Abstract: The present disclosure is directed to a gas turbine engine defining a radial direction, a longitudinal direction, and a circumferential direction, an upstream end and a downstream end along the longitudinal direction, and an axial centerline extended along the longitudinal direction. The gas turbine engine includes a fan assembly including a plurality of fan blades rotatably coupled to a fan rotor in which the fan blades define a maximum fan diameter and a fan pressure ratio. The gas turbine engine further includes a low pressure (LP) turbine defining a core flowpath therethrough generally along the longitudinal direction. The core flowpath defines a maximum outer flowpath diameter relative to the axial centerline. The gas turbine engine defines a fan to turbine diameter ratio of the maximum fan diameter to the maximum outer flowpath diameter. The fan to turbine diameter ratio over the fan pressure ratio is approximately 0.90 or greater.

Abstract: A turbine housing has: a first inner member; a second inner member contacting with the first inner member; a turbine scroll flow path enclosed and defined by the first inner member and the second inner member; a first casting housing covering the first inner member at a side opposite to the second inner member; a second casting housing covering the second inner member at a side opposite to the first inner member; an aperture formed in one or both of the first casting housing and the second casting housing and including an opening that opens to an outside; a tube member arranged in the aperture and defining an inlet flow path connected to the turbine scroll flow path; and an inner opening defined by the first inner member and the second inner member and overlapping with one end of the tube member.

Abstract: The invention in at least one embodiment includes a system for treating water having an intake module, a vortex module, a disk-pack module, and a motor module. In at least one embodiment, a water system includes vortex housing having an interior wall defining a vortex chamber in fluid communication with the expansion chamber of said disk-pack turbine and inlets into the vortex chamber, and the vortex chamber having an upper section with a bowl or modified concave hyperbolic shape into which fluid is received from said inlets and a lower section with a conical or funnel shape with a steep vertical angle of change that opens into expansion chamber. In at least one further embodiment, the disk-pack module includes a disk-pack turbine having a plurality of disks having at least one waveform present on at least one of the disks.

Abstract: A cooling system for a plurality of conductive cables in a gas turbine engine includes a cooling source and an electric motor disposed in a tail cone. The cooling source may comprise an electric fan or an oil pump. The cooling source may be configured for active cooling of the plurality of conductive cables. The electric fan may be in fluid communication with ambient air during operation of the gas turbine engine.

Abstract: A centrifugal pump includes an impeller that is rotatable about a rotational axis. The impeller includes impeller vanes disposed between a base plate and a shroud. The shroud outer surface includes recessed pump out vanes. For each pump out vane, the ratio R1 of the vane outer diameter to the shroud outer diameter is in a range of 0.8 to 0.98, the number of vanes N is in a range of 5 to 9, the ratio R2 of the width of the pump out vane to the shroud outer diameter is in a range of 0.02 to 0.04 and the pump out vane has a square leading edge profile with a square or chamfered trailing edge profile.

Abstract: A plastic pump comprises a complete body having an inner body made of a fluorine resin and an outer body made of a plastic material by molding the plastic material in a first mold after fixing a pre-manufactured inner body to the first mold, an impeller made of a fluorine resin material by means of injection molding, and an impeller cover made of a plastic material by molding the plastic material in a second mold to protect the impeller, and a fluid transporting path is lined with the fluorine resin of the inner body.

Abstract: A containment system for a gas turbine engine includes an outer containment ring having a first projection that extends radially inward and an inner containment ring having at least a second projection that extends radially outward toward the outer containment ring. The second projection is offset and spaced apart from the first projection to define a chamber in a first state. The containment system includes a lattice defined within the chamber that spans the chamber, and the lattice is integrally formed with each of the outer containment ring and the inner containment ring. A density of the lattice varies in at least one of an axial direction and a radial direction. The second projection is configured to interlock with the first projection in a second state.

Abstract: A gas turbine engine includes a fan case assembly adapted to extend around blades of a fan rotor included in the gas turbine engine. The fan case assembly includes an annular case that extends around an axis, an acoustic panel coupled to the annular case and configured to dampen vibrations and a bolting arrangement that couples the acoustic panel to the annular case.

Abstract: The invention relates to an annular assembly for a dual-flow turbomachine having a longitudinal axis (A) and comprising a casing (12) with an annular shell (14), one face of which supports a piece of annular equipment, a plurality of means of attachment (18) for attaching the equipment to the annular shell (14) being distributed around the longitudinal axis (A) and allowing the equipment (16) a degree of freedom in the tangential direction relative to the annular shell (14), characterised in that each means of attachment (18) comprises a rail (20) integral with the annular equipment (16) and arranged radially between a first radially internal plate (22) and a second, radially external plate (24) and capable of sliding in the tangential direction between the first plate (22) and the second plate (24), and in that a removable support element (56) is securely connected to the annular shell and to the first plate (22) and second plate (24).

Abstract: A duct for a ducted-rotor aircraft may include an internal structure and an aerodynamic exterior skin that is adhesively bonded to the internal structure. The skin may include a leading-edge portion disposed at an inlet of the duct and an inner portion disposed along an interior of the duct. The inner portion of the skin may be bonded to the internal structure with a first bondline of adhesive and the leading-edge portion of the skin may be bonded to the inner portion of the skin with a second bondline of adhesive. One or both of the first and second bondlines of adhesive may be of non-uniform thickness to take up tolerance stackups between the inner portion of the skin, the leading-edge portion of the skin, and the internal structure.

Abstract: A horizontal decanter centrifuge for enhanced recovery of drilling mud from drilling mud solids. Oilfield decanters will always suffer some drilling mud losses because they can only achieve a certain effectiveness with respect to solids dryness. The embodiment describes a process to mitigate the financial burden of drilling mud losses by adding a less expensive sacrificial fluid to take the place of drilling mud in the solids phase. A process and apparatus for drilling mud displacement is described including flowing the drilling mud into a horizontal decanter centrifuge, wherein the stresses imposed within the decanter act to force a sacrificial fluid to displace the drilling mud. The embodiment also describes a process wherein vapours or mist are prevented from escaping and becoming airborne into the external atmosphere.

Abstract: The present disclosure is directed to a gas turbine engine defining a radial direction, a longitudinal direction, and a circumferential direction, an upstream end and a downstream end along the longitudinal direction, and an axial centerline extended along the longitudinal direction. The gas turbine engine includes a fan assembly including a plurality of fan blades rotatably coupled to a fan rotor in which the fan blades define a maximum fan diameter and a fan pressure ratio. The gas turbine engine further includes a low pressure (LP) turbine defining a core flowpath therethrough generally along the longitudinal direction. The core flowpath defines a maximum outer flowpath diameter relative to the axial centerline. The gas turbine engine defines a fan to turbine diameter ratio of the maximum fan diameter to the maximum outer flowpath diameter. The fan to turbine diameter ratio over the fan pressure ratio is approximately 0.90 or greater.

Abstract: A diffuser subassembly for use in downhole submersible pump assemblies includes a bearing set for supporting a drive shaft of the pump assemblies. The bearing set includes a sleeve for supporting the drive shaft in upward, downward and radial directions. The sleeve includes a central flange captured axially between a pair of bushings fixed to a diffuser body. Axial loads from the drive shaft may be transferred through the central flange of the sleeve to one or the other of the bushings into the diffuser body to accommodate upward and downward thrust forces. The bushings may be keyed to discourage rotational motion with respect to the diffuser body.

Abstract: The present disclosure describes a system and method for varying pressure from a pressure generator without pressure generator motor speed variations. The system comprises a pressure generator housing, a centrifugal compressor housed within the housing, and at least one impeller blade. The centrifugal compressor is configured to generate a pressurized flow of gas. The pressure generator system includes a pressure adjustment body (e.g., a plate) that is movably attached to and/or within the housing, and an actuator configured to displace the pressure adjustment body with respect to the housing, such that displacement of the pressure adjustment body is configured to regulate pressure of the generated gas flow by varying a gap between the impeller blade and a surface of the pressure adjustment body.

Abstract: A compressor housing for a turbocharger, which is composed of a scroll piece, a shroud piece, and an outer-circumferential annular piece. The scroll piece includes a through part constituting a discharge port, a first intermediate wall surface extended from an intake-side wall surface of a scroll chamber and smoothly connected with the discharge port, and a scroll outer-circumferential part. The outer-circumferential annular piece includes an outer-circumferential annular press-fit part press fitted into the scroll outer-circumferential part, and a protruding part bent from an outer-circumference-side wall surface of the scroll chamber. The protruding part is inserted into the through part to form an inner wall surface of an intermediate part that communicates the discharge port with the scroll chamber. Then, the compressor housing is fixed to a center housing that is made of iron with high rigidity through joining parts provided at the scroll piece.

Abstract: A housing for a turbocharger that makes it possible to prevent sticking of deposit and attain satisfactory assembling workability and easy moldability by die casting. The housing dividably includes a scroll piece and a shroud piece, including an annular refrigerant flow path defined by a first flow-path formation part of the scroll piece and a second flow-path formation part of the shroud piece. The first and second flow path formation parts are fitted with each other at inner and outer circumferential seal parts for sealing the refrigerant flow path on inner and outer circumferential sides thereof. The inner circumferential seal part is formed by press-fitting a first press-fitting portion of the shroud piece into a first press-fitted portion of the scroll piece. The outer circumferential seal part is formed by press-fitting a second press-fitting portion of the shroud piece into a second press-fitted portion of the scroll piece.

Abstract: A technique facilitates operation of a pump, such as a submersible pump in an electric submersible pumping system. The pump has a sequential diffuser and impeller which are operationally engaged via a thrust device. In some embodiments, the diffuser and impeller also are operationally engaged via a front seal. A bypass channel is used to route a flow of fluid from a tip region of the impeller to an inlet region of the impeller without passing through the thrust device during operation of the pump.

Abstract: The present invention provides a casing for a radial compressor including: a scroll portion which is disposed on an outer circumferential side of an impeller and an intake portion and extends in a circumferential direction, has a discharge port opening in a circumferential direction and a scroll flow path through which the gas from the impeller flows toward the discharge port, and includes a resin material having a gradually increasing external shape dimension; and a plurality of ribs which connect an outer circumferential surface of the intake portion and an outer surface of the scroll portion. The plurality of ribs are provided at intervals in the circumferential direction, an installation interval gradually decreases toward the discharge port in the circumferential direction, and a length dimension in a radial direction on the outer surface of the scroll portion gradually decreases.

Abstract: Multilayer sheet metal housing assemblies suitable for use in turbocharger systems and related fabrication methods are provided. One exemplary compressor housing includes a first volute structure including an impeller opening, an inlet structure including an inlet opening, a second volute structure joined to the first volute structure about its periphery and including an interior opening radially circumscribing at least a first portion of the inlet structure, and a core volute structure circumscribing at least a second portion of the inlet structure, wherein the core volute structure is joined to the second volute structure about the interior opening and joined to the inlet structure.

Abstract: A turbocharger, with a turbine that includes a turbine housing, turbine inflow housing, a rotor, and a compressor, which has a compressor housing and a rotor coupled to the turbine rotor via a shaft. A bearing housing is arranged between and coupled to the turbine and the compressor housings. The turbine inflow housing has a radially inner, outer and middle walls. The inner wall delimits an exhaust gas flow duct, and a cooling channel between the outer and middle walls. The bearing housing, extends, seen in the axial direction as far as into the region of the inner wall of the turbine inflow housing. A cooling water channel in the bearing housing surrounds the inner wall of the turbine inflow housing in the axial region and the bearing housing extends as far as into the region of the radially inner wall of the turbine inflow housing, radially on the outside.

Abstract: A containment for a continuous flow machine, in particular for a gas turbine, is disclosed. The containment has at least one annular housing with at least one axial section of lesser radial wall thickness and at least one axial section adjacent thereto of greater wall thickness, where the housing is designed and constructed so that the section of greater wall thickness is at a distance in the axial direction of the continuous flow machine from a trailing edge of a guide vane lying downstream in the direction of flow of the continuous flow machine, and extends downstream in the direction of flow of the continuous flow machine over a leading edge of the next downstream guide vane.

Abstract: A turbocharger includes a compressor housing including a scroll chamber, and a seal plate assembled to the compressor housing. The compressor housing and the seal plate define an intake passage. The seal plate includes a plate-side connecting portion in contact with the compressor housing. The radius of curvature of a wall surface of the scroll chamber of the compressor housing, in a section including a compressor rotational axis, is increased in a direction toward an outlet located on the downstream side of the scroll chamber in an intake air flow direction. The plate-side connecting portion protrudes in a direction along the compressor rotational axis. The radius of curvature of an inner surface of the seal plate continuous with the scroll chamber of the intake passage, in the section including the compressor rotational axis, is increased in the direction toward the outlet of the scroll chamber.

Abstract: A turbocharger includes a turbine housing adapted to be arranged in the middle of an engine exhaust passage, a bearing housing coupled to the turbine housing, a turbine wheel located inside the turbine housing, a rotary shaft that is connected to the turbine wheel and is rotationally supported by the bearing housing, and a cooling water passage that is provided inside the turbine housing. The cooling water passage is located around the turbine wheel. The turbine housing includes a first connection portion joined to the bearing housing, a second connection portion joined to a part of the engine exhaust passage located on a downstream side of the turbine housing, and a heat insulating portion located between the cooling water passage and at least one of the first connection portion and the second connection portion.

Abstract: A torque converter is provided including a turbine with a turbine hub. A cover plate is fixed to the turbine hub. A damper assembly including a damper flange with an axially extending sleeve portion having a splined or toothed inner surface that is adapted to engage a transmission input shaft is provided. A spring is located between the cover plate and the damper flange for transferring torque from the turbine hub to the transmission input shaft via the damper flange. The turbine hub includes axially protruding tabs that contact an outer surface of the sleeve portion to center the turbine hub on the sleeve portion. The turbine hub also includes a radially inwardly extending portion that at least partially overlaps an axial end of the sleeve portion.

Abstract: A compressor housing is provided with a shroud member, which surrounds a compressor impeller, and a sealing member. The shroud member has a facing surface that is located at a position on a radially outside of the compressor impeller on an inner circumferential surface of the shroud member. The sealing member is provided on the facing surface. The sealing member is formed from a cylindrical material that has free-cutting property to the compressor impeller. The sealing member is press-fitted into the facing surface of the shroud member.

Abstract: Embodiments of the invention provide a hydraulic isolator to split a volute of a pump into two compartments. The hydraulic isolator is positioned within the volute and includes an inlet positioned around a volute inlet channel of the pump, and an outlet positioned adjacent to an outlet channel of the pump. The hydraulic isolator also includes a toroidal portion to at least partially surround an impeller of the pump.

Abstract: Composite article includes a generally cylindrical body having an internal grid structure interleaved with casing layers formed of reinforcing fibers disposed in a resin matrix. The composite article may be utilized in a fan case containment system for aircraft engine applications. Methods for fabricating the composite article are also provided.

Abstract: A coupling pin for use in a pump housing, the pump housing including an outer casing and an inner pump liner, the coupling pin being suitable for locating the liner and casing relative to one another, the coupling pin including a shank and a head at one end of the shank. The head includes a cammed surface thereon which is adapted to co-operate with a follower on the liner, and a locating section on a remote or terminal end of the head which is adapted to be positioned against a seat in the outer casing when fitted. The arrangement is such that rotation of the coupling pin causes the follower to track along the cammed surface so as to cause relative movement between the outer casing and the inner pump liner.

Abstract: An air turbine starter is provided and includes a rotor including turbine blades, which is rotatable about a rotational axis, a housing including a portion thereof radially surrounding the turbine blades to define a pathway along which fluids flow to interact with the turbine blades and a containment ring affixed to an exterior of the portion of the housing radially surrounding the turbine blades.

Abstract: The present invention relates to an exhaust-gas turbocharger (1) having a turbine housing (2) and having a manifold section (3) which is connected to the turbine housing (2), wherein the turbine housing (2) and the manifold section (3) are formed as a single-piece cast part.

Abstract: A pump casing for a centrifugal pump, which comprises an inlet opening, a discharge outlet, and a transition surface extending between an inner peripheral surface of the main pumping chamber and an inner peripheral surface of the discharge outlet, the transition surface arranged for separating an in use exit flow of material in the discharge outlet from an in use recirculation flow of material in the main pumping chamber. The transition surface has a cutwater having a profiled section which comprises a protrusion which extends irregularly from an otherwise generally rounded arched or U-shaped transition surface and is configured such that, in use, the velocity and/or turbulence resulting from the in use flow of the material being pumped in the main pumping chamber is reduced.

Abstract: In a turbine housing for an exhaust gas turbocharger of an internal combustion engine with at least one spiral channel, which can be coupled into an exhaust gas flow of an exhaust tract of the internal combustion engine, and a receiving space for a turbine wheel which is disposed downstream of the at least one spiral channel and can be acted upon by the exhaust gas of the internal combustion engine passing through the at least one spiral channel of the turbine housing, there is at least one partial housing including the at least one spiral channel, and a housing module which is fastened to the partial housing and has a vane structure disposed upstream of the receiving space which also includes an attachment surface for a bearing section of the exhaust gas turbocharger. The invention also resides in an exhaust gas turbocharger with such a turbine housing as well as to a method for producing such a turbine housing.

Abstract: A turbine nozzle or a compressor diffuser includes sectors made of CMC material, each having an inner platform, an outer platform, and airfoils. An abradable material support ring is made up of sectors, each presenting upstream and downstream attachment tabs. Each inner platform presents on the inside an upstream hook and a downstream hook, and the abradable material support ring is supported by the nozzle or the diffuser by mutually engaging without fastening together firstly the end portions of the upstream attachment tabs and the upstream hooks and secondly the end portions of the downstream attachment tabs and the downstream hooks.

Abstract: A floor standing pedestal fan for creating an air current includes a base housing an impeller and a motor for rotating the impeller to create an air flow, an air outlet, and a telescopic duct for conveying the air flow to the air outlet.

Abstract: A thermal module includes a fan device having a fan and a fan housing for covering the fan. A vent is disposed on the fan housing. The thermal module further includes an airflow guiding device installed on the fan housing in a protrudable manner and disposed on a side of the vent for guiding airflow into the vent.

Abstract: A turbojet engine nacelle includes an air intake structure having a longitudinal outer panel incorporating an air intake lip, a middle structure to which the air intake structure is attached, at least one inner panel including an acoustic shroud, rails guiding the outer panel able to allow a rectilinear movement of the outer panel, and a reinforcing member to react the mechanical loads of the guide rails. In particular, the reinforcing member reacts the loads of the guide rails beyond a predetermined deformation of the guide rails.

Abstract: A guide vane assembly for a turbomachine, comprising a guide vane and a liner: the guide vane comprising an aerofoil portion having a radially outer platform, wherein one of the outer platform and the liner has a hook element, the hook element comprising an opening and a circumferentially extending channel, and the other one of the outer platform and the liner comprises a retaining element having a head portion, wherein in an operational orientation the head portion located within the channel and is too wide to be withdrawn through the opening of the hook element.

Abstract: A pump casing for a centrifugal pump, which comprises an inlet opening, a discharge outlet, and a transition surface extending between an inner peripheral surface of the main pumping chamber and an inner peripheral surface of the discharge outlet, the transition surface arranged for separating an in use exit flow of material in the discharge outlet from an in use recirculation flow of material in the main pumping chamber. The transition surface has a cutwater having a profiled section which comprises a protrusion which extends irregularly from an otherwise generally rounded arched or U-shaped transition surface and is configured such that, in use, the velocity and/or turbulence resulting from the in use flow of the material being pumped in the main pumping chamber is reduced.

Abstract: A liquid ring pump is provided that includes an annular housing having an inner surface forming a housing cavity. The annular housing is filled with an operating fluid during operation of the pump. The operating fluid forms an eccentric liquid ring in the annular housing during operation of the pump. A rotor is disposed in the housing cavity and includes a plurality of rotor blades. A shaft extends into the annular housing into the housing cavity. The plurality of rotor blades extend radially outward from the shaft toward the inner surface of the annular housing. A liner formed from a corrosion resistant material is disposed substantially flush with at least a portion of the annular housing inner surface opposite a plurality of rotor blade ends.

Abstract: A process of fabricating a shield, a process of preparing a component, and an erosion shield are disclosed. The process of fabricating the shield includes forming a near-net shape shield. The near-net shape shield includes a nickel-based layer and an erosion-resistant alloy layer. The nickel-based layer is configured to facilitate secure attachment of the near-net shaped to a component. The process of preparing the component includes securing a near-net shape shield to a substrate of a component.

Abstract: A compressor housing resistant to a titanium fire (burning titanium). A mixed housing is constructed, in which a structure holding stator blades includes a single-cast part made from titanium or titanium alloy, and at least one element forming a shield made from refractory alloy(s), and which is incombustible in presence of burning titanium, where each shield is secured to the single-cast part by fasteners. The fasteners are positioned with each shield so as to define jointly an inner wall demarcating an outer contour of the compressor airstream.

Abstract: A liner for an interior surface of an engine casing, comprises a number of liner panels disposed radially outwardly of a rotatable component of the engine, such as a fan blade, and the panels are mounted on the interior surface of the casing, wherein each panel is individually adjustable, such that the clearance between the panel and the rotatable component of the engine may be varied individually for each panel.

Abstract: A liner for a gas turbine engine includes a liner defining an inner surface exposed to exhaust gases and a duct spaced radially outward of the liner. A plurality of hanger assemblies is disposed within the radial space between the liner and the duct for supporting the liner relative to the duct. Each of the hanger assemblies includes a cable having a first end attached to the duct and a second end attached to the liner.

Abstract: A fan with a sound deadening box has in its body a double inlet centrifugal fan and an inlet-port sound absorber formed between the fan and a body air inlet. The fan further includes a casing-inlet-port-side air passage and triangular prism shaped first inlet-port-sound-absorber air passage. With this structure, the fan has a low pressure loss, a low input, high static pressure, and a low level of airflow collision noise.

Abstract: A centrifugal pump is provided having a volute casing having a discharge conduit, an impeller provided in the volute casing, and a suction sideliner enclosing the impeller in the volute casing, the suction sideliner being at least partially covered with sintered tungsten carbide tiles. In one embodiment, the impellor has a central hub, a plurality of vanes spacedly attached to the hub, and at least one side plate attached to the vanes, whereby each vane is individually wear protected prior to attaching each vane to the hub.

Abstract: A guide system for translating components of an aircraft engine nacelle includes a track assembly and a slider assembly. The track assembly includes a track guide member having a track channel. The slider assembly translatably engages the track assembly. The slider assembly includes a slider body configured to be received within the track channel. The slider assembly further includes a slider arm member pivotably coupled to the slider body with a hinge joint disposed within the track channel. The slider arm member extends from the body portion and outwardly of the track assembly. Associated apparatuses are also provided.

Abstract: A compressor shroud for containing fragments of a compressor impeller and a turbine wheel within a gas turbine engine. The compressor shroud includes a compressor containment section, a turbine containment section, and a containment continuity section. The containment continuity section connects the compressor containment section and the turbine containment section to form a one-piece part.

Abstract: The present invention provides a non-axisymmetric flow member disposed in a duct of a gas turbine engine. The flow member narrows the area aft of a vane to reduce the cross sectional area through which a wake from the vane traverses.

Abstract: A floor standing pedestal fan for creating an air current includes a base housing an impeller and a motor for rotating the impeller to create an air flow, an air outlet, and a telescopic duct for conveying the air flow to the air outlet.

Abstract: A hydraulic vane pump includes a pump body defining an interior pumping chamber, an inlet port, and at least one discharge port. A cam ring is disposed within the interior pumping chamber and defines a continuous peripheral cam surface. A rotor is mounted for axial rotation within the interior pumping chamber. A plurality of vanes are mounted for radial movement within slots formed in the rotor. The pump includes axially opposed first and second wear disks disposed within the interior pumping chamber. The first wear disk is a floating wear disk and has an outer periphery which is positioned radially inward of the cam surface and is adapted and configured to slide axially with respect to the cam surface. The second wear disk is positioned adjacent to a second end surface of the rotor.