| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 416183000 | Circumferentially or radially angulated or discontinuous blades or sections (e.g., stepped, etc.) | 22 |
| 20090074580 | RADIAL TURBINE WHEEL STRUCTURE - A radial turbine wheel structure comprises a wheel disc, a plurality of full blades and a plurality of splitting blades. The splitting blades are disposed equidistantly around the wheel disc and are alternately disposed with the full blades. Wherein each of inlet shrouds, outlet shrouds, inlet hubs and outlet hubs separately has an included angle to a meridian plane of the wheel disc, and the full blades are related to the splitting blades in length. Hence, the radial turbine wheel is applied to the gas turbine generator set to increase the electricity generation efficiency of the gas turbine generator. | 03-19-2009 |
| 20090269201 | Air diffuser system for industrial pumps - An air diffuser system for an impeller for a centrifugal pump has least one channel ( | 10-29-2009 |
| 20100098544 | RADIAL FAN IMPELLER - A radial fan impeller has the following features: a plurality of blades distributed around the periphery; viewed in the radial direction, the blades extend from an inner inlet region to an outer discharge region; the blades extend axially, viewed in the direction of a rotation axis, between an inlet side and an axially opposite hub side; on the inlet side, the blades are connected by means of their radial extension as far as the discharge region to a covering disc which has a central inflow opening, opening out into the inlet region; on the hub side the blades are only connected with their radial inner end regions to a central hub; the blades and the covering disc define an outer fan impeller diameter which is at least ten times an axially measured flow discharge width of the blades provided in the discharge region. | 04-22-2010 |
| 20100166557 | ROTOR DOVETAIL HOOK-TO-HOOK FIT - A male dovetail for a bucket mounted on a drum rotor for a steam turbine is provided by a tight hook-to-hook fit with the female dovetail of a retaining groove around the periphery of the drum rotor wheel. The tight hook-to-hook fit eliminates the use of loading pins which heretofore have been driven between a base of the male dovetail and a bottom of the retaining groove, a manually intensive operation with the potential to damage the bucket and the rotor. | 07-01-2010 |
| 20100202887 | RADIAL OR DIAGONAL FAN WHEEL - The present invention relates to a fan wheel in a version as a radial or diagonal fan, consisting of a shroud with an inlet port, of a baseplate and of a plurality of fan blades arranged so as to be distributed over the circumference of the inlet port and around an axis of rotation. The shroud and/or the baseplate have/has in this case a nonrotationally symmetrical geometry which in each case has a continuous and point-invariable profile, as seen in the axial or axially parallel direction. | 08-12-2010 |
| 20110020124 | TIP-FORMING MEMBER FOR A WHEEL OF A HYDRAULIC MACHINE, AND WHEEL AND HYDRAULIC MACHINE EQUIPPED WITH SUCH A MEMBER - This member ( | 01-27-2011 |
| 20110103955 | CONICAL FRUSTUM WIND TURBINE - A self-funneling conical frustum wind turbine that has the widest end open and the smallest end and conical surfaces closed. The widest end turbine will automatically face into the wind causing a funneling effect of the wind into the center of the turbine. This turbine has a plurality of openings that are partially obstructed by optimally angled blades that cause rotational spin when the high pressure air exits the turbine. This turbine is connected to a centrally located shaft, and the centrally located shaft transfers the rotational energy from the shaft to an energy conversion device. A vertical support structure supports a horizontal pivot plane that includes a bearing. This allows the turbine assembly to rotate freely to automatically face the wind. This horizontal pivot plane supports the rotating turbine assembly. | 05-05-2011 |
| 20110142652 | ROTATING BLADE SYSTEM FOR A ROW OF ROTATING BLADES OF A TURBOMACHINE - The invention concerns a moving blade system for a moving blade sequence of a continuous-flow machine, in particular a thermal gas turbine with at least two moving blade segments, of which each moving blade segment encompasses at least two moving blades that are disposed, in reference to a rotation axis of the moving blade sequence, at least primarily radially between a radially interior and a radially exterior shroud band and are coupled to the shroud bands, wherein at least the radially exterior shroud bands of the two moving blade segments encompass contact surfaces that correspond to one another, wherein radial equilibrium axes of neighboring moving blades of the at least two moving blade segments are disposed in a tilted manner by respectively axially an angle (60 | 06-16-2011 |
| 20110318182 | GAS COMPRESSOR AND METHOD FOR CONTROLLING FLOW RATE THEREOF - Provided is a gas compressor with a variable diffuser system capable of suppressing stall and surge. The gas compressor includes i) an impeller fixed to a rotation shaft and having a plurality of blades each including a wing surface and an edge surface on an outer circumferential surface thereof; ii) a shroud surrounding the wing surface; iii) a ring valve installed on a diffuser passage connected with an outlet of the impeller and moving in a direction parallel to the rotation shaft to open and close the diffuser passage; iv) a plurality of veins installed in a circumferential direction of the diffuser passage outside the ring valve in the diffuser passage; and v) an actuator coupled with the ring valve and the plurality of veins to sequentially control movement of the ring valve and rotational angles of the veins. | 12-29-2011 |
| 20120009067 | Rotor of a Turbomachine - A rotor of a turbomachine has a rotor base body and a plurality of rotor blades. Every rotor blade has a blade body and a coupling element segment. The coupling element segment of every rotor blade is contoured at a first side and at a second side opposite the first side that, at the first side and at the second side, a radially outer edge of the respective coupling element segment extends substantially in axial direction and a radially inner edge of the respective coupling element segment extends substantially in axial direction respectively delimit two surfaces separated from one another by a separating line. In at least one circumferential position of the rotor between two directly adjacent rotor blades, the separating lines run approximately parallel to, or in alignment with, the mounting direction of the rotor blades at the rotor base body, which mounting direction is defined by the blade roots. In every other circumferential position between two directly adjacent rotor blades, the separating lines formed at directly adjacent sides of the coupling element segments are oblique relative to the mounting direction. | 01-12-2012 |
| 20120027597 | CENTRIFUGAL FAN - A centrifugal fan according to an exemplary embodiment of the present invention includes: a hub penetrated by a rotational axis; a plurality of main blades extended in a radial direction from a predetermined point of the top of the hub; a bell mouth formed on a top of the exteriors of the plurality of main blades; and a plurality of auxiliary blades extended in the radial direction between the plurality of main blades, wherein a ratio (D1/D2) of an inner diameter D1 to an outer diameter D1 of each of the auxiliary blades is in the range of 07 to 0.9. | 02-02-2012 |
| 20120269635 | Hub features for turbocharger wheel - A turbocharger including a wheel having suction surfaces and hub surfaces contoured to reduce secondary flow. The suction surfaces are radially contoured with a sinusoidal component, and further have a chamfered edge at the shroud edge. The hub end-walls are contoured both streamwise and cross-stream with sinusoidal components. | 10-25-2012 |
| 20130017090 | SCALLOP CURVATURE FOR RADIAL TURBINE WHEELAANM Duong; Loc QuangAACI San DiegoAAST CAAACO USAAGP Duong; Loc Quang San Diego CA USAANM Hu; XiaolanAACI San DiegoAAST CAAACO USAAGP Hu; Xiaolan San Diego CA USAANM Yang; GaoAACI San DiegoAAST CAAACO USAAGP Yang; Gao San Diego CA USAANM Jones; Anthony C.AACI San DiegoAAST CAAACO USAAGP Jones; Anthony C. San Diego CA US - A turbine wheel is disposed about an axis and has a back face including a plurality of lobes disposed about a periphery of the back face. The lobes define scalloped areas therebetween. The scalloped areas are further defined by a radius BR | 01-17-2013 |
| 20130028741 | CAP FOR CERAMIC BLADE TIP SHROUD - A ceramic shroud assembly includes a tip shroud having an outer platform supporting at least one seal tooth, a shroud cap less brittle than the outer platform and including a shroud cap base on the outer platform, and clockwise and counter-clockwise facing clockwise and counter-clockwise contact surfaces located at clockwise and counter-clockwise distal ends respectively of the base. A rotor assembly may include a circumferential row of turbine blades made of a ceramic material and extending radially outwardly from a disk of a turbine rotor. The turbine blades include airfoils having the airfoil tip shrouds and the shroud caps at blade tips. The clockwise and counter-clockwise contact surfaces of circumferentially adjacent ones of the shroud caps contact each other. The shroud and the platform may be made of a ceramic or ceramic matrix composite material and the shroud cap may be made of a metallic material. | 01-31-2013 |
| 20140050587 | POWER-CONVERSION INSTALLATION INCLUDING A HYDRAULIC MACHINE PROVIDED WITH A RUNNER - The invention relates to a Francis runner ( | 02-20-2014 |
| 20150125302 | IMPELLER FOR A FLUID ENERGY MACHINE - In an impeller for a fluid energy machine with a hub and a plurality of rotor blades which are mounted on the hub and around which a medium may flow through the fluid energy machine and which form a blade duct between two neighboring rotor blades with a blade duct length which extends in the axial direction of the impeller, wherein each rotor blade is connected to the hub via a first transition region with a first curvature and via a second transition region with a second curvature and with a straight conical blade duct bottom of the blade duct formed between the first transition region and the second transition region. | 05-07-2015 |
| 20150322793 | METHOD FOR TURBINE WHEEL BALANCE STOCK REMOVAL - A turbine wheel ( | 11-12-2015 |
| 20150345306 | TURBOMACHINE BLADE TIP SHROUD - Embodiments of the present disclosure are directed toward systems including a turbomachine blade tip shroud having a pressure side portion and a suction side portion. The pressure side portion and the suction side portion are divided by a mean camber line of a turbomachine blade, and the pressure side portion has a greater surface area than the suction side portion. | 12-03-2015 |
| 20150361814 | GAS TURBINE ROTOR BLADE AND GAS TURBINE ROTOR - A gas turbine rotor and blade include a root portion, a platform and airfoil portion arranged along a span direction of the rotor blade, the platform located between the root and airfoil portion. The platform has an upstream and downstream side, side faces which extend from upstream to downstream side, an axial groove in each side face extends perpendicular to the span direction with a minor component of extension in span direction. A radial groove in each side face extends towards the axial groove with a component of extension in span direction and a component of extension perpendicular to the span direction. The radial groove has a first end that shows away from the axial groove and a second end that shows towards the axial groove. The second end is located a distance from the axial groove forming a groove free section between the second end and axial groove. | 12-17-2015 |
| 20160146010 | ROTOR FOR A THERMAL TURBOMACHINE - A rotor for a thermal turbomachine, in particular a gas turbine, is configured for guiding a medium in its interior. In order to guide the medium in the interior with low flow losses, a pair of rotor disks lie on one another, of which the first of the two rotor disks of the pair has holes, in order to feed the medium from the outside into the rotor interior, and rib-shaped ribs, in order to guide the medium further in the direction of the rotational axis, and the second rotor disk of the pair being configured with the aid of an auxiliary web in such a way that the flow passages which are formed between the ribs as viewed in the circumferential direction are delimited axially at least over the large part of the radial extent of the ribs. | 05-26-2016 |
| 20160186590 | COVER PLATE ASSEMBLY FOR A GAS TURBINE ENGINE - A cover plate assembly according to an exemplary aspect of the present disclosure includes, among other things, a first cover plate and a second cover plate in contact with a portion of the first cover plate to at least axially retain the first cover plate. | 06-30-2016 |
| 20160186773 | AXIAL COMPRESSOR ROTOR INCORPORATING SPLITTER BLADES - A compressor apparatus includes: a rotor having: a disk mounted for rotation about a centerline axis, an outer periphery of the disk defining a flowpath surface; an array of airfoil-shaped axial-flow compressor blades extending radially outward from the flowpath surface, wherein the compressor blades each have a root, a tip, a leading edge, and a trailing edge, wherein the compressor blades have a chord dimension and are spaced apart by a circumferential spacing, the ratio of the chord to the circumferential spacing defining a blade solidity parameter; and an array of airfoil-shaped splitter blades alternating with the compressor blades, wherein the splitter blades each have a root, a tip, a leading edge, and a trailing edge; wherein at least one of a chord dimension of the splitter blades at the roots thereof and a span dimension of the splitter blades is less than the corresponding dimension of the compressor blades. | 06-30-2016 |
