Abstract: An axial turbine includes an upstream turbine stage that includes: a cover disposed at a distal end of an upstream bucket and opposed to an inner wall of an upstream diaphragm outer ring across a gap; and a downstream diaphragm outer ring that is disposed downstream of the upstream turbine stage and that has an inner peripheral-side end wall shaped into a flare. The inner peripheral-side end wall of the downstream diaphragm outer ring has a flare angle formed to be greater than a slant angle of an inner peripheral-side wall of the cover. In the axial turbine, the inner peripheral-side end wall of the downstream diaphragm outer ring is formed to have a meridional shape that has at least one inflection point between the upstream turbine stage and a downstream turbine stage and such that a tangent at the inflection point with respect to a steam flow direction has a positive gradient.

Abstract: A vehicle air-conditioning apparatus that includes a blower unit including a scroll casing including a first wall having an intake port, a second wall opposing the first wall, and a peripheral wall, and an impeller. The apparatus further includes a motor of the impeller, a blow-out flow channel, and a motor cooling air introduction chamber. The motor cooling air introduction chamber is in communication with the blow-out flow channel via an air intake port opening in the peripheral wall of a tongue portion facing the blow-out flow channel at a position more closer to the first wall side than an inner wall surface of the second wall. At least one airflow regulating rib facing the peripheral wall provided with the air intake port is provided, and the airflow regulating rib projects from the inner wall surface of the second wall and having a top portion in the blow-out flow channel.

Abstract: A turbine housing for a turbocharger is provided. The turbine housing includes an exterior housing and an interior housing as well as a bearing flange. The exterior housing is connected to the bearing flange. The interior housing includes a flange socket on which the bearing flange is positioned. A fastening ring is inserted inside in the bearing flange and connected to the flange socket, with the bearing flange being fixed in the axial direction (AR) by the fastening ring.

Abstract: Fan assemblies, and in particular fan wheels and stator assemblies for fan assemblies, are disclosed. In one embodiment, the fan wheel includes a wheel back having an outer surface forming one of a curved dome-shape and a truncated cone-shape. The fan wheel may also include a plurality of fan blades radially spaced about and mounted to the outer surface of the wheel back. In one embodiment, each of the fan blades is formed from a segment of an airfoil-shaped aluminum extrusion defining at least one internal cavity. The fan blade first ends can be provided with a compound cut profile with at least one curved cut such that the first end of the blade is mounted flush to the wheel back outer surface. The stator assembly can also be provided with a plurality of stator blades formed from airfoil-shaped aluminum extrusion segments and provided with compound cut profiles.

Abstract: An axial flow water turbine according to an embodiment includes a discharge ring and a runner vane. When seen in the runner meridional cross section, a straight line that passes a border between a cylindrical surface and a spherical surface of the discharge ring and that is perpendicular to a water turbine rotation axis is denoted as A. A crossing point between the straight line A and the water turbine rotation axis is denoted as B. A straight line inclined by an angle ? of 10 degrees or less is denoted as C. A cross point between the straight line C and the external peripheral end surface of the runner vane is denoted as D. In this case, the external peripheral end of the forward edge of the runner vane is located on the crossing point D.

Abstract: A diffuser includes a ring-shaped parallel part, and a ring-shaped throttling part formed continuously to the inside of the parallel part in a radial direction. A wall surface of the throttling part includes a flow passage area minimum portion which makes minimal a flow passage area of the diffuser, and a ring-shaped protruding portion located closer to the outlet side of the compressor wheel than the flow passage area minimum portion, and protruding toward the flow passage of the diffuser.

Abstract: A blower housing, especially for a side channel blower, includes a first housing part (22) with a motor mounting space (25) for a blower motor (14). A rotor shaft (16), rotatable about a shaft axis of rotation (A), of a blower motor (14) is or can preferably be rotatably mounted at the first housing part (22). A housing cover (44) seals the motor mounting space (25). The housing cover (44) has a cover meshing opening (46). A second housing part (50), with a cover meshing projection (52), is positioned or can be positioned in a meshing manner in the cover meshing opening (46). The cover meshing opening (46) is sealed with the cover meshing projection (52) being positioned in a meshing manner in the cover meshing opening (46).

Abstract: A system and method is provided for an integrated aircraft turbofan engine outer flowpath ducting and front frame that minimizes assembly interfaces and reduces overall aircraft engine weight. The system and method provide an integrated turbofan engine outer flowpath ducting and front frame system that decouples the fairing/aerodynamic duties from the struts/weight bearing duties thereby enabling efficient distribution of mechanical load.

Abstract: The invention generally relates to two-bladed turbine nacelles and platforms integrated into the nacelle structure. In certain embodiments, the invention provides an assembly encompassing a nacelle that houses a two-bladed turbine and a hoisting platform. The hoisting platform is integrated into the structure of the nacelle so as to form the roof of the nacelle.

Abstract: A prime mover that is powered by the energy of a fluid is provided. Such a prime mover may include a first fairing, a second fairing spaced apart from the first fairing to define a gap therebetween and a blade assembly mounted on a shaft that extends between the first and second fairings. The first and second fairings each have a curved peripheral edge for directing a fluid into the gap. When the fluid flows into the gap it contacts the blade assembly to thereby rotate the blade assembly about an axis that is defined by the shaft. The prime mover may be mounted on a cell phone tower and used to generate electricity for powering components of the tower and/or for providing electricity to the power grid.

Abstract: Various aspects of the technology provide for reducing noise and vibration in a pressure exchanger for high pressure fluid handling equipment such as a desalination system, by disposing grooves between a seal surface and a port. The groove reduces a hammer effect in moving high pressure fluid to a low pressure port and moving low pressure fluid to a high pressure port. Reduction in the hammer effect, in addition to reducing noise, reduces vibration that can cause deterioration of high pressure fluid handling equipment.

Abstract: An assembly of a first element, such as a fan shroud, with a second element, such as an air guide, realized by assembling an elongate thin lip belonging to the second element in an elongate narrow slit formed by the three sides of an elongate planar plate attached in parallel to a planar wall of the first element. The elongate thin lip includes a concave edge and includes, at either side thereof, extended tips, and the elongate slit includes, at either side thereof, areas in which the thickness of the slit is increased, configured to engage with the extended tips of the lip so that the insertion of the lip into the slit begins by inserting the tips into the areas and then continues with gradual insertion of the rest of the concave edge of the lip as the lip is being advanced.

Abstract: A method for controlling a two-bladed pitchable swept-blade wind turbine in extreme wind conditions is described, wherein when extreme conditions are detected or forecast for the wind turbine, the wind turbine blades are pitched such that they will passively align in a substantially horizontal arrangement. The blades can be yawed such that a tip of one of the wind turbine blades points into the wind direction, resulting in a reduced surface area of the blades exposed to the extreme wind forces. This reduced surface area provides for a reduction in the extreme loads which may be experienced by the wind turbine in such extreme wind conditions.

Abstract: An airfoil array is disclosed. The airfoil array may include an endwall, and a plurality of airfoils radially projecting from the endwall. Each airfoil may have a first side and an opposite second side extending axially in chord between a leading edge and a trailing edge. The airfoil array may further include a convex profiled region extending from the endwall adjacent the first side of at least one of said plurality of airfoils and near the leading edge of the at least one of said plurality of airfoils. The airfoil array may further include a concave profiled region in the endwall adjacent the first side of said at least one of said plurality of airfoils and aft of the convex profiled region.

Abstract: Turbocharger provided with a bypass valve device comprising a valve element having a shaft movably connected to a valve element support, with a spindle between the valve element support and an adjusting lever extending transversely to the spindle, and an adjusting lever actuating element pivotably connected to the adjusting lever; an annular spring element is provided in at least one of a first position between the valve element and the valve element support and a second position between the adjusting lever and the adjusting lever actuating element, the spring element comprising at least one annular spring steel disc with a bead being configured and dimensioned so as to minimize play between the valve element and its support or between the adjusting lever and its actuating element.

Abstract: A turbine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. At least some of the platforms have a scalloped flow surface including a bulge adjoining the pressure side and a bowl adjoining the suction side, aft of the leading edge, of the respective airfoils. The bulge is configured having a maximum height located within its respective flow passage, and wherein the bulge decreases in height in a forward and aft direction and decreases in height laterally toward the pressure side of the airfoil and toward the bowl adjoining the suction side of a next adjacent airfoil.

Abstract: A compressor component having an airfoil with a profile in accordance with Table 1 is disclosed. The compressor component, such as a compressor vane, has a decreased surface area over a portion of the airfoil chord length. The decreased surface area compressor vane operates in conjunction with a compressor blade having an increased surface area.

Abstract: Various fluid turbine systems and methods are described. The turbine can be a vertical axis wind turbine configured to generate power from wind energy. The turbine system can have a blade assembly. The blade assembly can have a plurality of blades rotatable about an axis. The turbine system can have a concentrator positionable upwind and in front of a return side of the blade assembly. The concentrator can define a convex surface facing the wind. The turbine system can also have a variable concentrator positionable upwind of a push side of the blade assembly. The variable concentrator can be adjustable between a first position and a second position, the variable concentrator being capable of deflecting more wind toward the turbine in the first position than in the second position.

Abstract: Various embodiments include steam turbine static nozzles having transitional interfaces. In one embodiment a steam turbine static nozzle blade includes: an airfoil; an inner sidewall integral with a first side of the airfoil; and an outer sidewall integral with a second side of the airfoil; the inner sidewall and the outer sidewall each including: a first side having one of: an arcuate concave surface extending substantially an entire length of the sidewall, or an arcuate convex surface extending substantially the entire length of the sidewall; and a second side opposing the first side and having an angled interface extending substantially the entire length of the sidewall.

Abstract: An array of flow-directing elements for a compressor of a gas turbine including at least one first flow-directing element and at least one second flow-directing element different from the first flow-directing element; the flow-directing elements each having a leading edge facing the gas turbine inlet, a trailing edge, a pressure side connecting them and located ahead in the direction of rotation, a suction side located opposite thereof, as well as successive chords along a stacking axis; the flow-directing elements each extending between an airfoil root proximate to the rotor and an airfoil tip remote from the rotor. The trailing edge of the first flow-directing element is, at least in a portion thereof, axially offset from the trailing edge of the second flow-directing element in a direction toward the leading edge at least in a half proximate to the airfoil tip.

Abstract: A fan includes a frame and an impeller. The frame defines a hole in a middle of the frame. An inner wall of the frame bounding the hole defines a circumferential groove and forms a circumferential protrusion adjoining the groove. The impeller is received in the hole of the frame. When the impeller is rotated, airflow through the hole is pressurized by the groove and the protrusion, and concentrates when the airflow is blown out of the hole.

Abstract: A fan salt-fog-resistant structure and a fan frame thereof. The fan salt-fog-resistant structure includes a base seat having a bearing cup and at least one flow guide body. Multiple connection bodies outward extend from the base seat. The flow guide body is disposed at a junction between the base seat and the connection bodies. The fan frame includes a main body having a first open side and a second open side and a flow passage defined therebetween. One end of the connection body is connected with the second open side. When airflow entraining moisture and salt fog flows through the junction between the base seat and the connection bodies, the flow guide body serves to guide the airflow and prevent the airflow from forming eddy, whereby the salt fog entrained by the airflow will not crystallize to form sediments at the junction between the base seat and the connection bodies.

Abstract: Various embodiments of the invention include turbine nozzles and systems employing such nozzles. Various particular embodiments include a turbine nozzle having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and at least one endwall connected with the airfoil along the suction side, pressure side, trailing edge and the leading edge, the at least one endwall including a non-axisymmetric contour proximate a junction between the endwall and the leading edge of the airfoil.

Abstract: A nozzle segment for a gas turbine engine has a turbine airfoil bound on a first side by an arcuate inner endwall having an inner platform and on a second side by an arcuate outer endwall having an outer platform. The airfoil extends outwardly from the inner platform toward the outer platform. The airfoil body includes opposed pressure and suction sidewalls extending between a leading edge and a trailing edge of the airfoil body. The airfoil body includes a first trailing edge fillet blending into the inner platform at a trailing edge of the airfoil body.

Abstract: A turbine blade can include a root configured to connect to a turbine and supporting an airfoil configured to extend into a flowpath of the turbine. The airfoil can include a tip disposed substantially opposite the root and a first tip fillet disposed proximate the tip that can extend substantially perpendicular to a local flow direction at points along a surface of the turbine blade over the extremity of the first tip fillet. The tip fillet can enhance performance of the turbine by beneficially altering flow through a stage in which the blade is included.

Abstract: A fan housing of a ram air fan assembly is provided including a flange having at least one tab. The at least one tab includes a first portion extending generally perpendicularly from the flange and a second portion extending generally parallel to the flange. A notch is formed by an inclined surface and a curved surface at an intersection between the first portion and the second portion. The second portion is elongated and extends about 0.020 inches beyond a front surface of the first portion.

Abstract: An inlet connection piece for an axial compressor, particularly for a turbocompressor, includes an inlet housing (1) in which is arranged a bearing housing (2) with a bearing (3), particularly a radial and/or axial bearing, for a rotor. The bearing housing (2) is connected to the inlet housing (1) by an inlet strut (4) which is connected to the inlet housing in a front cross section. The center of the bearing (3) is arranged axially in the flow direction of a fluid to be compressed behind the area center of the front cross section by at least 0.1-times, particularly at least 0.15-times, particularly at least 0.2-times, particularly at least 0.25-times, the chord length of the front cross section. In addition or alternatively, a fluid passage (5, 6) is formed in the inlet strut (4), and at least portions of this fluid passage (5, 6) form an acute angle with a normal plane relative to the longitudinal axis of the inlet connection piece.

Abstract: The present application thus provides a gas turbine engine. The gas turbine engine may include a turbine and a diffuser positioned downstream of the turbine. The turbine may include a number of last stage buckets, a number of last stage nozzles, and a gauging ratio of the last stage nozzles of about 0.95 or more.

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: A turbocharger for an internal combustion engine includes a shaft, a first turbine wheel, a compressor wheel, and a second turbine wheel. The shaft includes a first end and a second end and is supported for rotation about an axis. The first turbine wheel is mounted on the shaft proximate to the first end and configured to be rotated about the axis by post-combustion gasses emitted by the engine. The compressor wheel is mounted on the shaft between the first and second ends and configured to pressurize an airflow being received from the ambient for delivery to the engine. The second turbine wheel is mounted on the shaft proximate to the second end and configured to be rotated about the axis by a pressurized fluid. An internal combustion engine employing such a turbocharger is also disclosed.

Abstract: A turbocharger is disclosed for use with an engine. The turbocharger may include a housing at least partially defining a compressor shroud and a turbine shroud. The turbocharger may also include a compressor wheel disposed within the compressor shroud, a shaft connected to the compressor wheel, and a turbine wheel disposed within the turbine shroud and connected to an end of the shaft opposite the compressor wheel. The turbine wheel may have a generally annular hub, and a plurality of blades disposed radially around the hub. Each of the plurality of blades may include an airfoil having a hub face connected to the hub, a shroud face opposite the hub face and oriented towards the turbine shroud, a trailing edge, and a leading edge opposite the trailing edge. The leading edge may be substantially straight or substantially concave in a meridional plane. An angle between a base of the hub and the leading edge may be about 25-55 degrees.

Abstract: A stator for eccentric screw pumps with a stator casing for an elastomer body for accommodating a rotor, the elastomer body being provided with at least one collar, wherein the collar is disposed in a recess between the stator casing and a connection body, wherein the fixing of the elastomer body in the stator casing is to be improved. The stator casing includes for this purpose open cavities, recesses and/or elevations at least at one side on the end face.

Abstract: A number of fan assemblies are shown. Configurations are shown that include one or more diffusers. Diffuser locations and specific diffuser configurations are described that improve one or more fan assembly characteristics, including, but not limited to fan efficiency.

Abstract: The invention presented is an outer race for a stator assembly which includes keys that extend radially outward from the outer circumferential edge. The keys include transverse projecting splines. The splines are configured to cut grooves into the body of a stator to form a press fit connection between the outer race and the stator. The connection reduces or eliminates a loosening of the stator-outer race connection when fluid temperatures increase as well as reducing the effects of lash by reducing or eliminating gaps in the stator-outer race connection.

Abstract: An airfoil includes a radially inner edge extending in a radial direction of the airfoil to a radially outer edge. Also included is a leading edge extending in an axial direction of the airfoil to a trailing edge. Further included is a trailing edge geometry comprising at least one wave segment having simultaneous curvature in at least two directions.

Abstract: The invention relates to a horizontal agitator for producing a flow in a clarifier, a submersible motor and a propeller drivingly connected thereto forming an assembly unit, wherein a receiving portion for removably attaching the assembly unit is provided and can be supported on the bottom of the clarifier, and wherein a guide for guiding the assembly unit along a substantially vertical movement path between a surfacing position above a maximum nominal sewage level defined for the clarifier and the receiving portion is provided. In order to improve the efficiency of the horizontal agitator and to reduce complexity of manufacture, the guide is formed by at least one first cable extending between the surfacing position and the receiving portion.

Abstract: An air inlet deflector for a structure having an air inlet. The deflector may be retractable within the structure, may be integrally formed with the structure, and may prevent the structure from ingesting foreign matter, such as birds. The deflector may include a series of ribs, spokes, or vanes that may vary in width and/or thickness from fore to aft, and/or may be curvilinear in one or more planes of view, and/or may serve double duty as inlet vanes for redirecting inlet air.

Abstract: A turbine vane for a gas turbine engine may include a composite airfoil structure. The composite airfoil structure may have an opening. The turbine vane may include a spar. The spar may have a body, which may be disposed within the opening. A standoff structure may be disposed within the opening. In some non-limiting embodiments, a cooling air gap may be defined between the body and an internal surface of the composite airfoil structure.

Abstract: A thermal barrier coating that includes a YAG-based ceramic is prepared by a solution precursor plasma spray method that includes injecting a precursor solution into a thermal jet, evaporating solvent from the precursor solution droplets, and pyrolyzing the resulting solid to form a YAG-based ceramic that is melted and deposited on a substrate. The thermal barrier coating can include through-coating-thickness cracks that improve the strain tolerance of the coating.

Abstract: Air blower incorporates in housing thereof: suction port; a high pressure air generating portion; a blowout port; first air passage; introduction air suction port; introduction air mixing portion; introduction air blowout port; and second air passage.

Abstract: A gas turbine vane containment cap is attached to an inboard surface of the vane inner shroud by penetrating flat weld filler, formed in a root gap between the cap and inner shroud. A semi-circular bead weld filler is formed outboard the penetrating weld filler closer to the vane exterior. Vane containment caps so welded are more resistant to in-service cracking along weldments.

Abstract: An axial flow compressor blade unit including a platform section and an airfoil section, which are used as arranged on a circumference about an axis of the compressor. The platform section includes an inner diametric surface segment inwardly of the circumference, an outer diametric surface segment outwardly of the circumference, two annular side surface segments extending in a circumferential direction, two axially side surface segments extending in the axial direction, and a coupling portion formed in each of the annular side surface segments so as to extend in the circumferential direction and being of a shape projecting or recessed in the axial direction. The airfoil section is formed to erect from the platform section so as to extend in a radial direction. The platform section and the airfoil section are formed integrally with each other while having a powdered metal sintered structure.

Abstract: A low vibration fan including a housing, a driving member and a fan wheel is provided. The housing has an outer frame and a base, wherein the outer frame has two openings, a positioning rim, and a guiding channel linking the two openings, wherein the base couples with the positioning rim, and wherein a radial buffer gap is formed between an outer periphery of the base and an inner periphery of the positioning rim. The driving member is mounted on the base. The fan wheel couples with the driving member rotatably. Accordingly, the radial buffer gap can largely reduce the vibration transmitted from the base to the outer frame.

Abstract: The propensity for turbocharger turbine divider wall to crack in the turbine housing is minimized by matching the mass of the divider wall more closely to the transient heat transfer between said divider wall and the exhaust gas flowing past it. This is achieved by providing said divider wall having a cross-sectional shape defined substantially by a Log2 curve.

Abstract: One aspect of the present disclosure includes a turbine vane assembly comprising a vane made from ceramic matrix composite material having an outer wall extending between a leading edge and a trailing edge and between a first end and an opposing second end; an endwall made at least partially from a ceramic matrix composite material configured to engage the first end of the vane; and a retaining region including corresponding bi-cast grooves formed adjacent the first end of the vane and a receiving aperture formed in the endwall; wherein a bond is formed in the retaining region to join the vane and endwall together.

Abstract: A gas turbine stage including a rotor blade array having a plurality of rotor blades and an adjacent stator vane array having a plurality of stator vanes which have leading edges facing the rotor blade array. In a first radial position of a rear face of the rotor blade array, a minimum axial gap is formed between this rear face and an opposite first contact region a stator vane leading edges, and in a second radial position of the rear face different from the first position, the minimum axial gap is formed between the rear face and an opposite second contact region. Between the first and second contact regions, this stator vane leading edge has an axial offset of no more than 0.6% of a radial height of the stator vane leading edge.

Abstract: The invention relates to a guide vane arrangement and a method for mounting a guide vane. The guide vane arrangement has at least one guide vane having a radially inner journal, which engages in a borehole of a bushing. The bushing is disposed in a borehole of an inner ring segment. The journal is connected to the bushing in a rotation-resistant manner and a slide mounting is provided between the bushing and the inner ring borehole. For mounting the guide vane in an inner ring segment, the journal of the guide vane is introduced into the borehole of the bushing. Further, the journal is fastened to the bushing in a rotation-resistant manner, and the bushing is slide-mounted with the inner ring segment. The slide mounting is conducted prior to or simultaneously with or after the fastening of the journal to the bushing in a rotation-resistant manner.

Abstract: A gas turbine engine strut is disclosed as having a will forebody positioned upstream of a point of maximum thickness and an aft body positioned downstream of the point of maximum thickness. The aft body includes a discontinuity in a curvature distribution which provides for a “subsonic shock.” The discontinuity in curvature distribution can include in inflection point that marks a transition from a curvature associated with an upstream portion of the aft body to a second curvature associated with a downstream portion of the aft body. In some forms, the aft body can additionally include boundary layer aspiration. The gas turbine engine strut can be symmetrical about a centerline.

Abstract: A turbomachine having at least one circulation structure is disclosed. The circulation structure has an annular space with baffle elements surrounding a main flow path and is open to the main flow path. A housing of the turbomachine to receive the circulation structure is divided in an axial plane into a front housing region and a rear housing region and the circulation structure is divided into a front structure region and a rear structure region in the axial plane of separation. A circulation structure divided into two parts in the axial direction and a method for the same is also disclosed.

Abstract: In a motor, a connection portion between a lead wire and an aluminum wire is provided distant from a terminal block, with a leading end of a winding residing on one of cores that is not adjacent to a core that is at a position where the terminal block is provided.