Abstract: A luminous fan includes a fan frame, a main circuit board, a light guide element and a light-guiding impeller. The main circuit board is disposed on a bracket of the fan frame and includes a first light-emitting element. The light guide element is located over the main circuit board, and includes a light input surface and light output surface. A light guide post is disposed on the light input surface. A reflective structure is formed on the light output surface. The light-guiding impeller is pivotally coupled to the bracket. The first light-emitting element emits a first light beam. After the first light beam is transmitted to the reflective structure through the light guide post, the first light beam is reflected by the at least one reflective structure and diffused toward a middle region of the light guide element.

Abstract: An intelligent control clogging-free water-cooled multifunctional pump includes a housing, a water-through tank, a motor, an axial flow style cover plate, a flexible rubber conical impeller, a double-channel conical diffuser, a filter and an intelligent water level controller. The motor is placed inside the housing. The motor is provided with a control board. The water-through tank is placed under the housing. The flexible rubber conical impeller is coaxially connected to the motor. The axial flow style cover plate is placed at the bottom of the water-through tank. The double-channel conical diffuser is disposed under the cover plate and the conical pattern of the flexible rubber impeller is consistent with the conical pattern of the double-channel conical diffuser.

Abstract: An assembly includes: a movable blade for a turbomachine including a tip; and a removable part including an anti-wear material, configured to be attached removably to an edge of the tip to limit wear of the tip.

Abstract: An improved gas turbine engine, a blade for a gas turbine for attachment to a rotor disk of the gas turbine engine and a method for manufacturing thereof. Specifically, the blade includes an airfoil attached to at least one base, wherein each of the bases is adapted to be received within a slot defined in the disk. At least one of the bases has a contacting surface for contacting a corresponding surface of the disk. Increased edge radii at the ends of the contacting surfaces are provided by not having contacting surfaces that blend in with the side surfaces.

Abstract: An accelerator and water turbine assembly is provided for mounting in a tidal stream having a water turbine (12) and a water flow accelerator for providing a turbine driver current having a speed greater than that of the uninterrupted ambient tidal stream in which the accelerator has an accelerator body member (11) having a water flow facing front face (13) and side faces (14) depending therefrom around which the water flows adjacent each of the side faces as a turbine driver current and in which the water turbine (12) is mounted to be at least partially shrouded by the accelerator body member from the accelerated turbine driver current flowing adjacent and relatively close to a side face of the accelerator where the water flow achieves substantially maximum velocity and in which the accelerator is laterally spaced apart from the turbine driver current modifying effect of any other flow obstruction.

Abstract: Auxiliary lead-through device for a turbomachine, including two coaxial annular shell rings, respectively an inner and an outer one, between which there extend radial arms, through at least one of which auxiliaries (20) are led through. An auxiliary retention unit is housed inside the arm, on one wall, the arm includes an aperture that can be closed off by a cover that is attached and fixed to the arm. The retention unit includes at least one first member fixed to the internal surface of the arm and at least one second member fixed to the internal surface of the cover. The fixing of the cover to the arm causes the auxiliaries to be clamped and retained between the first and second members.

Abstract: A sealing system for a rotary machine is provided. The sealing system includes a pair of circumferentially adjacent rotary components. Each of the rotary components includes a platform, a shank, and a radial seal. The shank extends radially inwardly from the platform and includes a radially extending first side channel and an opposite radially extending second side channel. The radial seal includes a first leg received in the first side channel of a first of the pair of rotary components, a second leg received in the second side channel of a second of the pair of rotary components (201), and a resiliently deformable body extending therebetween, the body including a U-shaped portion located generally centrally between the first leg and the second leg.

Abstract: A method of assembling and disassembling a gas turbine, and a gas turbine assembled thereby, improves work efficiency and reduces time and cost by carrying out various disassembly and reassembly processes depending on circumstances. In one process, a turbine section is disassembled from a gas turbine by sequential steps of disassembling an upper turbine case; disassembling a rear diffuser assembly and a rear bearing assembly; disassembling a combustor assembly; disassembling a vane assembly; and disassembling a blade assembly. In another process, first-stage to fourth-stage blade assemblies and first-stage to fourth-stage vane assemblies in a turbine section are disassembled from the gas turbine by sequential steps of disassembling an upper turbine case; disassembling a combustor assembly; disassembling a vane assembly; and disassembling a blade assembly.

Abstract: A wind turbine blade includes: a blade body extending from a blade root along a blade longitudinal direction toward a blade tip; and a metal strip provided to cover at least a leading edge at the blade tip side of the blade body so as to suppress erosion at the leading edge of the blade body.

Abstract: A cantilevered vane, for use with a rotary disc of a gas turbine, includes a root supported in a dovetail slot formed in a circumferential surface of the rotary disc; and an airfoil protruding a predetermined height from the root and having a J-shaped cross-section throughout a front-wing portion and a rear-wing portion of the airfoil. The airfoil includes a straight portion vertically extending upward from the root by a predetermined height; and a curved portion integrally formed with an upper end of the straight portion to cantilever toward one side of the airfoil, the curved portion being inclined at a predetermined angle with respect to the straight portion. Cooling fluid flows through a first channel formed in the straight portion and a second channel formed in the curved portion. The first channel includes front-wing and rear-wing channels for guiding the cooling fluid to the front-wing and rear-wing portions.

Abstract: An assembly according to an exemplary aspect of the present disclosure includes, among other things, a disk, a cover plate providing a cavity at a first axial side of the disk, a passageway including an inlet provided by a notch in at least one of the disk and the cover plate in fluid communication with the cavity, and the passageway extending from the inlet to an exit provided at a second axial side of the disk opposite the first axial side, the exit in fluid communication with the inlet, and the passageway configured to provide fluid flow from the cavity to the exit.

Abstract: The rotatable machine includes a compressor and an inner annular casing circumscribing at least a portion of the compressor. The inner annular casing includes an outer surface in a radial direction, an upper portion in a vertical direction, and a lower portion in a vertical direction. The clearance control system includes a manifold system including at least one conduit extending circumferentially around the lower portion of the inner annular casing. The clearance control system includes a header system including at least one header extending circumferentially around only the lower portion of the inner annular casing. The at least one header configured to receive a flow of cooling fluid from the at least one conduit. The at least one header configured to channel the flow of cooling fluid to the lower portion of the outer surface of the inner annular casing.

Abstract: An intake structure of a compressor includes an intake duct forming an intake port opening in a direction away from a central axis of the compressor and a bellmouth forming an annular channel expanding from an inlet of the compressor toward an inner space of the intake duct. The bellmouth includes a plurality of struts connecting an inner casing positioned inside the annular channel and an outer casing positioned outside the annular channel. At least one of a plurality of transverse struts, of the plurality of struts, which are located on both sides of a center plane passing through the central axis of the compressor and the center of the intake port has a trailing edge positioned on a virtual plane passing through the central axis of the compressor and a leading edge positioned on a side of the intake port with respect to the virtual plane.

Abstract: A gas turbine engine component array includes first and second components each having a platform. The platforms are arranged adjacent to one another and provide a gap. A seal is arranged circumferentially between the first and second components and in engagement with the platforms to obstruct the gap. A cooling hole is provided in the seal and is in fluid communication with the gap. The cooling hole has an increasing taper toward the gap.

Abstract: Turbomachines having one or more flow guiding features designed to increase the performance of the turbomachine (3400, 3700, 4000, 4800). In some examples, flow guiding features are designed and configured to bias a circumferential pressure distribution at a diffuser inlet (2210, 2310, 3410, 4204, 4810, 5208, 808) toward circumferential uniformity, otherwise account for such low-frequency spatial pressure variations, increase the controllability of spatial flow field variations, or modifying flow field variations, etc.

Abstract: A turbine vane assembly adapted for use in a gas turbine engine includes a support strut and a turbine vane arranged around the support strut. The support strut is made of metallic materials. The turbine vane is made of ceramic matrix composite materials to insulate the metallic materials of the support strut.

Abstract: A flexible damper (24) for turbine blades (10) includes a plurality of segments (32) positioned together in a substantially linear pattern, each segment (32) having a first side (46), a second side (48), a top side (50), a bottom side (52), a length (56), a width (54), and a thickness (58).

Abstract: A compressor includes a compressor screen mounted on the outer circumferential surface of a compressor disk or the inner wall of a compressor casing. The compressor screen is positioned between a row of compressor blades and a row of compressor vanes to stabilize airflow by regulating the amount of air flowing in the compressor. The compressor screen is formed of annular plate having openings through which the compressed air flows, arranged in a pattern to smoothly regulate the flow of air. The compressor screen may be variously configured, for example, to facilitate installation or to guide the flow of air using a tapered surface or a directionality of the openings or a flow guide. A gas turbine includes a combustor, a turbine, and a compressor employing the compressor screen.

Abstract: A ventilation flow path, a cooling air flow path, a mixing space, and a mixed air flow path are formed in a gas turbine rotor. The ventilation flow path guides compressed air farther on an axially upstream side than an air discharge port of a compressor to an interior of a compressor rotor as compressor extracted air. The cooling air flow path guides cooling air to a part farther on an axially downstream side than the air discharge port. The compressor extracted air and the cooling air are mixed in the mixing space. The mixed air flow path guides mixed air containing the compressor extracted air and the cooling air into a turbine rotor.

Abstract: Various embodiments of an unmanned aerial vehicle are disclosed. In some embodiments, the UAV includes a motor assembly rotatable about a rotation axis and a propeller hub assembly removably engageable with the motor assembly. The propeller hub assembly includes a retainer configured and dimensioned for engagement with the motor assembly such that rotation of the motor assembly causes corresponding rotation of the propeller hub assembly. The retainer includes a pair of deflectable arms resiliently repositionable between a first position and a second position, for engagement and disengagement with the motor assembly, respectively. The arms are movable inwardly towards the rotation axis from the first position to the second position upon application of an external force and movable outwardly away from the rotation axis from the second position to the first position upon removal of the external force.