Abstract: A rotor damping device for a turbomachine is provided. The rotor damping device includes a first fluid damper; and a second damper in communication with the first fluid damper, the second damper comprising a wire mesh, wherein the first fluid damper is transitionable between a working condition and an interruption condition, and wherein, during the interruption condition, the wire mesh of the second damper dampens vibration of the turbomachine.

Abstract: Provided is a direct drive wind turbine that includes: a hub, at least one blade fixed to the hub, a nacelle on which the hub is rotatably mounted for rotating about a rotational axis, the nacelle including an electrical generator connected to the hub in order to receive rotational energy from the hub, a tower on which the nacelle is mounted, and a lightning protection arrangement including a plurality of protection conductors extending between the at least one blade and the tower, the plurality of protection conductors including at least a first protection conductor mounted on an external surface of the electrical generator.

Abstract: A turbine blade includes a blade tip defining pressure side cooling apertures. The turbine blade defines a serpentine cooling passage having a first, second, and third legs, and first and second junction portions. The first leg extends radially and is connected to the second leg by the first junction portion proximate the blade tip. The second leg extends radially between the first and second junction portions. The second junction portion connects the second leg to the third leg which extends radially toward the blade tip and is connected to a trailing edge cooling aperture to exhaust the gas to an exterior of the turbine blade. The turbine blade defines a plenum connected to the first junction portion. At least one tip cooling aperture connects to the plenum and is radially outward of the third leg and axially aftward of at least a portion of the third leg.

Abstract: A bucket includes a pair of radially-inner part-span shrouds, and a pair of radially-outer part-span shrouds. The buckets also include a dovetail, an airfoil and a platform extending between the airfoil and the dovetail. The airfoil includes a pressure side and an opposite suction side. The radially-inner part-span shrouds extend outward from the airfoil such that each of the radially-inner part-span shroud is spaced a distance from the leading edge and a distance from the airfoil trailing edge. The radially-outer part-span shrouds extend outward from the airfoil such that each of the radially-outer part-span shrouds is spaced a distance from the airfoil leading edge and a distance from the airfoil trailing edge, and such that the radially-inner part-span shrouds are between the radially-outer part-span shrouds and the platform. At least one of the airfoil and the dovetail includes at least one aerodynamic feature that facilitates mode shape adjustment of the bucket.

Abstract: A method for producing a split rotor blade, a method for connecting a split rotor blade, a rotor blade, a rotor blade segment, a rotor, a wind power plant, and a production device for producing rotor blades. A method for producing a split rotor blade, comprising: providing a rotor blade having a spar cap and an extension in the longitudinal direction from a blade root region to a blade tip; making at least one groove in the spar cap, the groove being arranged in a first connection region of the rotor blade, and a portion of the main extension direction of the groove being oriented parallel to the longitudinal direction; splitting the rotor blade, in the first connection region, into a rotor blade section facing the blade root and a rotor blade section facing away from the blade root, a first groove section being arranged in the rotor blade section facing the blade root and a second groove section being arranged in the rotor blade section facing away from the blade root.

Abstract: Disclosed is a wind turbine blade with a connecting element for a lightning protection system of the wind turbine blade. The connecting element comprising: a root end part configured to be mechanically and electrically connected to a root region of the wind turbine blade; and a conductor part comprising a first conductor part and a second conductor part, wherein the first conductor part is configured to receive and electrically connect to a stripped part of the down conductor and the second conductor part is configured to receive and mechanically connect to an insulated part of the down conductor.

Abstract: A vertical-axis renewable-power generator is an apparatus that is used to efficiently generate power in various weather conditions using renewable energy sources. The apparatus includes a vertically-oriented foil and a fluid turbine. The foil is designed to generate areas of relative high fluid velocity and low pressure on one side and relative lower fluid velocity and higher pressure on the opposite side. The foil is also self-directing so that the foil can follow the direction of the fluid flow. The fluid turbine is integrated into the foil so that the fluid turbine can be rotated by the high-speed fluid flow. The rotation of the fluid turbine can be used to generate electricity. The apparatus conforms to the Bernoulli's principle that is proven to increase the speed of the fluid flow over the foil, which is used to increase the speed of the fluid flow impacting the fluid turbine.

Abstract: Airfoils for gas turbine engines are describe. The airfoils include a leading edge having an interior surface with an inflection point line extending radially between a root and a tip of the airfoil. The inflection point line is defined at a location of minimum radii that separates a pressure side and a suction side of the airfoil body. An interlaced trip strip array is arranged along the leading edge and includes a chevron trip strip having an apex and ligaments extending from the apex to form a chevron shape and a skew trip strip arranged proximate to the chevron trip strip with a leading end proximate the inflection point line. The skew trip strip is positioned adjacent to the chevron trip strip such that a gap is formed between the skew trip strip and one of the ligaments of the chevron trip strip.

Abstract: A torque converter includes a front cover arranged to receive a torque and a damper assembly including an output flange arranged to non-rotatably connect to a transmission input shaft. The torque converter further includes a seal plate disposed between the front cover and the output flange. The seal plate is non-rotatably connected to the cover. The torque converter further includes a thrust washer including a body axially disposed between the seal plate and the output flange. The thrust washer is fixed to the seal plate.

Abstract: A rotor blade assembly of a wind turbine includes a rotor blade having an aerodynamic body with an inboard region and an outboard region. The inboard and outboard regions define a pressure side, a suction side, a leading edge, and a trailing edge. The inboard region includes a blade root, whereas the outboard region includes a blade tip. The rotor blade also defines a chord and a span. Further, the inboard region includes a transitional region of the rotor blade that includes a maximum chord. Moreover, a unitless first derivative of the chord with respect to the span of the rotor blade in the transitional region ranges from about ?0.10 to about 0.10 from the maximum chord over about 15% of the span of the rotor blade. In addition, the unitless first derivative of the chord with respect to the span a slope of a change in the chord in is greater than about ?0.03 at an inflection point of the chord in the outboard region.

Abstract: Example embodiments relate to an air cooling system for an electronic spinning assembly. An example embodiment includes a plurality of vanes coupled to a static base. A vane cover is rotatably coupled to the static base. The vane cover at least partially encloses the plurality of vanes. Additionally, the vane cover is coupled to an electronic spinning assembly and configured to rotate with the spinning assembly. The vane cover further includes at least one air inlet configured to act as an air intake for an airflow, at least one air duct extending from the vane cover and configured to direct the airflow, and at least one choke point disposed in the cover. The at least one choke point is configured to increase a pressure of the airflow.

Abstract: The present disclosure relates to a compressor including: a motor having a rotating shaft; a first impeller housing forming a first inlet, through which a first refrigerant flows, and having a chamber into which a second refrigerant flows; a first impeller coupled to one end of the rotating shaft, and rotatably received in the first impeller housing; a diffuser spaced apart from an inside of the first impeller housing, and forming a first outlet; a second impeller housing having a second inlet formed therein; a second impeller coupled to the other end of the rotating shaft, and rotatably received in the second impeller housing; a volute case in which a volute is formed; and a motor housing having a connecting passage formed therein and connecting the first outlet and the second inlet.

Abstract: A rotor assembly for generating thrust for a vehicle. The rotor assembly includes a rotor hub and a plurality of rotor blade assemblies coupled to the rotor hub. Each rotor blade assembly includes a metallic bearing race, a composite rotor blade and a metallic coupling assembly. The composite rotor blade has a root section with a radially outwardly tapered outer surface. The metallic coupling assembly has a radially inwardly tapered inner surface that receives the radially outwardly tapered outer surface of the root section of the rotor blade therein to provide a centrifugal force seat for the rotor blade. The coupling assembly includes at least two circumferentially distributed coupling members. The coupling assembly is configured to couple the rotor blade to the bearing race and to provide a centrifugal force load path therebetween.

Abstract: A blade component of a compressor or turbine stage of a gas turbine, in particular of a gas turbine engine is provided. The blade component has at least two structural elements which can be connected together by means of a connection process, in particular sintering. The at least two structural elements can be coupled and/or connected to at least one means for internal cooling of the blade component, and/or the means for internal cooling of the blade component is arranged in at least one of the least two structural elements. The at least two structural elements, when assembled, can be coupled to a cooling insert inside the blade component, wherein during operation, cooling air flowing into the cooling insert can be guided in targeted fashion via impingement cooling openings onto the inside of the blade component, in particular as impingement flow cooling.

Abstract: A blower may include a lower case having a suction port, a fan provided inside the lower case, an upper case provided above the lower case and having a space through which air blown from the fan flows, a discharge port penetrating the upper case and formed to be elongated, and a flow guide provided in the space and extending in a direction crossing a longitudinal direction of the discharge port.

Abstract: A turbine engine having counter-rotating rotors comprising a first rotor, rotating in a first rotational direction, defining a first rotor set of blades axially spaced to define a gap, and a second rotor, rotating in a second rotational direction counter the first rotational direction. The second rotor further including a second set of blades received within the gap of the first rotor. A plurality of fluid passages is formed in the first rotor with an outlet facing the gap.

Abstract: A cooling assembly includes a coolant chamber disposed inside an airfoil of a turbine assembly that directs coolant inside the airfoil. The airfoil extends between a leading edge and a trailing edge along an axial length of the airfoil. Inlet cooling channels are fluidly coupled with the coolant chamber and direct the coolant in a direction toward a trailing edge chamber of the airfoil. The trailing edge chamber is fluidly coupled with at least one inlet cooling channel. The trailing edge chamber is disposed at the trailing edge of the airfoil and includes an inner surface. The inlet cooling channels direct at least a portion of the coolant in a direction toward the inner surface of the trailing edge chamber. One or more outlet cooling channels direct at least a portion of the coolant in one or more directions away from the trailing edge chamber.

Abstract: A brush seal for a rotating machine, intended to be disposed between a first part and a second part of the rotating machine, the first and second parts being movable relative to each other about an axis, extending along an axial direction, the brush seal comprising a body intended to be attached to the first part, and a brush attached to the body, intended to be in contact with the second part, wherein the brush comprises at least a first group of bristles and a second group of bristles, at least one parameter of the bristles of the first group of bristles being different from the corresponding parameter of the bristles of the second group of bristles.

Abstract: The invention concerns an inter-blade profile (14) for a turbine runner blade, said inter-blade profile (14) comprising a profile (16), and a plug (18), forming a basis of the profile (16) and intended for being inserted into a corresponding hole (21) made in a blade.

Abstract: Systems and methods for identifying and mitigating gas turbine component misalignment using virtual simulation are disclosed herein. An example method may include capturing data associated with a first nozzle segment and a second nozzle segment of a gas turbine. The method may also include creating, based on the captured data, a virtual representation of the first nozzle segment and the second nozzle segment. The method may also include determining that a misalignment exists in a connection between the virtual representation first nozzle segment and the virtual representation of the second nozzle segment. The method may also include identifying, based on the determination that the misalignment exists, a third nozzle segment. The method may also include determining that a connection between a third nozzle segment and the first nozzle segment includes a smaller misalignment.