Abstract: There is provided with an axial fan comprising an impeller having a plurality of vanes; a motor rotating the impeller; a casing housing the impeller and the motor; a motor base mounting the motor; and a plurality of spokes connecting the motor base and the casing, wherein the motor base has a plurality of reinforcement ribs thereon, the plurality of reinforcement ribs being equal to or more than the plurality of spokes in number, and wherein the casing has a natural frequency equal to or higher than a frequency being transmitted to the casing from the motor when the motor is rotated at a rotation speed of 20000 rpm or more.

Abstract: A compressor rectifier of a turbomachine including a plurality of stationary blades extending in a circular fashion between an inner shroud and an outer shroud that are concentric and define interblade channels forming an air duct in which air to be compressed flows, the inner shroud including at least one vortex generator extending into the air duct to reduce corner vortices. The vortex generator is positioned axially in the interblade channel, between the axial position of a leading edge of the blades and those of a trailing edge thereof.

Abstract: The present invention relates to a multi-stage vacuum pump having a plurality of compression stages 12, 14, 16, 18 20 and a booster stage 22. The pump 10 is arranged to pump a chamber 24. The pumping stages include respective rotors supported for rotation on one or more common drive shafts 26. A recirculation valve 28 is associated with the booster stage 22 for selective recirculation of pumped fluid from an outlet 32 to an inlet 30 of the booster stage above a predetermined pressure.

Abstract: A linear gasket for an inter-blade platform that presents a length, the gasket including a linear base for fastening to the inter-blade platform and a linear lip projecting from the linear base, the linear lip including a linear distal end portion configured to contact a pressure side wall or a suction side wall of a blade, a linear groove being formed between the linear base and the linear lip over at least a fraction of a length of the linear gasket. The linear distal end portion includes at least one linear slit extending over at least a fraction of the length of the gasket.

Abstract: An exhaust gas turbocharger may include a shaft mounted in a bearing housing carrying a compressor wheel and a turbine wheel. The shaft may include a sealing bush arranged on the shaft in a rotationally fixed manner. The sealing bush together with a bearing housing cover may at least partially delimit an annular oil centrifuging space arranged coaxially to the sealing bush. The bearing housing cover may include a guiding nib located radially outside the sealing bush partially covering the sealing bush in axial direction. The guiding nib may be configured to guide oil separated in the oil centrifuging space onto the rotating sealing bush. The rotating sealing bush may be configured to direct the oil into the oil centrifuging space in response to centrifugal force creating an oil swirl.

Abstract: A turbomachine, in particular, a compressor, having a housing and having at least one housing insert accommodated therein and having a fitting piece for the adjustment of a gap dimension between the housing and the housing insert, wherein the housing comprises, for the adjustment of the gap dimension, a horizontally adjustable guide element into which the fitting piece is inserted, is provided.

Abstract: An electric submersible pump (ESP) assembly bearing is described. A bearing set for an ESP assembly includes a rotatable sleeve, and a bushing outward of the rotatable sleeve, the bushing including a tubular portion, and a radial flange extending around a downstream side of the tubular portion. An ESP assembly includes a rotatable shaft, at least one stage stacked in series on the rotatable shaft, each stage including a diffuser, a stationary bearing member including a tubular portion secured within a working fluid exit of the diffuser, a stationary member flange extending radially outward from a top of the tubular portion, and a rotatable sleeve inward of the stationary bearing member and secured to the rotatable shaft. A bearing set for an ESP assembly includes a bushing including a tubular portion, and an annular retaining ring groove extending around an outer surface of the tubular portion.

Abstract: A clamping and support system for a turbine is disclosed. The clamping and support system may include a support bar coupled with a lower diaphragm portion of the turbine. The support bar may have a protuberance extending from a first end portion thereof that may at least partially extend into a slot formed in the lower diaphragm portion of the turbine. The clamping and support system may also include a clamping bar coupled with a second end portion of the support bar. The clamping bar may at least partially extend into a slot formed in an upper diaphragm portion of the turbine such that at least a portion of the lower diaphragm portion and at least a portion of the upper diaphragm portion are interposed between the clamping bar and the protuberance of the support bar, thereby coupling the lower diaphragm portion with the upper diaphragm portion.

Abstract: A blower device includes an axial flow fan having blades to blow air, and a fan shroud that includes a cylindrical portion surrounding an outer circumference of the fan at a distance from the outer circumference, and an air guiding portion guiding air drawn by the fan. The fan shroud includes a short end part shorter in distance to the outer circumference of the fan than another part in an outer end portion of the fan shroud, and a protruding end part provided at a position advanced in a rotational direction from the short end part, protruding upstream in a flow of the drawn air more than the fan and protruding outward of the air guiding portion. Accordingly, the blower device which includes the fan shroud capable of reducing rotational noise can be provided.

Abstract: A cooling structure for a turbomachine. In one embodiment, the cooling structure is for a seal slot of the turbomachine. The cooling structure includes a body coupled to a surface of the seal slot. The body includes a passageway on a first surface of the body for providing a cooling fluid to the seal slot. In an other embodiment, a apparatus includes a first component and a second component adjacent the first component. The apparatus also includes a seal slot extending between the first component and the second component, and a cooling structure positioned within the seal slot. The cooling structure includes a body coupled to a surface of the seal slot. The body has a passageway on a first surface of the body for providing a cooling fluid to the seal slot.

Abstract: A wind turbine comprises a hub, a blade rotatably mounted to the hub, and a pitch system. The pitch system includes a support, a first drive configured to rotate the blade relative to the support, a second drive configured to rotate the support relative to the hub. The support is configured to be selectively fixed relative to the blade and the hub such that the first or second drive may be used to pitch the blade. A method of pitch corresponding to this operation is provided.

Abstract: A gas turbine engine comprising at least one drum pack having two or more annular discs 62a-c. Adjacent discs 62a-c are connected by drive arms 68 the drum pack is provided with a tubular sealing body 84 positioned radially inwards of the drive arms 68 and extending from a first disc 62a to a last disc 62c in the drum pack. The first 62a and last 62c discs have the greatest axial separation of all discs 62a-c in the drum pack. The sealing body 84 engaging the first 62a and last 62c discs and the engagement being arranged to limit or prevent the ingress of liquid into a drum cavity 76 defined between the first 62a and last 62c discs, the drive arms 68 and the sealing body 84.

Abstract: A power generation system comprising a first vessel, a second vessel, a pump operably connected to the first vessel and the second vessel, and a turbine manifold assembly operably connected to the first vessel and the second vessel, wherein the pump creates a positive pressure in the first vessel to force a fluid in a first direction through the turbine manifold assembly and into the second vessel to a pre-determined level by a negative pressure in the second vessel, wherein, once the fluid reaches the pre-determined level in the second vessel, the pump creates a positive pressure in the second vessel to force the fluid in an opposing second direction through the turbine manifold assembly and back into the first vessel by a negative pressure in the first vessel to complete a cycle is provided. Furthermore, associated methods and a turbine manifold assembly is also provided.

Abstract: A nozzle for a fan assembly has an air inlet, an annular air outlet, and an interior passage for conveying air from the air inlet to the air outlet. The interior passage is located between an annular inner wall, and an outer wall extending about the inner wall. The inner wall at least partially defines a bore through which air from outside the nozzle is drawn by air emitted from the air outlet. The inner wall is eccentric with respect to the outer wall so that the cross-sectional area of the interior passage varies about the bore. The variation in the cross-sectional area of the interior passage can control the direction in which air is emitted from around the air outlet to reduce turbulence in the air flow generated by the fan assembly.

Abstract: A turbine engine system includes a heat source, a heat exchanger, a cooling medium inlet and a cooling medium outlet. The heat source includes a first passage. The heat exchanger includes a second passage and a third passage. The first and the second passages are configured in a closed loop circuit. The third passage is configured between the inlet and the outlet in an open loop circuit.

Abstract: A rotor system has a rotor, an axis of rotation about which the rotor may be rotated, a linkage system having a first adjustable length portion and a second adjustable length portion, wherein the second adjustable length portion is configured to provide a relatively finer adjustment of an overall effective length of the linkage system as compared to the first adjustable length portion and wherein the rotor is configured to rotate about the axis in response to changing the overall effective length of the linkage system.

Abstract: A flow deflector arrangement is used in combination with a pipe arrangement secured through a component, the flow deflector arrangement comprising: a nut to secure the pipe arrangement to the component, and a shroud for attachment to the component so as to extend at least partially around the pipe arrangement when the pipe arrangement is secured to the component by the nut. The nut has an outwardly directed flange to adopt a position spaced from the component, and the shroud defines at least one deflector surface which, when the shroud is attached to the component, extends away from the component in spaced relation to the pipe arrangement. The flange and the deflector surface cooperate in deflecting a flow of fluid flowing from the component and along the outside of the pipe arrangement such that the flow is deflected generally outwardly from the pipe arrangement with a degree of swirl.

Abstract: A lubrication system for a device located between an internal shaft and an external shaft of an aircraft turbine, that are free to rotate, concentric and arranged at least partially one around the other, is provided. The lubrication system includes an annular element provided with an external groove and being mounted integral with the external shaft, the external groove being supplied with lubricant from a fixed part of the turbine; and a grooved element mounted integral with the internal shaft, the grooved element having a relief which directs a lubricant in contact with its external surface along a longitudinal direction when the internal shaft is rotating. The external groove is in fluid communication with an external surface of the grooved element through at least two conduits arranged through the external shaft.

Abstract: A centrifugal fan includes a fan frame, a stator assembly and an impeller. The fan frame has a base plate portion, a cover plate portion and a lateral wall portion. The cover plate portion includes first and second faces. The cover plate portion includes an air inlet, and the lateral wall portion includes an air outlet. The impeller has a radial rotational range. The cover plate portion includes an air-guiding section and an enlarged guiding section. The air-guiding section is aligned with the radial rotational range, and the enlarged guiding section is aligned with an area outside the radial rotational range. A part of the second face is spaced from a bottom of the base plate portion by a first minimal axial distance, and another part of the second face is spaced from the bottom by a second minimal axial distance smaller than the first minimal axial distance.

Abstract: Embodiments of the present disclosure are directed towards a centrifugal compressor, a heat exchanger integral with the centrifugal compressor and configured to transfer heat from a fluid pressurized by the centrifugal compressor to a cooling fluid flow, and a cooling fluid supply head of the heat exchanger comprising an integral flow control valve configured to regulate a cooling fluid flow rate through the heat exchanger.