Class / Patent application number | Description | Number of patent applications / Date published |
416243000 | Concave surface | 43 |
20080206065 | TURBINE BUCKET - A turbine bucket is provided that can make centrifugal stress acting on a blade or dovetail not greater than a limit value of a material and that is provided with a shape of a blade root that can ensure a steam passage even if the blade is increased in length in order to increase an exhaust area. | 08-28-2008 |
20090257883 | COOLING FAN IMPELLER - An impeller of a centrifugal fan includes a hub and a plurality of blades arranged on and around the hub. Each of the blades includes a root portion and a tip portion. The tip portion of each of the blades has a concave surface and a convex surface in rear and front sides thereof respectively. In a rotational direction of the impeller, the tip portion of a rear blade protrudes towards a front blade. | 10-15-2009 |
20090257884 | WIND TURBINE BLADE AND ASSEMBLY - A blade is disclosed for use in a wind turbine, with the blade having a longitudinal axis for extending radially outwardly from a center of rotation of the blade on the wind turbine. The blade has a front side with a front surface for orienting in a windward direction and a rear side with a rear surface for orienting in a leeward direction. The blade has a profile taken in a plane oriented substantially perpendicular to the longitudinal axis of the blade. The profile of the blade has a leading edge and a trailing edge. The profile is characterized by a camber ratio, and the camber ratio of the profile is greater than or equal to approximately 4%. | 10-15-2009 |
20100014984 | Turbofan gas turbine engine fan blade and a turbofan gas turbine fan rotor arrangement - A fan blade comprises a root portion and an aerofoil portion. The aerofoil portion has a leading edge, a trailing edge and a tip remote from the root portion. A concave pressure surface extends from the leading edge to the trailing edge and a convex suction surface extends from the leading edge to the trailing edge. A portion of the tip of the aerofoil portion between the leading edge and the trailing edge of the aerofoil portion is thinner than the remainder of the tip. The portion of the tip of the aerofoil portion is spaced from the leading edge and is spaced from the trailing edge. The portion of the tip of the aerofoil portion has a recess such that the portion of the tip of the aerofoil portion is thinner than the remainder of the tip. The recess is arranged on the concave pressure surface of the aerofoil portion. This reduces vibrations of the fan blade. | 01-21-2010 |
20100054951 | Dual Zone Amplifier Turbine Blade - The Dual Zone Amplifier Turbine Blade is for use on a vertical axis wind turbine. It is a 40 degree conic with a three sided opening at the base region for wind collection. The 40 degree conic turbine blade allows for amplification of collected wind and minimum air resistance to foreword movement. The curved, three sided opening at the base region allows for maximum collection of wind. When attached to a spoked hub in balanced plurality for the purpose of turning an electric generator or other device, an efficient collection, amplification and transfer of wind energy is attained. | 03-04-2010 |
20100158696 | CURVED PLATFORM TURBINE BLADE - A turbine blade includes an airfoil and integral platform at the root thereof. The platform is contoured in elevation from a ridge to a trough, and is curved axially to complement the next adjacent curved platform. | 06-24-2010 |
20100158697 | MULTI-ROTOR VERTICAL AXIS WIND TURBINE - New aerodynamically improved rotors for use in vertical axis wind turbine (VAWTs) are disclosed. In some examples, the VAWT rotors include one or more blades with an aerodynamic front shape with low drag coefficient and a blunt or concave back shape that effectively catches the wind. Example rotors can be used by themselves or in conjunction with vertically attached rotating airfoils. The new rotors add to the overall energy production while acting as supports for the vertical airfoils. Furthermore, the new rotors provide energy in low wind speed conditions where the vertical airfoils are ineffective and can act as jump starters for the vertical airfoils. Guy wire structures for stabilizing VAWTs are also disclosed. The structures allow for reduced construction costs for a given tower height compared to conventional HAWTs and allows for taller towers for a given construction cost. The overall stability under wind gusts is improved by the guy wire design | 06-24-2010 |
20100247325 | WIND TURBINE BLADE AND METHOD FOR MANUFACTURING A WIND TURBINE BLADE - Wind turbine blade ( | 09-30-2010 |
20100284819 | 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. | 11-11-2010 |
20110052410 | POWDER METAL SCROLLS - Scrolls made from one or more near-net shaped powder metal processes either wholly or fabricated together from sections. Both “conventional” press and sinter methods and metal injection molding methods will be described. | 03-03-2011 |
20110070094 | BLADE FOR A DEVICE FOR GENERATING ENERGY FROM A FLUID FLOW - A blade for a device for generating energy from a fluid including a driving surface inside which a fluid is intended to flow in order to rotate the blade about a rotational axis {right arrow over (X)} | 03-24-2011 |
20120082560 | VERTICAL SPIRAL ANGLE WIND TURBINE - The present device is a vertically oriented wind turbine blade having a rectangular curvilinear shaped blade which includes a top edge, a bottom edge, an outer edge, a helical inner edge, an inner surface and an outer surface. The blade's top edge is curved and defines a radius R and the helical inner edge defines an angle theta relative to a vertical reference line. The blade further includes an L shaped outer rib with a transverse leg mounted to the inner surface and extending along the outer edge, the outer rib also includes a perpendicular leg extending perpendicular to the transverse leg, | 04-05-2012 |
20120100006 | BLADE - A turbomachine blade having features arranged to initiate bending of the leading edge towards the pressure surface upon impact of a foreign object on the leading edge. The features may be features weaker than the material of the leading edge located on the pressure surface side of a mid-thickness line. By causing the leading edge to bend towards the pressure surface on impact the volume of the foreign object, typically a bird, that passes over the suction surface is reduced. | 04-26-2012 |
20120114498 | FAN STRUCTURE - A fan structure is provided, including a hub and a plurality of blades surrounding the hub. Each blade has a first segment connected to the hub and a second segment extended outwardly from the first segment. A first surface is formed between the first segment and the hub, and a second surface is formed between the first and second segments. The first and second surfaces respectively have a first and second setting angle relative to a base plane of the fan structure, wherein the first setting angle exceeds the second setting angle. | 05-10-2012 |
20120121432 | IMPELLER OF CENTRIFUGAL COMPRESSOR - Provided is an impeller of a centrifugal compressor including: a hub; a plurality of blades protruding from a surface of the hub, wherein a passage is formed by the hub and a blade being adjacent with the hub, so that a fluid, flowing in along an axial direction at an inner circumferential side in a radial direction, is flowed out toward an outer circumferential side in a radial direction; each of the plurality of blades includes a main body part and a leading edge, the main body part including a pressure side and a suction side; an angle between a component central line of the main body part and the axial direction increases from an inner end toward an outer end; and a radius of curvature at a central position, intersecting with the component central line of the leading edge, decreases from the inner end toward the outer end. | 05-17-2012 |
20120163988 | GAS TURBINE ENGINE AIRFOIL SHAPED COMPONENT - A gas turbine engine airfoil shaped component is disclosed including in one form a compressor blade or vane having a tip portion capable of producing a relatively low pressure near the leading edge of the tip to induce a local jet of stream-wise momentum flow. In one form the tip portion includes a camber angle distribution that produces relatively large change in camber angle near the leading edge but relatively flat distribution for remainder of blade. In one form the tip portion includes relatively large change in camber angle near trailing edge. | 06-28-2012 |
20120177502 | ROTOR FOR A WIND POWER GENERATOR - A rotor according to a preferred embodiment of the invention has at least one blade arranged at a hub of the rotor, wherein the blade has a curvature between its leading edge and its trailing edge which curvature has a first convex surface and an opposite second concave surface, wherein the first surface is to be arranged against the direction of the wind striking the blades. The convex profile of the first surface and the concave profile of the opposite second surface are spaced by the thickness of the blade which is preferably constant. The hub is arranged at the rotational axis. | 07-12-2012 |
20120183411 | AEROFOIL BLADE FOR AN AXIAL FLOW TURBOMACHINE - An exemplary aerofoil blade for an axial flow turbomachine has a radially inner platform region, a radially outer tip region, an axially forward leading edge, and an axially rearward trailing edge. The aerofoil blade has a pressure surface which is convex in a radial direction, and a suction surface which is concave in the radial direction. The axial width (W) of the aerofoil blade can vary parabolically between maximum axial widths (W | 07-19-2012 |
20120195767 | BLADE FOR A HELICOPTER ANTI-TORQUE DEVICE | 08-02-2012 |
20120230834 | COMPRESSOR BLADE FOR AN AXIAL COMPRESSOR - A compressor blade for an axially permeated compressor, preferably of a stationary gas turbine is provided. The camber line of the blade tip side profile of the blade of the compressor blade includes at least two inflection points for reducing radial gap losses. By means of two inflection points, there is a concavely designed suction side contour segment in a segment from 35% to 50% for the suction side contour, and a convexly implemented pressure side contour segment for the pressure side contour. It is possible by means of the geometry to generate low-loss gap vortices, in order to increase the overall efficiency of an axial compressor including the compressor blades. | 09-13-2012 |
20120230835 | CONCAVE BLADE FOR A WIND GENERATOR - The present invention relates to a concave blade for a wind generator, formed by a body ( | 09-13-2012 |
20130004329 | FAN, MOLDING DIE, AND FLUID FEEDER - A centrifugal fan includes a plurality of fan blades arranged spaced apart from each other in a circumferential direction. The fan blade has an inner edge portion disposed on an inner peripheral side and an outer edge portion disposed on an outer peripheral side. The fan blade has a blade surface including a pressure surface and a suction surface. When cut along a plane orthogonal to a rotation axis of the fan, the fan blade has a blade cross section having concave portions formed at the pressure surface and the suction surface. A plurality of fan blades include fan blades having blade cross sections of different shapes. With such a configuration, the fan has an excellent air-blowing capacity while preventing noise. A molding die for use in production of the fan and a fluid feeder including the fan are also provided. | 01-03-2013 |
20130028748 | PROPELLER WITH REACTIONARY AND VACUUM FACES - A novel airfoil design comprising a reactionary front face that pushes into the flow of air with a high angle of attack and a vacuum-producing face which forces the early separation of the flow of air from the top side of the airfoil, creating an area of high negative pressure which pulls upward, contributing to lift. | 01-31-2013 |
20130028749 | GUIDE BLADE OF A TURBOMACHINE - A guide blade of a turbomachine, in particular of a compressor, a blade of the guide blade without an inner shroud having a flow inlet edge, a flow outlet edge, a suction side, and a pressure side. The blade is formed by a plurality of blade sections stacked one on top of the other in the radial direction, and the centers of gravity of the blade sections extend along a stacking axis. The blade sections are stacked one on top of the other in the radial direction in such a way that, in a radially inner section of the blade adjacent to a radially outer section of the blade, the stacking axis has its single inflection point in its radial curvature, namely, between a first, radially inner subsection of the radially inner section in which the stacking axis has a concave curvature toward the pressure side, and a second, radially outer subsection of the radially inner section in which the stacking axis has a concave curvature toward the suction side. | 01-31-2013 |
20130045107 | PROPELLER BLADE - A propeller blade includes a body configured to extend radially from the hub of a propeller. The body can include a front surface, a back surface, a leading edge, and a trailing edge. The top of the body can form a tippet that generally transitions the front and back surfaces from extending in a generally radial direction to a generally axial direction. The tippet can reduce radial flow and force losses, redirect the radial flow in an axial direction, reduce the exit flow area of the propeller, and increase the inlet flow area of the propeller. The front surface of the blade can have a planar configuration that prevents or reduces the creation of low or negative pressure across the front surface of the blade and associated cavitation. | 02-21-2013 |
20130129524 | CENTRIFUGAL IMPELLER - A centrifugal impeller includes a hub and a plurality of impeller blades extending from the hub. Each impeller blade extends over a chord length between a leading end and a trailing end, over a span from a root at the hub to a tip end and over a thickness between a convex side and a concave side. The blades collectively or individually have profiles that define a circumferential pitch (CP) with regard to a spacing distance between the leading ends of neighboring ones of the blades and blade angles at positions along the convex side of each blade between the leading end and the trailing end. The blades have a solidity value (S) defined as CD/CP that is less or equal to 1.0 and the blade angles (α) of each blade increase from the respective leading end to the corresponding trailing end. | 05-23-2013 |
20130136621 | BLADING - A blading for a turbomachine, particularly for a gas turbine, wherein thickened areas and depressions are formed and disposed on a lateral wall having a plurality of blades such that at least one depression or thickened area is disposed at a blade pressure side and at least one thickened area or depression is disposed at a blade suction side for each blade of the plurality of blades. | 05-30-2013 |
20130142663 | FLUID INTERFACE DEVICE AND METHOD - A fluid interface device, such as an airfoil assembly, can include a device structure and at least one moveable band oriented such that the band moves in a direction of fluid flow. The at least one moveable band can be supported on the device structure such that an outer surface of the moveable band is exposed along the device structure and is capable of movement relative thereto such that a relative velocity can be maintained between the outer surface and the device structure. The fluid interface device can have a cross section that includes first and second boundary layer collision points disposed along one side of the device structure with at least one of said first and second boundary layer collision points formed by the endless band. An airplane, a wind turbine and a method are also included. | 06-06-2013 |
20130149167 | MARINE PROPELLER APPLICABLE TO ALL SPEED RANGES - An all speed range propeller includes a propeller hub and plural propeller blades having their shafts symmetrically connected with the propeller hub. Each propeller blade is divided into a first region and a second region from the propeller hub to an outer end. The first region and the second region are different in wing structure, and the wing cross-sectional area of the second region is smaller than that of the first region. Thus, in speed ranges that common ships navigate most frequently, the all speed range propeller of this invention can lower the influence of cavitation produced because of different speed ranges, able to maintain high efficiency in use and prevent the efficiency of the propeller from lowered exceedingly. | 06-13-2013 |
20130189117 | ROTOR WITH FLATTENED EXIT PRESSURE PROFILE - A rotor blade comprises an airfoil extending radially from a root section to a tip section and axially from a leading edge to a trailing edge, the leading and trailing edges defining a curvature therebetween. The curvature determines a relative exit angle at a relative span height between the root section and the tip section, based on an incident flow velocity at the leading edge of the airfoil and a rotational velocity at the relative span height. In operation of the rotor blade, the relative exit angle determines a substantially flat exit pressure ratio profile for relative span heights from 75% to 95%, wherein the exit pressure ratio profile is constant within a tolerance of 10% of a maximum value of the exit pressure ratio profile. | 07-25-2013 |
20130330204 | Turbine Rotor and Blade Assembly with Multi-Piece Locking Blade - The present application provides a turbine rotor and blade assembly for a steam turbine. The turbine rotor and blade assembly may include a rotor, a number of buckets positioned about the rotor, and a locking blade positioned about the rotor. The locking blade may include a multi-piece configuration. | 12-12-2013 |
20130336801 | ROTATING AIRFOIL COMPONENT WITH PLATFORM HAVING A RECESSED SURFACE REGION THEREIN - A rotating airfoil component of a turbomachine, in which the component has an airfoil aligned in a spanwise direction of the component, a shank, and a platform therebetween oriented transverse to the spanwise direction. The platform has an outer radial surface adjacent the airfoil, and at least one recessed region defined in its outer radial surface. The recessed region extends opposite the spanwise direction from a platform plane that contains portions of the outer radial surface that are upstream and downstream from the recessed region. The recessed region is contiguous with an end wall of the platform and extends therefrom toward the airfoil. The recessed region defines a surface shape whose boundary is contained by the platform plane, and has a profile shape that extends from the end wall toward the airfoil. The recessed region is sized and shaped to increase the stiffness of the platform. | 12-19-2013 |
20140017089 | AIRFOIL - An airfoil includes a leading edge, a trailing edge downstream from the leading edge, a pressure surface between the leading and trailing edges, and a suction surface between the leading and trailing edges and opposite the pressure surface. A first convex section on the suction surface decreases in curvature downstream from the leading edge, and a throat on the suction surface is downstream from the first convex section. A second convex section is on the suction surface downstream from the throat, and a first convex segment of the second convex section increases in curvature. | 01-16-2014 |
20140030110 | DIRECT DRIVE ROTATION DEVICE FOR PASSIVELY MOVING FLUID - The device is configured for moving a fluid within a gearbox. In one illustrative embodiment, the device includes a base portion coupled to a rotatable member within the gearbox. An inlet portion of the device is configured to draw the fluid from a reservoir portion of the gearbox. The device is configured to utilize a centrifugal force for moving the fluid from the inlet portion toward the base portion along an interior surface of a conical portion. In another illustrative embodiment, the device includes a conical portion having an external threaded portion configured to capture a fluid during a rotation of the device. In such an embodiment, the threaded portion is configured to utilize a centrifugal force for moving the fluid captured by the threaded portion along an exterior surface of the conical portion. | 01-30-2014 |
20140044553 | BLADE FOR A CONTINUOUS-FLOW MACHINE AND A CONTINUOUS-FLOW MACHINE - A blade for a continuous-flow machine is disclosed, especially an aircraft engine, whereby, starting from the middle section, the cross section of the blade tip is reduced with respect to the middle section, at least over a front partial section in the direction of the leading edge and over at least a rear section in the direction of the trailing edge, and a continuous-flow machine having at least one row of blades including such blades is also disclosed. | 02-13-2014 |
20140234120 | Blade, Wind Turbine and Wind Power Generating System - A blade comprises a first blade surface, a second blade surface forming the reverse surface of the first blade surface, a front edge portion connected to the front end of the first blade surface and the front end of the second blade surface and formed in a curved shape convex toward the travelling direction, and a back edge portion connected to the back end of the first blade surface and the back end of the second blade surface extending toward the opposite of the travelling direction, and formed in an acute angle, and the blade is formed to be curved in an arc viewed from the side of the travelling direction. | 08-21-2014 |
20140241901 | IMPELLER - An impeller for increasing the pressure of a fluid circulating in an annular fluid path, the impeller comprising: a plurality of centrifugal compressor vanes circumferentially interspaced around the axis of the annular fluid path, the plurality of compressor vanes extending from an axially-oriented inlet to a radially-oriented outlet, and each having an inner edge and a free edge, the free edge of the plurality of compressor vanes coinciding with an outer limit of the annular fluid path, and a hub having a solid-of-revolution shape centered around an axis, the hub having an outer hub surface forming an inner limit to the annular fluid path and to which the inner edge of the plurality of centrifugal vanes is secured, the outer hub surface having a portion which leans forward, forming an axial recess therein. | 08-28-2014 |
20140348661 | BLADE ROW, BLADE AND TURBOMACHINE - A blade row for a turbomachine is disclosed. The blade row has an inner lateral wall and an outer lateral wall for bordering a hot gas channel in the turbomachine through which hot gas passes. At least one of the lateral walls has a rounded lateral wall front edge, which is provided with a circumferentially asymmetrical edge contouring that is elliptical or is comprised of one or more segments of a circle. | 11-27-2014 |
20150118061 | Radial Compressor - A radial compressor has at least one compressor stage. The compressor stage includes: an impeller having moving blades on a rotor side arranged in a flow channel of the compressor stage. The flow channel is bounded by a hub contour and a housing contour or cover disc contour. Each moving blade has a flow inlet edge and a flow outlet edge. In the region of the compressor stage on the hub contour of the flow channel, initially a curvature change from a first concave curvature into a convex curvature and following this a curvature change from the convex curvature into a second concave curvature is formed; and/or on the housing contour or cover disc contour of the flow channel, initially a curvature change from a first convex curvature into a concave curvature and following this a curvature change from the concave curvature into a second convex curvature is formed. | 04-30-2015 |
20150337854 | PROPELLER BLADE - A propeller blade includes a body configured to extend radially from the hub of a propeller. The body can include a front surface, a back surface, a leading edge, and a trailing edge. The top of the body can form a tippet that generally transitions the front and back surfaces from extending in a generally radial direction to a generally axial direction. The tippet can reduce radial flow and force losses, redirect the radial flow in an axial direction, reduce the exit flow area of the propeller, and increase the inlet flow area of the propeller. The front surface of the blade can have a planar configuration that prevents or reduces the creation of low or negative pressure across the front surface of the blade and associated cavitation. | 11-26-2015 |
20160061042 | ROTARY AIRFOIL - A rotary airfoil in a gas turbine engine is provided. The airfoil includes opposed pressure and suction sides joined together at chordally opposite leading and trailing edges. The pressure and suction sides extend in a span direction from a root to a tip. An axial component of a center of gravity of a cross-section taken chordally toward the tip of the airfoil being upstream relative to an axial component of a center of gravity of a cross-section taken chordally toward the root of the airfoil. A method for forming such blade is also presented. | 03-03-2016 |
20160061217 | COMPRESSOR AIRFOIL - A compressor airfoil in a gas turbine engine is presented. Opposed pressure and suction sides are joined together at chordally opposite leading and trailing edges. The pressure and suction sides extend in a span direction from a root to a tip of the airfoil. A leading edge sweep angle is defined relative to a tangent to the airfoil and flow velocity vector at a point on the leading edge. A leading edge dihedral angle is defined relative to the tangent to the airfoil and a vertical at the point on the leading edge. A ratio of the leading edge sweep angle to the leading edge dihedral angle being smaller than 1. A method of forming such airfoil is also presented. | 03-03-2016 |
20160376894 | Spiral turbine blade having at least one concave compartment that may be rotated by a moving fluid for electrical energy generation - A spiral turbine blade having at least one concave compartment that is rotatable by a moving fluid for the generation of electricity is provided. A spiral turbine blade is aligned so that the axis of rotation is generally parallel to the mean direction of a moving fluid. Attached to the intake-facing side of the at least one spiral turbine blade are concave compartments comprised of an intake void, interior space, and exit void. The concave compartments are oriented to capture an additional range of velocity imaginary vectors; specifically those aligned via vortex inducing elements, such as spiral depressions on a conical intake shroud, thereby augmenting the torque induced the spiral turbine blade, and thus improving the conversion efficiency and electrical energy output. | 12-29-2016 |