Abstract: Embodiments of this application provide a centrifugal pump. The centrifugal pump includes a pump casing and a first drive mechanism, a second drive mechanism, a pump shaft, and an impeller that are disposed in the pump casing. The pump casing includes a first chamber and a second chamber that are connected. An axis of the pump shaft coincides with axes of the first chamber and the second chamber. An inner diameter of the second chamber is greater than that of the first chamber. The impeller is connected to an end of the pump shaft. The first drive mechanism and the second drive mechanism are connected to the pump shaft and located on a side, away from the impeller, of the pump shaft. The first drive mechanism is configured to drive the pump shaft to rotate.

Abstract: A borescope plug assembly includes a housing, a plug, and a spring. The housing extends between a first housing end and a second housing end. The housing includes a plug aperture, an internal chamber, and a bayonet interface. The plug aperture is located at the second housing end. The internal chamber extends from the plug aperture toward the first housing end. The plug includes a shaft, a first sealing surface, and at least one tab. The shaft extends between a first shaft end and a second shaft end. The first sealing surface is disposed at the first shaft end. The at least one tab projects radially outward from the shaft. The plug extends through the plug aperture with the second shaft end and the at least one tab disposed within the internal chamber. The spring is positioned within the internal chamber between the first housing end and the at least one tab.

Abstract: A variable channel diffuser includes a shroud, a backing plate, a channel plate adjacent to the backing plate, a floor plate adjacent to the shroud, standoffs formed on the floor plate, and recessed areas formed in the channel plate. The channel plate is between the shroud and the backing plate. The floor plate is between the shroud and the channel plate and is movable relative to the channel plate. The standoffs and the recessed areas define channels for fluid flow. Each channel has an area which is variable through movement of the floor plate relative to the channel plate.

Abstract: A variable vaneless diffuser includes a shroud, a backing plate, a divider plate adjacent to the backing plate, a floor plate adjacent to the shroud, a plurality of standoffs formed on the divider plate, and a plurality of clearance slots formed in the floor plate. The divider plate is between the shroud and the backing plate. The floor plate is between the shroud and the divider plate and is movable relative to the divider plate. The plurality of standoffs and the plurality of clearance slots define a flow path for fluid flow. The flow path has an area which is variable through movement of the floor plate relative to the divider plate.

Abstract: Centrifugal pump systems and related methods are disclosed herein that can shift a best efficiency point of a pump based on one or more operating conditions to operate more efficiently across and/or adjust to a broader range of conditions. Pumps provided for herein can include an adaptive volute in which a geometry of the volute can be adjusted to shift an operating efficiency of the pump. In some embodiments, a height or radial dimension of the adaptive volute can be adjusted based on one or more operating condition. A geometry of the adaptive volute can be adjusted during operation of the pump and/or while an impeller is disposed within the volute. In some embodiments, a first and second collar can be disposed within the adaptive volute. Rotation of the first component can move the second component axially, which can expand or contract an axial dimension of the adaptive volute.

Abstract: Provided are a variable geometry turbine and a supercharger including the same that can change flow rate characteristics of a turbine in accordance with engine output with simple structure and can adjust the flow angle of a fluid flowing into a turbine impeller to any angle in the circumferential direction of the turbine impeller. The variable geometry turbine (10) includes a turbine impeller (12) configured to rotate about an axis line, a turbine housing (30) configured to accommodate the turbine impeller (12) and form a throat passage (32) and a scroll flow channel (34) on the outer circumferential side of the turbine impeller (12), the scroll flow channel (34) communicating with the throat passage (32), and a width changing mechanism in which a width change portion (52) that changes a passage width of the throat passage (32) along the circumferential direction of the turbine impeller (12) is movable in the width direction of the passage width.

Abstract: A variable vane assembly includes a variable vane; a trunnion arranged on one end of the variable vane; a bushing mated to the trunnion to define an interface between the trunnion and the bushing; and a surface modification on at least one of the trunnion and the bushing at the interface, whereby frictional heating at the interface during operation of the assembly is reduced.

Abstract: A rotor hanging tool includes a beam extending in parallel to an axial direction above a rotor main body, a pair of ring support portions disposed at an interval in the axial direction, connected to the beam, and attachable to and detachable from a support ring, a pair of rotor support portions disposed at an interval in the axial direction, connected to the beam, attachable to and detachable from the rotor main body at positions different from the ring support portions in the axial direction, and respectively supporting the rotor main body from below, and a vertical position adjustment unit for adjusting a position of each of the rotor support portions in a vertical direction with respect to the beam.

Abstract: A bearing chamber housing for supporting a shaft of a turbomachine is provided, the bearing chamber housing including an additively built-up housing wall which bounds an oil chamber of the bearing chamber housing radially outwardly relative to an axis of rotation of the shaft, the housing wall being built up with an oil duct which has an inlet opening toward the oil chamber for admission of oil from the oil chamber into the oil duct, and which has an outlet opening for discharging the oil from the oil duct, the outlet opening being located at a different axial position and at a different circumferential position than the inlet opening, considered relative to the axis of rotation of the shaft, and the oil duct having an extent with both an axial component and a circumferential component, at least over a portion thereof.

Abstract: There is provided a nozzle for a fan assembly. The nozzle comprises an air inlet, a first air outlet for emitting an air flow and a second air outlet for emitting an air flow, the first and second air outlets together defining an aggregate air outlet of the nozzle, a single internal air passageway extending between the air inlet and the first and second air outlets, and a valve for controlling an air flow from the air inlet to the first and second air outlets. The valve comprises one or more valve members that are moveable to adjust the size of the first air outlet relative to the size of the second air outlet while keeping the size of the aggregate air outlet of the nozzle constant, and wherein the air outlets are oriented towards a convergent point.

Abstract: A centrifugal blower assembly includes a scroll wall, a pair of opposing sidewalls, and a cutoff plate. The scroll wall is positioned between the pair of opposing sidewalls such that the scroll wall and opposing sidewalls together define a blower chamber and a blower outlet. The scroll wall extends circumferentially between a cutoff point to an end point and defines a cutout extending circumferentially from the cutoff point. The scroll wall, the pair of opposing sidewalls, and the cutoff point define a blower outlet, wherein the blower outlet defines a blower outlet area. The cutoff plate extends circumferentially from the end point. The cutoff plate defines a notch defining a notch area, the notch area and the blower outlet area define a total blower outlet area, wherein the notch includes a center portion that defines a portion of an elliptical shape.

Abstract: A downrod assembly includes: an electric motor, an adapter subassembly and a downrod. The adapter subassembly is connected to an electric motor shaft of the electric motor; and the downrod is connected to the adapter subassembly and is capable of rotating with respect to the electric motor by means of the adapter subassembly. The downrod is able to be folded by rotating with respect to the electric motor during transportation, thereby reducing the overall packaging volume of a ceiling fan.

Abstract: A monitoring sensor for a state of a blade of a rotating machine includes a sensor for monitoring a state of the blade of the rotating machine, a first section configured to be fixed to a casing of the rotating machine, and a second section holding the sensor and supported by the first section so as to be able to adjust a position of the sensor in an axial direction of the casing.

Abstract: A fan assembly in which all of the major structural components of the assembly are mechanically fastened together by non-welding means, such as mechanical fasteners, is disclosed. The disclosure also relates to a fan assembly in which the major structural components have planar segments separated by bend lines that approximate a curved shape, and that can be formed, for example, by a press brake machine. Such a construction can eliminate the necessity for rolling, welding, and painting of the structural components of the fan assembly.

Abstract: The invention relates to an exhaust gas turbine, comprising a turbine rotor (12) having a plurality of turbine rotor blades (2) with a turbine rotor blade height H. The exhaust gas turbine further comprises a diffuser arrangement (20) having a transverse diffuser (1) and an exhaust gas collection chamber (9). The transverse diffuser (1) is arranged downstream of the turbine rotor blades (2). The transverse diffuser (1) has a curved diffuser channel (13) which opens into the exhaust gas collection chamber (9) at a diffuser channel outlet (17). A M/H ratio between an axial extension M of the exhaust gas collection chamber (9) and the turbine rotor blade height H has a value of 1.0?M/H?4.6 and a P/H ratio between a radial extension P of the diffuser arrangement (20) and the turbine rotor blade height H has a value of 2.7?P/H?4.9. A D/H ratio between a radial expansion D of the diffuser channel section (13) and the turbine rotor blade height H has a value of 2.5?D/H?3.

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 steam turbine (ST) includes a rotor (11) which is rotatable around an axis (Ar), an inner casing (21) surrounding the rotor (11) from an outer peripheral side, an outer casing (30) surrounding the rotor (11) and the inner casing (21) and defining an exhaust chamber between the inner casing (21) and the outer casing (30), the steam being exhausted to the exhaust chamber (30s), and a flow guide (27) which has a tubular shape and is installed on one end portion of the inner casing 21 in an axial direction (Da) in the exhaust chamber (30s) to guide the steam discharged from the rotor (11). The flow guide (27) has a turning surface (RA) which is connected to an outer peripheral surface (27A) and turns a fluid flowing along the outer peripheral surface (27A) toward the other side in the axial direction (Da).

Abstract: A submersible machine guide assembly suitable for guiding a submersible machine from an upper position towards an operative position. The guide assembly includes a top mount configured to be arranged at the upper region of the tank, a supporting member configured to be arranged in the tank, and two guide wires running along each other in the vertical direction of the tank. Each of the guide wires is connected to the top mount at a first end and is connected to a seat of the supporting member at a second end. A runner is displaceable along the guide wires. The runner includes two guide members that engage the guide wires and that are connected to each other at the lower ends thereof. The lower end of each guide member is configured to engage the corresponding seat of the supporting member when the runner is in the operative position.

Abstract: A gas turbine engine includes a compressor section having a first portion and an aft portion. A compressor case clearance (CCC) control system is configured to adjust an amount of bleed air delivered to the front portion and the aft portion based on an in-flight phase of an aircraft. In response to invoking a first mode, the CCC control system delivers air to both the front portion and the aft portion. In response to invoking a second mode, the CCC control system reduces the amount of air delivered to the aft portion prior to transitioning from the cruise phase to the descent phase. Accordingly, clearance areas within the compressor section can be selectively increased during specific portions of the flight to avoid contact between blade tips and the engine case.

Abstract: A casing of a turbocharger, which surrounds a housing to be encased such as a turbine housing and/or a compressor housing and/or a bearing housing of the turbocharger at least in sections, with axial casing segments, which axially adjoin the housing to be encased, with at least one radial casing segment, which radially adjoins the housing to be encased radially outside, and at least one stiffening element is formed or acts on at least one casing segment.

Abstract: A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Cooling air is directed onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.

Abstract: A pump assembly includes a pump and a base. The pump has mounts located at multiple positions on the pump to effect different configurations of the assembly. Each mount includes two engagements spaced apart on the pump. The base has a retainer constructed to slidably engage one engagement and a seat constructed to support the other engagement. The seat has a socket with two holes extending into the base. A bracket includes a jaw engageable with the second engagement and two locking pins extending from the bracket for sliding engagement with the socket. The locking pins retain the bracket and jaw from moving away from the base. A fastener engages the bracket with the base so the two locking pins cannot slidably disengage the socket.

Abstract: A bearing arrangement comprising a shaft with a recess in its end, a bearing housing, an annular first bush comprising an inner first portion and an inner second portion and a second bush that engages the recess of the shaft. The first bush bears against the bearing housing. The shaft engages the inner first portion of the first bush. The second bush engages the inner second portion of the first bush.

Abstract: A variable diffuser for a centrifugal compressor comprises a passage between opposing disc faces and a plurality of vanes extending therethrough with a fixed angle relative to the engine centerline. Axial displacement between the opposing disc faces is variable. The vanes extend through one of the opposing disc faces as that disc face is axially translated.

Abstract: An outer housing 12 formed of a sheet metal is provided such that its open end portion 312 surrounds an outer edge portion 26 of an inner housing 11 formed by casting. An outer protrusion 216, an annular protrusion 227, and a connecting portion 27 are provided on the outer edge portion 26 of the inner housing 11. The open end portion 312 of the outer housing 12 is joined to a protruding end 217 of the outer protrusion 216, a protruding end 228 of the annular protrusion 227, and an end edge 271 of the connecting portion 27, whereby the inner housing 11 and the outer housing 12 are integrated.

Abstract: A blade track for a gas turbine engine includes a plurality of blade track segments. The blade track segments are arranged circumferentially around a central axis to form the blade track.

Abstract: Electric power from the low spool of a turboshaft engine is transferred to drive the compressor of another turboshaft engine. This is used to assist in maintaining the other turboshaft idling while a single engine provides flight power or to increase acceleration for instance.

Abstract: A device for adjusting a gap between the housing of an impeller and the impeller in a radial compressor of a turbomachine is provided. The device comprises at least one mechanical setting device by means of which the housing of the impeller can be axially adjusted in a targeted manner for the purpose of adjusting the gap, wherein the at least one setting device can be actuated via an adjusting ring, and a transmission of a force and/or a torsional moment from the adjusting ring can be effected via at least one adjustment lever device, in particular a thread lever, or a tilting lever.

Abstract: An attachment interface assembly for a gas turbine engine has a component configured for attachment to an engine static structure. A fastener has a threaded body portion and an enlarged head portion. The threaded body portion is inserted through aligned holes in the component and engine static structure. A clip has a center opening that receives the threaded body portion such that the clip is positioned between the enlarged head portion and the component.

Abstract: A pin insertion hole penetrating an outer member from an outer circumferential side to an inner circumferential side is formed in the outer member. A pin groove that is concave from an outer circumferential side to an inner circumferential side is formed in an inner member. A positioning device includes a pin that is inserted into the pin insertion hole of the outer member and the pin groove of the inner member, a liner holder that comes in contact with a groove side surface of the pin groove, and a liner that is disposed between the liner holder and the pin in the pin groove.

Abstract: A variable pitch rectifier for a compressor includes a plurality of radial vanes having respectively, at outer and inner ends of same, outer and inner pivots, the inner pivots being received between two upstream and downstream inner rings, which are assembled by a link device. The link device includes only a set of angular sectors of elastically deformable stirrups, arranged to grip together the inner peripheral edges of the upstream and downstream rings by clamping one against the other.

Abstract: An improved variable geometry diffuser (VGD) mechanism for use with a centrifugal compressor. This VGD mechanism extends substantially completely into the diffuser gap so that the VGD mechanism may be used more fully to control other operational functions. The VGD mechanism may be used to minimize compressor backspin and associated transient loads during compressor shut down by preventing a reverse flow of refrigerant gas through the diffuser gap during compressor shutdown, which is prevented because the diffuser gap is substantially blocked by the full extension of the diffuser ring. During start-up, transient surge and stall also can be effectively eliminated as gas flow through the diffuser gap can be impeded as load and impeller speed increase, thereby alleviating the problems caused by startup loads at low speeds. The VGD mechanism can be used for capacity control as well so as to achieve more effective turndown at low loads.

Abstract: Various embodiments of the disclosure include an alignment apparatus for assembly alignment and load sharing. The alignment apparatus may include: an alignment pin including a first end and an opposing, second end, wherein the first end is configured to couple with a first hole in a first turbine nozzle diaphragm and the second end is configured to couple with a second hole in a second, adjacent turbine nozzle diaphragm. Embodiments of the disclosure may also include a turbine and a combined-cycle power plant. The turbine may include: a first nozzle diaphragm; and a second, adjacent nozzle diaphragm, wherein the first diaphragm is directly coupled to the second diaphragm. The combined-cycle power plant may include: a steam turbine; a gas turbine; a first nozzle diaphragm within the gas turbine; a second, adjacent nozzle diaphragm within the gas turbine; and an alignment pin coupling the first diaphragm directly to the second diaphragm.

Abstract: A gas turbine engine comprises bearing(s). A structure supporting the bearing defines a bearing cavity surrounding the at least one bearing, an ambient chamber and an intermediate chamber having a portion between the bearing cavity and the ambient chamber, with at least one wall forming a passage from the bearing cavity to the ambient chamber and through the portion of the intermediate chamber. A tube is received in the passage and having a first end open to the bearing cavity and a second end open to the ambient chamber, the second end adapted to be connected to a conduit for fluid communication between the bearing cavity and the through the tube, wherein a portion of or near the first end of the tube is sealingly joined to the at least one wall, and the second end of the tube contacts the at least one wall and is free to move relative to the at least one wall.

Abstract: A jacking assembly for a rotor of a turbine includes an arc-shaped saddle which extends around and supports a lower portion of a rotor. A lifting beam extends over the rotor transversely to an axial direction of the rotor. The lifting beam is axially aligned with the arc-shaped saddle. Two connectors are disposed on respective lateral sides of the rotor, each connector extending between and being coupled to the lifting beam and the arc-shaped saddle such that the saddle is configured to lift the rotor vertically when the lifting beam is displaced vertically.

Abstract: The invention relates to an intermediate casing hub of an aircraft turbojet engine, which includes: an outer shroud (14) intended for defining a secondary flow space of a stream of secondary gas on the inside and an inter-flow area on the outside, the outer shroud (14) being provided with a secondary opening (29), and a bleed valve comprising an outlet pipe (30) made of composite material, located in the inter-flow area, wherein the outlet pipe (30) is attached to the outer shroud (14) at the secondary opening (29), at least one gasket (33) for sealing against air and fire being arranged between the outlet pipe (30) and the outer shroud (14), and the outlet pipe (30) made of composite material includes a draped composite wall (30a, 30b), made up of a plurality of folds impregnated with resin.

Abstract: A tangential flow machine can be operated both as electric propulsion and as a generator, having a jacket housing which can have flow passing around it on an outer side, the profile of which is formed on a first front-side opening, and tapers to a second front side, on which a second front-side opening is formed. Between the two front-side openings, there extends a flow path along a main axis, and with an electrical machine, which on the jacket housing has a stator and a rotor that is supported so as to rotate within the stator. The rotor defines a free rotary axis and has a rotor ring and an arrangement of rotor blades which each extend from the rotor ring, radially to a free edge and the free edges of the rotor blades, in the projection direction parallel to the main axis.

Abstract: A system includes a diffuser section comprising an outer barrel, an outer aft plate, an inner barrel, an inner aft plate, and a plurality of poles, where the outer aft plate is disposed at a downstream end of the outer barrel, the inner aft plate is disposed at a downstream end of the inner barrel, the outer barrel and the inner barrel are disposed about a turbine axis, the diffuser section receives an exhaust gas from a gas turbine, the plurality of poles is circumferentially spaced about the turbine axis, and each pole of the plurality of poles couples a downstream end of the outer aft plate to a downstream end of the inner aft plate.

Abstract: A device for guiding variable pitch stator vanes of a turbine engine is provided. The device includes a plurality of inner ring angular sectors arranged end-to-end in order to form an inner ring, each inner ring sector having chimneys passing radially through the inner ring sector, a plurality of cylindrical bushings, each being put into place in a chimney of the inner ring from the inside and each serving to receive a guide pivot of a stator vane, a plurality of reconstitution ring angular sectors arranged end-to-end in order to form a reconstitution ring and put into place radially from the inside against the inner ring, and a plurality of blocking elements passing axially through the inner and reconstitution rings in order to assemble the rings together.

Abstract: Embodiments of the present invention relate to a determination of a user's exclusiveness toward a particular brand. User-specific entities are extracted from social media content associated with a user. At least a portion of the user-specific entities are brand-related entities that are specifically relevant to a particular brand. These brand-related entities are analyzed with respect to the user-specific entities extracted from the social media content to determine a level of exclusivity of the user to the brand.

Abstract: A modular panel for covering a portion of a structure and directing air impacting against the structure into a common path to harness wind energy includes a rear side that is adapted for mounting with the structure and a front side having a plurality of apertures therethrough. At least one central conduit leads from an inlet port on a first edge of the modular panel to an outlet port on a second edge of the modular panel. A plurality of branch conduits are each fixed between one of the plurality of apertures and the at least one central conduit. At least one of the modular panels affixed to the structure further preferably includes a wind turbine within the panel and along the central conduit. The wind turbine is adapted for receiving air from the central conduit and each branch conduit for spinning the wind turbine to produce electricity.

Abstract: A sensor system includes a sensor and a mast on which the sensor is mounted. The mast includes a core body and a shroud, wherein the shroud is provided about the core body, and the shroud is independently rotatable with respect to the core body under the influence, in use, of a fluid flow flowing past the shroud. The shroud is shaped so that, from at least one fluid flow direction, the shroud presents a different flow resistance in dependence upon the rotational orientation of the shroud. The rotational orientation of the shroud adjusts to reduce the flow resistance produced by the shroud to the fluid flow in response to the commencement of, or a change in the fluid flow direction to, one of the at least one fluid flow direction.

Abstract: A method for disassembly of a rotor, in particular the front rotor of a gas turbine with a housing and a channel which diverges in a direction of flow and in which the rotor is arranged, is disclosed. An embodiment of the method includes axially displacing an outer sealing ring that is radially opposite the rotor, and whose minimum inside diameter is smaller than the maximum outside diameter of the rotor, against the direction of flow. Then, the rotor is axially displaced against the direction of flow, in particular out of the housing. A method for assembly of such a rotor, as well as a tool for the same, is also disclosed.

Abstract: The invention relates to a method for installation of a power control module in a tower for a wind turbine. The method includes, providing a power control module (101) and providing a tower section (201). According to the invention the following steps are included in the mentioned sequence. a) providing a temporary support device (301), b) placing the power control module (101) on the temporary support device (301), c) placing the tower section (201) around the power control module (101), d) connecting the power control module (101) to the tower section (201), and e) removing the connected power control module (101) and tower section (201) from the temporary support device (301). The invention also relates to an aggregate component for a wind turbine. The component includes a power control module (101) and a tower section (201). The power control module (101) is connected to and supported by the tower section (201) in a state as a pre-fabricated and mobile component.

Abstract: An engine nacelle is provided and includes an outer fixed structure (OFS) assembly disposed about an inner fixed structure (IFS) barrel and a latch beam, which is separate from the IFS barrel along an entire length thereof. The latch beam includes forward and trailing ends directly and indirectly supportively coupled to the OFS assembly, respectively.

Abstract: A method includes inserting axially a radially interior surface of an aft plate assembly into a circumferential groove of an inner barrel of a diffuser section of a gas turbine, where the aft plate assembly is inserted into a first circumferential orientation relative to the circumferential groove, and the circumferential groove is disposed on a radially exterior surface of the inner barrel. The method includes rotating the aft plate assembly circumferentially within the circumferential groove from the first circumferential orientation to a second circumferential orientation, where the inner barrel is configured to axially retain the aft plate assembly when the aft plate assembly is disposed in the second circumferential orientation.

Abstract: A fan assembly in which all of the major structural components of the assembly are mechanically fastened together by non-welding means, such as mechanical fasteners, is disclosed. The disclosure also relates to a fan assembly in which the major structural components have planar segments separated by bend lines that approximate a curved shape, and that can be formed, for example, by a press brake machine. Such a construction can eliminate the necessity for rolling, welding, and painting of the structural components of the fan assembly.

Abstract: A turbine shroud assembly is disclosed including an inner shroud having a surface adjacent to a hot gas path, an outer shroud, a damper block disposed between the inner shroud and the outer shroud, a first biasing apparatus, and a second biasing apparatus. The first biasing apparatus provides a first biasing force to the inner shroud, biasing the inner shroud a first deflection distance in a direction toward the hot gas path and away from the outer shroud. The second biasing apparatus provides a second biasing force to the damper block, biasing the damper block a second deflection distance in a direction toward the hot gas path and away from the outer shroud. The second deflection distance is greater than the first deflection distance.

Abstract: A gas turbine engine includes a bleed structure which includes a forward wall and a rear structural wall to define a deposit space downstream of the bleed structure for a hail event of a predetermined duration.

Abstract: An appliance having a fresh food storage compartment and a freezer compartment. The appliance includes a forced air coil system disposed between the fresh food storage compartment and the freezer compartment and is configured to selectively provide cooling to one or both of the at least one fresh food storage compartment and the at least one freezer compartment. The forced air coil system includes an evaporator fan configured to provide cooling to the food storage compartment, the freezer compartment, or both.