Abstract: A drying fan has a shroud with a shape selected to improve fan efficiency by designated fluid dynamics of air flow through the fan.

Abstract: A method of component forming according to an exemplary aspect of the present disclosure includes, among other things, positioning a metal powder in a mold cavity, melting the metal powder within the mold cavity, and cooling the melted metal powder to form a component.

Abstract: Trying to save nature and people from pollution and help regenerating nature since using it, power is inexpensive. Also the current from these devices can be used to extract hydrogen and oxygen (by electrolysis) from water and the extracted hydrogen is a valuable motor-fuel.

Abstract: Disclosed are wind turbines comprising a turbine shroud and optionally an ejector shroud. The shrouds are segmented, or in other words have longitudinal spaces between segments. Such wind turbines have reduced drag load, particularly those loads due to off-axis wind forces.

Abstract: A compressor housing for an air cycle machine includes an inlet and an outlet. The compressor housing additionally includes a plurality of ribs that extend generally perpendicularly from a surface of the compressor housing. Formed within an internal region of the compressor housing is a bearing support structure. The bearing support structure receives and limits the axial movement of a bearing, seal and at least one O-ring.

Abstract: A compressor is provided and may include a shell having an inner surface and an outer surface and a bearing housing disposed within the shell and having an engagement surface opposing the inner surface. The engagement surface may include a first channel formed substantially perpendicular to a longitudinal axis of the shell and a second channel formed substantially parallel to the longitudinal axis of the shell and in communication with the first channel. The first channel and the second channel may receive a deformed portion of the shell therein to fix a position of the bearing housing relative to the shell.

Abstract: According to one aspect of the invention, a turbine assembly includes a rotor wheel and a circumferential slot formed in the rotor wheel, the circumferential slot including a uniform cross-section shape for a circumference of the rotor wheel. The assembly also includes a first ring member positioned in the circumferential slot, the first ring member being configured to prevent radial movement of a dovetail attachment when positioned in the circumferential slot, wherein the dovetail attachment is part of a turbine blade.

Abstract: A turbine vibration reduction system includes a nozzle, a bucket in operable communication with the nozzle, and a structure having at least one opening configured to inject fluid into flow traveling past the nozzle and the bucket to disrupt formation of a vortex.

Abstract: A fan assembly includes an annular nozzle and a system for creating a primary air flow. The nozzle includes an outer wall and an inner wall surrounded by the outer wall, the inner wall defining a bore having a bore axis. The nozzle also includes an interior passage located between the inner and outer walls, and extending about the bore axis for receiving an air flow, and an air outlet located at or towards the front of the nozzle for emitting the air flow. The nozzle is configured to emit the air flow through the air outlet in a direction extending away from the bore axis.

Abstract: A nacelle for an aircraft bypass turbofan engine includes an upstream section via which an airflow enters, a middle section surrounding the fan of the turbofan and a downstream section having an inner structure and an outer structure delimiting a flow duct in which the air flows. The outer structure includes one cowling movably mounted on the inner fixed structure. The nacelle also has a top to accept a pylon for attaching a wing of the aircraft. The nacelle further includes one first panel mounted on the inner structure on one side of the nacelle and one second panel mounted on the other side of the nacelle. The first panel undergoes a physical interference with a part of the wing. The second panel increases the air removed from this other side of the nacelle during thrust reversal.

Abstract: A fan assembly includes a nozzle and a device for creating an air flow through the nozzle. The nozzle includes an interior passage, a mouth for receiving the air flow from the interior passage, and a Coanda surface located adjacent the mouth and over which the mouth is arranged to direct the air flow. The mouth and the Coanda surface extend about an axis. The Coanda surface comprises a diffuser portion, the angle subtended between the axis and the diffuser portion of the Coanda surface varying about the axis.

Abstract: The Stockly Swimming Pool Pump Motor Cover protects both sides; top, and front of the swimming pool pump motor from sun, rain, sprinklers and morning dew. It has an optional base, which secures the top in one place and does not restrict ventilation to the swimming pool pump motor. No tools are required.

Abstract: In a cylinder head (104) of a compressor (100), suction chamber (119) arranged on an extension line of an axis of driving shaft (106), a cylindrically arranged discharge chamber (120) surrounding suction chamber (119), and communication passage (104b) extending from radially outside of discharge chamber (120) to suction chamber (119) bridging over discharge chamber (120) are provided. In the communication passage (104b), valve (250) regulating an opening of the communication passage (104b) depending on a flow rate of refrigerant is arranged. Valve (250) includes passage forming member (254) cylindrically made of heat insulating material and internally inserted into communication passage (104b), valve housing (253) locked at the downstream of member (254), valve body (251) received in valve housing (253), and compression coil spring (252) urging valve body (251) toward a valve closing direction. Member (254) integrally includes part (254b) regulating movement of valve body (251) in a valve closing direction.

Abstract: A method produces a casting, in particular a housing of a turbocharger. Wherein at least one mold part for forming the casting has a respective parting plane which is arranged at a predetermined angle with respect to the longitudinal axis of the casting, and wherein at least one core element is provided.

Abstract: Method forming a composite structure (9) comprising a main body and a flange. The composite structure is manufactured by laying-up a preform (7) on a mould (6). The preform (7) does not have the first and second bends and comprises a first part which corresponds to the main body of the composite structure and a second part which corresponds to the flange of the composite structure. The second part of the (preform (7) has a proximal portion which corresponds to the wall portion of the flange and a distal portion which corresponds to the lip portion of the flange. The preform (7) comprises a plurality of plies and uni-directional ply material extends from the first part of the preform (7) to the distal portion of the second part of the preform (7).

Abstract: The present invention is concerned with an improved hydro/aero turbine with a split venturi effect shroud that accelerates the fluid stream through it and boosts the power output, providing a location for energy transfer around its perimeter either by mechanical or electrical means or may have a magnetic ring generator/bearing and other distinctive features that simplify manufacture, assembly, transport, installation and service with the latest technology in direct drive permanent magnet generator.

Abstract: Various methods and systems are provided for an axial turbine including a containment shroud. In one example, an axial turbine for use in an engine system comprises a turbine disc/blisk and a shroud housing the turbine disc/blisk, the shroud including a first region, a second region, and a third region. A thickness of the second region is dependent on a length between the first region and the third region, and the third region has a burst strength that under a burst condition retains one or more fragments of the turbine disc/blisk.

Abstract: An air turbine handpiece having: a head portion with built-in free turbine blade, a neck portion installed consecutively with the head portion and grasped by an operator, a grip portion installed consecutively with the neck portion, an air supply duct for driving the turbine blade, and an exhaust duct for exhausting the air. The exhaust duct is provided with a reflux duct, open at one end to the exhaust duct, and open at the other end to the turbine room as the exhaust exit, a value in which an aperture at the reflux exit of the reflux duct is divided by an aperture in the air supply port of the air supply duct, becomes one or less, and the reflux exit of the reflux duct is opened to the turbine room near the air supply port between the air supply port and the exhaust exit.

Abstract: A nacelle for an engine has outer and inner cowl doors that are independently rotatable about offset hinge lines. A connection device is provided for selectively connecting the outer and inner cowl doors so as to cause them to open simultaneously. The inner cowl door is arranged to rotate by a greater angle than the outer cowl door so as to improve access to the engine for maintenance purposes.

Abstract: Embodiments of the present disclosure are directed towards an electrical equipment system including an electrical equipment component, a thermal management system configured to direct air over features of the electrical equipment component, a rectangular fan housing of the thermal management system, and a fan disposed within the fan housing, wherein an axis of rotation of the fan is offset relative to a geometric center point of the rectangular fan housing.

Abstract: A compressor including: a substantially tubular casing; a substantially cylindrical lid that is provided inside an inner periphery of the casing so as to close off both ends of the casing; a space that is enclosed by the lid and an inner circumferential surface of the casing so as to accommodate a blade; and a seal member that is provided so as to extend in a circumferential direction on the space side of an outer circumferential surface of the lid. A recessed portion, extending inward in the radial direction from the outer circumferential surface of the lid, is provided on the lid at a position between the seal member and the end surface at the space side of the lid.

Abstract: The present application provides a steam turbine side support system for use with a steam turbine having a rotor. The steam turbine side support system may include a shell for the steam turbine, a number of side support arms extending from the shell in a perpendicular configuration with respect to the rotor, and a foundation in communication with the side support arms.

Abstract: The structural case has an annular body having a central axis and including a plurality of boss sections circumferentially interspaced from one another around the axis by a plurality of arcuate panel sections, each panel section having: two parallel arcuate structural flange members being axially interspaced from one another; a sheet metal wall extending between and interconnecting the two flange members; and at least one rib having an edge welded to the sheet-metal wall.

Abstract: In this method of preventing deformation in a turbine casing of a gas turbine, in a turbine casing 10 there is arranged a buffer tank 30. In this buffer tank 30 there are formed a stagnation part agitation air opening 52 which ejects part of the air from an air compressor 21 as stagnation part agitation air Ga2 toward a stagnation part 19 within the turbine casing, and an overall agitation air opening 51 which ejects overall agitation air Ga1 for agitating gas held in an upper space within the turbine casing. In the buffer tank 30 there is provided a partition wall 36 with through holes 53 formed therein serving to resist air from the air compressor 21, in order to make the ejection speed of the overall agitation air lower than the ejection speed of the stagnation part agitation air.

Abstract: Surface dryers having uniform exit velocity profiles, and associated systems and methods are disclosed. Surface dryers in accordance with certain embodiments include a housing, a gas driver positioned in the housing, an inlet aperture formed in the housing and positioned upstream of the gas driver, and a nozzle carried by the housing and positioned downstream of the gas driver. The nozzle can have an indentation forming a convergent portion positioned to accelerate the flow of air and a divergent portion positioned to decelerate the flow of air.

Abstract: The invention relates to a cover plate (2) for a screw-type centrifugal wheel pump (1), wherein the cover plate (2) has a front side (2h) and a rear side (2i), and wherein the front side (2h) comprises a surface part (2k) which runs in a preferably frustoconical manner and the profile of which is designed to be matched to the rear side of a screw-type centrifugal wheel (25), wherein the surface part (2k) has, in the centre thereof, a central opening (2g), wherein the central opening (2g) runs in the direction of an axis (A), and wherein the cover plate (2) has at least one aperture (2a) which is arranged in the region of the surface part (2k) and spaced apart from the central opening (2g), and wherein the aperture (2a) forms a fluid-conducting connection between the front side (2h) and the rear side (2i) of the cover plate (2).

Abstract: A compressor casing to allow easy assemblage and disassembling, a compressor provided with the same, and a method of assembling the compressor are provided. The compressor casing includes a substantially tubular casing, a plurality of sealing surfaces provided on an inner circumferential surface of the casing along an axial direction thereof, a sealing means provided for each sealing surface, a substantially cylindrical bundle for accommodating a blade inside and for being assembled to the casing so as to contact with the sealing surfaces, and a roller provided on an outer circumferential surface of the bundle, for rolling on the inner circumferential surface of the casing when the bundle is assembled to or removed from the casing. The sealing surfaces are connected with one another tapered surfaces.

Abstract: A bladeless fan includes a wind supply device and a first wind guide device disposed on the wind supply device and having a loop-shaped space. Airflow is created by the wind supply device, and enters the loop-shaped space. When the airflow exits the loop-shaped space through an air outlet, surrounding air is forced to flow through a flow guide channel in the first wind guide device to combine with the air flowing from the air outlet, so as to increase the amount and speed of the airflow.

Abstract: An exemplary centrifugal fan includes a casing defining an air outlet, and an impeller in the casing. An air channel is defined in the casing between a sidewall of the casing and outermost free ends of the impeller. The sidewall includes a first curved section adjoining a second curved section. The first curved section is located at a more upstream portion of the sidewall than the second curved section along a rotation direction of the impeller. The first curved section extends along a part of an Archimedes spiral or a part of a logarithmic spiral. The second curved section is located farther away from the impeller than an imaginary extension line of the first curved section along the Archimedes spiral or the logarithmic spiral. An air guide plate is formed in the casing and extends from the air outlet to an inner region of the air channel.

Abstract: A housing for a turbomachine includes a peripheral wall delimiting an annular space and a fluid conveying system for redirecting a partial flow of a main flow, which has an axial channel, a front annular channel and a rear annular channel in fluid connection with the axial channel and having a front annular space opening and a rear annular space opening. The fluid conveying system has a front valve device and a rear valve device controllable independently of the front valve device, for opening and closing the annular space openings, and an outlet opening for tapping the partial flow from the fluid conveying system. In the closed state of the rear annular space opening, the partial flow is directable through the rear annular channel and, in the closed state of the front annular space opening, the partial flow is directable through the front annular channel.

Abstract: A pump and pump section, where the pump section has a centre line and where the pump section comprises at least one pump step, the pump step has a centre line and each pump step comprises a motor and one or more pump stages, and where the pump comprises an outer casing enclosing one or more inner casings, the outer casing forms an enclosure round the pump section and has a larger diameter then the inner casings, and the inner casings form an enclosure round the at least one pump step, and where the centre line of the pump section is displaced relative to the centre line of the pump steps, thereby forming an annulus between the outer casing and the inner casing.

Abstract: Disclosed are an apparatus and a method for recovering energy after carbon dioxide capture. The apparatus includes an energy recovery unit at a discharge part of a carbon dioxide capturing apparatus through which captured carbon dioxide is discharged. The energy recovery unit reduces a discharge pressure of the carbon dioxide to a pressure level suitable for a fixation or conversion treatment, and simultaneously generates and recovers energy generated during the pressure reduction.

Abstract: An auxiliary member for assembly/disassembly includes a fixing portion which is fixed to one half casing of a lower half casing and an upper half casing, and a jack receiving portion which extends from the fixing portion and faces an outer surface of the other half casing. When an interval between both end portions in the radial direction of the upper half casing is widened due to heat deformation, the fixing portion of the auxiliary member for assembly/disassembly is fixed to the lower half casing, a jack is disposed between the jack receiving portion of the auxiliary member for assembly/disassembly and the outer surface of the upper half casing, and the interval between both end portions of the jack is widened.

Abstract: The invention relates to a nacelle (1) for an aircraft bypass turbojet engine comprising, in downstream cross section, an inner fixed structure (8) intended to surround part of the bypass turbojet engine and an outer structure (9) at least partially surrounding the inner fixed structure (8) so as to delimit an annular flow path (10), the outer structure (9) comprising at least one inner flap (101) positioned facing the annular flow path (10), an outer flap (103) not in contact with the annular flow path (10) at least partially surmounting each inner flap (101) in aerodynamic continuity with the rest of the outer structure (9), and an intermediate flap (105) positioned between each inner flap (101) and each outer flap (103), said intermediate flap (105) being capable of translational movement so as to increase or decrease the cross section of the annular flow path (10), and each inner flap (101) and each outer flap (103) being capable of rotational movement so as to remain in permanent contact with the interme

Abstract: An oil pump for a machine is disclosed. The oil pump may have a housing. The oil pump may further have a spacer fixedly connected to the housing. The spacer may divide the housing into a main chamber and an auxiliary chamber. The spacer may also have an opening. The oil pump may further have a drive shaft rotatably disposed within the housing generally orthogonal to the spacer. The drive shaft may pass through the opening. In addition, the oil pump may have a collar fixedly connected to the drive shaft. The collar may be positioned within the opening generally orthogonal to the spacer. The collar may have a diameter of about 2.5 to 3.0 inches and the opening may have a diameter such that an annular gap area between the collar and the spacer is about 0.25 to 0.29 square inches.

Abstract: A seal for a turbine casing is provided. The turbine casing includes a plurality of sections joined at flanges provided on each section. Each flange includes a bore and a counterbore. The seal comprises a compression sleeve seal having a length that is greater than a counterbore-to-counterbore length of two flanges; a fastener configured to extend through the compression sleeve seal; and a nut threadable on each end of the fastener. The compression sleeve seal is compressible between each flange and each nut to create a first seal and is radially extensible to create a second seal against each bore.

Abstract: An aircraft nacelle comprising a lip extended by an inner conduit forming an air intake, a front frame delimiting with said lip an annular channel wherein hot air circulates, as well as a panel for acoustic treatment comprising, from outside inwardly, an acoustic resistive layer, at least one honeycomb structure, and a reflective layer, as well as ducts for channeling hot air with each one inlet communicating with the annular channel and one outlet communicating with the inner conduit, wherein the panel for acoustic treatment comprises, upstream from the ducts, an annular channel which extends over at least a portion of the nacelle circumference, at least one conduit providing communication between said annular channel and the upstream annular channel, and a plurality of ducts that open into said downstream annular channel, the panel for acoustic treatment being connected to the front frame in regard to the annular channel.

Abstract: The invention relates to a vacuum pump having at least one molecular pump stage, in particular a Holweck stage, which includes a rotor member which forms the pump-active surface of the molecular pump stage and having at least one side channel pump stage which is arranged downstream of the molecular pump stage and which includes a plurality of rotor elements, wherein the rotor elements of the side channel pump stage are supported by the rotor member of the molecular pump stage. The invention further relates to a vacuum pump having at least one molecular pump stage, in particular a Holweck stage, and having at least one side channel pump stage which is arranged downstream of the molecular pump stage and which includes a plurality of rotor elements, wherein the side channel pump stage is arranged between a pump inlet and the molecular pump stage.

Abstract: A cover hub for a torque converter includes a radial wall arranged for axial alignment with a cover of the torque converter, a first circumferential surface including an opening for receiving a seal, and a second circumferential surface disposed radially inside of the first circumferential surface and arranged for sealing to a transmission input shaft. The hub has a first fluid passage exiting the hub at a first axial side of the opening and a second fluid passage, circumferentially offset from the first fluid passage and exiting the hub on a second axial side of the opening, opposite the first axial side, and a first circumferential protrusion for sealing the hub to the cover.

Abstract: A low-pressure turbine and a steam power plant with a low-pressure turbine (1) is suggested that is connected to an additional condensing system (25), thus allowing to maintain the electric output at a high level, even if the main condensing system (17) has a reduced capacity due to cooling water restrictions.

Abstract: An aircraft propulsion system has an engine assembly having an axis of rotation, a fan assembly operatively connected to the engine assembly and comprising a plurality of fan blades arranged circumferentially around the axis of rotation and a monolithic nacelle assembly which circumferentially encloses the fan assembly. The propulsion system has a ratio of fan assembly outer diameter to nacelle assembly outer diameter of at least 0.87. As a result, the propulsion system provides for a significantly larger fan assembly outer diameter for a given nacelle assembly outer diameter than a conventional prior art turbofan engine, thereby increasing the specific power output or the bypass ratio of the propulsion system, which will result in improved propulsive efficiency without an increase in nacelle drag.

Abstract: In a method of mounting cooling air fans (2) in an electronic equipment unit (3) having a unit front (4) a unit rear (5) and unit sides (6, 7) and wherein the cooling air fan/fans produce cooling air flow (AF) directed from the unit front to the unit rear, cooling air fans are attached to a flexible cooling air fan carrier (8) that is introduced through a slot (3A) in the unit front and is advanced along a non-linear path (9). The cooling air fan carrier is advanced along a first, generally straight path section (9A) from the unit front and approximately to the unit rear, further through a second, bent path section (9B) and through a third, generally straight path section (9C) extending along the unit rear, thereby positioning the cooling air fans along the unit rear.

Abstract: A variable fan nozzle assembly includes a cowl member mounted on a slider track. The slider track may be articulated relative to a support member to slightly modify the position of the cowl member to vary the fan nozzle exit area. At least one 4-bar linkage may be utilized to allow articulation of the slider track responsive to an actuator. A method for varying a fan nozzle exit area includes mounting a first slider track in articulatable relationship with a support member; mounting a first cowl member in slidable relationship with a first slider track such that a fan nozzle is at least partially defined by a surface of the first cowl member; varying the operational position of the first cowl member by articulating the first slider track without sliding the first cowl member with respect to the first slider track to vary the fan nozzle exit area.

Abstract: The invention provides a fan casing for a gas turbine engine, the casing having a substantially cylindrical portion that terminates at one end in an annular flange made of composite material. The flange includes at least one setback in a fraction of its thickness and at least one bolt for fastening pieces of equipment passing right through the flange in the axial direction, the bolt for fastening pieces of equipment having a head that presents a flat that is to bear flat against a rim of the setback, and a shank forming a stud for fastening pieces of equipment on the casing.

Abstract: A nozzle for a fan assembly includes an air inlet, a plurality of air outlets, and an annular casing having an annular inner wall defining a bore through which air from outside the nozzle is drawn by air emitted from the air outlets and an outer wall extending about the inner wall. The annular casing includes an air passage for conveying air to the air outlets. The air passage has an inlet section located between the inner wall and the outer wall and extending about the bore of the nozzle, and a plurality of outlet sections each extending across the bore for conveying air to a respective air outlet. To achieve an even air pressure at each end of each of the outlet sections, the inlet section of the air passage is arranged to convey air to each end of each of the outlet sections.

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 gas turbine engine includes a seal assembly that is supported by a member at a joint. The seal assembly includes a seal support having a radial flange secured to the joint. A first bend adjoins the radial flange to a first leg, which is oriented generally in an axial direction. A second bend adjoins the first leg to a second leg, which is conical in shape. A seal is supported by the second leg.

Abstract: A turbine engine includes a compressor section, a combustor section in fluid communication with the compressor section, a high pressure turbine in fluid communication with the combustor, a low pressure turbine in fluid communication with the high pressure turbine, and a mid turbine frame located axially between the high pressure turbine and the low pressure turbine. The mid turbine frame includes an outer frame case, an inner frame case, and a plurality of hollow spokes that distribute loads from the inner frame case to the outer frame case. The spokes are hollow to allow cooling airflow to be supplied through the spokes to the inner frame case.

Abstract: A turbine engine includes a compressor section, a combustor section in fluid communication with the compressor section, a high pressure turbine in fluid communication with the combustor, a low pressure turbine in fluid communication with the high pressure turbine, and a mid turbine frame located axially between the high pressure turbine and the low pressure turbine. The mid turbine frame includes an outer frame case, an inner frame case, and a plurality of hollow spokes that distribute loads from the inner frame case to the outer frame case. The spokes are hollow to allow cooling airflow to be supplied through the spokes to the inner frame case.

Abstract: A turbofan engine has a fan having a circumferential array of fan blades. A fan case encircles the fan. There is at least one compressor section, a combustor, and at least one turbine section. The fan case comprises a composite structural member and a metallic member encircled by the composite structural member. The metallic member is mounted to the composite structural member to permit differential thermal expansion proximate the blades.