Abstract: The present invention provides a method of erecting a wind turbine on a wind turbine site. The wind turbine comprises a turbine tower and a nacelle. The method comprises the following steps: providing a plurality of tower sections being arrangeable upon each other in a vertical orientation in a tower structure to form the turbine tower, providing at least two damper units configured to dampen oscillations of the turbine tower, attaching one of the at least two damper units to one of the plurality of the tower sections on an outside thereof, and subsequently arranging said tower section in the tower structure, attaching a subsequent one of the at least two damper units to another one of the plurality of the tower sections on an outside thereof, and subsequently arranging said tower section in the tower structure, while the previous one of the at least two damper units is still attached to the previous one of the plurality of tower sections.

Abstract: A gas turbine engine article includes a cooling passage network embedded in an article wall between inner and outer portions of the article wall. The network has an inlet orifice through the inner portion to receive cooling air from a cavity, a sub-passage region that includes an array of pedestals, and at least one outlet orifice through the outer portion. The array of pedestals includes first pedestals arranged in a first row and second pedestals arranged in a second, adjacent row. The first pedestals and the second pedestals define inter-row sub-passages there between. Each of the inter-row sub-passages has an inlet mouth, an outlet mouth, and a compound channel connecting the inlet mouth and the outlet mouth. The compound channel includes a first channel length over which the inter-row sub-passage has a constant cross-section and a second channel length over which the inter-row sub-passage has a non-constant cross-section.

Abstract: A system for controlling a generator rotor locking pin, comprising a fixed locking pin and a rotor formed with a locking hole, and further comprising a detection reference component synchronously rotating with the rotor and formed with a detection hole, the detection hole radially corresponding to the locking hole; an optical quantity detection component fixed with respect to the rotor; and a control component configured to output a first control instruction to a rotor driving component according to a position signal of the detection hole obtained by the optical quantity detection component. The detection hole is used as an object to be detected, so that the circumferential relative position relationship of the locking hole with respect to the locking pin can be accurately determined, to output the first control instruction to the rotor driving component, thereby accurately centering the locking pin and the locking hole along with the rotation of the rotor.

Abstract: A locking spacer assembly for filling a final spacer slot in a disk groove between platforms of adjacent blades of a blade assembly in an industrial gas turbine engine is presented. The locking spacer assembly includes a first side piece, a second side piece, a mid piece and a bolt. The bolt is disposed into the mid piece to position the mid piece in a radial position in an assembled state. The mid piece contacts the first side piece and the second side piece in the assembled state to prevent axial movements of the first and second side pieces in the disk groove. The bolt prevents a radial movement of the mid piece.

Abstract: A centrifugal blower having high efficiency and reduced noise is provided. A centrifugal blower to be accommodated in a housing having an air inlet includes a spiral casing having a bell mouth and a centrifugal fan housed in the casing. The bell mouth includes a first region and a second region. The first region is disposed closest to the air inlet. A distance from a rotational axis of the centrifugal fan to a downstream end in the first region is greater than a distance from the rotational axis to the downstream end in the second region. A curvature of a surface of the first region in a cross section including the rotational axis is smaller than a curvature of a surface of the second region in a cross section including the rotational axis.

Abstract: An arrangement having an impeller that rotates about an axis and a stationary diffuser located downstream with guide vanes. The impeller has an inlet for an axial supply flow and an outlet for a radial out-flow, wherein radially and axially extending rotor blades are arranged between a wheel disc and a cover disc of the impeller. The impeller channels are separated from one another in a circumferential direction. The diffuser extends substantially radially along a main flow direction and has an axial channel width. The diffuser has a diffuser inlet and outlet, wherein guide vanes extending axially along a blade vertical direction and radially along a through-flow direction are arranged between the wheel disc side and the cover disc side of the diffuser, which separate the guide vane channels from one another. An inlet edge angle is smaller on the cover disc side than on the wheel disc side.

Abstract: A case clearance control system comprising a blade outer air seal support structure having a plurality of protrusions extending radially from the blade outer air seal support structure opposite a blade outer air seal proximate the blade outer air seal support structure; a thermal control ring coupled to the blade outer air seal support structure, the thermal control ring including a plurality of receivers configured to couple with the plurality of protrusions; a thermal break formed between the plurality of protrusions and the plurality of receivers, the thermal break configured to control heat transfer between the blade outer air seal support structure and the thermal control ring; and a plurality of flow passages formed between the blade outer air seal support structure, the thermal control ring and the plurality of protrusions, the plurality of flow passages configured to allow cooling air flow to condition the thermal control ring and maintain thermal control ring dimensions.

Abstract: In a guide vane according to an embodiment of the invention, where in a section perpendicular to a guide vane rotation axis, a curvature of a contour line forming a runner side vane surface of the guide vane is referred to as a positive curvature when the contour line is formed to be convex, while the curvature of the contour line is referred to as a negative curvature when the contour line is formed to be concave, a negative curvature portion where the curvature of the contour line becomes negative is provided on the runner side vane surface. The negative curvature portion is formed from an upper end portion to a lower end portion of the runner side vane surface.

Abstract: The present embodiments set forth a blade including an airfoil including an outer tip having a floor, a leading edge and a trailing edge, a concave pressure sidewall and a convex suction sidewall extending axially between corresponding leading and trailing edges and radially between the floor and the tip cap. The airfoil further includes a tip cap extending from the floor of the outer tip and coextensive with the pressure sidewall and suction sidewall and around the leading edge and trailing edge. The tip cap includes a squealer tip configuration including a suction side tip cap portion and a pressure side tip cap portion. The suction side tip cap portion and pressure side tip cap portion extend unequal distances above the floor providing for cooling fluid flow out of the tip cap.

Abstract: A turbomachine includes a shroud and a rotor, which includes first and second blades. A first blade tip and a second blade tip respectively include a base and a first layer. The second blade tip also includes an abrasive second layer layered over the respective first layer. The first layer has a lower material hardness than the shroud. The second layer has a lower thermal stability than the shroud and the first layer. The rotor performs a grind operation and, subsequently, a post-grind operation. The second layer, in the grind operation, contacts and removes material from the shroud, and wears away, thereby revealing the first layer of the second blade tip for the post-grind operation. The first layer of the first blade tip is spaced apart with at least some radial clearance from the shroud in the grind and post-grind operations.

Abstract: A compressor case to blade tip clearance system comprising a rotor having blades with tips, the case including an inner case comprising at least one surface feature fluidly coupled to a distribution manifold disposed in a cooling air passageway, the at least one surface feature configured to interact with the cooling air, and a tip clearance located between the tips and the inner case; wherein the tip clearance is maintained responsive to a flow of the cooling air over the at least one surface feature.

Abstract: An expansion turbine configured such that even when pressure of process gas steeply changes, the amount of process gas leaking from a gap between an impeller and a cover is made small. The expansion turbine includes a gas supply passage which is connected to any one of a gas supply passage and a gas discharge passage and through which gas is supplied to a region located between a rotor member and a casing member.

Abstract: A heat shield includes an outer jacket including a fluid inlet port and a fluid outlet port, and an inner jacket nested within the outer jacket and spaced apart therefrom to define a fluid passageway therebetween. The fluid passageway is in fluid communication with the fluid inlet port and the fluid outlet port for directing a cooling fluid from the fluid inlet port to the fluid outlet port through the fluid passageway. The inner jacket at least partially defines a main cavity configured to at least partially protect a turbocharger of the marine engine.

Abstract: An impeller includes a hub, a plurality of blades provided around an outer periphery of the hub, and at least two connecting rings connected to the plurality of blades. Each of the plurality of blades has a top edge and a bottom edge opposite to the top edge. One or more of the at least two connecting rings is disposed between but not connected to the top edges and the bottom edges of the plurality of blades. A cooling fan including the impeller is also provided.

Abstract: A compressor includes an impeller and a diffuser. The impeller is mounted for rotation about an axis of the gas turbine engine. The diffuser is coupled to the impeller to receive the high velocity air from the impeller. The diffuser includes a first plate, a second plate spaced apart from the first plate axially, and a plurality of vanes located between the first and second plates.

Abstract: A turbine unit for an aircraft turbine engine, comprises a rotor disc (17) axially continued by a rim (36) and carrying rotary blades (18) defining together with the disc (17) channels for air flow (43); an annular flange (33) including a bearing end (34) and defining together with the rim (36) an air passage (42) communicating with the channels for air flow (43); a member (32) for axially retaining the blades applied against the disc (17) by the bearing end (34), this turbine unit being characterised in that at least one element, out of the retaining member (32) and the flange (33), comprises a groove (44) formed facing the other element, out of the retaining member (32) and the flange (33), and into which a sealing joint (45) against which the other element axially bears is inserted.

Abstract: An airfoil vane includes an airfoil section including an outer wall that defines an internal cavity; and a baffle situated in the internal cavity, the baffle including a baffle wall that defines a central cavity having a leading end and a trailing end corresponding to a leading end and a trailing end of the airfoil section, and a tail extending from the baffle wall, the tail including at least one feature configured to disturb an airflow surrounding the tail. A baffle for the airfoil vane assembly and a method of assembling a ceramic matrix composite airfoil vane are also disclosed.

Abstract: A fan device and a fan holder are provided. The fan device includes the fan holder and a fan. The fan holder includes a bracket, four ratchet sets, a seat, and a frame. Each of two ends of the bracket is connected to two of the four ratchet sets. The seat is connected to the two of the four ratchet sets arranged to the one of two ends of the bracket. The frame is connected to the other two of the four ratchet sets arranged to the other one of two ends of the bracket. The seat and the frame are rotatable between a use position and a storage position relative to the bracket through the four ratchet sets. The fan is connected to the frame. The seat and the frame are rotated to the storage position, so that the bracket can be arranged on the seat.

Abstract: Example apparatus, systems, and articles of manufacture to control deflection mismatch are disclosed herein. Further examples and combinations thereof include: A deflection limiter comprising an inner shroud segment to support a stator structure, the inner shroud segment including a first end face and a first outer upper portion, the first end face positioned radially inward and aft relative to the first outer upper portion, and an outer shroud segment to support the inner shroud segment, the outer shroud segment including a second end face and a second outer upper portion, the second end face positioned aft relative to the first end face and the second outer upper portion positioned aft relative to the first outer upper portion of the inner shroud segment, the second end face coupled to the first end face of the inner shroud segment and the second outer upper portion coupled to the first outer upper portion.

Abstract: A clearance adjusting apparatus disposed in front of a compressor of a gas turbine to axially move a compressor disk back and forth to adjust a tip clearance formed between a compressor blade and a compressor casing is provided. The clearance adjusting apparatus includes a hollow fastening part disposed in front of the compressor casing, a shaft disposed in the fastening part and coupled to a front side of the compressor disk, an adjusting part disposed between the fastening part and the shaft to axially move the shaft back and forth to adjust the tip clearance, and a biasing part disposed on the fastening part to bias the adjusting part back and forth to adjust a position of the adjusting part and the shaft.