| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 416198000 | MULTIPLE AXIALLY SPACED WORKING MEMBERS | 47 |
| 20090016887 | Rotor Drum for Multiple Rotor Wind Turbine - According to embodiments described in the specification, provided is a rotor drum for use with a multiple-rotor wind turbine, the rotor drum being mountable on a generator shaft of a generator. The rotor drum comprises a plurality of rotors, each rotor being configured to permit a mounting of a plurality of blades. The rotor drum further comprises a plurality of cross straps affixed to the plurality of rotors for maintaining each of the plurality of rotors in a predetermined spaced-apart relationship. The rotor drum is provided with a mounting coupler provided on at least one of the plurality of rotors for affixing the rotor drum on the generator shaft. | 01-15-2009 |
| 20090290984 | FAN SYSTEM - A fan system with enhanced air flow-static pressure characteristics and reduced fan noise compared to the related art is provided. The number of duct blades of a duct is the same as the number of stationary blades of an axial flow fan located in front of the duct, and the duct blades correspond to the stationary blades respectively. An end surface of a rear end portion of each stationary blade and an end surface of a front portion of a duct blade corresponding to the stationary blade have the same shape, and they align together and contact each other to form one composite stationary blade, with a discharge port of each axial flow fan communicating with an inlet port of a duct housing located behind the axial flow fan. | 11-26-2009 |
| 20090317255 | VERTICAL AXIS WIND TURBINE - A vertical axis wind turbine ( | 12-24-2009 |
| 20100310377 | Fan assembly - A fan assembly generally comprising at least one fan blade unit of at least two curved fan blades centrally attached to a hollow rotational shaft through which air flows into the fan blade and exits on the leeward edge of the fan blade tip; | 12-09-2010 |
| 20110135480 | STEAM TURBINE ROTOR - A joined rotor that includes a primary join and a locking device and a method for joining thereof is disclosed. The primary join includes a threaded boss that is inserted in a tapped cavity formed in an adjacent rotor section. The primary join is locked, so as to prevent unscrewing, by at least one locking member that is located partially in both first and second rotor sections. This arrangement enables the join to be locked at a desired torque point. | 06-09-2011 |
| 20120027599 | IMPELLER AND ROTARY MACHINE - An impeller of a rotary machine, in which the direction of flow changes from an axial direction to a radial direction as it goes from the inside in the radial direction of a fluid flow passage to the outside in the radial direction thereof, includes: a hub surface constituting at least a portion of the fluid flow passage; a blade surface constituting at least a portion of the fluid flow passage; and a bulge that bulges toward the inside of the fluid flow passage at a corner where a pressure surface, which configures the blade surface, comes in contact with the hub surface in the vicinity of an inlet of the fluid flow passage. | 02-02-2012 |
| 20120134832 | BLOOD PUMP WITH SPLITTER IMPELLER BLADES AND SPLITTER STATOR VANES AND RELATED METHODS - A rotordynamic pump for delivering continuous flow of fluids, such as blood, is provided. In one embodiment, the pump includes a stator housing having an inlet and an outlet. A rotor hub is disposed within the stator housing having a mixed-stage or mixed-flow impeller. The mixed flow impeller includes both principle blades and splitter blades, the splitter blades exhibiting a shorter axial length than the principle blades. One or more stator vanes and extend radially inwardly from the stator housing. The splitter blades and principle blades are arranged in a circumferentially alternating pattern. The stator vanes include principle stator vanes and splitter stator vanes, the splitter stator vanes exhibiting a shorter axial length than the principle stator vanes. The splitter vanes and principle vanes are arranged in a circumferentially alternating pattern. The rotor hub may be magnetically suspended and rotated within the stator housing. | 05-31-2012 |
| 20120251323 | IMPELLER - An impeller is provided. The impeller includes a hub, a plurality of upper blades, and a plurality of lower blades. The hub has an upper surface and a lower surface. The upper blades are disposed around the hub and connect to the upper surface. The lower blades are disposed around the hub and connect to the lower surface. The upper and lower blades are alternately disposed and outwardly extend from the hub. | 10-04-2012 |
| 20130089425 | BLADE STRUCTURE FOR CENTRIFUGAL FAN - A blade structure for centrifugal fan includes a hub, a first blade unit, and a second blade unit. The hub includes at least one connection section, to a radially outer end of which an annular body is connected. The annular body has a first side and an opposite second side; and the first and the second blade unit are arranged on and spaced along the first and the second side of the annular body, respectively. By providing the first and the second blade unit around the hub of a centrifugal fan, the air flows and pressure produced by the centrifugal fan can be largely increased at effectively reduced noise. | 04-11-2013 |
| 20130142655 | MULTILAYER-TYPE FAN DEVICE - A multilayer-type fan device has a base, a major blade group and at least one minor blade group. The base is circular and has a top, a bottom, an external surface, an axle hole and at least one inclined plane. The external surface is formed around the base at the bottom of the base. The axle hole is formed through the base from the top to the bottom of the base. The at least one inclined plane is formed on the base between the external surface and the top of the base. The major blade group is mounted on the base and has multiple blades mounted on the external surface of the base at intervals. The at least one minor blade group is mounted on the base and has multiple blades mounted on one of the at least one inclined plane of the base. | 06-06-2013 |
| 20140072433 | METHOD OF CLOCKING A TURBINE BY RESHAPING THE TURBINE'S DOWNSTREAM AIRFOILS - A method of clocking a turbine is disclosed in which the leading edge of clocked downstream airfoils are bathed by either a low total pressure wake, or a cooled low total temperature wake, or both, by reshaping at least the leading edge of an airfoil along the airfoils' span or radial distance. The improvement is due to the fact that gas turbine wakes tend to be non-linear, such that a straight clocked downstream airfoil will receive a benefit of low total temperature or pressure over a portion of its span, while a restacked airfoil receives a benefit over a greater portion of the airfoil span from turbine hub to casing. | 03-13-2014 |
| 20140072434 | FAN IMPELLER STRUCTURE OF CENTRIFUGAL FAN - A fan impeller structure of centrifugal fan includes a hub, a first blade body set and a second blade body set. The hub has an extension section having a first side and a second side. The first blade body set is disposed on the first side, while the second blade body set is disposed on the second side. The first blade body set defines multiple first air inlets and multiple first air outlets. The second blade body set defines multiple second air inlets and multiple second air outlets. The first air outlets of the first blade body set or the second air outlets of the second blade body set are selectively arranged at unequal intervals so as to effectively reduce noise. | 03-13-2014 |
| 20140099207 | FAN BLADE SYSTEM WITH MULTIPLE SPACED LAYERS OF BLADES AND CENTRIFUGAL FAN USING SAME - A fan blade system with multiple spaced layers of blades and a centrifugal fan using same are disclosed. The centrifugal fan includes a housing, in which the fan blade system is mounted. The fan blade system includes a hub, and a first and a second blade group outward extended from a circumferential wall of the hub to axially space from each other. The housing includes a main housing portion and a secondary housing portion integrally formed on one side of the main housing portion. When the fan blade system is mounted in the housing, the two blade groups are separately located in the main housing portion and the secondary housing portion to produce higher airflow pressure and more air volume. With these arrangements, the centrifugal fan can have upgraded performance and be manufactured with reduced labor, time and material costs. | 04-10-2014 |
| 20140119924 | Laminar flow radial ceiling fan - The prior art has used pitched blades attached to a stationary motor, normally electric. to move air within the confines of a structure or room. The preferred invention incorporates a series of solid discs. The discs are affixed to a stationary electric motor and thus rotate around a central axis. The discs are equally spaced and centrally perforated in a manner that will allow air to flow in high volumes through the perforations and pass along the discs thus exiting symmetrically between each disc perpendicularly to the flow of air that is at its entrance. Due to the less restrictive or low pressure air entrance as well as the correct vertical disc spacing a corresponding increase in the laminar flow is realized. This feature of the preferred invention allows for operation at a rotational speed that practical for use as a ceiling fan. | 05-01-2014 |
| 20140154084 | NON-UNIFORM BLADE DISTRIBUTION FOR ROTARY WING AIRCRAFT - A translational thrust system for a rotary wing aircraft is provided including a propeller system. The propeller system includes more than one pair of propeller blades extending radially outward from a rotatable propeller hub. Each pair of propeller blades includes a first propeller blade and a second propeller blade arranged diametrically opposite one another about a circumference of the propeller hub. Each pair of propeller blades is arranged at an angle to an adjacent pair of propeller blades such that the angle is less than is the pairs of propeller blades were uniformly distributed around the circumference of the propeller hub. | 06-05-2014 |
| 20160067658 | Blade Device for the Mixing Propeller and the Application Thereof - The present invention discloses a blade device for the mixing propeller comprises a rocking shaft and a plurality of blade units; the said blade unit is made of flexible material and is installed on the rocking shaft via the fixing groove; the said blade unit consists of a horizontal propelling flexible blade and a vertical uplifting flexible blade whereas the said fixing groove consists of a horizontal section and a vertical section; one end of the said horizontal propelling flexible blade is inserted in the vertical section of the fixing groove while the other end of which is kept free so that it can swing back and forth; one end of the said vertical uplifting flexible blade is inserted in the horizontal section of the fixing groove while the other end of which is kept free so that it can swing back and forth. | 03-10-2016 |
| 20090016886 | Apparatus and method for retaining bladed rotor disks of a jet engine - An apparatus ( | 01-15-2009 |
| 20100054943 | TURBINE ROTOR AND TURBINE HAVING THE SAME - A turbine rotor is provided with a torque transfer mechanism equipped between a pair of adjacent rotor discs among a plurality of rotor discs so as to transfer a torque from one rotor disc to another rotor disc. The torque transfer mechanism is provided with a first groove having a semi-circle in cross section formed on a first contact face of one rotor disc, and a second groove having a semi-circle cross section formed on a second contact face of another rotor disc, and a torque pin inserted into cylindrical holes formed by combining the first grooves and the second grooves. The flange of the torque pin has long sides and short sides, and the length of the short sides is shorter than the width of an binary flange receiving plane formed by a pair of outer circumference planes of adjacent two rotor disc along the circumferential direction, and the long side of the flange has a longer length than the width of the binary flange receiving plane. A pair of flange receiving recessed portions is provided for receiving the end portions of the long sides of the flange on both side walls of the binary flange receiving plane. | 03-04-2010 |
| 20100166559 | ROTOR OF A GAS TURBINE - A rotor of a thermal turbomachine, particularly a gas turbine, is provided. The rotor includes a plurality of individual rotor components that are held together by a tie-bold and combined into a unit. The tie-bolt is supported by the assembly of the surrounding rotor components including the tie-bolt and the rotor disks. A hollow shaft which is made up of two tubular sections and a support wheel further support the rotor. | 07-01-2010 |
| 20100172761 | METHOD OF FABRICATING A TURBOMACHINE COMPRESSOR DRUM - A method of fabricating a turbomachine compressor drum comprising at least one rotor disk connected to an annular flange on the same axis via a wall of revolution, the method consisting in making said wall of revolution with a local annular extra thickness of material, and then once said wall of revolution has become deformed in use, in cutting through the extra thickness and in removing the wall, in positioning a new wall of revolution to take the place of the removed wall, and in welding the new wall to the drum. | 07-08-2010 |
| 20100290911 | Turbine Rotor for a Gas Turbine - A turbine rotor ( | 11-18-2010 |
| 20110164982 | APPARATUS AND METHOD FOR A LOW DISTORTION WELD FOR ROTORS - A rotor includes a first rotor segment having a first outer surface and a second rotor segment having a second outer surface. A mechanical joint is between the first and second rotor segments, and a cavity is radially outward of the mechanical joint and beneath the first and second outer surfaces. A weld bead is between the first and second outer surfaces. A method for manufacturing a rotor includes machining a first rotor segment having a first concentric axis of rotation and machining a second rotor segment having a second concentric axis of rotation. The method further includes aligning the first rotor segment to the second rotor segment radially using a mechanical joint and applying a weld bead over a portion of the first and second rotor segments to connect the first rotor segment to the second rotor segment. | 07-07-2011 |
| 20110223026 | GAS TURBINE ENGINE COMPRESSOR AND TURBINE SECTION ASSEMBLY UTILIZING TIE SHAFT - A gas turbine engine has a compressor section carrying a plurality of compressor rotors and a turbine section carrying a plurality of turbine rotors. The compressor rotors and the turbine rotors are constrained to rotate with the tie shaft. An upstream hub provides an upstream abutment face for the compressor rotors. A downstream hub bounds the downstream end of the compressor rotor to bias the compressor rotors against the upstream hub using an abutment member. The downstream hub has a rearwardly extending arm which provides a stop for the turbine rotors. A second abutment member is tightened on the tie shaft to force the turbine rotors against the downstream hub to hold together the turbine rotors. | 09-15-2011 |
| 20110255977 | TURBINE ENGINE SPACER - A turbine is provided and includes a spacer having an annular body formed with opposing outward and inward surfaces and an orifice extending through the body from the outward to the inward surface, an assembly to secure the spacer around a rotor axially between sequential buckets of a forward turbine stage and an aft turbine stage, the spacer forming an annular passage around the rotor into which a fluid flows through the orifice and a circuit fluidly coupled to the annular passage to deliver the fluid from between the sequential buckets of the forward turbine stage and the aft turbine stage to an axial location forward of the forward turbine stage. | 10-20-2011 |
| 20120039716 | Guide vane system for a turbomachine having segmented guide vane carriers - A turbine guide vane system, in particular for a gas turbine is provided. The turbine guide vane system includes a number of guide vane rows and a guide vane carrier, to enable particularly simple replacement of guide vanes, while maintaining a particularly high degree of efficiency, and thus designed for particularly short repair durations. For this purpose, the guide vane carrier has a number of segments, wherein a segment extends over the entire radial extension of the guide vane carrier and the connection of the remaining segments may be detached, and wherein the turbine guide vane carrier includes at least two sections along the axial extension thereof that are connected to one another and have a different number of segments. | 02-16-2012 |
| 20130004316 | MULTI-PIECE CENTRIFUGAL IMPELLERS AND METHODS FOR THE MANUFACTURE THEREOF - Embodiments of a multi-piece centrifugal impeller are provided, as are embodiments of a method for manufacturing a multi-piece centrifugal impeller. In one embodiment, the centrifugal impeller includes an inducer piece and an exducer piece. The inducer piece includes, in turn, an inducer hub and a plurality of forward blade segments, which extend radially outward from the inducer hub. The exducer piece includes an exducer hub, which is positioned axially adjacent the inducer hub, and a plurality of aft blade segments, which extending outward from the exducer hub. The plurality of aft blade segments interlock with the plurality of forward blade segments to form a plurality of contiguous blade structures, which extend from a forward portion of the inducer hub to an aft portion of the exducer hub. | 01-03-2013 |
| 20130045104 | COMPOSITE RINGS FOR IMPELLER-SHAFT FITTING - Systems and methods for attaching one or more impellers to a shaft and attaching composite rings to a back and front lip on each impeller to secure the impellers for high angular velocity operation. The composite rings are constructed of a material that provides a greater specific strength and greater specific stiffness relative to the material of the impellers. In multi-impeller assemblies, an impeller spacer is attached between each pair of impellers. | 02-21-2013 |
| 20130156583 | AIRFOILS INCLUDING TIP PROFILE FOR NOISE REDUCTION AND METHOD FOR FABRICATING SAME - An airfoil, a fan assembly and an unducted contra-rotating fan engine include fabricating at least one airfoil including a suction and a pressure side coupled together at a leading and a trailing edge and extending therebetween. The airfoil includes a plurality of chord sections having a chord length. The airfoil including a tip profile defining a reducing slope extending from the leading edge at the tip portion along at least a portion of the chord length. The tip profile is configured to reduce the high unsteady pressure near the tip portion of the airfoil. | 06-20-2013 |
| 20130236315 | COMPRESSOR/TURBINE ROTOR-TORQUE TRANSMISSION THROUGH HYBRID DRIVE - A torque transmission for a gas turbine rotor includes a plurality of adjacent rotating machine wheels. Each wheel includes a first flange on a first axial side and a second flange on a second axial side. The first flange has a plurality of first teeth extending around the circumference of the first flange and spaced by first slots, and the second flange has a plurality of second teeth extending around a circumference of the second flange and spaced by second slots. The first teeth of a first wheel are received in the second slots of a second, adjacent wheel to transmit torque through shear of the teeth and the first flange and the second flange are engaged to transmit torque through friction between the flanges. | 09-12-2013 |
| 20140301851 | ROTOR - A rotor for a gas-turbine engine, is provided having a first and a second rotor disc that are suitable to be joined directly. The first and second rotor discs are symmetric with respect to an axis of rotation common to the two rotor discs. The first rotor disc provides an interrupted screw on one side. The second rotor disc provides an interrupted screw on another side. The interrupted screw of the second rotor disc reciprocates the interrupted screw of the first rotor disc. | 10-09-2014 |
| 20150110628 | FASTENING SYSTEM FOR ROTOR HUBS - A rotor disk assembly comprises a first rotor disk with a plurality of circumferentially distributed first throughbores. A second rotor disk comprises a connection portion projecting at least partially axially, a plurality of circumferentially distributed second throughbores being provided in the connection portion in cooperative distribution relative to the first rotor disk for the first and second throughbores to be in register with one another in the rotor disk assembly. Connector bolts each have an elongated body with a flange between its ends, a head at its first end and a removable head at its second end, the head at the first end spaced apart from the flange for the connector bolt to be secured to one of the rotor disks at a respective throughbore, the removable head at the second end being spaced apart from the flange for the second end to project. An anti-rotation feature is between each said connector bolt and at least one of the rotor disks to prevent rotation of the connector bolts when the removable head is installed on the second end in the rotor disk assembly. | 04-23-2015 |
| 20150125306 | Method for Connecting a Shaft to a Rotary Component and Turbocharger Shaft Produced by said Method - A method for producing a connection of at least one rotary component with a central opening to a shaft with a first section along the shaft and a second section on an end face of the shaft includes fixing the shaft at the first section in the central opening of the at least one rotary component by an eccentric arrangement. The fixing of the shaft is such that the shaft is fixed in the radial direction relative to the at least one rotary component. The method also includes fixing the shaft at the second section by press-fitting a ball so that the shaft is secured in the axial direction relative to the at least one rotary component. The fixing steps are carried about by a positive engagement. | 05-07-2015 |
| 20150354530 | MULTIPLE AIRFOIL WIND TURBINE BLADE ASSEMBLY - A wind turbine blade assembly for a wind turbine having a root portion proximal to a hub of said wind turbine and a tip portion distal to said hub, comprising a primary airfoil having a primary leading edge and a secondary airfoil having a secondary leading edge wherein there is an aerodynamic gap between said primary airfoil and said secondary airfoil, with said primary airfoil configured to be located upwind of said secondary airfoil when assembled on the wind turbine. | 12-10-2015 |
| 20160186594 | 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 |
| 20160186719 | PSP WIND-POWERED GENERATOR COMPRISING BLADES AT DIHEDRAL ANGLES - The invention relates to a wind-powered generator comprising blades at dihedral angles (PSP), characterised by an aerodynamic, semi-flat blade having, on one if its sides, a bent section measuring approximately a quarter of the total width of the blade and forming a dihedral angle of less than 30°, the interior space of which captures the kinetic power of the wind impacting on the blade, thereby generating a powerful rotary movement in that direction. The blades form a diametrical set of two blades generating a strong and effective rotary movement at a 90° angle to the linear movement of the wind. The invention can be used to create: a generator comprising one single set of two blades; a generator comprising two sets of blades moving in one direction and generating an aggregate output; and/or a generator comprising two sets of blades rotating in opposite directions that generate twice the output of a set of blades rotating in one direction, with one single fixed and mobile structure, one single generator and one single wind mass. | 06-30-2016 |
| 20160376889 | RADIAL TIE-BOLT SUPPORT SPRING - According to some embodiments, a tie-bolt support assembly is provided which includes a support spring for engagement with both the tie-bolt and a rotor assembly to maintain a load path between the tie-bolt and the rotor assembly while also allowing for axial movement of the tie-bolt. | 12-29-2016 |
| 20160376902 | BELLY BAND SEAL WITH ANTI-ROTATION STRUCTURE - A belly band seal for use in a multi-stage turbomachine having plural rotor disks includes a seal strip positionable in a space between a pair of arms defined by opposing portions of adjoining rotors. The seal strip includes opposite edges for locating in respective slots in end faces of said pair of arms. The belly band seal further includes an anti-rotation structure disposed on a radially inner surface of the seal strip. The anti-rotation structure is configured as a cantilever having a pivoted end fixed to the radially inner surface and a free end comprising a radially inwardly extending engagement member for removably positioning in a radial recess in one of the arms. The cantilever is configured so as to urge the engagement member toward the radial recess by spring action. The radial recess is configured to constrain a tangential movement of the engagement member upon being positioned therein. | 12-29-2016 |
| 416200000 | Circumferentially offset | 6 |
| 20100104441 | Method and apparatus for vertical-axis turbine - A vertical turbine comprising a plurality of fluid capture element layers, where each layer provides a plurality of fluid capture elements. The layers are radially offset, thereby providing a spacing between vertically-adjacent fluid capture elements. This spacing permits fluid to flow around the fluid capture elements that are turning into the direction of fluid flow, thereby reducing back-pressure on the device while maintaining a large fluid capture profile. The turbine provides a low rpm, high-torque power generation device which may be used to generate electricity, or to provide direct applications such as pumping. | 04-29-2010 |
| 20110052396 | FAN STRUCTURE - A fan structure including a hub and at least one blade. The hub includes a top section, an annular section and at least one first connection section. The first connection section is selectively disposed on the top section or the annular section. One end of the annular section is connected with a circumference of the top section to define a receiving space. The blade has at least one second connection section disposed at one end of the blade. The second connection section is complementary to the first connection section and connected thereto. The blades are positioned in an overlapping pattern. The blades are independently formed and are easier to manufacture. Therefore, the manufacturing process of the fan structure is simplified and the manufacturing cost is lowered. Moreover, the wind power of the fan structure is increased. | 03-03-2011 |
| 20130259693 | SHIP PROPELLER - A ship propeller includes a hub having an outer periphery, a first blade set including a plurality of first blades each having a span-chord ratio substantially in a range of 3 to 8 and a second blade set including a plurality of second blades each having a span-chord ratio substantially in a range of 3 to 8. The first blade set and the second blade set are situated in different planes of rotation and working at the same rotation direction and the same rotation speed. Furthermore, the distance between the first blade set and the second blade set is 30 percent less than the mean blade radius. Specifically, the ship propeller has a total expanded area ratio substantially no less than 0.7. | 10-03-2013 |
| 20140294588 | Vertical Axis Wind Turbine using Helical Blades with Serrated Edges - A vertical-axis wind turbine system includes a novel wind turbine having helical shaped blades with serrated edges that exhibit unique airfoil characteristics. Such innovative designs of blades improve the efficiency of the turbine. Airfoil characteristics of such blades make it effective at lower wind speeds than conventional wind turbines. The exemplary system is expandable for more efficiency when the number of turns in the helical shape of blades is increased. Such a design of blades in a wind turbine generate airflow and drag in the upward direction affecting other wind turbine(s) located vertically above in close proximity. This system is modularized with many smaller wind turbines sharing the same vertical axis arranged one above another in close proximity to each other. Such an incremental design of modularized wind turbines is uniquely used to scale up for increased power generation needs. | 10-02-2014 |
| 20110091324 | ROTOR SHAFT OF A TURBOMACHINE AND METHOD FOR THE PRODUCTION OF A ROTOR OF A TURBOMACHINE - The invention relates to a rotor ( | 04-21-2011 |
| 20130209259 | BLADE GROUP ARRANGEMENT AS WELL AS TURBOMACHINE - 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. | 08-15-2013 |
| 416200000 | Turbo machine | 2 |
| 20100104441 | Method and apparatus for vertical-axis turbine - A vertical turbine comprising a plurality of fluid capture element layers, where each layer provides a plurality of fluid capture elements. The layers are radially offset, thereby providing a spacing between vertically-adjacent fluid capture elements. This spacing permits fluid to flow around the fluid capture elements that are turning into the direction of fluid flow, thereby reducing back-pressure on the device while maintaining a large fluid capture profile. The turbine provides a low rpm, high-torque power generation device which may be used to generate electricity, or to provide direct applications such as pumping. | 04-29-2010 |
| 20110052396 | FAN STRUCTURE - A fan structure including a hub and at least one blade. The hub includes a top section, an annular section and at least one first connection section. The first connection section is selectively disposed on the top section or the annular section. One end of the annular section is connected with a circumference of the top section to define a receiving space. The blade has at least one second connection section disposed at one end of the blade. The second connection section is complementary to the first connection section and connected thereto. The blades are positioned in an overlapping pattern. The blades are independently formed and are easier to manufacture. Therefore, the manufacturing process of the fan structure is simplified and the manufacturing cost is lowered. Moreover, the wind power of the fan structure is increased. | 03-03-2011 |
| 20130259693 | SHIP PROPELLER - A ship propeller includes a hub having an outer periphery, a first blade set including a plurality of first blades each having a span-chord ratio substantially in a range of 3 to 8 and a second blade set including a plurality of second blades each having a span-chord ratio substantially in a range of 3 to 8. The first blade set and the second blade set are situated in different planes of rotation and working at the same rotation direction and the same rotation speed. Furthermore, the distance between the first blade set and the second blade set is 30 percent less than the mean blade radius. Specifically, the ship propeller has a total expanded area ratio substantially no less than 0.7. | 10-03-2013 |
| 20140294588 | Vertical Axis Wind Turbine using Helical Blades with Serrated Edges - A vertical-axis wind turbine system includes a novel wind turbine having helical shaped blades with serrated edges that exhibit unique airfoil characteristics. Such innovative designs of blades improve the efficiency of the turbine. Airfoil characteristics of such blades make it effective at lower wind speeds than conventional wind turbines. The exemplary system is expandable for more efficiency when the number of turns in the helical shape of blades is increased. Such a design of blades in a wind turbine generate airflow and drag in the upward direction affecting other wind turbine(s) located vertically above in close proximity. This system is modularized with many smaller wind turbines sharing the same vertical axis arranged one above another in close proximity to each other. Such an incremental design of modularized wind turbines is uniquely used to scale up for increased power generation needs. | 10-02-2014 |
| 20110091324 | ROTOR SHAFT OF A TURBOMACHINE AND METHOD FOR THE PRODUCTION OF A ROTOR OF A TURBOMACHINE - The invention relates to a rotor ( | 04-21-2011 |
| 20130209259 | BLADE GROUP ARRANGEMENT AS WELL AS TURBOMACHINE - 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. | 08-15-2013 |
| 416201000 | Differing radii | 4 |
| 20100061857 | STEAM TURBINE HAVING STAGE WITH BUCKETS OF DIFFERENT MATERIALS - A steam turbine having a stage including buckets of different material. For example, a set of first buckets may be made of a first material and a set of second buckets may be made of a second material, where the first material is different than the second material. | 03-11-2010 |
| 20110318184 | ROTOR FOR AN AXIAL FLOW TURBOMACHINE - A rotor for an axial flow turbomachine is provided. The rotor includes a plurality of rotor discs that are arranged in stacks and clamped together with at least one tie rod. At least one of the rotor discs of the rotor comprises a smaller outer diameter than one of the neighboring rotor discs and that the difference in diameter is compensated by a drum surrounding the rotor disc with the smaller outer diameter as a ring. The drum may be made of a heat resistant material. The rotor discs surrounded by the drum may be made of a less expensive material. Furthermore, the drum may include at least one more blade ring than the rotor discs that are surrounded by the drum. | 12-29-2011 |
| 20130343892 | PROPFAN ENGINE - The present disclosure relates to a propfan engine comprising: one or more rotor stages comprising a plurality of rotors; and an outer wall comprising an outer profile, at least a portion of the outer profile defining a substantially circular cross-section, wherein the diameter of the substantially circular cross-section increases in the direction of flow over the outer wall and downstream of a leading edge of the rotors, and the diameter increases at substantially all points defining the circumference of the substantially circular cross-section. | 12-26-2013 |
| 20150328721 | RADIOGRAPHIC MARKERS FOR PARTIAL PENETRATION WELDED JOINTS - A weldment member for a gas turbine engine including a forward welding member and an aft welding member. The forward welding member has an annular shape with a forward welding face formed at one end. The forward welding face has a forward radiographic marking hole formed therein. The aft welding member has an annular shape with an aft welding face formed at one end. The aft welding face has an aft radiographic marking hole formed therein. The forward welding face is aligned with the aft welding face and the forward radiographic marking hole is angularly offset from the aft radiographic marking hole. | 11-19-2015 |
| 416198000 | Turbo machine | 21 |
| 20090016887 | Rotor Drum for Multiple Rotor Wind Turbine - According to embodiments described in the specification, provided is a rotor drum for use with a multiple-rotor wind turbine, the rotor drum being mountable on a generator shaft of a generator. The rotor drum comprises a plurality of rotors, each rotor being configured to permit a mounting of a plurality of blades. The rotor drum further comprises a plurality of cross straps affixed to the plurality of rotors for maintaining each of the plurality of rotors in a predetermined spaced-apart relationship. The rotor drum is provided with a mounting coupler provided on at least one of the plurality of rotors for affixing the rotor drum on the generator shaft. | 01-15-2009 |
| 20090290984 | FAN SYSTEM - A fan system with enhanced air flow-static pressure characteristics and reduced fan noise compared to the related art is provided. The number of duct blades of a duct is the same as the number of stationary blades of an axial flow fan located in front of the duct, and the duct blades correspond to the stationary blades respectively. An end surface of a rear end portion of each stationary blade and an end surface of a front portion of a duct blade corresponding to the stationary blade have the same shape, and they align together and contact each other to form one composite stationary blade, with a discharge port of each axial flow fan communicating with an inlet port of a duct housing located behind the axial flow fan. | 11-26-2009 |
| 20090317255 | VERTICAL AXIS WIND TURBINE - A vertical axis wind turbine ( | 12-24-2009 |
| 20100310377 | Fan assembly - A fan assembly generally comprising at least one fan blade unit of at least two curved fan blades centrally attached to a hollow rotational shaft through which air flows into the fan blade and exits on the leeward edge of the fan blade tip; | 12-09-2010 |
| 20110135480 | STEAM TURBINE ROTOR - A joined rotor that includes a primary join and a locking device and a method for joining thereof is disclosed. The primary join includes a threaded boss that is inserted in a tapped cavity formed in an adjacent rotor section. The primary join is locked, so as to prevent unscrewing, by at least one locking member that is located partially in both first and second rotor sections. This arrangement enables the join to be locked at a desired torque point. | 06-09-2011 |
| 20120027599 | IMPELLER AND ROTARY MACHINE - An impeller of a rotary machine, in which the direction of flow changes from an axial direction to a radial direction as it goes from the inside in the radial direction of a fluid flow passage to the outside in the radial direction thereof, includes: a hub surface constituting at least a portion of the fluid flow passage; a blade surface constituting at least a portion of the fluid flow passage; and a bulge that bulges toward the inside of the fluid flow passage at a corner where a pressure surface, which configures the blade surface, comes in contact with the hub surface in the vicinity of an inlet of the fluid flow passage. | 02-02-2012 |
| 20120134832 | BLOOD PUMP WITH SPLITTER IMPELLER BLADES AND SPLITTER STATOR VANES AND RELATED METHODS - A rotordynamic pump for delivering continuous flow of fluids, such as blood, is provided. In one embodiment, the pump includes a stator housing having an inlet and an outlet. A rotor hub is disposed within the stator housing having a mixed-stage or mixed-flow impeller. The mixed flow impeller includes both principle blades and splitter blades, the splitter blades exhibiting a shorter axial length than the principle blades. One or more stator vanes and extend radially inwardly from the stator housing. The splitter blades and principle blades are arranged in a circumferentially alternating pattern. The stator vanes include principle stator vanes and splitter stator vanes, the splitter stator vanes exhibiting a shorter axial length than the principle stator vanes. The splitter vanes and principle vanes are arranged in a circumferentially alternating pattern. The rotor hub may be magnetically suspended and rotated within the stator housing. | 05-31-2012 |
| 20120251323 | IMPELLER - An impeller is provided. The impeller includes a hub, a plurality of upper blades, and a plurality of lower blades. The hub has an upper surface and a lower surface. The upper blades are disposed around the hub and connect to the upper surface. The lower blades are disposed around the hub and connect to the lower surface. The upper and lower blades are alternately disposed and outwardly extend from the hub. | 10-04-2012 |
| 20130089425 | BLADE STRUCTURE FOR CENTRIFUGAL FAN - A blade structure for centrifugal fan includes a hub, a first blade unit, and a second blade unit. The hub includes at least one connection section, to a radially outer end of which an annular body is connected. The annular body has a first side and an opposite second side; and the first and the second blade unit are arranged on and spaced along the first and the second side of the annular body, respectively. By providing the first and the second blade unit around the hub of a centrifugal fan, the air flows and pressure produced by the centrifugal fan can be largely increased at effectively reduced noise. | 04-11-2013 |
| 20130142655 | MULTILAYER-TYPE FAN DEVICE - A multilayer-type fan device has a base, a major blade group and at least one minor blade group. The base is circular and has a top, a bottom, an external surface, an axle hole and at least one inclined plane. The external surface is formed around the base at the bottom of the base. The axle hole is formed through the base from the top to the bottom of the base. The at least one inclined plane is formed on the base between the external surface and the top of the base. The major blade group is mounted on the base and has multiple blades mounted on the external surface of the base at intervals. The at least one minor blade group is mounted on the base and has multiple blades mounted on one of the at least one inclined plane of the base. | 06-06-2013 |
| 20140072433 | METHOD OF CLOCKING A TURBINE BY RESHAPING THE TURBINE'S DOWNSTREAM AIRFOILS - A method of clocking a turbine is disclosed in which the leading edge of clocked downstream airfoils are bathed by either a low total pressure wake, or a cooled low total temperature wake, or both, by reshaping at least the leading edge of an airfoil along the airfoils' span or radial distance. The improvement is due to the fact that gas turbine wakes tend to be non-linear, such that a straight clocked downstream airfoil will receive a benefit of low total temperature or pressure over a portion of its span, while a restacked airfoil receives a benefit over a greater portion of the airfoil span from turbine hub to casing. | 03-13-2014 |
| 20140072434 | FAN IMPELLER STRUCTURE OF CENTRIFUGAL FAN - A fan impeller structure of centrifugal fan includes a hub, a first blade body set and a second blade body set. The hub has an extension section having a first side and a second side. The first blade body set is disposed on the first side, while the second blade body set is disposed on the second side. The first blade body set defines multiple first air inlets and multiple first air outlets. The second blade body set defines multiple second air inlets and multiple second air outlets. The first air outlets of the first blade body set or the second air outlets of the second blade body set are selectively arranged at unequal intervals so as to effectively reduce noise. | 03-13-2014 |
| 20140099207 | FAN BLADE SYSTEM WITH MULTIPLE SPACED LAYERS OF BLADES AND CENTRIFUGAL FAN USING SAME - A fan blade system with multiple spaced layers of blades and a centrifugal fan using same are disclosed. The centrifugal fan includes a housing, in which the fan blade system is mounted. The fan blade system includes a hub, and a first and a second blade group outward extended from a circumferential wall of the hub to axially space from each other. The housing includes a main housing portion and a secondary housing portion integrally formed on one side of the main housing portion. When the fan blade system is mounted in the housing, the two blade groups are separately located in the main housing portion and the secondary housing portion to produce higher airflow pressure and more air volume. With these arrangements, the centrifugal fan can have upgraded performance and be manufactured with reduced labor, time and material costs. | 04-10-2014 |
| 20140119924 | Laminar flow radial ceiling fan - The prior art has used pitched blades attached to a stationary motor, normally electric. to move air within the confines of a structure or room. The preferred invention incorporates a series of solid discs. The discs are affixed to a stationary electric motor and thus rotate around a central axis. The discs are equally spaced and centrally perforated in a manner that will allow air to flow in high volumes through the perforations and pass along the discs thus exiting symmetrically between each disc perpendicularly to the flow of air that is at its entrance. Due to the less restrictive or low pressure air entrance as well as the correct vertical disc spacing a corresponding increase in the laminar flow is realized. This feature of the preferred invention allows for operation at a rotational speed that practical for use as a ceiling fan. | 05-01-2014 |
| 20140154084 | NON-UNIFORM BLADE DISTRIBUTION FOR ROTARY WING AIRCRAFT - A translational thrust system for a rotary wing aircraft is provided including a propeller system. The propeller system includes more than one pair of propeller blades extending radially outward from a rotatable propeller hub. Each pair of propeller blades includes a first propeller blade and a second propeller blade arranged diametrically opposite one another about a circumference of the propeller hub. Each pair of propeller blades is arranged at an angle to an adjacent pair of propeller blades such that the angle is less than is the pairs of propeller blades were uniformly distributed around the circumference of the propeller hub. | 06-05-2014 |
| 20160067658 | Blade Device for the Mixing Propeller and the Application Thereof - The present invention discloses a blade device for the mixing propeller comprises a rocking shaft and a plurality of blade units; the said blade unit is made of flexible material and is installed on the rocking shaft via the fixing groove; the said blade unit consists of a horizontal propelling flexible blade and a vertical uplifting flexible blade whereas the said fixing groove consists of a horizontal section and a vertical section; one end of the said horizontal propelling flexible blade is inserted in the vertical section of the fixing groove while the other end of which is kept free so that it can swing back and forth; one end of the said vertical uplifting flexible blade is inserted in the horizontal section of the fixing groove while the other end of which is kept free so that it can swing back and forth. | 03-10-2016 |
| 20090016886 | Apparatus and method for retaining bladed rotor disks of a jet engine - An apparatus ( | 01-15-2009 |
| 20100054943 | TURBINE ROTOR AND TURBINE HAVING THE SAME - A turbine rotor is provided with a torque transfer mechanism equipped between a pair of adjacent rotor discs among a plurality of rotor discs so as to transfer a torque from one rotor disc to another rotor disc. The torque transfer mechanism is provided with a first groove having a semi-circle in cross section formed on a first contact face of one rotor disc, and a second groove having a semi-circle cross section formed on a second contact face of another rotor disc, and a torque pin inserted into cylindrical holes formed by combining the first grooves and the second grooves. The flange of the torque pin has long sides and short sides, and the length of the short sides is shorter than the width of an binary flange receiving plane formed by a pair of outer circumference planes of adjacent two rotor disc along the circumferential direction, and the long side of the flange has a longer length than the width of the binary flange receiving plane. A pair of flange receiving recessed portions is provided for receiving the end portions of the long sides of the flange on both side walls of the binary flange receiving plane. | 03-04-2010 |
| 20100166559 | ROTOR OF A GAS TURBINE - A rotor of a thermal turbomachine, particularly a gas turbine, is provided. The rotor includes a plurality of individual rotor components that are held together by a tie-bold and combined into a unit. The tie-bolt is supported by the assembly of the surrounding rotor components including the tie-bolt and the rotor disks. A hollow shaft which is made up of two tubular sections and a support wheel further support the rotor. | 07-01-2010 |
| 20100172761 | METHOD OF FABRICATING A TURBOMACHINE COMPRESSOR DRUM - A method of fabricating a turbomachine compressor drum comprising at least one rotor disk connected to an annular flange on the same axis via a wall of revolution, the method consisting in making said wall of revolution with a local annular extra thickness of material, and then once said wall of revolution has become deformed in use, in cutting through the extra thickness and in removing the wall, in positioning a new wall of revolution to take the place of the removed wall, and in welding the new wall to the drum. | 07-08-2010 |
| 20100290911 | Turbine Rotor for a Gas Turbine - A turbine rotor ( | 11-18-2010 |
| 20110164982 | APPARATUS AND METHOD FOR A LOW DISTORTION WELD FOR ROTORS - A rotor includes a first rotor segment having a first outer surface and a second rotor segment having a second outer surface. A mechanical joint is between the first and second rotor segments, and a cavity is radially outward of the mechanical joint and beneath the first and second outer surfaces. A weld bead is between the first and second outer surfaces. A method for manufacturing a rotor includes machining a first rotor segment having a first concentric axis of rotation and machining a second rotor segment having a second concentric axis of rotation. The method further includes aligning the first rotor segment to the second rotor segment radially using a mechanical joint and applying a weld bead over a portion of the first and second rotor segments to connect the first rotor segment to the second rotor segment. | 07-07-2011 |
| 20110223026 | GAS TURBINE ENGINE COMPRESSOR AND TURBINE SECTION ASSEMBLY UTILIZING TIE SHAFT - A gas turbine engine has a compressor section carrying a plurality of compressor rotors and a turbine section carrying a plurality of turbine rotors. The compressor rotors and the turbine rotors are constrained to rotate with the tie shaft. An upstream hub provides an upstream abutment face for the compressor rotors. A downstream hub bounds the downstream end of the compressor rotor to bias the compressor rotors against the upstream hub using an abutment member. The downstream hub has a rearwardly extending arm which provides a stop for the turbine rotors. A second abutment member is tightened on the tie shaft to force the turbine rotors against the downstream hub to hold together the turbine rotors. | 09-15-2011 |
| 20110255977 | TURBINE ENGINE SPACER - A turbine is provided and includes a spacer having an annular body formed with opposing outward and inward surfaces and an orifice extending through the body from the outward to the inward surface, an assembly to secure the spacer around a rotor axially between sequential buckets of a forward turbine stage and an aft turbine stage, the spacer forming an annular passage around the rotor into which a fluid flows through the orifice and a circuit fluidly coupled to the annular passage to deliver the fluid from between the sequential buckets of the forward turbine stage and the aft turbine stage to an axial location forward of the forward turbine stage. | 10-20-2011 |
| 20120039716 | Guide vane system for a turbomachine having segmented guide vane carriers - A turbine guide vane system, in particular for a gas turbine is provided. The turbine guide vane system includes a number of guide vane rows and a guide vane carrier, to enable particularly simple replacement of guide vanes, while maintaining a particularly high degree of efficiency, and thus designed for particularly short repair durations. For this purpose, the guide vane carrier has a number of segments, wherein a segment extends over the entire radial extension of the guide vane carrier and the connection of the remaining segments may be detached, and wherein the turbine guide vane carrier includes at least two sections along the axial extension thereof that are connected to one another and have a different number of segments. | 02-16-2012 |
| 20130004316 | MULTI-PIECE CENTRIFUGAL IMPELLERS AND METHODS FOR THE MANUFACTURE THEREOF - Embodiments of a multi-piece centrifugal impeller are provided, as are embodiments of a method for manufacturing a multi-piece centrifugal impeller. In one embodiment, the centrifugal impeller includes an inducer piece and an exducer piece. The inducer piece includes, in turn, an inducer hub and a plurality of forward blade segments, which extend radially outward from the inducer hub. The exducer piece includes an exducer hub, which is positioned axially adjacent the inducer hub, and a plurality of aft blade segments, which extending outward from the exducer hub. The plurality of aft blade segments interlock with the plurality of forward blade segments to form a plurality of contiguous blade structures, which extend from a forward portion of the inducer hub to an aft portion of the exducer hub. | 01-03-2013 |
| 20130045104 | COMPOSITE RINGS FOR IMPELLER-SHAFT FITTING - Systems and methods for attaching one or more impellers to a shaft and attaching composite rings to a back and front lip on each impeller to secure the impellers for high angular velocity operation. The composite rings are constructed of a material that provides a greater specific strength and greater specific stiffness relative to the material of the impellers. In multi-impeller assemblies, an impeller spacer is attached between each pair of impellers. | 02-21-2013 |
| 20130156583 | AIRFOILS INCLUDING TIP PROFILE FOR NOISE REDUCTION AND METHOD FOR FABRICATING SAME - An airfoil, a fan assembly and an unducted contra-rotating fan engine include fabricating at least one airfoil including a suction and a pressure side coupled together at a leading and a trailing edge and extending therebetween. The airfoil includes a plurality of chord sections having a chord length. The airfoil including a tip profile defining a reducing slope extending from the leading edge at the tip portion along at least a portion of the chord length. The tip profile is configured to reduce the high unsteady pressure near the tip portion of the airfoil. | 06-20-2013 |
| 20130236315 | COMPRESSOR/TURBINE ROTOR-TORQUE TRANSMISSION THROUGH HYBRID DRIVE - A torque transmission for a gas turbine rotor includes a plurality of adjacent rotating machine wheels. Each wheel includes a first flange on a first axial side and a second flange on a second axial side. The first flange has a plurality of first teeth extending around the circumference of the first flange and spaced by first slots, and the second flange has a plurality of second teeth extending around a circumference of the second flange and spaced by second slots. The first teeth of a first wheel are received in the second slots of a second, adjacent wheel to transmit torque through shear of the teeth and the first flange and the second flange are engaged to transmit torque through friction between the flanges. | 09-12-2013 |
| 20140301851 | ROTOR - A rotor for a gas-turbine engine, is provided having a first and a second rotor disc that are suitable to be joined directly. The first and second rotor discs are symmetric with respect to an axis of rotation common to the two rotor discs. The first rotor disc provides an interrupted screw on one side. The second rotor disc provides an interrupted screw on another side. The interrupted screw of the second rotor disc reciprocates the interrupted screw of the first rotor disc. | 10-09-2014 |
| 20150110628 | FASTENING SYSTEM FOR ROTOR HUBS - A rotor disk assembly comprises a first rotor disk with a plurality of circumferentially distributed first throughbores. A second rotor disk comprises a connection portion projecting at least partially axially, a plurality of circumferentially distributed second throughbores being provided in the connection portion in cooperative distribution relative to the first rotor disk for the first and second throughbores to be in register with one another in the rotor disk assembly. Connector bolts each have an elongated body with a flange between its ends, a head at its first end and a removable head at its second end, the head at the first end spaced apart from the flange for the connector bolt to be secured to one of the rotor disks at a respective throughbore, the removable head at the second end being spaced apart from the flange for the second end to project. An anti-rotation feature is between each said connector bolt and at least one of the rotor disks to prevent rotation of the connector bolts when the removable head is installed on the second end in the rotor disk assembly. | 04-23-2015 |
| 20150125306 | Method for Connecting a Shaft to a Rotary Component and Turbocharger Shaft Produced by said Method - A method for producing a connection of at least one rotary component with a central opening to a shaft with a first section along the shaft and a second section on an end face of the shaft includes fixing the shaft at the first section in the central opening of the at least one rotary component by an eccentric arrangement. The fixing of the shaft is such that the shaft is fixed in the radial direction relative to the at least one rotary component. The method also includes fixing the shaft at the second section by press-fitting a ball so that the shaft is secured in the axial direction relative to the at least one rotary component. The fixing steps are carried about by a positive engagement. | 05-07-2015 |
| 20150354530 | MULTIPLE AIRFOIL WIND TURBINE BLADE ASSEMBLY - A wind turbine blade assembly for a wind turbine having a root portion proximal to a hub of said wind turbine and a tip portion distal to said hub, comprising a primary airfoil having a primary leading edge and a secondary airfoil having a secondary leading edge wherein there is an aerodynamic gap between said primary airfoil and said secondary airfoil, with said primary airfoil configured to be located upwind of said secondary airfoil when assembled on the wind turbine. | 12-10-2015 |
| 20160186594 | 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 |
| 20160186719 | PSP WIND-POWERED GENERATOR COMPRISING BLADES AT DIHEDRAL ANGLES - The invention relates to a wind-powered generator comprising blades at dihedral angles (PSP), characterised by an aerodynamic, semi-flat blade having, on one if its sides, a bent section measuring approximately a quarter of the total width of the blade and forming a dihedral angle of less than 30°, the interior space of which captures the kinetic power of the wind impacting on the blade, thereby generating a powerful rotary movement in that direction. The blades form a diametrical set of two blades generating a strong and effective rotary movement at a 90° angle to the linear movement of the wind. The invention can be used to create: a generator comprising one single set of two blades; a generator comprising two sets of blades moving in one direction and generating an aggregate output; and/or a generator comprising two sets of blades rotating in opposite directions that generate twice the output of a set of blades rotating in one direction, with one single fixed and mobile structure, one single generator and one single wind mass. | 06-30-2016 |
| 20160376889 | RADIAL TIE-BOLT SUPPORT SPRING - According to some embodiments, a tie-bolt support assembly is provided which includes a support spring for engagement with both the tie-bolt and a rotor assembly to maintain a load path between the tie-bolt and the rotor assembly while also allowing for axial movement of the tie-bolt. | 12-29-2016 |
| 20160376902 | BELLY BAND SEAL WITH ANTI-ROTATION STRUCTURE - A belly band seal for use in a multi-stage turbomachine having plural rotor disks includes a seal strip positionable in a space between a pair of arms defined by opposing portions of adjoining rotors. The seal strip includes opposite edges for locating in respective slots in end faces of said pair of arms. The belly band seal further includes an anti-rotation structure disposed on a radially inner surface of the seal strip. The anti-rotation structure is configured as a cantilever having a pivoted end fixed to the radially inner surface and a free end comprising a radially inwardly extending engagement member for removably positioning in a radial recess in one of the arms. The cantilever is configured so as to urge the engagement member toward the radial recess by spring action. The radial recess is configured to constrain a tangential movement of the engagement member upon being positioned therein. | 12-29-2016 |
