Abstract: A multi-stage regenerative rotary pump assembly includes a housing, and an elongated shaft received in the housing for rotation about a rotational axis. The shaft has a longitudinal axis aligned with the rotational axis. A rotary member is operatively connected to the shaft and dimensioned for receipt in the housing. The rotary member has opposite, first and second faces axially spaced from one another in a direction of the longitudinal axis. At least the first face of the rotary member includes a first pump stage having a first stage inlet and a first stage outlet in fluid communication therewith. At least the first face includes a second pump stage having a second stage inlet and a second stage outlet in fluid communication therewith, and the second stage inlet is configured to be in fluid communication with the first stage outlet.

Abstract: A structure for a gas turbine engine includes a first engine component, a second engine component and fasteners. The component apertures include first fastener apertures and intergroup apertures. The first fastener apertures are arranged into a plurality of groups. The first group is formed by N1-number of the first fastener apertures. The second group is formed by N2-number of the first fastener apertures where the N2-number is different than the N1-number. Each of the intergroup apertures is disposed circumferentially between and adjacent a respective circumferentially neighboring pair of the groups. The second engine component includes a surface and second fastener apertures. The surface axially engages the first engine component and covers the intergroup apertures. The fasteners attach the first engine component and the second engine component together. Each of the fasteners is mated with one of the first fastener apertures and one of the second fastener apertures.

Abstract: A wind turbine (1) comprising a tower (2), a nacelle (3) and a hub (7) is disclosed. The hub (7) comprises a blade carrying structure (4) with one or more wind turbine blades (5) connected thereto. Each of the wind turbine blades (5) defines an aerodynamic profile having a chord which varies along a length of the wind turbine blade (5). Each of the wind turbine blades (5) is connected to the blade carrying structure (4) via a hinge (6) at a hinge position of the wind turbine blade (5), each wind turbine blade (5) thereby being arranged to perform pivot movements relative to the blade carrying structure (4) between a minimum pivot angle and a maximum pivot angle. The hinge position is arranged at a distance from the inner tip end (5a) and at a distance from the outer tip end (5b), and the chord at the hinge position is larger than or equal to the chord at the inner tip end (5a) and larger than the chord at the outer tip end (5b).

Abstract: A method of repairing a tip for an airfoil is disclosed herein. In various embodiments, the method comprises: removing a portion of the airfoil that reduces a radial height of the airfoil and at least partially removes a defect of the airfoil; removing a remainder of the defect; joining, via gas tungsten arc welding, a filler material to the airfoil to repair the defect; and joining a first mating surface of the airfoil to a second mating surface of a blade tip body via a solid-state joining process.

Abstract: Disclosed herein are example variable flowpath casings for blade tip clearance control. An example casing for a turbine engine includes an annular substrate extending along an axial direction, the annular substrate defining a cavity at a radially inward surface of the annular substrate, and a smart structure coupled to the annular substrate, the smart structure including a support structure; an actuator structure to at least one of expand or contract in response to a change in temperature of the actuator structure, and a variable surface coupled to the support structure, the support structure to move the variable surface in a radial direction.

Abstract: A gas turbine engine comprises a fan; an engine core comprising a compressor, a combustor, and a turbine coupled to the compressor through a shaft; a reduction gearbox; an Engine Section Stator (ESS) comprising a plurality of ESS vanes with an external surface washed by the core airflow; an ESS heating system adapted to heat the ESS vanes, and a temperature sensor adapted to detect the temperature of the external surface of the ESS vanes and send a signal to the ESS heating system when said temperature is below a reference temperature. Upon detection and/or inference of ice crystal conditions and receiving from the temperature sensor the signal that the temperature is below the reference temperature, the ESS heating system is activated to heat at least a portion of the external surface of the ESS vanes and promote melting and adhering of ice crystals thereto.

Abstract: There is provided a fan assembly comprising an air flow generator that is arranged to generate an air flow through the fan assembly, and a nozzle arranged to emit the air flow from the fan assembly. The nozzle comprises a nozzle body and a plurality of steerable air outlets that are each arranged to emit a portion of the air flow, wherein the plurality of steerable air outlets are arranged to be independently rotated relative to the nozzle body.

Abstract: A seal plate for a rotary machine includes a hub centered on a central axis of the rotary machine, a disk portion extending radially outwards from the hub, and a variable lattice structure in an interior of the seal plate. The variable lattice structure includes a first region of the seal plate having a first lattice structure, and a second region of the seal plate having a second lattice structure. The second lattice structure of the second region is denser than the first lattice structure of the first region. The second region is a deflection region, a stress region, or an energy containment region of the seal plate.

Abstract: A pump arrangement including a magnetic clutch pump arrangement, the pump arrangement including an inner chamber formed by a housing arrangement, a separating can which hermetically seals a chamber enclosed by it with respect to the inner chamber, an impeller shaft that can be driven in rotation about an axis of rotation, an impeller arranged on one end of the impeller shaft, an inner rotor arranged on the other end of the impeller shaft, a drive device, a drive shaft that can be driven in rotation about the axis of rotation by the drive device, and an outer rotor arranged on the drive shaft and cooperating with the inner rotor. The outer rotor includes a first carrier element and a second carrier element connected to the first carrier element. The first carrier element includes a thermal barrier device.

Abstract: The present disclosure relates to louvers for enabling an air passage between an outside and an inside. More particularly, the present disclosure relates to louvers enabling said air passage while minimizing rain ingress towards an interior and minimizing noise produced in the interior. The present disclosure further relates to wind turbines including said louvers.

Abstract: A system includes a vertical molten sulfur pump assembly that includes a top portion adjacent to a first end of the vertical molten sulfur pump assembly and a bottom portion adjacent to a second end of the vertical molten sulfur pump assembly. A pump motor is disposed in the top portion, an impeller is disposed in the bottom portion within an impeller casing, and a shaft is disposed within a central column and connecting the pump motor with the impeller. A pump inlet is disposed at the second end below the impeller casing. The pump inlet and the impeller casing are configured to be immersed in molten sulfur. The vertical molten sulfur pump assembly is configured to pump the molten sulfur into the inlet and upwards through a discharge passageway by rotation of the impeller. A vibration sensor and a temperature sensor are disposed on an external surface of the bottom portion, on or proximate to the impeller casing and the pump inlet.

Abstract: The present invention is directed to a portable fan for the use in firefighting and other ventilation use-cases. The portable fan provides firefighters the ability to provide positive pressure ventilation in use for fighting fires which does not require power cables or combustible fuel powered motors, and provides increased portability, reduced risk, and reduced deployment time associated with managing and fighting a fire.

Abstract: A rotor assembly may be used in a gas turbine. The rotor assembly includes rotor segments arranged in succession in an axial direction and interconnected in the axial direction by a tie-rod, and a rotor segment disposed forwardly in the axial direction having a first contact surface and a rotor segment disposed rearwardly in the axial direction having a second contact surface. The first and second contact surfaces are at least partially in contact with each other, are substantially annular in shape, and extend in a radial direction and in a circumferential direction. The first contact surface and/or the second contact surface extend at least partially obliquely relative to the radial direction. An angle is formed between the first contact surface and the second contact surface when viewed in a sectional plane defined by the axial direction and the radial direction.

Abstract: A blade for a turbomachine intended to be disposed about an axis while extending radially between a radially outer end and a radially inner end, the blade having at least one cooling cavity opening out to the radially outer end of the blade and to the radially inner end of the blade, the blade having at least a first tubular liner and at least a second tubular liner each engaged in the cavity, the radially outer end of the first liner opening out to the radially outer end of the blade, and the radially inner end of the second liner opening out to the radially inner end of the blade.

Abstract: An electric submersible pump (ESP) electric motor. The ESP electric motor comprises a drive shaft; a first metal compliance ring located around the drive shaft; a second metal compliance ring located around the drive shaft; a first bearing sleeve located around the drive shaft, located around the first metal compliance ring, and located around the second metal compliance ring, wherein there is an interference fit between the inside of the first bearing sleeve and the first metal compliance ring and between the inside of the first bearing sleeve and the second metal compliance ring; and a second bearing sleeve located around the first bearing sleeve and located inside an inner bore of a stator of the electric motor.

Abstract: An excellent abrasive blade tip is provided by a two-layer coating system consisting of a brazing solder coating and an NiCoCrAlY coating containing cBN (cubic Boron Nitride).

Abstract: A gas turbine engine has a compression system blade ratio defined as the ratio of the height of a fan blade to the height of the most downstream compressor blade in the range of from 45 to 95. This results in an optimum balance between installation benefits, operability, maintenance requirements and engine efficiency when the gas turbine engine is installed on an aircraft.

Abstract: A fan system and a computing system with the fan system are disclosed. The fan system includes a fan module. The fan module includes a housing configured to retain a fan and a motor to rotate the fan. The housing includes an air inlet aperture on an air inlet side of the housing and an air outlet aperture on an air outlet side of the housing. The fan system further includes an outlet fan guard coupled to the fan module on the air outlet side of the housing. The outlet fan guard includes at least one flap rotatable between a closed position, covering the air outlet aperture of the housing, and an open position, uncovering the air outlet aperture of the housing. The outlet fan guard further includes at least one spring urging the at least one flap into the closed position.

Abstract: Turbomachine components and compressors are provided. The turbomachine component includes a platform and a mounting portion that extends from the platform. The mounting portion includes a dovetail received by a slot defined in the turbomachine. The slot includes a floor and a ceiling. The dovetail includes an inner surface and an outer surface. A hole is defined in the dovetail from an inlet at the inner surface to an end wall. The hole has a cylindrical portion and a tapered portion. A mechanical spring is disposed within the hole and in contact with the floor and the end wall such that the outer surface of the dovetail is forced into contact with the ceiling of the slot.

Abstract: A stator vane assembly for a gas turbine engine is disclosed. The stator vane assembly includes an inner carrier including a metallic material and an outer carrier including a metallic material. The stator vane assembly further includes a ceramic-containing airfoil that extends from the inner carrier to the outer carrier and is at least partially received by the inner carrier and the outer carrier. The stator vane assembly further includes a load transfer device disposed between the airfoil and at least one of the inner carrier and the outer carrier. The load transfer device includes a support member fixedly attached to the at least one of the inner carrier and the outer carrier, and a plurality of micropillars coupled to the support member and extending towards the airfoil. Each micropillar is deformable and engages the airfoil.