Abstract: A grinder accessory is useful for a pump in a wastewater application. The grinder accessory has a cutter plate and a cutting body that co-act on solids, especially fibriform solids. The cutter plate has first and second planar faces, mounted in an inlet of the pump, with a plurality of through holes and a central aperture. The cutting body is poised atop the first planar face and extends through the central aperture to rotationally couple with a drive shaft of the pump. A central hub of the cutting body has a plurality of arms that extend radially proximate to the first planar face, so that a leading edge of the arms interacts with the through holes on solids passing therethrough. A housing defines a cutting chamber around the cutter plate and the cutting body to protect them and to induce swirling action.

Abstract: An axial cooling fan for a vehicle includes an electrically powered motor operable to rotate fan blades to move air to cool a component or accessory of the vehicle. A stator is at the motor and has a plurality of struts that fixedly support the motor at the vehicle. The struts of the stator include leading edge surfaces that generally face air that is flowing towards the struts and past the struts and stator, such as when the motor is powered to rotate the fan blades. The leading edge surfaces of the struts comprise an aerodynamic design or pattern or structure established thereat, such as a toothed pattern or structure at the leading edge surfaces of the struts.

Abstract: A detachable water pump reservoir to collect coolant leakage from a housing of an engine water pump to which the reservoir is attached in use is described herein. The reservoir includes a hollow body defining a chamber in which the coolant leakage is collected and having a mouth shaped to complement a surface of the housing, at least one attachment apparatus configured to enable the reservoir to be easily and quickly attached to and removed from the housing of the water pump, and a level indicator to indicate the level of the coolant collected in the reservoir.

Abstract: A steam turbine 10 according to an embodiment includes rotor blades 22 implanted to a turbine rotor 21, stationary blades 26 making up a turbine stage together with the rotor blades 22, diaphragm outer rings 23 including an annular extending part 24 surrounding a periphery of the rotor blades 22, and supporting the stationary blades 26, and diaphragm inner rings 25 supporting the stationary blades 26. The steam turbine 10 further includes an annular slit 40 formed at an inner surface of the diaphragm outer ring 23 between the stationary blades 26 and the rotor blades 22 along a circumferential direction, and communication holes 50 provided in plural at an outer surface of the diaphragm outer ring 23 along the circumferential direction, communicated to the annular slit 40 from the outer surface side, and communicated to an exhaust chamber sucking water films via the annular slit 40.

Abstract: A method of making a reinforcement for reinforcing a leading edge of a blade, the method including depositing a metal coating on the leading edge by thermal spraying in compression. A blade, for example a blade for a turbine engine, a helicopter, or a propeller, can have the leading edge protected by such a reinforcement.

Abstract: An axial turbine includes a plurality of ribs provided in such a way as to be sandwiched between the diaphragm outer ring and the axial seal fin in the gap between the shroud and the diaphragm outer ring, the ribs being extended from the diaphragm outer ring toward the shroud in the radial direction of the rotor and in the direction of the rotation axis thereof, and a guide plate provided in such a way as to be present along the axial seal fin and a face of the diaphragm outer ring, opposed to the rotor, so as to be extended in the rotation radial direction of the rotor.

Abstract: An oil purge system for a mid turbine frame (MTF) of a gas turbine engine has an oil transfer tube surrounded by a heat shield tube. The oil transfer and heat shield tubes extend at their respective inner ends downwardly from an oil port of a bearing housing and terminate at their respective outer ends projecting outwardly from an annular wall of an outer case of the MTF. Oil leaked from the oil port is purged by pressurized air through an annular cavity formed between the oil transfer and heat shield tubes, and is discharged out of the MTF.

Abstract: Systems and devices for substantially fluidly isolating portions of a rotary machine are disclosed. In one embodiment, a seal assembly for a rotary machine includes: a complementary set of seal segments configured relative one another so as to form a substantially continuous body with butt gaps between the seal segments, the segments including: a head flange; and an axial neck connected to the head flange, wherein the axial neck extends radially inboard and includes an axial slot formed substantially there through; and at least one butt gap seal element, wherein the at least one butt gap seal element includes an axial flange and a radial flange, the axial flange disposed within the axial slots of adjacent seal segments; and the radial flange extending radially inboard from the axial slots to a proximity of the rotary machine substantially forming a barrier to axial flow through the butt gap.

Abstract: A flexible impeller pump includes improved flexible impeller geometry, an impeller shaft having protruding portions that produce a stronger and more durable connection between the impeller shaft and the flexible impeller, a smoother housing cam surface, and wear resistant surfaces that are disposed between end faces of the flexible impeller and adjacent housing end walls.

Abstract: A slinger shield structure is provided and includes a first annular disc, having a body, opposing faces defining an aperture extending through the body and through-holes extending through the body, which are arrayed around the aperture, a second annular disc having a body and opposing faces defining an aperture extending through the body, a hub for connection with the first and second annular discs at the respective apertures and radial vanes suspended between the first and second annular discs at a distance from the hub to define radial channels between adjacent radial vanes and drainage channels between the radial vanes and the hub.

Abstract: A pump having anti-airlock provisions. The pump is comprised of a volute comprised of a volute wall, and an impeller comprising back vanes on a side of the impeller that is proximate to the volute wall, with the back vanes having a length extending radially outwardly along the impeller. A bleed hole is formed in the volute wall in communication with the portion of the volute between the back vanes and the volute wall, and the exterior of the volute, such that the bleed hole is located midway along the length of the back vanes. When the pump is operating with air, liquid, or a combination of air and liquid in the volute, the bleed hole is under positive pressure with respect to the exterior of the volute. The bleed hole may be in communication with the exterior of the volute through a lateral tunnel formed in the pump.

Abstract: Systems and devices configured to reduce windage and mixing losses in a turbine by redirecting and/or aligning a direction of a leakage flow with the flowpath of the main flow of a turbine are disclosed. In one embodiment, a device includes: a base configured to connect to a diaphragm of a turbine; and a radial portion connected to the base and extending radially inboard from the base toward a rotor of the turbine, the radial portion oriented to adjust a direction of travel of a leakage flow of working fluid radially inboard at an angle complementary to a primary working fluid path of the turbine.

Abstract: A gas system has a first compressor stage for compressing a process gas. The first compressor stage includes an intake side and a pressure side. A seal gas is provided outside the first compressor stage in order to prevent process gas from issuing from leaks in the first compressor stage, having at least one second line for returning a gas mixture issuing from the gas system, this mixture including at least of process gas and seal gas. The at least one second line is configured for returning the issuing gas mixture to the intake side of the first compressor stage and/or to a location in the gas system upstream of the first compressor stage.

Abstract: A compressor of a turbine engine, the compressor including stator blades with shrouds, the shrouds being surrounded, at least in part, by rotating structure and forming a shroud cavity therebetween, the compressor including: a plurality of tangential flow inducers disposed within the shroud cavity; wherein each tangential flow inducer comprises a surface disposed on the rotating structure that is configured such that, when rotated, induces a tangential directional component to and/or increases the velocity of a flow of leakage exiting the shroud cavity.

Abstract: A method for reducing clearance flow in a channel between a bucket and an enclosure of a turbine. The method includes separating a single flow in the channel into a first flow and a second flow and directing the second flow radially inward toward the bucket so that the second flow rejoins with the first flow to increase total flow onto the bucket. A turbine includes an inner casing, a rotatable shaft positioned axially within the inner casing, a plurality of buckets connected to the shaft, a first tooth projecting radially inward from and connected to the inner casing, wherein the first tooth and at least one bucket form a first fluidic channel therebetween and a second tooth connected to and in parallel with the first tooth form a radial fluidic channel. The axial fluidic channel is in communication with the radial fluidic channel to form a second fluidic channel.

Abstract: A system for recirculating a hot gas flowing through a gas turbine generally includes a transition piece having a downstream surface, a stationary nozzle having a leading edge surface adjacent to the transition piece downstream surface, a gap defined between the transition piece downstream surface and the stationary nozzle leading edge surface, and a projection having an inner arcuate surface radially separated from an outer surface. The projection generally extends from the stationary nozzle leading edge surface towards the transition piece downstream surface and at least partially decreases the gap. A seal extends across the gap and may be in contact with the transition piece and the stationary nozzle leading edge surface. A recirculation zone may be at least partially defined between the projection inner arcuate surface, the stationary nozzle leading edge surface and the transition piece downstream surface.

Abstract: An oil purge system for a mid turbine frame (MTF) of a gas turbine engine has an oil transfer tube surrounded by a heat shield tube. The oil transfer and heat shield tubes extend at their respective inner ends downwardly from an oil port of a bearing housing and terminate at their respective outer ends projecting outwardly from an annular wall of an outer case of the MTF. Oil leaked from the oil port is purged by pressurized air through an annular cavity formed between the oil transfer and heat shield tubes, and is discharged out of the MTF.

Abstract: This compression device comprises first and second compressors mounted in parallel, a suction line intended to be connected to an outlet of an evaporator, first and second suction conduits arranged for putting the suction line respectively in communication with the admission orifices of the first and second compressors, and an oil level equalization conduit connecting the oil pans of the first and second compressors. The compression device further comprises an oil separator mounted on the suction line or on the second suction conduit, and an oil return conduit arranged for connecting an oil outflow orifice of the oil separator to the oil pan of the first compressor.

Abstract: A steam turbine includes a final turbine stage, a flow diffuser receiving a main flow from the final turbine stage, a diverging wall in the axial or radial flow diffuser that extends from a diffuser inlet to a diffuser exit, and a centerbody in the axial or radial flow diffuser. An opening is provided in the diverging wall and an opening is provided in the centerbody for fluidically actuating the main flow. The openings are located downstream from the diffuser inlet and upstream from a point where boundary layer separation would occur along the walls in a diffuser without the openings. A plurality of openings are provided in the diverging wall, and an end packing seal is positioned adjacent an end portion of the final turbine stage. An annular manifold collects fluid from leakage flow from the end packing seal and distributes the leakage flow to the openings.

Abstract: A feather seal is positioned in a mold and a shroud body is metal injection molded about a proximal end of the feather seal to provide a shroud segment with an integrated feather seal. A seal groove is provided in an opposite lateral side of the shroud body to receive the feather seal of a circumferentially adjacent shroud segment.

Abstract: A gas turbine engine has a nacelle, a plurality of pipes and a drains assembly, the drains assembly including a drains mast that extends through the nacelle and provides an outlet for the pipes. The engine is characterised in that drains assembly has a connection block defining internal passages and is arranged to connect between the pipes and the drains mast. The connection block also has lateral connections to the pipes enabling the nacelle to have a lower profile; thereby reducing aerodynamic drag.

Abstract: An axial compressor comprises a stator component and a rotor component, which cooperate to perform work on a fluid flow in a primary flow-passage defined by the stator and rotor components, the stator component and the rotor component further defining a secondary flow-passage which interconnects a higher pressure region and a lower pressure region of the primary flow-passage, the rotor component being provided with at least one secondary rotor element which, in normal operation of the machine, pumps a bypass flow of fluid through the secondary flow passage from the lower pressure region to the higher pressure region.

Abstract: With highly loaded rotors and stators problems can occur with secondary flows sweeping low momentum fluid across the blades reducing efficiency. By provision of collector slots to collect the secondary air and direct that air to a return slot in a rotor hub it is possible to provide impetus to the collected secondary flow to an outlet slot such that there is dispersal of the secondary flow and therefore reduce the effects upon the overall performance of a gas turbine engine incorporating the arrangement.

Abstract: A turbomachine exhaust case having an annular groove perforated with an orifice in which there is mounted a drain, which is formed by a tubular cylindrical body, for discharging liquids retained in this groove is disclosed. The drain includes a skirt, formed at one end of the cylindrical body, for fastening the drain by crimping in the orifice in the groove of the case.

Abstract: An axial flow gas turbine (35) has a rotor with alternating rows of air-cooled blades (40) and rotor heat shields, and a stator with alternating rows of air-cooled vanes (41) and stator heat shields (47) mounted on inner rings (46A reduction in cooling air mass flow and an improved cooling and effective thermal protection of critical parts within the turbine stages of the turbine is achieved by adapting the stator heat shields (47) and outer vane platforms (38) within a turbine stage (TS) to one another such that air (37) leaking through the joints between the outer vane platforms (38) and the adjacent stator heat shields (47) into the hot gas path (42) is directed onto the blade crown (32) of the blades (40).

Abstract: A system for ventilating a downstream cavity of an impellor of a centrifugal compressor in a turbomachine, this system including flow diversion system mounted fixedly in the downstream cavity of the impellor in order to divert the ventilation air taken from the outlet of the compressor and cause it to circulate radially from the inside to the outside along the downstream face of the impellor.

Abstract: A self-monitoring adjustment system is provided for evaluating and effecting adjustment of the leakage restricting mechanism between the rotating and non-rotating elements of a rotodynamic pump to restrict leakage and to establish desired gap dimensions between the rotating and non-rotating elements of the pump. The adjustment system is structured to be self-monitoring for determination of when an adjustment of the leakage restricting mechanism is warranted by the conditions of the pump, and is structured with adjusting mechanisms that are self-adjusting responsive to the monitored conditions of the pump, though manual adjustment is also enabled.

Abstract: A pump pulley is supported on a pump body via a bearing interposed between the outer peripheral surface of the pump body and the pump pulley so that the pump pulley can freely rotate relative to the pump body. A pump shaft extends along the rotation axis of the pump pulley into a pump chamber formed by a pump base and the pump body, and one end of the pump shaft is fitted to the pump pulley and the other end is fitted to an impeller located within the pump chamber. A body side seal member and a shaft side seal member that form a mechanical seal to maintain the leak tightness of the pump chamber are in opposite to and contact each other in the direction of extension of the pump shaft to form a seal surface, and the plane that includes the load support center of the bearing and the plane that includes the seal surface of the mechanical seal are substantially coincidental.

Abstract: A water pump includes an impeller provided on an end of a rotational shaft supported on a body through a bearing, a mechanical seal provided between the impeller and the bearing, a draining hole guiding a coolant leaked from the impeller side to a reservoir provided at a bottom of the body via the mechanical seal, a vapor outlet provided above the reservoir for establishing communication between the reservoir and the atmosphere, and the draining hole opening to the reservoir at a lower level than the vapor outlet. An axis of the reservoir is offset from a vertical plane which passes through an axis of the rotational shaft.

Abstract: A turbofan engine includes a fan variable area nozzle having a multiple of vents through a fan nacelle and a sleeve system movable relative to the vents by an actuator system. The fan variable area nozzle changes the effective area of the fan nozzle exit area to permit efficient operation at predefined pressure ratios. The vents include a grid structure which directs and smoothes the airflow therethrough as well as to reduce noise generation.

Abstract: A turbocharger having a sliding piston for regulating exhaust gas flow into the turbine wheel includes a set of first vanes mounted on a fixed first wall of the turbine nozzle and projecting axially toward an opposite second wall of the nozzle, and/or a set of second vanes mounted on the end of the piston and projecting in an opposite axial direction toward the first wall of the nozzle. For the/each set of vanes, there are leakage dams formed on the wall that is adjacent the vane tips when the piston is closed. The leakage dams are closely adjacent the vane tips and discourage exhaust gas from leaking in a generally radial direction past the vane tips as the piston just begins to open from its fully closed position.

Abstract: A seal gas recovery method including introducing a first seal gas stream to a first mechanically coupled booster/expander assembly, where the first booster/expander assembly includes a first booster, a first expander, a first shaft that mechanically couples the first booster and the first expander, and a first seal on the first shaft. The method further includes removing at least a portion of a first recoverable gas stream from the first seal, where the first recoverable gas stream includes at least a portion of a first process leak gas stream and at least a portion of a first seal gas vent stream. The method further includes introducing a second seal gas stream to a second expander assembly, where the expander assembly includes a second expander, a second shaft, and a second seal on the second shaft.

Abstract: A deflector arrangement is provided for improving turbine efficiency by imparting added tangential velocity to a leakage flow entering the working fluid flowpath of a gas turbine engine.

Abstract: An early warning system for equipment or processes which can be permanently or temporarily damaged by contaminants coming from air moving equipment, such as a compressor, positioned upstream of air flowing through the equipment. The present invention provides a seal-leak detection arrangement that, when incorporated into air moving equipment, monitors the air passing through the air moving equipment for the presence of contaminants such as lubricant oil, which could damage the equipment downstream. At least one sensor is positioned downstream of a contaminant retaining seal within the air moving equipment. The seal-leak detection arrangement is particular useful when incorporated into systems upstream of a fuel cell.

Abstract: Drainage is enhanced in an orifice formed inside the internal passage of a pneumatic line by providing the orifice with first and second portions. The first portion defines a diameter that is smaller than the diameter of the internal passage, and the second portion defines a progressively increasing diameter. Generally, a first end of the second portion has a diameter that is equal to the first portion diameter, and a second end of the second portion has a diameter that is equal to the internal passage diameter.

Abstract: A vapor tube structure in a gas turbine comprises first connecting tubes fixed to a casing, second connecting tubes fixed to a blade ring, a recovery ring and a cooling recovery ring, a bellows tube of the flexible structure, springs, a tube and a piston rings provided between the first connecting tubes and the second connecting tubes. As a result, it is possible to absorb and follow the thermal expansion/contraction difference and prevent leaking of vapor.

Abstract: The object of the invention is to provide a method of operating a simply constructed centrifugal compressor equipped, in the region of the rear wall of the compressor impeller, with no sealing elements in the separating gap between the compressor impeller and the compressor casing, which method increases the service life of the centrifugal compressor. An appliance for carrying out the method is also to be made available. In accordance with the invention, this is achieved by introducing a cooling medium into the separating gap downstream of the leakage flow of the working medium and by finally removing this again after the cooling process has taken place. For this purpose, at least one supply duct for a gaseous cooling medium, the duct penetrating the compressor casing, opening into the separating gap in the region of the rear wall of the compressor impeller and directed onto the rear wall, and at least one removal duct for the cooling medium are arranged in the compressor casing.