Abstract: A bearing assembly of a rotor of a wind turbine, for mounting a shaft of the rotor in a fixed housing, wherein the shaft of the rotor is coupled to rotor blades of the rotor via a hub, includes: a plurality of first housing-side axial slide bearing segments engaging on the housing; a plurality of second housing-side axial slide bearing segments; a plurality of first housing-side radial slide bearing segments; and a plurality of second housing-side radial slide bearing segments. An axial distance between the first and second axial sliding surfaces of the rotor defines a bearing length l. The radial sliding surfaces of the rotor on which the first and second radial slide bearing segments are supported, define a bearing diameter d of the bearing assembly, and V?1 applies to a ratio V=l/d between the bearing length l and the bearing diameter d.

Abstract: A turbine wheel consists of a first shroud component and a second bladed disc component. The shroud component comprises a shroud structure, a hub structure and a spoke formed integrally therewith and extending between the shroud structure and the hub structure. The bladed disc component comprises a hub member having inner and outer rims, turbine blades disposed on the outer rim, and at least one receiving zone for receiving the spoke, said at least one receiving zone extending radially between the inner and outer rims. The shroud component and the bladed disc component are connected and thus provide the turbine wheel with a shrouded portion. A shrouded turbine wheel can therefore be conveniently assembled starting from at least two components. Further, these components have simplified geometries for easy manufacture, for example using a casting technique, while the overall mechanical performance of the turbine is preserved or improved.

Abstract: A blade damage evaluation apparatus includes: a registration unit for design information of a turbine and maintenance information; an acquisition processor for detection data of sensors; a first discrimination processor for first facility states of the turbine at a plurality of past time points; a classification processor for classes Cn of a plurality of first facility states; a first determination processor for first operating state values of the turbine; another registration unit for first damage rates at past time points; a setting processor of a characteristic function for each of the classes Cn; a second discrimination processor for a second facility state of the turbine at the current time point; a second determination processor for a second operating state value of the turbine at the current time point; and an analyzer for a second damage rate at the current time point.

Abstract: A plurality of exhaust holes (4f) for exhausting compressed air to the outside of a case body (4) are drilled at a bottom portion of a second flowing path (4e) in a circumferential direction at prescribed intervals in an annular blowing path (8) formed by combining a first case (4a) and a second case (4b) around an outer side in a radial direction of the case body (4), and a diffuser (4r) inclined diagonally downward with respect to a rotation direction of a centrifugal fan (2) is provided at a position facing respective exhaust holes (4f).

Abstract: A device for sealing a space at a juncture between elements of a nacelle, the device being non-flammable by heat, having a predetermined shape, and having a proximal end configured to be inserted into the space to be sealed so as to seal it, and a distal end configured to be fastened to an element of the nacelle at a fire area.

Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a first side plate, a second side plate and a backing plate that extend circumferentially about an assembly axis. A first brush seal and a second brush seal are positioned on opposite sides of the backing plate such that the first brush seal is between the first side plate and the backing plate and such that the second brush seal is between the second side plate and the backing plate. The first brush seal is dimensioned to establish a first sealing relationship with a first gas turbine engine component. The second brush seal is dimensioned to establish a second sealing relationship with a second gas turbine engine component. A method of assembly is also disclosed.

Abstract: An assembly or disassembly method for a casing of a steam turbine in which an inner casing is installed in an outer casing, and the inner casing and the outer casing are fixed at a fixing position, wherein when the inner casing is assembled or disassembled in a state where the fixing position and a gravity center of the inner casing are at different positions in an axial direction of the inner casing, a tilt adjusting jig is interposed between the outer casing and the inner casing so that the assembly or disassembly of the casing is performed while maintaining a tilt of the inner casing with the tilt adjusting jig.

Abstract: An airfoil for a gas turbine engine defining a radial direction and an axial direction, the airfoil including: a flared portion extending from a suction surface of the airfoil at an outer edge of the airfoil along the radial direction; and a plenum disposed at the outer edge of the airfoil, the plenum having a suction-side sidewall and a pressure-side sidewall, wherein the suction-side sidewall has a first sidewall portion adjacent to a second sidewall portion disposed outside of the first sidewall portion along the radial direction, wherein the first sidewall portion defines a first angle, wherein the second sidewall portion defines a second angle, and wherein the first angle is greater than the second angle.

Abstract: A vane assembly includes an airfoil fairing that has first and second fairing platforms and a hollow airfoil section that extends there between. A spar has a spar leg that extends through the hollow airfoil section. The spar leg has a through-passage and an end portion that protrudes from the second fairing platform. A support is secured with the end portion of the spar leg. The support has a platform that includes first and second sides, an opening that extends between the first and second sides, and a nozzle tube that extends from the second side. The first side is adjacent the second fairing platform. The end portion of the spar leg is disposed in the opening so as to fluidly connect the through-passage with the nozzle tube.

Abstract: An article of manufacture includes an article body portion (36); at least one pedestal (58A, 60A, 84, 86) integrally formed with the article body portion (36), and disposed at an outer periphery of (52), and structurally coupled to the article body portion (36); and at least one internal feature (72) disposed at least partially within the article body portion (36) and at least partially within the pedestal (58A, 60A, 84, 86). At least a portion of the internal feature (72) is hollow.

Abstract: A motor adapter assembly can couple a motor shaft for a ceiling fan motor to a downrod. The motor adapter assembly can include a base plate, a cradle with arms extending through the base plate, and a threaded bushing secured between the arms of the cradle. Threading a cap to the threaded bushing can be used to pivot the downrod between an upright position and a pivoted position.

Abstract: A turbo fluid machine includes a rotary shaft configured to rotate in one rotational direction, and a radial foil bearing. The radial foil bearing includes: a bump foil formed of an elastic thin plate having a corrugated shape. The bump foil is divided into first and second foil portions located respectively on one side and on the other side in an axial direction of the rotary shaft. Ridges on the first foil portion are inclined in the other rotational direction of the rotary shaft while extending from an edge of the first foil portion adjacent to the other side toward the one side in the axial direction. The ridges on the second foil portion are inclined in the other rotational direction of the rotary shaft while extending from an edge of the second foil portion adjacent to the one side toward the other side in the axial direction.

Abstract: A forced induction device for an internal combustion engine is provided, which includes a shaft, and a compressor wheel that is threadably mounted to the shaft, and a tool that is configured to engage one or more through bores in the compressor wheel to thread and unthread the compressor wheel onto and off of the shaft. The compressor wheel has a plurality of blades with leading edges that converge at an apex. The apex is aligned with a centerline of the shaft. The tool allows a technician to rotate the compressor wheel relative to the shaft to install or remove the compressor wheel from the shaft without applying any pressure to the blades of the compressor wheel. An associated assembly method is also provided.

Abstract: A ring segment having improved cooling efficiency is provided. The ring segment may include a shield plate mounted to a casing which accommodates a turbine and configured to face an inner wall of the casing, a pair of hooks configured to protrude from the shield plate toward the casing to be coupled to the casing, a cavity defined between the shield plate and the pair of hooks, a plurality of first cooling passages configured to connect the cavity and first side surfaces facing each other of the shield plate, and a plurality of second cooling passages configured to connect the cavity and second side surfaces facing each other of the shield plate, wherein the first cooling passages extend in a longitudinal direction of a central axis of the turbine, and the second cooling passages extend in a circumferential direction of the turbine.

Abstract: A method for installing a gas turbine assembly of a first type at a position of an existing power plant where previously a gas turbine assembly of a second type was installed on a foundation specially designed for said second type. The gas turbine assembly includes at least one housing, a compressor, a combustion chamber, a gas turbine, and a plurality of venting and removal lines guided along the exterior of the housing. Modifications to the venting and/or removal lines of the gas turbine assembly of the first type are carried out in a first step, and the modified gas turbine assembly is installed on the existing foundation in a second step.

Abstract: Disclosed herein are a ring segment having an air pouch and a first cooling hole formed therein, and a turbine including the same. The air pouch and the first cooling hole are formed in a shield wall, thereby achieving an improvement in cooling performance as well as simplification of production process.

Abstract: An assembly for a turbomachine turbine includes a housing (1) extending circumferentially about an axis X, sectors (2) intended to form a ring capable of delimiting a gas flow path, each sector (2) comprising a first side (17) and a second side (18) extending radially and circumferentially about the said axis X and spaced axially from each other, each side (17, 18) of the sector (2) including at least one radial bearing surface of an oblong hole capable of cooperating with support pins (13, 14) of the housing (1), at least one of the sides (17, 18) including means (23) for the circumferential positioning of the sector (2) with respect to the housing (1), wherein each radial bearing surface is cylindrical relative to axis X and is capable of bearing on a complementary cylindrical surface relative to axis X of a support pin.

Abstract: A flow control device for constraining fluid flow between axial flow turbomachines in series has a flow constrainer which constrains the fluid flow downstream of the first turbomachine in the series to the blades region of the second turbomachine, preventing fluid flow from impacting the hub or nosecone of the second turbomachine and providing more uniform fluid flow to the second turbomachine. The flow control device includes connective elements for positioning between the downstream region of the first turbomachine and the upstream region of the second turbomachine. The device may be equipped with stator vanes having a variety of optional configurations to further improve the uniformity of the fluid flow load on the second turbomachine.

Abstract: A turbo device provides a flow-path arrangement in a generator device. Part of a working fluid are used to lubricate at least one of a first bearing part, a second bearing part and a bearing assembly, or the working fluid of an auxiliary flow channel is led to a generator housing for cooling the generator device. In addition, a circulatory system is also provided to include bearing loops and auxiliary loops for leading the working fluid to lubricate at least one of the first bearing part, the second bearing part and the bearing assemble part, and to cool the generator device.

Abstract: A system for placing a wind turbine assembly on a support surface of a support structure being supported on a seabed with a lifting crane provided on a floating vessel, said system can be changed from a first operation mode into a second operation mode to compensate a vertical reciprocal crane movement of the crane relative to the support structure.