Entries |
Document | Title | Date |
20080226452 | Modular fan housing - A modular fan housing unit designed to create a focused column or columns of downwardly moving air such that there is little deflection when the column or columns of downwardly moving air arrives at the ground level. The modular fan housing includes an elongated body element having a fluid impelling device to create the downwardly moving air. At least one plate disposed within the elongated body element directs the downwardly moving air into columns. The modular fan housing unit may be coupled to another modular fan housing unit to provide additional columns of downwardly moving air. The modular fan housing units may be coupled in various configurations, depending on the type of application. Furthermore, the modular fan housing unit or multiple modular fan housing units may be coupled to an elevated structure. | 09-18-2008 |
20080298969 | STATOR-ROTOR ASSEMBLY HAVING SURFACE FEATURE FOR ENHANCED CONTAINMENT OF GAS FLOW AND RELATED PROCESSES - A stator-rotor assembly which includes at least one interface region between the stator and rotor is described. At least one stator or rotor surface in the interface region includes a pattern of inverted turbulators. The inverted turbulators restrict gas flow through a gap between the stator and the rotor. Various turbomachines which can contain such a stator-rotor assembly are also described. The disclosure also discusses methods to restrict gas flow through gaps in a stator-rotor assembly utilizing the inverted turbulators. | 12-04-2008 |
20080317599 | BLADE FOR A HORIZONTAL-AXIS WIND GENERATOR - The invention relates to a blade for a horizontal-axis wind generator consisting of two flattened bodies which are arranged opposite one another in longitudinal convergence towards the tip without making contact with one another, said bodies being attached by means of an intermediate latticework formed by ties ( | 12-25-2008 |
20090041583 | BLADE STRUCTURE FOR TORQUE CONVERTER AND PROCESS OF PRODUCING THE SAME - A blade structure for a torque converter is produced as follows. A flat sheet is stamped into a shape including: a holding section; an inner connecting section located around the holding section, and held by the holding section; an outer connecting section located around the inner connecting section; and a plurality of blades connected between the inner connecting section and the outer connecting section. Then, the blades are bended into a curved shape between the inner connecting section and the outer connecting section. Then, the blades are angled by a predetermined angle with respect to the inner connecting section and the outer connecting section. Then, the holding section is displaced with respect to the inner connecting section perpendicularly of the sheet so as to shrink the sheet toward the holding section and shrink spaces between the blades. Then, the displaced holding section is removed from the sheet. | 02-12-2009 |
20090087315 | BLADE STRUCTURE OF TORQUE CONVERTER AND METHOD FOR PRODUCING BLADE STRUCTURE OF TORQUE CONVERTER - A blade structure of a torque converter, having a plurality of blades, is produced according to processes. The processes has (a) stamping a plane plate into a first shape, the first shape has (i) the plurality of circumferentially arranged blades, (ii) ring-shaped first connecting portions, each of which integrally couples the adjacent blades together at an outer circumference side of the blade structure, and (iii) ring-shaped second connecting portions, each of which integrally couples the adjacent blades together at an inner circumference side of the blade structure, (b) curving a surface of the stamped blade, (c) inclining the blade at a predetermined angle with respect to the first and second connecting portions while inclining the first and second connecting portions, and (d) adjusting a distance between the adjacent blades and shrinking the first shape in a radial direction by the inclination of the first and second connecting portions. | 04-02-2009 |
20090155076 | Shrouded Dual-Swept Fan Impeller - A fan impeller includes rotating ring attached to the tip of dual-swept fan blades. Besides shrouding the impeller; the blades are dual-swept forward, and sweep increases in magnitude towards the tip. The shrouded dual-swept impeller resides inside classical fan housing. The integrated effects of shrouding the impeller, forward sweep into the direction of incoming flow, and forward sweep into the direction of rotation (circumferential forward sweep) render the fan quiet; the magnitude of noise reduction is between 7 and 12 dB. | 06-18-2009 |
20090214345 | LOW PRESSURE SECTION STEAM TURBINE BUCKET - A bucket for use in the low-pressure section of a steam turbine engine is provided. The bucket has a vane length of at least about 45 inches. The bucket is comprised of a dovetail section disposed near an inner radial position of the bucket, a tip shroud disposed near an outer radial position of the bucket and a part span shroud disposed at an intermediate radial position. The intermediate radial position is located between the inner and outer radial positions. The bucket is comprised of a titanium-based alloy having between about 2% and about 6.25% by weight aluminum, up to about 3.5% vanadium, up to about 2.25% tin, up to about 2.25% zirconium, between about 1.75% and about 5.0% molybdenum, up to about 2.25% chromium, up to about 0.7% silicon and up to about 2.3% iron, with the balance being titanium. | 08-27-2009 |
20090311102 | METHOD FOR PRODUCING THE ROTOR OF A WATER TURBINE, AND ROTOR - The invention relates to a method for producing a rotor for a Francis turbine, comprising a rotor base, a rotor ring and rotors. | 12-17-2009 |
20100119371 | SHIPLAP ARRANGEMENT - An arrangement between blade elements in a blade row in a turbine is described. Each blade element has at least one shroud element and a blade airfoil which abuts on, and is connected to, the shroud element, and essentially extends radially with regard to a principal axis of the blade row. When installed, the shroud element sides, which extend circumferentially, abut on the respectively adjacent shroud element of the respectively adjacent blade element, each forming an essentially radial gap. At least one blade element has a projection which projects into the shroud element of the abutting blade element and extends in the circumferential direction, and at least one blade element has a recess which accommodates such a projection. In the region of the projection or recess there is a stepped region of the radial gap, and the guiding of the radial gap in this stepped region is a labyrinth seal. | 05-13-2010 |
20100129224 | CENTRIFUGAL COMPRESSOR - A centrifugal compressor provided with an impeller which is configured to have a plurality of blades arranged at a predetermined interval in a circumferential direction of a hub rotating together with a rotation shaft, in which a blade angle on a shroud side of the blade distributes to have a minimum value at a position between a leading edge of the blade and a midpoint of a camber line on the shroud side, and a maximum value at a position between the midpoint of the camber line on the shroud side and a trailing edge of the blade, and a blade angle of the blade on a hub side distributes so as to have a maximum value at a position between a leading edge and a midpoint of a camber line on the hub side. | 05-27-2010 |
20100150721 | RADIAL BLADE WHEEL - This invention relates to a radial blade wheel comprising a first ( | 06-17-2010 |
20100202886 | CENTRIFUGAL FAN - A centrifugal fan has a circular main plate driven and rotated by a motor rotary shaft, a plurality of blades fixed to an outer circumferential portion of the main plate and spaced apart at predetermined intervals in a circumferential direction of the main plate, and a side plate attached to ends of the blades opposite to the main plate. An air inlet port is formed at the center of the side plate. The side plate inclines outward in centrifugal directions from the air inlet port and has an arcuate cross section with a predetermined radius of curvature. A dead water region reducing space is formed between the blades and the side plate. The dead water region reducing space forms a smooth flow between the two surfaces of each blade, bringing about desirable blade performance. | 08-12-2010 |
20100232967 | CENTRIFUGAL FAN - A centrifugal fan preferably includes a stator portion; a substantially cylindrical rotor holder; an annular support plate secured to an outer circumferential surface and/or a lower end portion of the rotor holder; and a plurality of blades secured to the support plate. The support plate is integrally defined by a substantially annular blade support portion arranged radially farthest from the rotor holder to support the plurality of blades; a cylindrical portion arranged radially closest to the rotor holder to encircle the outer circumferential surface of the rotor holder; and a sloping portion arranged between the blade support portion and the cylindrical portion to slope from an upper end portion of the cylindrical portion to the blade support portion. | 09-16-2010 |
20100316497 | Impeller For A Pump - An impeller for a pump, in particular for a cooling water pump of an internal combustion engine, having an impeller body having a hub, a suction-side cover disk having a central opening for suctioning a delivery medium, and having at least one blade, which is connected in one piece to the suction-side cover disk, and which has an inner section in the area of the central opening and an outer section in the area of the suction-side cover disk, the blade being implemented as three-dimensionally curved in the inner section and essentially two-dimensionally in the outer section, the impeller having a pressure-side cover disk, which is implemented as a separate part and is fixedly rotationally connected to the impeller body. The pressure-side cover disk has at least one grooved depression, shaped corresponding to the front face and the profile of the blade, for the blade for the formfitting connection thereto, on the side facing toward the blade, the impeller being produced in a casting method and each blade being free of overlaps and undercuts. | 12-16-2010 |
20110129344 | SLURRY PUMP IMPELLER - A slurry pump impeller which includes a front shroud and a back shroud each having an inner main face with an outer peripheral edge and a central axis, a plurality of pumping vanes extending between the inner main faces of the shrouds, the pumping vanes being disposed in spaced apart relation. Each pumping vane includes a leading edge in the region of the central axis and a trailing edge in the region of the outer peripheral edges of the shrouds with a passageway between adjacent pumping vanes. Each passageway has associated therewith a discharge guide vane, each discharge guide vane being disposed within a respective passageway and located closer to one or the other of the pumping vanes and projecting from the inner main face of at least one of the or each shrouds. | 06-02-2011 |
20110142651 | Two-Part Shroud or Shroud Section for a Stator Stage with Vanes of an Axial Compressor - A shroud or shroud section for a stator stage with vanes of an axial compressor is made of composite material and is built in two parts, each having a series of notches corresponding to a half of the profile of the vanes, so as to form apertures that follow the shape of the vanes when the two parts are assembled. The two parts also include mutual fastening members or means adapted to ensure their assembly. | 06-16-2011 |
20110189020 | Axial turbo engine with low gap losses - An axial turbomachine including a rotor blade cascade is provided. The rotor blade cascade includes rotor blades each including front edge, a radially outer free blade tip and an annular enclosure enclosing the rotor blade cascade with an annulus inner side by means of which the annular enclosure is arranged directly adjacent to the blade tips to give a radial gap between the enveloping ends of the blade tips and the annulus inner side. The rotor blades include a radial projection in the region of the front edge on the blade tip and the annular enclosure has an annular radial recess in the annulus inner side, arranged at a radial distance from the ends of the blade tips, such that in the main flow direction of the axial turbomachine the line of the radial projections on the side facing the radial gap matches the line of the radial recess. | 08-04-2011 |
20120177495 | MULTI-FUNCTION HEAT SHIELD FOR A GAS TURBINE ENGINE - A rotor disk assembly for a gas turbine engine includes a rotor disk with a circumferentially intermittent slot structure that extends radially outward relative to an axis of rotation. A heat shield has a multiple of radial tabs engageable with the circumferentially intermittent slot structure to provide axial retention of the cover plate to the rotor disk. | 07-12-2012 |
20120213636 | HORIZONTAL AXIS AIRFOIL TURBINE - A Horizontal Axis Airfoil Turbine (HAAT) for harnessing wind power is presented. The horizontal axis airfoil turbine has an airfoil design configured for low cut-in-speed and operational speeds, and for high torque operation. Multiple airfoil blade tips depend inwardly from a structural shroud along the periphery of the shroud. A number of full airfoil blades depend inwardly from the shroud along spokes providing mechanical engagement between the shroud and a central hub. Advantages are derived from a large wind swept area distributed to maximize leverage in order to enable high torque operation. | 08-23-2012 |
20130078099 | JOINING STRUCTURE OF ROTATION PART OF ROTARY MACHINE AND METHOD OF JOINING ROTATION PART OF ROTARY MACHINE - A joining structure of a rotation part of a rotary machine, where the rotation part including blades and a shroud, includes a welded part made up of a solidified melted part of the blades and the shroud, and a brazed part disposed at a junction part of the blades and the shroud. | 03-28-2013 |
20130089424 | BLADE ROW FOR A TURBOMACHINE - A blade row for a turbomachine, in particular a gas turbine, is disclosed. The blade row has a number of first blade arrangements each having at least one first blade and a first shroud with a first extension in the circumferential and/or axial direction and at least a number of additional blade arrangements each having at least one additional blade and one additional shroud with an additional extension in the same direction, which is different from the first extension. | 04-11-2013 |
20130149157 | BOUNDARY LAYER CONTROLLED LOGARITHMIC SPIRAL BLADE - An impeller structure for a centrifugal fan apparatus includes a circular back plate, a ring-shaped shroud, and a tubular hub. The ring-shaped shroud and the tubular hub are respectively located a predetermined distance above and at the center of said circular back plate. The impeller structure further includes a plurality of blades which are annularly disposed around the tubular hub between the circular back plate and the ring-shaped shroud. Each of the plurality of blades includes a chord with a logarithmic spiral shape, and a mean camber line with an angle of return against the chord. | 06-13-2013 |
20140050586 | Omni-Directional Wind Power Harnessing Device - An omni-directional wind power harnessing device is disclosed. The device of the present invention includes a platform, a rotary mechanism and an output shaft. The platform has a plurality of channeling ducts, which are circumferentially provided around the platform. Therefore, wind blowing in any direction may be channeled into the platform. Each of the vanes has an arc shape and the vanes are circumferentially provided around the rotary mechanism with a tilted angle to prompt the rotary mechanism to rotate. | 02-20-2014 |
20140079551 | TURBINE ROTOR BLADE AND STEAM TURBINE - A turbine rotor blade of the embodiment is made up of plural rotor blades each including: a blade effective part, a blade planting part, and a cover part, in which the cover parts adjacent in a turbine rotor circumferential direction are engaged with each other to make up an annular blade cascade. From among the rotor blades, a cover part of a stopping blade implanted to a planting part of the turbine rotor or the cover part of at least one of the rotor blades engaged with the cover part of the stopping blade is formed at the blade top part of the rotor blade so as to be able to be fitted when the rotor blade is installed in the turbine rotor. | 03-20-2014 |
20140105746 | MOTOR-VEHICLE FAN WHEEL WITH REINFORCED SHROUD - A fan of a motor vehicle is particularly suited as a main fan of an internal combustion engine. The fan has a fan wheel with an outer ring which has a substantially L-shaped ring cross section. The L-shape is defined with a radial limb and an axial limb. The radial limb has a cross-sectional enlargement on a free-end side. | 04-17-2014 |
20140119920 | TURBINE BLADE - A turbine blade has a root portion, a platform and an aerofoil, the aerofoil is mounted on the platform and is formed by a pressure side wall and a suction side wall and has an outer surface, the pressure side wall and the suction side wall meet at a leading edge and a trailing edge, the aerofoil has an axial chord length, the suction side wall defines part of the radially outward surface of the aerofoil, the suction side wall defines art overhang, the overhang has a maximum overhang length that is between 5% and 20% of the axial chord length of the blade and is located between 5% and 50% of the suction surface length from the leading edge. | 05-01-2014 |
20140169970 | ATTACHED DUCT PROPELLER SYSTEM - An attached duct propeller system may include at least one propeller blade having at least one blade tip. A duct having an inner wall may surround the at least one propeller blade. The at least one propeller blade may attach to the inner wall of the duct. In certain embodiments, the attached duct propeller system may include a propeller shaft attached to a bore of the at least one propeller blade. In certain embodiments, the at least one blade tip may be trimmed to allow alignment within the duct and allow for the attachment of the at least one blade to the inner wall of the duct. The attached duct propeller system may be used for vehicles that use at least one propeller for propulsion. | 06-19-2014 |
20140178201 | TURBINE BLADE HAVING A SHROUD AND A CUTTING TOOTH - A turbine blade ( | 06-26-2014 |
20140301849 | TURBINE SPLIT RING RETENTION AND ANTI-ROTATION METHOD - A gas turbine engine disk split retainer ring system is provided and includes an apparatus and method for retaining a split ring in relation to a turbine cover plate or disk. Pegs are used to capture and retain a split retainer ring of the gas turbine rotor in relation to the cover plate. An anti-rotation peg has a radially oriented tab for engaging the split ring so as to control the rotation of the ring. The system may be used to balance the operating condition of a turbo machine. | 10-09-2014 |
20150017002 | COMPOSITE GAS TURBINE ENGINE BLADE HAVING MULTIPLE AIRFOILS - An apparatus includes a composite gas turbine engine multi-airfoil blade that includes first and second circumferentially spaced adjacent composite airfoils coupled together via a common composite attachment. The common attachment does not employ a fastener. The composite multi-airfoil blade may have a unitary construction having a ceramic matrix composition. | 01-15-2015 |
20150017003 | GAS TURBINE ENGINE SHROUDED BLADE - A gas turbine engine bladed component, such as a turbine blade, is shown as including a shroud located above a blade portion and a stiffener located above the shroud. The stiffener is generally located in a central interior region of the shroud and includes a raised portion that extends above a top surface of the shroud. In one non-limiting form the stiffener can have a central ridge that is oriented in an axial direction. Seal members can be included in the shroud that can be used to interact with corresponding seal members in static gas turbine engine structure to discourage a flow of fluid. In one form the shroud includes an upturned leading edge portion. | 01-15-2015 |
20150037155 | FAN ROTOR PILOTING - A fan rotor has a plurality of blades arranged circumferentially about a central axis, wherein the plurality of blades extend between 2.9980 and 3.0020 inches radially from the central axis. The fan rotor has a root portion arranged radially inward from the plurality of blades. The fan rotor also has a web portion that connects the plurality of blades to the root portion, the web portion having a minimum longitudinal thickness between 0.2000 and 0.2100 inches. | 02-05-2015 |
20150044049 | DOVETAIL RETENTION SYSTEM FOR BLADE TRACKS - A turbine shroud for a gas turbine engine includes a metallic support ring and a ceramic blade track. The blade track is formed from a plurality of blade track segments including dovetail posts. The dovetail posts are inserted through apertures in the support ring and are coupled to the support ring by segment retainers coupled to the dovetail posts providing a retention system for the ceramic blade track. | 02-12-2015 |
20150044050 | COMPOSITE BLADE WITH AN INTEGRAL BLADE TIP SHROUD AND METHOD OF FORMING THE SAME - A gas turbine engine airflow member including a blade core portion, a shroud tip portion extending from the blade core portion, and an airfoil portion formed exteriorly to the blade core portion, where the blade core portion and the shroud tip portion are constructed as a first unitary structure and the airfoil portion is constructed as a second structure. A method of forming a gas turbine engine component is also disclosed. | 02-12-2015 |
20150104316 | TURBINE BLADES - A turbomachine apparatus for driving a compressor is disclosed. The turbomachine apparatus contains at least one rotor stage and at least one retaining element. The at least one rotor stage contains a plurality of blades and is configured to rotate about an axis. The at least one retaining element is configured to retain the at least one rotor stage with the blades thereof at least partly or wholly in radial compression during rotation thereof. | 04-16-2015 |
20150308452 | CENTRIFUGAL FAN - A centrifugal fan is provided that includes a main plate configured to be rotated about a rotational axis, a shroud, having a suction opening through which air is suctioned in, and a plurality of blades arranged in a circumferential direction between the main plate and the shroud to allow the air suctioned in through the suction opening to flow from a front edge to a rear edge of each blade. Assuming a first cross section, a second cross section, a third cross section, and a fourth cross section of each blade sequentially taken at layers from the shroud to the main plate, a front edge of the first cross section is located farther from the rotational axis than a front edge of the fourth cross section, and a rear edge of the first cross section is located closer to the rotational axis than a rear edge of the fourth cross section. Among rear edges of the respective cross sections, the rear edge of the second cross section is located farthest away from the rotational axis and the rear edge of the third cross section is closest to the rotational axis. | 10-29-2015 |
20160003058 | ROTOR AND GAS TURBINE ENGINE INCLUDING SAME - A rotor for a gas turbine engine includes a plurality of blades which extend from a rotor disk, adjacent ones of the plurality of blades are joined by a flexible web. | 01-07-2016 |
20160024926 | TURBINE RING FOR A TURBOMACHINE - A turbine engine turbine ring, in particular for a helicopter, in which vibratory behavior is reduced. The turbine ring includes an essentially cylindrical support, and one or more sectors forming a circle configured to define a segment of an air passage, each sector being fastened to the support by an attachment device, wherein the attachment device includes a hook portion belonging to the support and projecting towards the sector, and a hook portion belonging to the sector and projecting towards the support, the hook portions of the support and of the sector being configured to co-operate in order to fasten the sector to the support, the ring further includes a damper device provided within the attachment device and stressed radially between a portion of the sector and a portion of the support so as to damp relative movements between the sector and the support. | 01-28-2016 |
20160097303 | CMC SHROUD SUPPORT SYSTEM OF A GAS TURBINE - A shroud support system with load spreading comprises a shroud hanger having a first wall and a second wall spaced apart in an axial direction by a retainer support wall, a ceramic matrix composite shroud segment disposed in the shroud hanger between the first and second walls and the retainer support wall, a retainer having circumferentially spaced first and second bolt holes, the retainer passing through the shroud, first and second bolts passing through the shroud hanger and engaging the first and second bolt holes of the retainer. | 04-07-2016 |
20160123153 | TURBINE WHEEL FOR A TURBINE ENGINE - A turbine wheel for a turbine engine, comprising a disk carrying blades each having a platform, carrying an impeller connected by a stilt to a root. Each blade comprises an upstream radial wall and a downstream radial wall extending inwards from the platform of the blade. The roots of the blades are engaged into slots on the periphery of the disk, so that the radial walls of the blades and the platforms of the blades are circumferentially arranged end-to-end, and define inter-blade cavities radially inside the platforms, each accommodating an inter-blade sealing and vibration damping member. At least one member comprises an elastically deformable element configured so as to be elastically prestressed against the walls of a cavity in the member mounting position. | 05-05-2016 |
20160138408 | BLISK RIM FACE UNDERCUT - A high pressure BLISK includes at least one circular row of airfoils circumferentially disposed about, integral with, and extending radially outwardly from an annular rim having an annular flat aft facing face with coplanar radially outer and inner face portions radially separated by an annular undercut extending into the rim from the aft facing face. Airfoil roots including root fillets extend around the airfoil between the rim and pressure and suction sides of the airfoils. An axially aftwardly extending annular cylindrical section extends aftwardly from the flat face. The BLISK being a first of axially adjacent first and second rotor sections connected by a rabbet joint. A forward arm of the second rotor section includes an outer forward facing annular face spaced apart from the aft facing face radially outwardly of the annular undercut and a radially inner forward facing annular face contacting the aft facing face. | 05-19-2016 |
20160153470 | AERIAL CENTRIFUGAL IMPELLER | 06-02-2016 |
20160186593 | FLOWPATH BOUNDARY AND ROTOR ASSEMBLIES IN GAS TURBINES - A gas turbine that having a flowpath having a rotor assembly that includes: a first rotor wheel supporting a first rotor blade having a platform that defines a first axial section of an inner boundary of the flowpath; a second rotor wheel supporting a second rotor blade having a platform that defines a second axial section of the inner boundary of the flowpath; and an annulus filler that includes an outboard surface that defines at least part of a third axial section of the inner boundary of the flowpath occurring between the first axial section and the second axial section of the inner boundary of the flowpath. The first rotor wheel may include an axial connector for axially engaging a mating surface formed on a radially innermost face of the first rotor blade and a mating surface formed on a radially innermost face of the annulus filler. | 06-30-2016 |