| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 416090000 | WITH FLUID PASSAGE IN WORKING MEMBER COMMUNICATING WITH WORKING FLUID | 76 |
| 20080226461 | Intensively cooled trailing edge of thin airfoils for turbine engines - A cooling system designed to cool the trailing edge of a turbine blade usable in rear stages of a turbine engine. The turbine blade may have a leading edge cooling cavity and a trailing edge cooling cavity separated by an impingement rib. The cooling system may exhaust cooling fluids through the tip of the turbine blade rather than through the trailing edge of the turbine blade to prevent premature failure at the trailing edge of the turbine blade. | 09-18-2008 |
| 20080267783 | METHODS AND SYSTEMS TO FACILITATE OPERATING WITHIN FLAME-HOLDING MARGIN - A method to facilitate controlling flame-holding margins in a turbine engine is provided. The method includes coupling at least one turbine nozzle segment within the turbine engine, wherein the at least one turbine nozzle segment includes at least one vane extending between an inner band and an outer band. The method also includes positioning at least one fuel injection orifice in a surface of the at least one vane, channeling a fuel through the at least one fuel injection orifice into a compressed fluid flow to establish a jet penetration height, and defining an operating window by adjusting an operating parameter of the fuel to reduce the jet penetration height and to facilitate reducing the flame-holding margins. | 10-30-2008 |
| 20090155088 | DUST HOLE DOME BLADE - A hollow turbine airfoil includes a tip cap bounding an internal cooling circuit between opposite pressure and suction sidewalls. The tip cap includes an internal dome surrounding a dust hole, and the dome is inclined inwardly toward the airfoil root both transversely between the opposite sidewalls and chordally between opposite leading and trailing edges of the airfoil. | 06-18-2009 |
| 20090196763 | Vertical axis wind turbines with blades for redirecting airflow - Vertical axis wind turbines and Savonius blades incorporating an internal conduit for diverting a portion of an airflow incident on the blades are disclosed. | 08-06-2009 |
| 20100098553 | Aspirated impeller - In one embodiment, a centrifugal impeller is described having a front side with airfoils and a back side. A conduit may be formed between the front side and the back side, or any other side, and may convey pressurized working fluid between the two. The conduit may pass relatively high pressure working fluid between any two locations such as from the front side to the back side. The conduit may include an aperture located on the front side and an aperture located on the back side. Any number of conduits may be defined within the centrifugal impeller. Apertures located on the front side of the impeller may be formed in any suitable place, such as a hub of the impeller or an airfoil surface, to set forth just two non-limiting examples. | 04-22-2010 |
| 20100129230 | INSERT FOR THROUGH-HOLES AND METHOD THEREFOR - An insert and method for altering a through-hole in a body, such as a steam balance hole in a steam turbine rotor wheel. The insert has a body with oppositely-disposed first and second ends, a flange radially extending from the second end of the body, and an outer surface at a perimeter of the body between the first end and the flange. A first bore within the body defines a first opening at the first end, and the first bore and outer surface of the body cooperate to define therebetween a wall capable of being plastically deformed in a radially outward direction. A second bore within the body communicates with the first bore and has a smaller cross-section than the first bore. The installation method entails installing the insert in a through-hole and flaring the wall to clamp the axial thickness of the body between the flange and flared wall of the insert. | 05-27-2010 |
| 20100143152 | METHOD AND APPARATUS FOR INCREASING LIFT ON WIND TURBINE BLADE - A lift device for a wind turbine blade. The lift device includes a first sidewall and an opposing second sidewall. The lift device is configured to be coupled to the wind turbine blade along a leading edge of the wind turbine blade, and to generate lift when airflow is directed across a surface of the lift device. | 06-10-2010 |
| 20100150731 | FAN BLADES - A blade for an axial fan, including at least a front edge portion, a back edge portion, and multiple pressure balance holes. The front edge portion operates to blow air from the outside of the blade, the back edge portion operates to blow air to the outside of the blade, and the pressure balance hole is disposed on the back edge portion. The pressure balance holes are adapted to balance pressure and reduce pressure difference between the front side and the back side of the blade, eliminating backflow phenomenon caused by separation of boundary layer airflow at the back edge portion on a windward side of the blade and thus reducing power consumption and noise, and preventing dust from settling on the back edge portion on the windward side of the blade. | 06-17-2010 |
| 20100189568 | MANUFACTURING METHOD OF IMPELLER - A manufacturing method of an impeller includes: forming a plurality of blades integrally on a blade attachment surface of one of a disc and a cover; placing the cover on a floor so as to face up the blade attachment surface of the cover; disposing the disc on the cover so as to face down the blade attachment surface of the disc; and bonding the plurality of blades to the blade attachment surface of the other of the disc and the cover which is not formed integrally with the plurality of blades by using a bonding material. | 07-29-2010 |
| 20100209257 | WIND TURBINE BLADE WITH SUBMERGED BOUNDARY LAYER CONTROL MEANS - A wind turbine blade having a longitudinal direction with a root end and a tip end as well as a chord extending in a transverse direction between a leading edge and a trailing edge is described. The blade comprises a flow control surface with a suction side and a pressure side. A number of boundary layer control means is formed in the flow control surface. The boundary layer control means include a channel submerged in the flow control surface with a first end facing towards the leading edge and a second end facing towards the trailing edge of the blade. The channel comprises: a bottom surface extending from the first end to the second end, a first sidewall extending between the flow control surface and the bottom surface and extending between the first end and the second end, the first sidewall forming a first sidewall edge between the first side wall and the flow control surface, and a second sidewall extending between the flow control surface and the bottom surface and extending between the first end and the second end, the second sidewall forming a second sidewall edge between the second side wall and the flow control surface. The channel at the first end comprises a first flow accelerating channel zone adapted for accelerating a flow, and at the second end comprises a second channel zone, where the first sidewall and the second sidewall are diverging towards the trailing edge of the blade. | 08-19-2010 |
| 20100209258 | BLADE FOR A ROTOR OF A WIND TURBINE PROVIDED WITH BARRIER GENERATING MEANS - A blade for a rotor of a wind turbine has a substantially horizontal rotor shaft, the rotor including a hub, from which the blade extends substantially in a radial direction when mounted to the hub. The blade includes a profiled contour including a leading edge and a trailing edge as well as a pressure side and a suction side, the profiled contour when being impacted by an incident airflow generating a lift. The profiled contour is divided into a root region with a substantially circular profile closest to the hub, an airfoil region with a lift generating profile furthest away from the hub, and a transition region between the root region and the airfoil region. The profile of the transition region gradually changes in the radial direction from the circular profile of the root region to the lift generating profile of the airfoil region. The suction side comprises at least a first zone, which extends substantially in the direction of the incident airflow, and which is positioned in a zone of a cross-flow. The first zone includes a first barrier generating means adapted to generating a barrier of airflow, which extends essentially in the direction of the incident airflow, the barrier of airflow being of sufficient strength and length so as to effectively reduce the cross-flow. | 08-19-2010 |
| 20100215508 | Axially Segmented Impeller - An impeller with an axial inlet in relation to an impeller axis for pressurising a fluid comprises: a nose section that has a nose section central hub and multiple nose vane sections, each nose vane section extending from a leading edge to a generally radial nose section interface plane; a tail section that has a tail section central hub and multiple tail vane sections, each tail vane section extending from a generally radial tail section interface plane to a vane tip; a coupling that joins the nose section central hub to the tail section central hub and aligns each one of the nose vane sections with a corresponding one of the tail vane sections with an axial gap between the radial nose section interface plane and the radial tail section interface plane. | 08-26-2010 |
| 20100316502 | METHOD OF MANUFACTURING IMPELLER OF CENTRIFUGAL ROTARY MACHINE AND IMPELLER OF CENTRIFUGAL ROTARY MACHINE - A method of manufacturing an impeller of a centrifugal rotary machine, the impeller being formed in a substantially disk shape and including a passageway curved to follow the axial direction in an inner peripheral side of the impeller and to follow the radial direction as it goes to an outer peripheral side thereof, the method includes: a first passageway forming step of setting a rotation center at a position on one side of the axial direction where a curvature center of the passageway is located relative to a disk forming an external shape of the impeller, and rotating a processing tool about the rotation center relative to the disk so as to form at least a part of the passageway from a position which is an inner peripheral end of the passageway of the disk toward the outer peripheral side. | 12-16-2010 |
| 20110103969 | BOUNDARY LAYER ENERGISER - A boundary layer energiser ( | 05-05-2011 |
| 20110150665 | FAN ASSEMBLY - A fan assembly is mainly provided with a center hub and a plurality of fan blades. The center hub has a center rotational axis. The fan blades extend from the center hub. Each of the fan blades has a leading surface and a trailing surface. The trailing surface of at least one of the fan blades includes an intake opening disposed at a first radial distance from the center rotational axis and a jet disposed at a second radial distance from the center rotational axis. The jet is in direct fluid communication with the intake opening such that during operation of the fan assembly airflow is directed from the intake opening to the jet for reducing power required to operate the fan assembly. | 06-23-2011 |
| 20120237358 | TURBINE BLADE TIP - A tip rail configured to reduce stress when formed from a single crystal alloy is disclosed. The tip rail may be formed from at least one single crystal alloy oriented in a low modulus direction such that a gap exists at a location where the axis of orientation is positioned at a 45 degree angle to the outer surface of the suction side to reduce stress on the tip rail. The tip rail may be separately formed from a generally elongated blade to which the tip rail is configured to be attached. The tip rail may form a leading edge region recess proximate to the leading edge between an inner edge of the tip rail on the suction side and an inner edge of the tip rail on the pressure side and may form a trailing edge region recess proximate to the trailing edge. The gap reduces stress during use operation of a gas turbine engine in which the tip rail is attached to a turbine airfoil. | 09-20-2012 |
| 20130028750 | COMPRESSOR ROTOR - A compressor rotor is provided having a rotor blade groove thereon and also includes a device for cooling the rotor in the region of a compressor rotor exit. Efficient cooling is achieved by the compressor rotor, in a compressor rotor exit region, having a ring which is pushed concentrically, and at a distance, forming a gap, over a rotor disk of the rotor, and is fastened on the disk, by the rotor blades, in the compressor rotor exit region, being inserted into corresponding grooves on the ring and being retained there, by first means for directing an axial flow of cooling medium from the compressor rotor exit through the ring, and by second means for deflecting the cooling medium which issues from the ring such that the cooling medium flows back in the axial direction through the gap between the ring and the rotor disk, encompassed by the ring. | 01-31-2013 |
| 20130034451 | GAS TURBINE ENGINE - A gas turbine engine comprises a hollow rotor including a plurality of rotor segments stacked and coupled together in a direction of its center axis and forming at least one of a compressor and a turbine; and a pipe unit inserted into an inner space of the rotor in the center axis direction. In the gas turbine engine, a weight distribution of the pipe unit within an axial transverse section is set eccentric with respect to the center axis of the rotor. In this way, a gas turbine engine which is high in performance and reliability is provided, in which a pipe provided in an inner space of the rotor to transport a cooling medium or lay out a cable, etc., is prevented from whirling. | 02-07-2013 |
| 20130071254 | TURBINE BLADES AND METHODS OF FORMING MODIFIED TURBINE BLADES AND TURBINE ROTORS - Turbine blades and methods of forming modified turbine blades and turbine rotors for use in an engine are provided. In an embodiment, by way of example only, a turbine blade includes a platform and an airfoil. The platform includes a surface configured to define a portion of a flowpath, and the surface includes an initial contour configured to plastically deform into an intended final contour after an initial exposure of the blade to an operation of the engine. The airfoil extends from the platform. | 03-21-2013 |
| 20130121842 | PROPELLER / TURBINE BLADE POWER CHANNEL - The disclosed propeller/turbine blade enhancement will be used in the moving fluid kinetic energy conversion field. This power channel blade enhancement will increase the kinetic energy conversion of propeller/turbine blades by collecting, redirecting, channeling, compressing and then expelling a portion of the moving fluid that would otherwise be lost. The power channel's multiple interactions with the moving fluid impacting the blade will produce known fluid hydraulic actions upon the enhanced propeller/turbine blades. These known fluid hydraulic actions will impart more rotational energy to the power channel enhanced blades than previous propeller/turbine blades. | 05-16-2013 |
| 20130202451 | SAFETY PROPELLER - A propeller ( | 08-08-2013 |
| 20130236329 | ROTOR BLADE WITH ONE OR MORE SIDE WALL COOLING CIRCUITS - A rotor blade for a gas turbine engine includes an airfoil and a cooling microcircuit. The airfoil includes a first side wall, a second side wall and a tip endwall, where the first side wall and the second side wall extend to and cooperate to form the tip endwall, defining a main cavity between the first side wall and the second side wall. The cooling microcircuit includes a microcircuit cavity, an inlet, a side wall outlet and a tip outlet. The microcircuit cavity is embedded within the first side wall, and the inlet extends from the main cavity to the microcircuit cavity. The side wall outlet extends from the microcircuit cavity to an exterior first side surface of the airfoil. The tip outlet extends from the microcircuit cavity to an exterior tip surface of the airfoil. | 09-12-2013 |
| 20130251538 | TRAILING EDGE COOLING - An airfoil includes a leading edge, a trailing edge, a suction surface, a pressure surface, a cooling passageway, and a plurality of oblong pedestals. The suction surface and the pressure surface both extend axially between the leading edge and the trailing edge, as well as radially from a root section to a tip section of the airfoil. The cooling passageway is located between the suction surface and the pressure surface. The oblong pedestals connect the suction surface to the pressure surface at the trailing edge of the airfoil. | 09-26-2013 |
| 20130287591 | ROTOR BLADE FOR VERTICAL AXIS WIND TURBINE - One embodiment of a rotor blade for a vertical axis wind turbine comprises a central portion having a central axis and at least two blade members. The blade members each have a proximal end attached to the central portion, a high drag side and a low drag side that is opposite the high drag side. Each of the blade members also includes an uncovered vent comprising an opening through the blade member that provides an unobstructed path for airflow through the blade member. In one embodiment, a pair of fins are positioned adjacent the opening of the vent and extend from the high drag side of the blade member. | 10-31-2013 |
| 20130343904 | ROTARY DEGASSERS AND COMPONENTS THEREFOR - Disclosed are degassers, couplings, impeller shafts and impellers for use in molten metal. One such coupling transfers gas into an impeller shaft, the coupling having a smooth, tapered internal surface to align with a corresponding surface on the impeller shaft and help prevent gas leakage and to assist in preventing damage to the impeller shaft. Improved impellers for shearing and mixing gas are also disclosed, as is a degasser including one or more of these components. | 12-26-2013 |
| 20140086756 | INTERNALLY COOLED GAS TURBINE ENGINE AIRFOIL - A gas turbine engine airfoil has a hollow airfoil section extending chordwise between a leading edge and a trailing edge. The airfoil has a leading edge cooling passage and a separate serpentine passage for cooling a remaining portion of the airfoil. The serpentine passage has at least three segment serially interconnected in fluid flow communication. The leading edge cooling passage and the serpentine cooling passage have separate coolant inlets. The coolant inlet of the serpentine passage comprises a primary inlet branch connected in fluid flow communication with a first one of the segments of the serpentine passage and a secondary inlet branch connected in flow communication with a last one of the segments, thereby providing for a portion of the flow passing through the coolant inlet of the serpentine passage to be directly fed into the last segment of the serpentine passage. | 03-27-2014 |
| 20140140858 | COMPRESSOR BLADE WITH NOZZLE - A compressor blade having at least one nozzle for ejecting fluid, in particular for ejecting water, is provided. The at least one nozzle is produced as a laminar structure in which, in particular, individual layers such as metal sheets are laid on top of each other, and has differently orientated channel sections of a channel between an inlet and an outlet, wherein the metal sheets have cutouts corresponding to the channel sections. The nozzle geometry makes it possible to prevent the formation of droplets as water exits a compressor blade. | 05-22-2014 |
| 20140147286 | TURBOMACHINE ROTOR DISK - A rotor disk for a turbomachine, which is connectable to at least one rotor blade and/or a shaft of the turbomachine, having at least one borehole, which has an elliptical inlet opening having a first passage cross-sectional area and an elliptical outlet opening having a second passage cross-sectional area, so that the second passage cross-sectional area is smaller than the first passage cross-sectional area. | 05-29-2014 |
| 20140255205 | Reduced Drag System for Windmills, Fans, Propellers, Airfoils and Hydrofoils - Airfoil and hydrofoils systems with structures having a surface texture defined by fractal geometries are described. Raised portions or fractal bumps can be included on the surfaces, forming a surface texture. The surface textures can be defined by two-dimensional fractal shapes, partial two-dimensional fractal shapes, non-contiguous fractal shapes, three-dimensional fractal objects, and partial three-dimensional fractal objects. The surfaces can include indents having fractal geometries. The indents can have varying depths and can be bordered by other indents, or bumps, or smooth portions of the airfoil or hydrofoil structure. The fractal surface textures can reduce vortices inherent from airfoil and hydrofoil structures. The roughness and distribution of the fractal surface textures reduce the vortices, improving laminar flow characteristics and at the same time reducing drag. The systems are passive and do not require applied power. | 09-11-2014 |
| 20140286789 | AIRFLOW GENERATION DEVICE AND WIND POWER GENERATION SYSTEM - An airflow generation device of an embodiment has a main body and a voltage application unit. The main body has a base formed of an insulating material and provided with a first electrode and a second electrode. The voltage application unit generates an airflow by applying voltage between the first electrode and the second electrode. Here, the main body is formed to include a portion which gradually decreases in thickness from a center portion to an end portion. | 09-25-2014 |
| 20140301864 | WIND TURBINE BLADE - A wind turbine blade is described having noise reduction features. The blade has a plurality of projecting elements provided at the blade trailing edge to reduce the scattering noise produced during operation of the blade. The blade further comprises a fluid injection system which can inject a fluid into the turbulent airflow at the trailing edge of the blade, to absorb some of the turbulent kinetic energy at the trailing edge and accordingly further reduce the levels of output noise produced by the blade. In a further aspect, the fluid injection system may be adjustable to inject fluid in an upstream direction, i.e. against the oncoming airflow, in order to provide an increased absorption of turbulent kinetic energy from the incident airflow, and accordingly to provide improved noise-reduction characteristics. | 10-09-2014 |
| 20150064018 | TURBINE BLADE AND ASSOCIATED METHOD FOR PRODUCING A TURBINE BLADE - A turbine blade is provided, having a fastening section, a platform, and a blade, which follow one another along a longitudinal axis of the turbine blade, wherein the platform, in radial relation to the longitudinal axis, has an inner platform part and an outer platform part, wherein the outer platform part is designed as a closed platform frame that encloses the outer edge of the inner platform part. An associated method for producing a turbine blade is also provided. | 03-05-2015 |
| 20150086380 | WIND POWER GENERATION DEVICE - A wind power generation device, comprising a base ( | 03-26-2015 |
| 20150098834 | All-Supersonic ducted fan for propelling aircraft at high subsonic speeds - A supersonic fan has at least two fan blades extending radially from a rim surface of a hub and is circumscribed by a duct. An inboard leading edge having an inboard sweep angle rotates at approximately Mach 1 or greater. A low-pressure zone generates propulsion. An inboard flow regime may migrate outboard from the rim surface and contaminate the low-pressure zone, reducing propulsion. An outboard leading edge having an outboard sweep angle extends radially from the inboard leading edge to form an apex. The inboard and outboard sweep angles are each at least approximately 30 degrees and in the opposite direction. An inboard vortex forming near to and as a result of the apex trails circumferentially across the fan blades and is positioned to substantially confine the inboard flow regime to be inboard of the apex, thereby preserving the low-pressure zone and increasing propulsion for the supersonic fan. | 04-09-2015 |
| 20150308449 | GAS TURBINE ENGINE COMPONENT WITH BRAZED COVER - A component according to an exemplary aspect of the present disclosure includes, among other things, a body comprised of a first material, a cover attached to the body and comprised of a second material, and a braze alloy employable to braze the cover to the body and comprised of a third material. The first material, the second material and the third material are different materials. | 10-29-2015 |
| 20150330234 | Expandable Boundary Layer Turbine - A boundary layer turbine that uses flat disks that can be precision cut at low cost is more cost-effective to construct and maintain than conventional turbines. Bolt-on hub design significantly decreases breakage and distortion. Delta-wing shaped center spacers and flow enhancing, teardrop-shaped outer spacers further increase durability by providing improved support for the disks while minimizing the disturbance of the natural flow of fluids. Use of endplates with heavy outer rims results in turbines with greater gyroscopic effect and greater mass for kinetic energy storage. A disk-directed inlet valve and focused inlet nozzle system increases efficiency by directing flows to the individual disks valve in a low friction containment case. The directed flow tuned inlet nozzle system further increases efficiency. Coating the inner case of the turbine's enclosure with Teflon or similar materials reduces friction and further improves efficiency. | 11-19-2015 |
| 20150337860 | COMPOSITE COOLING FAN - A composite cooling fan includes a frame, a fan blade and a lateral valve. The frame has an air hole penetrating the frame and a lateral air outlet locating on one side of the frame and connecting with the air hole. The fan blade is disposed in the air hole and includes an impeller, multiple axial blades surrounding the impeller and multiple centrifugal blades surrounding the axial blades. The lateral valve is disposed on the lateral air outlet and includes a valve stem and a switch baffle linked with the valve stem. The valve stem is used for making the switch baffle at the lateral air outlet open or close. | 11-26-2015 |
| 20160069206 | STEAM TURBINE - A steam turbine includes a turbine body; a steam flow passage; a regulating valve which regulates opening and closing of the steam flow passage with a linear motion; a switching drive mechanism which drives the regulating valve; an electronic governor which controls at least the switching drive mechanism; and a controller unit. The switching drive mechanism has an electric motor which rotates when supplied with power, a conversion mechanism which converts a rotary motion of the electric motor into a linear motion of the regulating valve, and a brake which brakes the rotary motion of the electric motor. At least one of the controller unit and the electronic governor performs control such that the brake is actuated and the position of the regulating valve is maintained when at least one of the electric motor and the controller unit breaks down. | 03-10-2016 |
| 20160102651 | TURBINE BLADES AND SYSTEMS WITH FORWARD BLOWING SLOTS - A blade for use in a wind turbine comprises a pressure side and suction side meeting at a trailing edge and leading edge. The pressure side and suction side provide lift to the turbine blade upon the flow of air from the leading edge to the trailing edge and over the pressure side and suction side. The blade includes one or more openings at the suction side, in some cases between the leading edge and the trailing edge. The one or more openings are configured to provide a pressurized fluid towards the leading edge of the blade, in some cases at an angle between about 0° and 70° with respect to an axis oriented from a centerline of the blade toward the leading edge. | 04-14-2016 |
| 20160123154 | ENGINE COMPONENT FOR A TURBINE ENGINE - An engine component for a turbine engine includes a particle collector having a substrate configured to retain at least some particles from a particle-laden stream passing through a portion of the engine. A fluid bypass around the substrate of the collector enables the particle-laden stream to bypass the substrate if the substrate is filled with particles. | 05-05-2016 |
| 20160186771 | Rotor hub assembly, electric fan - The invention relates to a rotor hub assembly for an electric fan, in particular for a radiator fan of a motor vehicle, comprising a hub cup, which rotates during operation and which has air outlet guides on the inside of the hub cup, which air outlet guides are arranged and shaped in such a way that the air outlet guides guide and accelerate cooling air, wherein a magnetic return cup is arranged inside the hub cup, which return cup has air passage openings, which, together with the air outlet guides, form continuous air outlets for a cooling air flow from the pressure side to the vacuum side of the fan. The invention further relates to an electric fan having such a rotor assembly. | 06-30-2016 |
| 20160194963 | ROTOR FOR A THERMAL TURBOMACHINE | 07-07-2016 |
| 20100111703 | SAFETY PROPELLER - A propeller ( | 05-06-2010 |
| 20100303634 | FLUID DYNAMIC SECTION HAVING ESCAPELET OPENINGS FOR REDUCING INDUCED AND INTERFERENCE DRAG, AND ENERGIZING STAGNANT FLOW - A fluid dynamic section provides one or more fixed size escapelets through a foil body to reduce the induced and interference drag caused by trailing vortices and similar wake turbulence. The escapelets, which can be provided in both aerodynamic and hydrodynamic structures, such as wings, tail sections; rotary blades, guy wire frames, wing sails, and various underwater keels and wing keels. The escapelets transfer energy from an inlet located in the high-pressure surface of the foil or foil body to an outlet located in the lower-pressure surface, allowing energy that would normally form a vortex at the tip of the foil to be redirected and dissipated in a beneficial way. As a result, drag is reduced and fuel economy is increased, while at the same time increasing the authority of ailerons and similar flight control surfaces, allowing aircraft that were not previously spin recovery rated to become spin recoverable. | 12-02-2010 |
| 20150132146 | PROPULSION MECHANISM - A propulsion mechanism ( | 05-14-2015 |
| 416091000 | Both inlet and outlet to working fluid | 24 |
| 20080240919 | Airfoil for a gas turbine engine - An airfoil is provided for a turbine of a gas turbine engine. The airfoil comprises: an outer structure comprising a first wall including a leading edge, a trailing edge, a pressure side, and a suction side; an inner structure comprising a second wall spaced from the first wall and at least one intermediate wall; and structure extending between the first and second walls so as to define first and second gaps between the first and second walls. The second wall and the at least one intermediate wall define at least one pressure side supply cavity and at least one suction side supply cavity. The second wall may include at least one first opening near the leading edge of the first wall. The first opening may extend from the at least one pressure side supply cavity to the first gap. The second wall may further comprise at least one second opening near the trailing edge of the outer structure. The second opening may extend from the at least one suction side supply cavity to the second gap. The first wall may comprise at least one first exit opening extending from the first gap through the pressure side of the first wall and at least one second exit opening extending from the second gap through the suction side of the second wall. | 10-02-2008 |
| 20090162200 | ROTOR BLADES - A rotor blade has a tip with an outer face including at least two channels which each extend to an outlet in the vicinity of the trailing edge. Accordingly, gas leakage around the tip must cross at least three walls, at least in the vicinity of the uncovered turning region near the trailing edge of the blade. Leakage gas entering the channels will tend to create a vortex and pass along the channel to the outlet. | 06-25-2009 |
| 20090185903 | Turbine Blade - The invention relates to a turbine blade comprising a profiled vane around which working gas flows. The working gas cross-flows a front edge of the vane and flows away on a rear edge of the vane. The vane has a first and a second channel system for guiding two media separated from the turbine blade. Combustion taking place inside is reduced in a safe manner to maintain the service life of the turbine blade and to prevent damage in the gas turbine, such that a first outlet connected to the first channel system is arranged in the region of the rear edge for blowing out the first media into the working gas and a second outlet connected to the second channel system is arranged in the region of the rear edge for blowing out the second medium. | 07-23-2009 |
| 20100028149 | Turbine Blade System - A turbine blade system relating to a tip device appended to the blade tip of a turbine. The tip device controls the flow of air to ultimately reduce noise signatures while increasing aerodynamic efficiency. Passive or actively controlled configurations also permit the user to adjust the pitch angle of the tip device for maximum efficiency rather than making less effective adjustments to the entire turbine blade. | 02-04-2010 |
| 20100129217 | Castings, Casting Cores, and Methods - A gas turbine engine component has a leading edge and a trailing edge and a pressure side and a suction side. The pressure side and suction side extend between the leading edge and trailing edge. One or more cooling passageways extend through the airfoil and comprise a trunk extending from an inlet. At the inlet, there is an additional passageway adjacent the trunk and having at least one edge recessed relative to the trunk. | 05-27-2010 |
| 20100135802 | VANE STRUCTURE FOR VERTICAL AXIS WIND POWER GENERATOR - A vane for vertical axis wind power generator includes a vane body defining a rearward recess and having a front plate portion with a through hole; a first arcuate guide bar located in the recess with a second end connected to the vane body and a first end located in the through hole; an openwork screen fitted in the through hole and connected to the first end of the first arcuate guide bar; and a first movable baffle unit slidably fitted around the first arcuate guide bar and pivotally connected to the vane body to openably cover the openwork screen. When the rearward recess is against the wind, the first movable baffle unit covers the openwork screen for the rearward recess to effectively intercept the wind. When the rearward recess is before the wind, the first movable baffle unit naturally opens to reduce the air resistance to the vane. | 06-03-2010 |
| 20100303625 | RECOVERY TIP TURBINE BLADE - A turbine blade includes an airfoil having first and second tip ribs extending along the opposite pressure and suction sides thereof. A tip baffle bifurcates the airfoil tip into two pockets, with a first pocket being laterally open at its aft end to recover leakage flow, and a second pocket being laterally closed. | 12-02-2010 |
| 20110135477 | Method and Apparatus for Increasing Lift on Wind Turbine Blade - A lift generating apparatus for a wind turbine rotor blade comprising a first sidewall and an opposing second sidewall coupled together at a leading edge and at a trailing edge. The lift generating apparatus includes at least one forward blade extension coupled to the rotor blade to define a first airflow channel between the forward blade extension and the rotor blade. The lift generating apparatus also includes at least one aft blade extension coupled to the rotor blade to define a second airflow channel between the aft blade extension and the rotor blade. | 06-09-2011 |
| 20110142638 | WIND TURBINE ROTOR BLADE WITH ACTUATABLE AIRFOIL PASSAGES - A wind turbine rotor blade includes a pressure side and a suction side. At least one airfoil passage is defined through the blade between the pressure side and suction side. A respective cover is configured over the airfoil passage at each of the pressure and suction sides. The covers are actuatable between a closed position wherein the cover is flush with the respective pressure or suction side and an open position wherein the cover moves to open the airfoil passage. | 06-16-2011 |
| 20110206514 | ROTATING BLADE AND AIR FOIL WITH STRUCTURE FOR INCREASING FLOW RATE - According to one embodiment of the present invention, a rotating blade, having a collision face that collides with fluid and is rotated by the flow of said fluid, has at least one flow path that has been caved in from said colliding face; said flow path is located forward with respect to said rotation direction so that it is located in the rear with respect to the inlet wherein said flow is introduced and said rotation direction, and it has an outlet from which said fluid exits. Here, the cross-sectional area of said inlet may be greater than the cross-sectional area of said outlet. In addition, the cross-sectional area of said inlet may gradually decrease toward said outlet. | 08-25-2011 |
| 20110229322 | Wind Turbine Blade System with Air Passageway - In this presentation, we study various aspects of the wind turbines or wind mills. We optimize the performances of both a single wind turbine and a wind farm, collectively. We study the nozzles on the blades and all the variations and accessories for the operation of a nozzle. We also explore flow patterns around the blades, the mechanisms to get air or other gasses to the blades, the couplers for the electrical connections and the gas connections, and the gaps, holes, channels, conduits, or openings on the body or structure of a tower. We also present various mathematical models and formulations for optimizations. | 09-22-2011 |
| 20110243732 | PUMP IMPELLER - A pump impeller has two impeller bodies attached to each other. Each impeller body has an annular base wall and multiple partition protrusions separately formed on an inner surface of the base wall. Multiple outlet channels are respectively defined between the partition protrusions. Each outlet channel has a cross-sectional area decreasing from an inner end to an outer open end of the outlet channel. Thus, liquid flowing through the outlet channels does not become turbulent and a working efficiency of a pump with the pump impeller is certainly improved. | 10-06-2011 |
| 20120003090 | AIRFOIL FOR CIRCULATION CONTROLLED VERTICAL AXIS WIND TURBINES - A airfoil blade for vertical axis wind turbines is presented. The airfoil blade comprises an internal cavity, an upper blowing slot disposed on the airfoil blade, and a lower blowing slot on the airfoil blade, and further comprises a valve means for variably connecting the outside air to the internal cavity through the blowing slots to selectively produce a variable lift-drag condition of said airfoil blade. | 01-05-2012 |
| 20120009065 | ROTOR BLADE - A rotor blade for a gas turbine engine, comprising an aerofoil having pressure and suction surfaces, leading and trailing edges, and an array of passages at a tip region of the aerofoil. The passages extend from the pressure surface to the suction surface of the aerofoil and are disposed so that the array creates, in operation, a planar jet of gas issuing from the suction surface. The jet is inclined outwardly from the suction surface and towards the tip, and in the direction from the leading edge to the trailing edge. The jet inhibits migration away from the suction surface of a clearance vortex formed by leakage of air over the tip of the rotor blade. | 01-12-2012 |
| 20120128489 | Wind Turbine Speed Maintenance System - A system of operating a wind turbine that is capable of extending electricity production, such as in low and high wind speed environments. In accordance with various embodiments, a wind turbine speed maintenance system has a wind turbine with at least one turbine blade that has a trailing edge with a speed feature. The speed feature is connected to a controller and a pressure vessel, the controller selectively activating the speed feature in response to the turbine blade reaching a predetermined radial velocity. | 05-24-2012 |
| 20120156037 | Foil, utilized such as an airfoil or hydrofoil, characterized by a duct moving relative to a mass of fluid. A constriction within the duct increases the speed of the fluid flowing within the duct and thereby produces a pressure drop inducing a mass of fluid external to the duct to accelerate into the duct. The acceleration of the fluid into the duct generates a resultant force, which can be varied and controlled to improve performance and reduce drag - A foil, utilized such as an airfoil or hydrofoil, characterized by a duct moving relative to a mass of fluid. The duct channels the flow of the portion of the fluid through which the duct is moving. A constriction within the duct increases the speed of the fluid constrained within the duct and thereby produces a pressure drop. The pressure drop induces a mass of fluid external to the duct and approximately parallel to the duct to accelerate into the duct. The acceleration of the external fluid mass into the duct generates a resultant force vector, which can be utilized, varied, and controlled to improve performance and reduce drag. | 06-21-2012 |
| 20120156038 | PROPULSION DEVICE USING FLUID FLOW - A propulsion device using fluid flow quickly discharges the vortex flow generated on an upper surface of the propulsion device to the outside to improve the propulsion and thrust of transportation means provided with the propulsion device. For this purpose, the propulsion device includes a fluid storage unit in which a downwardly curved fluid storage surface is formed between a first inlet line and a first outlet line such that a fluid storage space is formed on the fluid storage surface. A fluid flow unit in which a downwardly curved fluid flow surface is formed between a second inlet line and a second outlet line which are outwardly and backwardly inclined such that a fluid flow space is formed on the fluid flow surface. The-fluid flow surface adjacent to the second outlet line becomes gradually flattened as it extends outwardly. | 06-21-2012 |
| 20130108444 | TURBOMACHINE BLADE INCLUDING A SQUEELER POCKET | 05-02-2013 |
| 20130142651 | TURBINE IMPELLER COMPRISING BLADE WITH SQUEALER TIP - A turbine impeller including a rotor; a blade extending from the rotor from a first end of the blade; and a squealer tip provided at a second end opposite to the first end of the blade, wherein at least one perforated portion penetrates through the squealer tip. | 06-06-2013 |
| 20130195660 | COMPRESSOR DISK BLEED AIR SCALLOPS - A rotor disk for a gas turbine engine includes a hub; a rim with a forward portion and an aft portion; and a plurality of circumferentially spaced radial scallops in the rim to form cooling slots between two disks when the rotor disk is connected to another rotor disk. | 08-01-2013 |
| 20130315733 | PASSIVE THRUST ENHANCEMENT USING CIRCULATION CONTROL - A passive thrust enhancement system having a propeller, which includes a propeller hub, a first propeller blade, a second propeller blade, wherein each of the first and second propeller blades include a fluid flow channel within the first and second propeller blades, which is fluidly connected to a flow exit slot, and a flow capture device, which includes a plenum chamber, mounted on the propeller hub, wherein the plenum chamber is fluidly connected to the fluid flow channels. | 11-28-2013 |
| 20140356167 | Apparatus and Methods for Electricity Generation from Exhaust of Condenser of HVAC System - A low RPM permanent magnet generator mounted over the exhaust port of a HVAC condenser provides a direct drive generator that allows low cogging and low startup resistance to effectively produce electricity at low wind speeds. | 12-04-2014 |
| 20150050147 | Active Bleed For Airfoils - An airfoil active bleed system and related method. A housing includes an induction wall, an exhaust wall having one or more exhaust ports, and a chamber between the induction and exhaust walls. Zero-net-mass-flux actuators are located in the chamber and configured and positioned to collectively induct fluid through the induction wall and selectively exhaust fluid through the exhaust port(s). | 02-19-2015 |
| 20150118048 | GAS TURBINE ENGINE ROTORS INCLUDING INTRA-HUB STRESS RELIEF FEATURES AND METHODS FOR THE MANUFACTURE THEREOF - Embodiments of a gas turbine engine rotor including stress relief features are provided, as are embodiments of method for producing a gas turbine engine rotor. In one embodiment, the method includes producing a hub preform in which a plurality of elongated sacrificial cores are embedded. Blades are attached to an outer circumference of the hub preform by, for example, bonding a blade ring to the outer circumference of the preform. The blades are spaced about the rotational axis of the gas turbine engine rotor and circumferentially interspersed with the plurality of elongated sacrificial cores. The plurality of elongated sacrificial cores are then removed from the hub preform to yield a plurality of stress distribution tunnels extending in the hub preform. | 04-30-2015 |
| 416092000 | Discharge solely at periphery normal to rotation axis | 7 |
| 20080199316 | ROTOR BLADE STRUCTURE FOR A PNEUMATIC DEVICE - The rotor blade structure for the pneumatic devices includes a blade mounted into the preset chamber of a drive rotor of a pneumatic device. The blade with predefined edge and thickness has an assembly side, an external side and two windshield surfaces. At least one windshield surface is provided with a recessed portion. There may be a single recessed portion or a plurality of recessed portions. Hence, the recessed portion could increase the compression area of blade's windshield surface, thus improving the driving force of the blade and torsion of drive rotor with higher practicability. | 08-21-2008 |
| 20090148287 | FAN BLADE WITH INTEGRAL DIFFUSER SECTION AND TIP TURBINE BLADE SECTION FOR A TIP TURBINE ENGINE - A fan-turbine rotor assembly for a tip turbine engine includes an outer periphery scalloped by a multitude of elongated openings which define an inducer receipt section to receive an inducer section and a hollow fan blade section. Each fan blade section includes a turbine section which extends from a diffuser section. | 06-11-2009 |
| 20090285683 | Triangular serpentine cooling channels - A cooled airfoil includes a concave pressure wall extending radially from a base to a tip of the airfoil, a convex suction wall connected to the concave pressure wall at a leading edge and a trailing edge spaced axially from the leading edge, and cooling channels extending radially between the base and the tip of the airfoil between the concave pressure wall and the convex suction wall and configured to receive a cooling fluid supply through the base of the airfoil. The cooling channels include a leading edge channel, a trailing edge channel, a serpentine cooling circuit, and a dedicated up-pass channel. The serpentine cooling circuit includes a first up-pass channel forward of the trailing edge channel and configured to be in flow communication with a supply channel through the base of the airfoil, a down-pass channel forward of and in flow communication with the first up-pass channel, and a second up-pass channel forward of and in flow communication with the down-pass channel. At least the down-pass channel and the second up-pass channel of the serpentine circuit have a generally triangular transverse cross-sectional shape. The dedicated up-pass channel is arranged between the leading edge channel and the second up-pass channel of the serpentine cooling circuit. | 11-19-2009 |
| 20090285684 | Turbine blade internal cooling configuration - A cooled airfoil includes a concave pressure wall extending radially from a base to a tip of the airfoil, a convex suction wall connected to the concave pressure wall at a leading edge and a trailing edge spaced axially from the leading edge, and a plurality of cooling channels formed between the concave pressure wall and the convex suction wall and configured to receive a cooling fluid supply from the base of the airfoil. The cooling channels include a leading edge channel extending radially from the base toward the tip, a trailing edge channel extending radially from the base toward the tip and in flow communication with a plurality of trailing edge apertures adapted to exhaust cooling fluid to the exterior of the airfoil, a serpentine cooling circuit including a plurality of channels, and a dedicated up-pass channel extending radially from the base toward the tip between the leading edge channel and the forward most channel of the plurality of channels in the serpentine cooling circuit. | 11-19-2009 |
| 20110293421 | Rotor blade having passive bleed path - A rotor blade includes a bleed path opening to a suction surface, extending through the blade, exiting to at least one of the suction or a trailing surface, and through which working fluid flows under centrifugal pumping forces when the blade rotates, to passively bleed working fluid from the suction surface. | 12-01-2011 |
| 20130045100 | ROTOR BLADE DRAIN - The invention relates to a rotor blade for a wind power plant comprising a rotor blade body, wherein the rotor blade body encloses a hollow space, wherein the rotor blade body comprises a penetration for draining the hollow space, and a functional element, wherein the functional element is displaceably connected to the rotor blade body and is disposed at the penetration. According to the invention, the functional element can be transferred from a closed position into an open position, wherein the functional element can be displaced purely by translation. Improved drainage is thereby achieved and clogging of the drain is prevented, with reduced noise production. | 02-21-2013 |
| 20130243596 | SHARK-BITE TIP SHELF COOLING CONFIGURATION - An airfoil includes a leading edge, a trailing edge, a suction surface, a pressure surface, and a tip shelf. The suction surface and the pressure surface both extend axially to connect the leading edge to the trailing edge. The suction surface and the pressure surface both extend radially from a root section of the airfoil a tip section of the airfoil. The tip shelf is formed along the tip section, and includes a triangular pocket. | 09-19-2013 |
| 416090000 | Air and watercraft propellers | 3 |
| 20080226461 | Intensively cooled trailing edge of thin airfoils for turbine engines - A cooling system designed to cool the trailing edge of a turbine blade usable in rear stages of a turbine engine. The turbine blade may have a leading edge cooling cavity and a trailing edge cooling cavity separated by an impingement rib. The cooling system may exhaust cooling fluids through the tip of the turbine blade rather than through the trailing edge of the turbine blade to prevent premature failure at the trailing edge of the turbine blade. | 09-18-2008 |
| 20080267783 | METHODS AND SYSTEMS TO FACILITATE OPERATING WITHIN FLAME-HOLDING MARGIN - A method to facilitate controlling flame-holding margins in a turbine engine is provided. The method includes coupling at least one turbine nozzle segment within the turbine engine, wherein the at least one turbine nozzle segment includes at least one vane extending between an inner band and an outer band. The method also includes positioning at least one fuel injection orifice in a surface of the at least one vane, channeling a fuel through the at least one fuel injection orifice into a compressed fluid flow to establish a jet penetration height, and defining an operating window by adjusting an operating parameter of the fuel to reduce the jet penetration height and to facilitate reducing the flame-holding margins. | 10-30-2008 |
| 20090155088 | DUST HOLE DOME BLADE - A hollow turbine airfoil includes a tip cap bounding an internal cooling circuit between opposite pressure and suction sidewalls. The tip cap includes an internal dome surrounding a dust hole, and the dome is inclined inwardly toward the airfoil root both transversely between the opposite sidewalls and chordally between opposite leading and trailing edges of the airfoil. | 06-18-2009 |
| 20090196763 | Vertical axis wind turbines with blades for redirecting airflow - Vertical axis wind turbines and Savonius blades incorporating an internal conduit for diverting a portion of an airflow incident on the blades are disclosed. | 08-06-2009 |
| 20100098553 | Aspirated impeller - In one embodiment, a centrifugal impeller is described having a front side with airfoils and a back side. A conduit may be formed between the front side and the back side, or any other side, and may convey pressurized working fluid between the two. The conduit may pass relatively high pressure working fluid between any two locations such as from the front side to the back side. The conduit may include an aperture located on the front side and an aperture located on the back side. Any number of conduits may be defined within the centrifugal impeller. Apertures located on the front side of the impeller may be formed in any suitable place, such as a hub of the impeller or an airfoil surface, to set forth just two non-limiting examples. | 04-22-2010 |
| 20100129230 | INSERT FOR THROUGH-HOLES AND METHOD THEREFOR - An insert and method for altering a through-hole in a body, such as a steam balance hole in a steam turbine rotor wheel. The insert has a body with oppositely-disposed first and second ends, a flange radially extending from the second end of the body, and an outer surface at a perimeter of the body between the first end and the flange. A first bore within the body defines a first opening at the first end, and the first bore and outer surface of the body cooperate to define therebetween a wall capable of being plastically deformed in a radially outward direction. A second bore within the body communicates with the first bore and has a smaller cross-section than the first bore. The installation method entails installing the insert in a through-hole and flaring the wall to clamp the axial thickness of the body between the flange and flared wall of the insert. | 05-27-2010 |
| 20100143152 | METHOD AND APPARATUS FOR INCREASING LIFT ON WIND TURBINE BLADE - A lift device for a wind turbine blade. The lift device includes a first sidewall and an opposing second sidewall. The lift device is configured to be coupled to the wind turbine blade along a leading edge of the wind turbine blade, and to generate lift when airflow is directed across a surface of the lift device. | 06-10-2010 |
| 20100150731 | FAN BLADES - A blade for an axial fan, including at least a front edge portion, a back edge portion, and multiple pressure balance holes. The front edge portion operates to blow air from the outside of the blade, the back edge portion operates to blow air to the outside of the blade, and the pressure balance hole is disposed on the back edge portion. The pressure balance holes are adapted to balance pressure and reduce pressure difference between the front side and the back side of the blade, eliminating backflow phenomenon caused by separation of boundary layer airflow at the back edge portion on a windward side of the blade and thus reducing power consumption and noise, and preventing dust from settling on the back edge portion on the windward side of the blade. | 06-17-2010 |
| 20100189568 | MANUFACTURING METHOD OF IMPELLER - A manufacturing method of an impeller includes: forming a plurality of blades integrally on a blade attachment surface of one of a disc and a cover; placing the cover on a floor so as to face up the blade attachment surface of the cover; disposing the disc on the cover so as to face down the blade attachment surface of the disc; and bonding the plurality of blades to the blade attachment surface of the other of the disc and the cover which is not formed integrally with the plurality of blades by using a bonding material. | 07-29-2010 |
| 20100209257 | WIND TURBINE BLADE WITH SUBMERGED BOUNDARY LAYER CONTROL MEANS - A wind turbine blade having a longitudinal direction with a root end and a tip end as well as a chord extending in a transverse direction between a leading edge and a trailing edge is described. The blade comprises a flow control surface with a suction side and a pressure side. A number of boundary layer control means is formed in the flow control surface. The boundary layer control means include a channel submerged in the flow control surface with a first end facing towards the leading edge and a second end facing towards the trailing edge of the blade. The channel comprises: a bottom surface extending from the first end to the second end, a first sidewall extending between the flow control surface and the bottom surface and extending between the first end and the second end, the first sidewall forming a first sidewall edge between the first side wall and the flow control surface, and a second sidewall extending between the flow control surface and the bottom surface and extending between the first end and the second end, the second sidewall forming a second sidewall edge between the second side wall and the flow control surface. The channel at the first end comprises a first flow accelerating channel zone adapted for accelerating a flow, and at the second end comprises a second channel zone, where the first sidewall and the second sidewall are diverging towards the trailing edge of the blade. | 08-19-2010 |
| 20100209258 | BLADE FOR A ROTOR OF A WIND TURBINE PROVIDED WITH BARRIER GENERATING MEANS - A blade for a rotor of a wind turbine has a substantially horizontal rotor shaft, the rotor including a hub, from which the blade extends substantially in a radial direction when mounted to the hub. The blade includes a profiled contour including a leading edge and a trailing edge as well as a pressure side and a suction side, the profiled contour when being impacted by an incident airflow generating a lift. The profiled contour is divided into a root region with a substantially circular profile closest to the hub, an airfoil region with a lift generating profile furthest away from the hub, and a transition region between the root region and the airfoil region. The profile of the transition region gradually changes in the radial direction from the circular profile of the root region to the lift generating profile of the airfoil region. The suction side comprises at least a first zone, which extends substantially in the direction of the incident airflow, and which is positioned in a zone of a cross-flow. The first zone includes a first barrier generating means adapted to generating a barrier of airflow, which extends essentially in the direction of the incident airflow, the barrier of airflow being of sufficient strength and length so as to effectively reduce the cross-flow. | 08-19-2010 |
| 20100215508 | Axially Segmented Impeller - An impeller with an axial inlet in relation to an impeller axis for pressurising a fluid comprises: a nose section that has a nose section central hub and multiple nose vane sections, each nose vane section extending from a leading edge to a generally radial nose section interface plane; a tail section that has a tail section central hub and multiple tail vane sections, each tail vane section extending from a generally radial tail section interface plane to a vane tip; a coupling that joins the nose section central hub to the tail section central hub and aligns each one of the nose vane sections with a corresponding one of the tail vane sections with an axial gap between the radial nose section interface plane and the radial tail section interface plane. | 08-26-2010 |
| 20100316502 | METHOD OF MANUFACTURING IMPELLER OF CENTRIFUGAL ROTARY MACHINE AND IMPELLER OF CENTRIFUGAL ROTARY MACHINE - A method of manufacturing an impeller of a centrifugal rotary machine, the impeller being formed in a substantially disk shape and including a passageway curved to follow the axial direction in an inner peripheral side of the impeller and to follow the radial direction as it goes to an outer peripheral side thereof, the method includes: a first passageway forming step of setting a rotation center at a position on one side of the axial direction where a curvature center of the passageway is located relative to a disk forming an external shape of the impeller, and rotating a processing tool about the rotation center relative to the disk so as to form at least a part of the passageway from a position which is an inner peripheral end of the passageway of the disk toward the outer peripheral side. | 12-16-2010 |
| 20110103969 | BOUNDARY LAYER ENERGISER - A boundary layer energiser ( | 05-05-2011 |
| 20110150665 | FAN ASSEMBLY - A fan assembly is mainly provided with a center hub and a plurality of fan blades. The center hub has a center rotational axis. The fan blades extend from the center hub. Each of the fan blades has a leading surface and a trailing surface. The trailing surface of at least one of the fan blades includes an intake opening disposed at a first radial distance from the center rotational axis and a jet disposed at a second radial distance from the center rotational axis. The jet is in direct fluid communication with the intake opening such that during operation of the fan assembly airflow is directed from the intake opening to the jet for reducing power required to operate the fan assembly. | 06-23-2011 |
| 20120237358 | TURBINE BLADE TIP - A tip rail configured to reduce stress when formed from a single crystal alloy is disclosed. The tip rail may be formed from at least one single crystal alloy oriented in a low modulus direction such that a gap exists at a location where the axis of orientation is positioned at a 45 degree angle to the outer surface of the suction side to reduce stress on the tip rail. The tip rail may be separately formed from a generally elongated blade to which the tip rail is configured to be attached. The tip rail may form a leading edge region recess proximate to the leading edge between an inner edge of the tip rail on the suction side and an inner edge of the tip rail on the pressure side and may form a trailing edge region recess proximate to the trailing edge. The gap reduces stress during use operation of a gas turbine engine in which the tip rail is attached to a turbine airfoil. | 09-20-2012 |
| 20130028750 | COMPRESSOR ROTOR - A compressor rotor is provided having a rotor blade groove thereon and also includes a device for cooling the rotor in the region of a compressor rotor exit. Efficient cooling is achieved by the compressor rotor, in a compressor rotor exit region, having a ring which is pushed concentrically, and at a distance, forming a gap, over a rotor disk of the rotor, and is fastened on the disk, by the rotor blades, in the compressor rotor exit region, being inserted into corresponding grooves on the ring and being retained there, by first means for directing an axial flow of cooling medium from the compressor rotor exit through the ring, and by second means for deflecting the cooling medium which issues from the ring such that the cooling medium flows back in the axial direction through the gap between the ring and the rotor disk, encompassed by the ring. | 01-31-2013 |
| 20130034451 | GAS TURBINE ENGINE - A gas turbine engine comprises a hollow rotor including a plurality of rotor segments stacked and coupled together in a direction of its center axis and forming at least one of a compressor and a turbine; and a pipe unit inserted into an inner space of the rotor in the center axis direction. In the gas turbine engine, a weight distribution of the pipe unit within an axial transverse section is set eccentric with respect to the center axis of the rotor. In this way, a gas turbine engine which is high in performance and reliability is provided, in which a pipe provided in an inner space of the rotor to transport a cooling medium or lay out a cable, etc., is prevented from whirling. | 02-07-2013 |
| 20130071254 | TURBINE BLADES AND METHODS OF FORMING MODIFIED TURBINE BLADES AND TURBINE ROTORS - Turbine blades and methods of forming modified turbine blades and turbine rotors for use in an engine are provided. In an embodiment, by way of example only, a turbine blade includes a platform and an airfoil. The platform includes a surface configured to define a portion of a flowpath, and the surface includes an initial contour configured to plastically deform into an intended final contour after an initial exposure of the blade to an operation of the engine. The airfoil extends from the platform. | 03-21-2013 |
| 20130121842 | PROPELLER / TURBINE BLADE POWER CHANNEL - The disclosed propeller/turbine blade enhancement will be used in the moving fluid kinetic energy conversion field. This power channel blade enhancement will increase the kinetic energy conversion of propeller/turbine blades by collecting, redirecting, channeling, compressing and then expelling a portion of the moving fluid that would otherwise be lost. The power channel's multiple interactions with the moving fluid impacting the blade will produce known fluid hydraulic actions upon the enhanced propeller/turbine blades. These known fluid hydraulic actions will impart more rotational energy to the power channel enhanced blades than previous propeller/turbine blades. | 05-16-2013 |
| 20130202451 | SAFETY PROPELLER - A propeller ( | 08-08-2013 |
| 20130236329 | ROTOR BLADE WITH ONE OR MORE SIDE WALL COOLING CIRCUITS - A rotor blade for a gas turbine engine includes an airfoil and a cooling microcircuit. The airfoil includes a first side wall, a second side wall and a tip endwall, where the first side wall and the second side wall extend to and cooperate to form the tip endwall, defining a main cavity between the first side wall and the second side wall. The cooling microcircuit includes a microcircuit cavity, an inlet, a side wall outlet and a tip outlet. The microcircuit cavity is embedded within the first side wall, and the inlet extends from the main cavity to the microcircuit cavity. The side wall outlet extends from the microcircuit cavity to an exterior first side surface of the airfoil. The tip outlet extends from the microcircuit cavity to an exterior tip surface of the airfoil. | 09-12-2013 |
| 20130251538 | TRAILING EDGE COOLING - An airfoil includes a leading edge, a trailing edge, a suction surface, a pressure surface, a cooling passageway, and a plurality of oblong pedestals. The suction surface and the pressure surface both extend axially between the leading edge and the trailing edge, as well as radially from a root section to a tip section of the airfoil. The cooling passageway is located between the suction surface and the pressure surface. The oblong pedestals connect the suction surface to the pressure surface at the trailing edge of the airfoil. | 09-26-2013 |
| 20130287591 | ROTOR BLADE FOR VERTICAL AXIS WIND TURBINE - One embodiment of a rotor blade for a vertical axis wind turbine comprises a central portion having a central axis and at least two blade members. The blade members each have a proximal end attached to the central portion, a high drag side and a low drag side that is opposite the high drag side. Each of the blade members also includes an uncovered vent comprising an opening through the blade member that provides an unobstructed path for airflow through the blade member. In one embodiment, a pair of fins are positioned adjacent the opening of the vent and extend from the high drag side of the blade member. | 10-31-2013 |
| 20130343904 | ROTARY DEGASSERS AND COMPONENTS THEREFOR - Disclosed are degassers, couplings, impeller shafts and impellers for use in molten metal. One such coupling transfers gas into an impeller shaft, the coupling having a smooth, tapered internal surface to align with a corresponding surface on the impeller shaft and help prevent gas leakage and to assist in preventing damage to the impeller shaft. Improved impellers for shearing and mixing gas are also disclosed, as is a degasser including one or more of these components. | 12-26-2013 |
| 20140086756 | INTERNALLY COOLED GAS TURBINE ENGINE AIRFOIL - A gas turbine engine airfoil has a hollow airfoil section extending chordwise between a leading edge and a trailing edge. The airfoil has a leading edge cooling passage and a separate serpentine passage for cooling a remaining portion of the airfoil. The serpentine passage has at least three segment serially interconnected in fluid flow communication. The leading edge cooling passage and the serpentine cooling passage have separate coolant inlets. The coolant inlet of the serpentine passage comprises a primary inlet branch connected in fluid flow communication with a first one of the segments of the serpentine passage and a secondary inlet branch connected in flow communication with a last one of the segments, thereby providing for a portion of the flow passing through the coolant inlet of the serpentine passage to be directly fed into the last segment of the serpentine passage. | 03-27-2014 |
| 20140140858 | COMPRESSOR BLADE WITH NOZZLE - A compressor blade having at least one nozzle for ejecting fluid, in particular for ejecting water, is provided. The at least one nozzle is produced as a laminar structure in which, in particular, individual layers such as metal sheets are laid on top of each other, and has differently orientated channel sections of a channel between an inlet and an outlet, wherein the metal sheets have cutouts corresponding to the channel sections. The nozzle geometry makes it possible to prevent the formation of droplets as water exits a compressor blade. | 05-22-2014 |
| 20140147286 | TURBOMACHINE ROTOR DISK - A rotor disk for a turbomachine, which is connectable to at least one rotor blade and/or a shaft of the turbomachine, having at least one borehole, which has an elliptical inlet opening having a first passage cross-sectional area and an elliptical outlet opening having a second passage cross-sectional area, so that the second passage cross-sectional area is smaller than the first passage cross-sectional area. | 05-29-2014 |
| 20140255205 | Reduced Drag System for Windmills, Fans, Propellers, Airfoils and Hydrofoils - Airfoil and hydrofoils systems with structures having a surface texture defined by fractal geometries are described. Raised portions or fractal bumps can be included on the surfaces, forming a surface texture. The surface textures can be defined by two-dimensional fractal shapes, partial two-dimensional fractal shapes, non-contiguous fractal shapes, three-dimensional fractal objects, and partial three-dimensional fractal objects. The surfaces can include indents having fractal geometries. The indents can have varying depths and can be bordered by other indents, or bumps, or smooth portions of the airfoil or hydrofoil structure. The fractal surface textures can reduce vortices inherent from airfoil and hydrofoil structures. The roughness and distribution of the fractal surface textures reduce the vortices, improving laminar flow characteristics and at the same time reducing drag. The systems are passive and do not require applied power. | 09-11-2014 |
| 20140286789 | AIRFLOW GENERATION DEVICE AND WIND POWER GENERATION SYSTEM - An airflow generation device of an embodiment has a main body and a voltage application unit. The main body has a base formed of an insulating material and provided with a first electrode and a second electrode. The voltage application unit generates an airflow by applying voltage between the first electrode and the second electrode. Here, the main body is formed to include a portion which gradually decreases in thickness from a center portion to an end portion. | 09-25-2014 |
| 20140301864 | WIND TURBINE BLADE - A wind turbine blade is described having noise reduction features. The blade has a plurality of projecting elements provided at the blade trailing edge to reduce the scattering noise produced during operation of the blade. The blade further comprises a fluid injection system which can inject a fluid into the turbulent airflow at the trailing edge of the blade, to absorb some of the turbulent kinetic energy at the trailing edge and accordingly further reduce the levels of output noise produced by the blade. In a further aspect, the fluid injection system may be adjustable to inject fluid in an upstream direction, i.e. against the oncoming airflow, in order to provide an increased absorption of turbulent kinetic energy from the incident airflow, and accordingly to provide improved noise-reduction characteristics. | 10-09-2014 |
| 20150064018 | TURBINE BLADE AND ASSOCIATED METHOD FOR PRODUCING A TURBINE BLADE - A turbine blade is provided, having a fastening section, a platform, and a blade, which follow one another along a longitudinal axis of the turbine blade, wherein the platform, in radial relation to the longitudinal axis, has an inner platform part and an outer platform part, wherein the outer platform part is designed as a closed platform frame that encloses the outer edge of the inner platform part. An associated method for producing a turbine blade is also provided. | 03-05-2015 |
| 20150086380 | WIND POWER GENERATION DEVICE - A wind power generation device, comprising a base ( | 03-26-2015 |
| 20150098834 | All-Supersonic ducted fan for propelling aircraft at high subsonic speeds - A supersonic fan has at least two fan blades extending radially from a rim surface of a hub and is circumscribed by a duct. An inboard leading edge having an inboard sweep angle rotates at approximately Mach 1 or greater. A low-pressure zone generates propulsion. An inboard flow regime may migrate outboard from the rim surface and contaminate the low-pressure zone, reducing propulsion. An outboard leading edge having an outboard sweep angle extends radially from the inboard leading edge to form an apex. The inboard and outboard sweep angles are each at least approximately 30 degrees and in the opposite direction. An inboard vortex forming near to and as a result of the apex trails circumferentially across the fan blades and is positioned to substantially confine the inboard flow regime to be inboard of the apex, thereby preserving the low-pressure zone and increasing propulsion for the supersonic fan. | 04-09-2015 |
| 20150308449 | GAS TURBINE ENGINE COMPONENT WITH BRAZED COVER - A component according to an exemplary aspect of the present disclosure includes, among other things, a body comprised of a first material, a cover attached to the body and comprised of a second material, and a braze alloy employable to braze the cover to the body and comprised of a third material. The first material, the second material and the third material are different materials. | 10-29-2015 |
| 20150330234 | Expandable Boundary Layer Turbine - A boundary layer turbine that uses flat disks that can be precision cut at low cost is more cost-effective to construct and maintain than conventional turbines. Bolt-on hub design significantly decreases breakage and distortion. Delta-wing shaped center spacers and flow enhancing, teardrop-shaped outer spacers further increase durability by providing improved support for the disks while minimizing the disturbance of the natural flow of fluids. Use of endplates with heavy outer rims results in turbines with greater gyroscopic effect and greater mass for kinetic energy storage. A disk-directed inlet valve and focused inlet nozzle system increases efficiency by directing flows to the individual disks valve in a low friction containment case. The directed flow tuned inlet nozzle system further increases efficiency. Coating the inner case of the turbine's enclosure with Teflon or similar materials reduces friction and further improves efficiency. | 11-19-2015 |
| 20150337860 | COMPOSITE COOLING FAN - A composite cooling fan includes a frame, a fan blade and a lateral valve. The frame has an air hole penetrating the frame and a lateral air outlet locating on one side of the frame and connecting with the air hole. The fan blade is disposed in the air hole and includes an impeller, multiple axial blades surrounding the impeller and multiple centrifugal blades surrounding the axial blades. The lateral valve is disposed on the lateral air outlet and includes a valve stem and a switch baffle linked with the valve stem. The valve stem is used for making the switch baffle at the lateral air outlet open or close. | 11-26-2015 |
| 20160069206 | STEAM TURBINE - A steam turbine includes a turbine body; a steam flow passage; a regulating valve which regulates opening and closing of the steam flow passage with a linear motion; a switching drive mechanism which drives the regulating valve; an electronic governor which controls at least the switching drive mechanism; and a controller unit. The switching drive mechanism has an electric motor which rotates when supplied with power, a conversion mechanism which converts a rotary motion of the electric motor into a linear motion of the regulating valve, and a brake which brakes the rotary motion of the electric motor. At least one of the controller unit and the electronic governor performs control such that the brake is actuated and the position of the regulating valve is maintained when at least one of the electric motor and the controller unit breaks down. | 03-10-2016 |
| 20160102651 | TURBINE BLADES AND SYSTEMS WITH FORWARD BLOWING SLOTS - A blade for use in a wind turbine comprises a pressure side and suction side meeting at a trailing edge and leading edge. The pressure side and suction side provide lift to the turbine blade upon the flow of air from the leading edge to the trailing edge and over the pressure side and suction side. The blade includes one or more openings at the suction side, in some cases between the leading edge and the trailing edge. The one or more openings are configured to provide a pressurized fluid towards the leading edge of the blade, in some cases at an angle between about 0° and 70° with respect to an axis oriented from a centerline of the blade toward the leading edge. | 04-14-2016 |
| 20160123154 | ENGINE COMPONENT FOR A TURBINE ENGINE - An engine component for a turbine engine includes a particle collector having a substrate configured to retain at least some particles from a particle-laden stream passing through a portion of the engine. A fluid bypass around the substrate of the collector enables the particle-laden stream to bypass the substrate if the substrate is filled with particles. | 05-05-2016 |
| 20160186771 | Rotor hub assembly, electric fan - The invention relates to a rotor hub assembly for an electric fan, in particular for a radiator fan of a motor vehicle, comprising a hub cup, which rotates during operation and which has air outlet guides on the inside of the hub cup, which air outlet guides are arranged and shaped in such a way that the air outlet guides guide and accelerate cooling air, wherein a magnetic return cup is arranged inside the hub cup, which return cup has air passage openings, which, together with the air outlet guides, form continuous air outlets for a cooling air flow from the pressure side to the vacuum side of the fan. The invention further relates to an electric fan having such a rotor assembly. | 06-30-2016 |
| 20160194963 | ROTOR FOR A THERMAL TURBOMACHINE | 07-07-2016 |
| 20100111703 | SAFETY PROPELLER - A propeller ( | 05-06-2010 |
| 20100303634 | FLUID DYNAMIC SECTION HAVING ESCAPELET OPENINGS FOR REDUCING INDUCED AND INTERFERENCE DRAG, AND ENERGIZING STAGNANT FLOW - A fluid dynamic section provides one or more fixed size escapelets through a foil body to reduce the induced and interference drag caused by trailing vortices and similar wake turbulence. The escapelets, which can be provided in both aerodynamic and hydrodynamic structures, such as wings, tail sections; rotary blades, guy wire frames, wing sails, and various underwater keels and wing keels. The escapelets transfer energy from an inlet located in the high-pressure surface of the foil or foil body to an outlet located in the lower-pressure surface, allowing energy that would normally form a vortex at the tip of the foil to be redirected and dissipated in a beneficial way. As a result, drag is reduced and fuel economy is increased, while at the same time increasing the authority of ailerons and similar flight control surfaces, allowing aircraft that were not previously spin recovery rated to become spin recoverable. | 12-02-2010 |
| 20150132146 | PROPULSION MECHANISM - A propulsion mechanism ( | 05-14-2015 |
