical quantity of the working fluid; and a control device for adjusting, on the basis of changes in the physical quantity, the opening degree of the inlet guide vanes and the amount extracted by the extraction part.