Abstract: A fan includes a frame and an impeller including a hub, a plurality of first blades, a first ring-shaped structure, and a plurality of second blades. The first blades are disposed around the hub. The hub and the first blades are surrounded by the first ring-shaped structure connected with the ends of the first blades, and a central area is structured therebetween. The second blades are connected with an outer rim of the first ring-shaped structure. The frame includes a base, an axle tube portion disposed on the base, and a receiving portion. The impeller is disposed on the axle tube portion. The receiving portion includes plural third blades disposed around the base corresponding to the central area. The first and third blades are matched to each other to be assembled for transforming a tangent velocity into a static pressure to increase the pressure generated by the central area.

Abstract: An indoor unit of an air conditioner having improved structures of suction, discharge and/or flow passages which may increase operation efficiency, reduce noises and realize a compact size. The indoor unit includes a housing comprising a front panel and a rear panel coupled to a rear portion of the front panel, at least one discharge outlet exposed to a front of the front panel, at least one suction inlet formed in the rear panel at a position corresponding to the discharge outlet, at least one heat exchanger disposed at a front portion of the suction inlet to absorb heat from air introduced through the suction inlet or transfer heat to the air introduced through the suction inlet, and at least one diagonal flow fan disposed between the heat exchanger and the discharge outlet to suction air passing through the heat exchanger and discharge the air through the discharge outlet.

Abstract: A blade group arrangement for a turbomachine in order to form a blade-row group, whereby a front blade and a rear blade each form an overlapping area that has a contraction ratio of at least 1.2, and it also relates to a turbomachine having such a contraction ratio between a front blade and a rear blade.

Abstract: Aspects of the manufacturing of Flow Deflection Devices (FDDs) for wind turbines are presented as a system that requires adjustments in order to improve power output and adjust for changes in different conditions yet provides stability of shape.

Abstract: A mixed flow fan assembly uses induced reverse ambient air flow through the in-line motor enclosure for motor cooling, motor segregation from primary exhaust contamination, and augmentation of volumetric flow rate. Induced ambient airflow through openings in and/or around the base of the fan housing balances low pressure around the fan wheel and the inlet cone to inhibit primary exhaust recirculation and increase volumetric flow rate. Straightening vanes downstream of the fan wheel are used to axially reorient radial and tangential velocity components of primary effluent flow. Airfoil impeller blades have a scalloped and/or perforated single-thickness trailing edge to attenuate fan noise.

Abstract: A system to generate electricity using a flow of air of the present disclosure, the system comprises a turbine assembly comprising a cylindrical blade drum comprising a plurality of vertical blades, a cone positioned at least substantially within the cylindrical blade drum, the cone defining an upper cone aperture and a lower cone aperture having a larger diameter than the upper cone aperture, and a fan blade positioned at or below the lower cone aperture, the fan capable of rotation to force air in an upward vertical direction, an exterior housing assembly surrounding the turbine assembly, and a vertical shaft having a first end and a second end, the first end positioned at or near the turbine assembly and the second end positioned within an alternator/generator in an interior portion of a building, wherein rotation of the cylindrical blade drum causes the alternator/generator to generate electricity.

Abstract: A series fan assembly structure includes a first fan frame and a second fan frame. The first fan frame has a first latch section, a second latch section, a first engagement recess, a second engagement recess, a first retainer section and a second retainer section. The second fan frame has a third latch section, a fourth latch section, a third engagement recess, a fourth engagement recess, a third retainer section and a fourth retainer section. The first and second engagement recesses are respectively connected with the third and fourth latch sections, the first and second latch sections are respectively connected with the third and fourth engagement recesses and the first and second retainer sections are respectively connected with the third and fourth retainer sections. Accordingly, the first and second fan frames can be quickly assembled and securely connected in both axial direction and radial direction.

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: A gas turbine engine includes a compressor, a combustor section, and a turbine. The turbine includes an integrated case/stator segment that is comprised of a ceramic matrix composite material.

Abstract: A generator system that includes an engine and an alternator which is driven by the engine to generate electrical power. A radiator is connected to the engine and an axial fan directs air toward the radiator to cool the radiator. A plurality of static vanes is located between the axial fan and the radiator. Each static vane includes an inner end and an outer end, the inner ends of the static vanes being joined together. The static vanes are curved in a plane orthogonal to the rotation axis in order to direct the air towards the axis, thereby counterbalancing the centrifugal forces. The static vanes may be twisted, the pitch angle increasing from 0 degree at hub to ca. 45 degrees at tip. Additionally, each static vane is attached to the shroud via a third member that extends axially, thereby allowing an axial offset between shroud and static vanes.

Abstract: A vane pack assembly is provided that can remove the spacers between the upper and lower vane rings to a location outside of the exhaust flow through the vane ring. In particular, the spacers are located within the vanes. Further, the assembly can effectively retain the small blocks used in varying the angle of the vanes on their associated vane pivot posts. A vane pack with such a configuration can use inexpensive parts, eliminate the need for welding of the vane pack and/or simplify the vane pack assembly process. Further, the vane pack can be decoupled from the turbine housing, thereby avoiding problems with differential thermal expansion.

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 turbine stator wheel of a gas turbine with a plurality of stator vanes spaced apart around the circumference is provided. Two adjacent stator vanes form a passage each between the suction side of the one stator vane and the pressure side of the other stator vane starting from the vane trailing edge, which includes a constant passage portion in which the passage has a substantially constant passage cross-section. The constant passage portion has an inlet area and an outlet area. Each stator vane forms on the pressure side a rear area that extends, starting from the vane trailing edge adjoining the constant passage portion as far as the inlet area of the passage portion, and on the pressure-side forms a front area that extends upstream of the rear area. Each stator vane has on the pressure side a convex pressure-side contour.

Abstract: A fan for a motor vehicle includes an impeller formed by multiple blades (3) extending radially from a hub (4), and a base supporting the impeller. The impeller is rotated about an axis of rotation by an actuator means and is positioned inside a hollow cylindrical cavity having the same axis and formed by an axial wall (25) attached to the base. The base includes an upstream front wall (22) extending externally in a radial plane with reference to the axis, and an outer wall (23) extending axially from the front wall (22). The front wall (22) has a protrusion (24) bordering the impeller, with the protrusion extending axially upstream with respect to the plane of the front wall (22). The upstream end of the protrusion is situated further upstream than the upstream end of the blades (3) of the impeller.

Abstract: A disclosed fixture for assembling a stator vane assembly for a gas turbine engine includes an outer locating ring including a plurality of outer locating pins defining a position for each of a plurality of vanes relative to an outer fairing and an inner locating ring including a plurality of inner locating rings defining a position of each of the plurality of vanes relative to an inner fairing. A clamp section includes a clamp portion and a clamp pin that define an angular orientation of each of the plurality of vanes relative to each of the inner and outer fairings, and an inner locating section supporting a plurality of radial locating pins defining a radial position of each of the plurality of vanes relative to the inner and outer fairings.

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: An inner combustion chamber casing of a turbomachine, which is intended to be placed downstream of a centrifugal compressor, is provided. The casing has the shape of a disc, pierced by a central circle, and includes on its disc at least one guide vane of the drawn-off air. The guide vane extends longitudinally over the disc between the periphery of the disc and the central circle and spreads out axially from the disc so as to form with the downstream face of the centrifugal compressor a guide channel for the air which is drawn off upon exit from the said compressor. The guide vane has a curved shape orienting in a radial direction at the level of its most central end.

Abstract: A turbocharger has a rotor housing. Said rotor housing has an insertion element. Said insertion element is configured such that the same forms an over-hanging spiral together with said rotor housing.

Abstract: A stator vane assembly for a compressor of a gas turbine, in particular of an aircraft engine, including a plurality of stator vanes whose airfoil sections form a stagger angle with an axis of rotation of the compressor, which stagger angle varies along a duct height of the stator vane assembly. Along the duct height from the inside to the outside, the stagger angle increases to a local maximum in a second section adjoining a first, radially innermost section, and decreases to an outer local minimum in a third section adjoining this second section and, along the duct height from the inside to the outside, the stagger angle decreases from the initial value to an inner local minimum in the first, radially innermost section and/or increases from the outer local minimum to a final value in a fourth, radially outermost section adjoining the third section.

Abstract: The present application relates to a stator blade sector configured to be fixed to a housing of an axial turbomachine, the sector having a plurality of blades with platforms juxtaposed, so as to describe an arc of a circle. At least one of the platforms comprises on its outer face a fixing screw and at least one other platform has no fixing screws, the platforms being fixed together at their adjacent edges. The application also relates to a stator or portion of stator having a housing forming a generally circular wall and blade sectors arranged along the wall. The housing includes several parts connected to each other by longitudinal flanges. Platforms with no fixing screws are located opposite the flanges.

Abstract: A gas turbine engine includes a compressor section and a nosecone assembly. The compressor section includes an inlet guide vane assembly including an inner shroud, an outer shroud, and an inlet guide vane extending from the inner shroud to the outer shroud. The nosecone assembly is attached to the inner shroud.

Abstract: Embodiments may provide variable geometry turbine, a nozzle vane for a variable geometry turbine, and a method. The variable geometry turbine that may include a turbine wheel and a plurality of adjustable vanes radially positioned around the turbine wheel. The turbine may also include a flow disrupting feature on one or more outside surfaces of one or more of the plurality of adjustable vanes.

Abstract: A wind turbine device may include turbine blades being radially spaced and extending vertically, diverter panels being respectively adjacent and radially outward of the turbine blades, an inner support ring coupled to the turbine blades, and an axle coupled to the turbine blades.

Abstract: A variable-nozzle turbocharger includes a turbine housing and a center housing, and a generally annular nozzle ring and an array of vanes rotatably mounted to the nozzle ring such that the vanes can be pivoted about their axes for regulating exhaust gas flow to the turbine wheel. The vanes extend between the nozzle ring and an opposite wall of the nozzle. An axially floating vane sealing ring is disposed in an annular recess formed in the face of the nozzle ring adjacent proximal ends of the vanes. The vane sealing ring is urged by exhaust gas pressure differential toward the proximal ends of the vanes, and the vanes are thus urged toward the opposite nozzle wall so that distal ends of the vanes are close to or abutting the wall, resulting in a reduction or closing of the gaps at the proximal and distal ends of the vanes.

Abstract: Embodiments relate to a guiding apparatus, a wind turbine system, and methods related thereto. In an embodiment, a guiding apparatus for guiding a flow of a fluid for use with a rotor, the rotor comprising an annular radial vane assembly surrounding a central space which is enclosed save via the vane assembly and being arranged to rotate about a vertical axis, includes a screening for guiding the fluid to circulate substantially about the vertical axis within the central space in the same direction as the rotor during use, wherein the screening comprises an inner guide array concentrically surrounded by the vane assembly.

Abstract: The present application provides a turbine nozzle including an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.

Abstract: The invention relates to a wind power station (1) for energy generation with an axial-flow, rotating, vortex-generating wind concentrator (2) pivot-mounted on a shaft (3), covered by a ring-shaped outer jacket (4) which on its outside features flow channels distributed over 360° and which is equipped concentrator blades (7) in a circular arrangement between the shaft (3) and the ring-shaped outer jacket (4). To create favourable conditions, it is proposed to include sawtooth-shaped, curved edge-vortex-generating guide profiles (5) producing a downstream vortex coil across the entire cross-section of the ring-shaped outer jacket (4).

Abstract: A columnar air moving device can comprise separately formed modular stator vanes in a stator vane assembly. The stator vanes can be arranged in a radial pattern, and can direct air in an axial direction. The modular stator vanes, as well as other components of the stator vane assembly, can be replaced, adjusted, and/or removed from the columnar air moving device.

Abstract: A turbine nozzle for an air cycle machine includes a base with a multiple turbine vanes which each extend for a vane height H, a throat width W defined between each of the multiple of turbine vanes, wherein a ratio W/H is 0.101-0.112.

Abstract: A hydraulic machinery 1 comprises: vanes 10 that are circumferentially arranged side by side; and rotatable guide vanes 20 that are arranged inside the respective stay vanes. An outlet end-point 11 of each stay vane is in contact with a common reference circle. Each guide vane includes a pressure side blade surface 21 and a negative-pressure side blade surface 22, and has a camber line connecting centers of inscribed circles 24 that are in contact with both the blade surfaces 21, 22. When each guide vane takes a maximum opening degree, a central point O of a maximum inscribed circle 24m is located on an outlet side of the guide vane, relative to an intersection point 32 at which a line as the shortest distance, which is drawn between the outlet end-point and the negative-pressure side blade surface 22, and the camber line 25 intersect with each other.

Abstract: A turbocharger for an internal combustion engine includes a center housing, a shaft rotatably supported in the center housing, and a turbine wheel connected at one end of the shaft. A turbine housing is connected to the center housing and disposed around the turbine wheel. A bore formed in the turbine housing extends from a gas outlet end of the turbine housing to an annular stop surface of the turbine housing disposed adjacent the turbine wheel. A nozzle ring disposed in the bore surrounds a portion of the turbine wheel. An outlet cone is disposed at least partially in the bore and surrounds a remaining portion of the turbine wheel. The outlet cone is connected to the gas outlet end of the turbine housing.

Abstract: A gas turbine component is provided having a repaired vane platform and rail region in which a portion of the vane rail having been damaged during operation is removed. A bar insert is rough machined and is secured within a groove in the rail. The bar insert and rail are finish machined to restore the platform and rail geometry to an original size and condition.

Abstract: An efficient and quiet construction machine has a heat exchanger in which the air flowing out from an axial flow fan avoids collision with the engine. The axial flow fan includes a plurality of blade pieces, a fan ring which guides a flow of air to the axial flow fan, a heat exchanger which is disposed on an upstream side or a downstream side of the flow of air with respect to the axial flow fan, and a structure which is disposed on the downstream side of the flow of air with respect to the axial flow fan. The fan ring includes a suction-side rounded part which reduces a flow channel on a suction side and a discharge-side rounded part which expands the flow channel on a discharge side, and each of the blade pieces is inclined at a sweep forward angle from an axial center toward a rotation direction.

Abstract: An exemplary diffuser includes a plurality of air flow channels defined by a corresponding plurality of vanes. The vanes extend from a first side of the diffuser and define a width of the air flow channel between the corresponding plurality of vanes. The first side has at least one tapered surface extending from an inner radial position to an outer radial position. The distance between a tapered surface and a top side of the plurality of the vanes defines a depth of the air flow channel. The width of the air flow channel varies relative to the depth of the air flow channel along the length of the air flow channel.

Abstract: The present invention relates to an improvement of an axial turbine. Thereto, the present invention includes a submerged turbine 100 in which a fluid is filled in an interior thereof. The present invention also includes a colliding turbine 200 for ejecting a fluid with a high pressure to rotate blades. The structure of the turbine according to the present invention includes a submerged turbine, a colliding turbine, or a combination type turbine (in which a submerged turbine and a colliding turbine are combined). Accordingly, quality and reliability of the product are significantly improved to satisfy the operator.

Abstract: A gas turbine having an annular casing with a series of circumferentially spaced openings defined therethrough; a plurality of vanes extending radially inwardly though respective casing openings, an outer end of the vanes projecting radially outwardly from the casing through the respective openings and located within the respective openings by grommets, and an inner end of the vanes being mounted to an inner portion of the casing; a flexible, segmented strap extending around the annular casing, surrounding the projecting outer ends of the vanes; and a spring radially loading the flexible strap configured to apply a tension force to the flexible strap.

Abstract: A method of modifying a steam turbine to change from a first maximum thermal power of the steam generator to a second maximum thermal power of the steam generator. The method can include replacing, in the high-pressure module, at least one set of fixed blades sized for the first maximum thermal power by at least one set of fixed blades sized for the second maximum thermal power. The at least one set of moving blades are sized to operate at the first and second maximum thermal powers. The rotor and the at least one set of moving blades of the high-pressure module remain unchanged on changing from the first maximum thermal power to the second maximum thermal power.

Abstract: A turbine nozzle for an air cycle machine includes a disk section with a multiple turbine vanes which each extend for a vane height H, a throat width W defined between each of the multiple of turbine vanes, wherein a ratio W/H is 0.745-0.769.

Abstract: An axial-flow fan structure is disclosed, having a localized area expansion between the rotor (i.e. front rotating impeller) and stator blades (i.e. rear stationary or fixed blades, sometimes called de-swirl vanes). The area expansion is provided by utilizing an impeller having a (slightly) falling tip contour (FTC).

Abstract: A device is provided for reducing the drive power requirement of a watercraft includes a fore-nozzle, wherein at least one outer fin projects outwards from the fore-nozzle.

Abstract: Fan tray assemblies for cooling electronic devices in data processing units are described herein. In some embodiments, an apparatus includes a fan tray and a stator member. The fan tray is configured to be mounted within a data processing unit, and defines an opening. The fan tray is configured to be coupled to a fan such that the fan and the opening collectively define a portion of an air flow path. The stator member includes multiple stator blades. The stator member is separate from the fan and configured to be coupled to the fan tray such that the stator blades are within the air flow path.

Abstract: The invention relates to a turbine (1), in particular of an exhaust gas turbocharger, having a turbine rotor (4), which is rotatably mounted in a housing (2), with which at least one radial inlet channel (9) for a guide apparatus (7) forming a medium which drives the turbine rotor (4) is associated, wherein said guide apparatus (7) has multiple guide vane bearing rings (10), which radially enclose said turbine rotor (4) and have guide vanes (8) which lie in said inlet channel (9), and a guide vane cover ring (12), and wherein said inlet channel (9) is axially delimited by said guide vane bearing ring (10) and said guide vane cover ring (12) and said guide apparatus (7) is mounted in the housing (2) so it is axially and/or radially movable for material relaxation. Furthermore, the invention relates to an exhaust gas turbocharger, in particular for a motor vehicle.

Abstract: A turbine nozzle apparatus for a gas turbine engine includes: an annular inner band; an annular outer band circumscribing the inner band; a plurality of airfoil-shaped structural vanes extending between and interconnecting the inner band and the outer band; and a plurality of airfoil-shaped non-structural vanes extending between the inner band and the outer band, each non-structural vane having a root end received by the inner band and a tip end received by the outer band, such that each non-structural vane is free to move to a limited degree relative to the inner and outer bands.

Abstract: A gas turbine engine includes first and second stages having a rotational axis. A circumferential array of airfoils is arranged axially between the first stage and the second stage. At least one of the airfoils have a curvature provided equidistantly between pressure and suction sides. The airfoils extend from a leading edge to a trailing edge at a midspan plane along the airfoil. An angle is defined between first and second lines respectively tangent to the intersection of the midspan plane and the curvature at airfoil leading and trailing edges. The angle is equal to or greater than about 10°.

Abstract: A method and apparatus for reducing a selected tonal noise generated by a fan operating in a non-uniform flow by locating at least one obstruction in the non-uniform flow such that the at least one obstruction generates a noise that is out of phase with the selected tonal noise. The noise generated by the at least one obstruction interferes with the selected tonal noise, thus reducing the selected tonal noise. It is also contemplated to use additional obstructions to reduce other tonal noises generated by the fan.

Abstract: Airfoils according to embodiments of this invention result in a hybrid controlled flow concept that reduces leakage loss by creating a different vortexing concept near endwall regions of the airfoils than at the core region of the airfoils. Specifically, a turbine static nozzle airfoil is disclosed having a variable, non-linear, throat dimension, s, divided by a pitch length, t, distribution (“s/t distribution”) across its radial length. In one embodiment, a plurality of static nozzle airfoils are provided, with each static nozzle airfoil configured such that a throat distance between adjacent static nozzle airfoils is larger proximate the hub regions of the airfoils than proximate the core regions of the airfoils, and the throat distance between adjacent static nozzle airfoils is smaller proximate the tip regions of the airfoils than proximate the core regions.

Abstract: A system, in certain embodiments, includes a plurality of detachable, three-dimensional diffuser vanes attached to a diffuser plate of a centrifugal compressor. In certain embodiments, the detachable, three-dimensional diffuser vanes may be attached to the diffuser plate using threaded fasteners. In addition, dowel pins may be used to align the detachable, three-dimensional diffuser vanes with respect to the diffuser plate. However, in other embodiments, the detachable, three-dimensional diffuser vanes may include a tab configured to fit securely within a groove in the diffuser plate. In addition, the tabs of the detachable, three-dimensional diffuser vanes may include indentions that mate with extensions extending from the diffuser plate, wherein the tabs may slide into slots between the extensions and the grooves of the diffuser plate.

Abstract: A method for fabricating a stator including positioning a cutting device, with a diameter equal to a desired pocket diameter, with respect to pockets in a side of a housing. Each pocket has an end wall with an indentation. The method axially displaces the device to remove material from side and end walls for the pockets to form desired diameters and lengths for the pockets, while leaving a portion of the respective indentation in place. The housing includes a plurality of blades. Each pocket is arranged to receive an engagement assembly for a one-way clutch. Each pocket includes a first opening facing in a second axial direction and a second opening in communication with the first opening and at least partially facing in a circumferential direction. The first side faces the second axial direction and the side walls are in communication with the first and second openings.

Abstract: An axial flow turbine includes in axial flow series a low pressure turbine section and a turbine exhaust system. The low pressure turbine section includes a final low pressure turbine stage having a circumferential row of static aerofoil blades followed in axial succession by a circumferential row of rotating aerofoil blades. Each aerofoil blade has a radially inner hub region and a radially outer tip region. The K value, being equal to the ratio of the throat dimension (t) to the pitch dimension (p), of each static aerofoil blade of the final low pressure turbine stage varies along the height of the static aerofoil blade, between the hub region and the tip region, according to a substantially W-shaped distribution.

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.