Class / Patent application number | Description | Number of patent applications / Date published |
416232000 | Hollow | 64 |
20080253898 | DAMPER CONFIGURED TURBINE BLADE - A turbine rotor blade includes a hollow airfoil joined to a platform and dovetail. A main flow channel extends longitudinally in span through the blade and is bound chordally by opposite partitions transversely bridging opposite sidewalls of the airfoil. A damper rib and transversely opposite damper pad are arranged together in a plurality of pairs spaced longitudinally apart in the airfoil and chordally positioned intermediate to the partitions to provide unobstructed forward and aft portions of the flow channel for channeling a coolant therethrough. The damper ribs and pads are configured to receive a wire damper through the channel to locally dampen vibration while minimizing obstruction of the coolant flow therethrough. | 10-16-2008 |
20090035148 | Wind Turbine Blade Drainage - A wind turbine includes a tower supporting a drive train with a rotor, at least one hollow blade extending radially from the rotor; a drain hole arranged in a tip portion of the blade; a baffle, arranged inside the blade and inboard of the drain hole, for impeding a flow of particulate matter to the drain hole; a flexible drain conduit arranged inside the blade for connecting to the drain hole; and a non-flexible drain conduit arranged inside the blade for connecting to the flexible drain conduit, the non-flexible conduit having a plurality of openings for receiving fluid from inside the blade. | 02-05-2009 |
20090110559 | Submersible mixing propeller - An aerating propeller for attaching to the end of a drive shaft includes blades having a chamber to receive a flow of fluids from a conduit in a drive shaft. A trailing face of the blade includes a first opening into the chamber to permit the flow of fluids in the chamber to exit the propeller and a tip of the blade includes a second opening extending into the chamber to permit the flow of fluids in the chamber to exit the propeller. The first opening of the first blade is aligned generally in the same plane with the leading face of the second blade which follows the first blade when the propeller is rotated. | 04-30-2009 |
20100014980 | Turbine blade - There is described a turbine blade with an aerodynamically profiled blade leaf which is produced from two assembled shell elements. The shell elements forming the suction-side and the pressure-side blade leaf wall have been assembled by means of a high-temperature high-pressure bonding process and, under certain circumstances, may come apart at the blade tip. In order to prevent this, in the region of the blade leaf tip, a cramp is provided which hooks the two blade walls together with one another with a form fit. | 01-21-2010 |
20100021308 | Aerofoil and method of making an aerofoil - An aerofoil | 01-28-2010 |
20100202890 | TURBINE OF A GAS TURBINE - A turbine of a gas turbine, in particular of a gas turbine aircraft engine, having a rotor that has at least one moving blade ring and having a stator that has at least one guide blade ring, moving blades of the, or each, moving blade ring and/or guide blades of the, or each, guide blade ring being fashioned as hollow blades having at least one cavity, wherein on at least one side of at least one moving blade and/or guide blade fashioned as a hollow blade, in a blade wall holes are made that connect the, or each, cavity to the surrounding environment of the respective moving blade and/or guide blade, so that the respective cavity can be used as a resonator or sound muffler in order to reduce the sound radiated by the turbine during operation. | 08-12-2010 |
20100209255 | AEROFOIL STRUCTURE AND A METHOD OF MAKING A RIB FOR AN AEROFOIL STRUCTURE - An aerofoil structure comprises first and second opposed skin components which are joined together and spaced apart by a pair of opposed spar components. The skin components have respective outer and inner surface profiles. The skin and spar components define a space envelope and a rib is arranged within the space envelope. The rib comprises a rib body and a series of rib feet. The rib feet comprise a leg and a rib foot plate. The rib foot plate is dimensioned, positioned and angled so as to conform to the inner surface profile of the skin component against which it is intended to be arranged. | 08-19-2010 |
20100226781 | METHOD OF MANUFACTURING AN AEROFOIL - A method of manufacturing an aerofoil structure capable of being diffusion bonded and superplastically formed to create a substantially hollow cavity within the aerofoil structure, the method comprising: providing a metallic plate for forming the aerofoil structure; joining mounting elements to opposing end surfaces of said metallic plate; dividing said plate along a plane extending substantially in a span-wise direction so as to produce two metallic panels each with one of said mounting elements joined thereto; assembling the two metallic panels so that the surfaces of the panels opposite to the surfaces which have been divided are facing each other; and joining the two metallic panels to one another to form the aerofoil structure; wherein the mounting elements are joined to one another to form the root of the aerofoil. | 09-09-2010 |
20100232975 | TURBINE BLADE PLATFORM - A turbine blade assembly is provided. The turbine blade assembly comprises a turbine blade comprising a cavity, and a blade platform supporting the turbine blade, the cavity extending into the blade platform. The blade platform comprises an upper surface adjacent the turbine blade and a lower surface comprising a first rib, the cavity extending into the first rib, the first rib coupled to the lower surface, tapering as it extends away from the turbine blade, and comprising a first port extending from the cavity to the upper surface. | 09-16-2010 |
20110020132 | DECOMPRESSION MACHINE (SUDARSHAN CHAKRA)SU [good], DARHAN [looking;appearance] CHAKRA [wheel] - A decompression machine to be called SUDARSHAN CHAKRA is a better efficiency of energy conversion method than prior arts i.e. turbine, internal combustion engine & steam engine. Gas or liquid containing intermolecular forces from anywhere is harnessed & released intra-corporally & sequentially to get discharged tangentially from the blades which absorb the momentum of the propellant by pressure drops &/or velocity rises, in order to produce torque force resulting into rotations of axle, which can drive any other machine for production or transfer of energy. This is an action& reaction turbine. Here the idea is to produce circular motion from natural linear motion of the propellants like wind, gas, steam, water, hydrocarbon Etc. | 01-27-2011 |
20110027097 | METHOD FOR MANUFACTURING A HOLLOW BLADE - A method for manufacturing a hollow blade for a turbomachine including drilling channels into a blank of the blade, placing inserts into the channels, forging the blank, and removing the inserts by chemical dissolution, and the blade is an aluminum alloy and the inserts are a copper alloy. | 02-03-2011 |
20110076151 | METHOD AND SYSTEM FOR FOCUSED ENERGY BRAZING - A method and system that includes generation of an energy beam. The energy beam may be generated from a focused energy source. Additionally, the energy beam may be directed towards a pre-sintered preform. The pre-sintered preform may be made of a braze material and may seal a hole that may be located in a turbine component. | 03-31-2011 |
20110182744 | METHOD OF FORMING A HOLLOW COMPONENT WITH AN INTERNAL STRUCTURE - A method of forming a hollow component with an internal structure from first and second panels includes the step of forming at least one protrusion on a surface of at least one of the first and second panels by a material deposition process. The first and second panels are assembled into a preform the panels being oriented such that each panel defines an interior and an exterior facing surface, with the at least one protrusion extending from an exterior facing surface of a panel. The preform is expanded against a die, such that the at least one protrusion is transferred from the exterior surface of a panel to the interior surface of a panel so as to define an internal structure. Forming the at least one protrusion may include encapsulating an elongate member on the surface of a panel by a material deposition process. | 07-28-2011 |
20110206531 | EFFICIENT LOW-COST WIND ENERGY USING PASSIVE CIRCULATION CONTROL - Methods, systems, and apparatuses for efficient low-cost wind energy improvements using passive circulation control including, for instance, a fixed-pitch blade having a hub mountable end, a tip end, a blade body between the hub mountable end and the tip end of the fixed-pitch blade, and a channel interior to the blade body having an one or more ingress ports and one or more egress ports, according to one embodiment. For example, the one or more egress ports may be configured as a slit or a series of slits near the trailing edge so as to vent air out of the slit or slits at an angle to the local air flow traversing the blades airfoil. The one or more egress ports may be positioned longitudinally upon a top side or a bottom side of a trailing edge of the blade body such that the one or more egress ports vent air out the top or bottom side of the trailing edge of the blade body to reduce lift or increase lift respectively, for the fixed-pitch blade when under rotation upon a rotating hub via passive circulation control. | 08-25-2011 |
20110268576 | SYSTEM AND METHOD FOR INCREASING ENERGY CAPTURE BY WIND TURBINES - A blade is presented. The blade includes a proximal end and a distal end, and a pronounced camber running between the proximal end to the distal end, wherein the pronounced camber is located in proximity to a trailing edge and on a suction side of the blade, and an amplitude of the pronounced camber at a location varies between about 0.7% to about 1.4% of a chord's length of a cross-section of the blade at said location. | 11-03-2011 |
20110299995 | WIND TURBINE ROTOR BLADE JOINT - A blade joint for joining a first blade segment and a second blade segment, each having an aerodynamic profile, in a rotor blade is disclosed. The blade joint includes a first joint segment and a second joint segment each having an outer surface, an inner surface, and a thickness therebetween. The outer surface of each joint segment has an aerodynamic profile. The first joint segment and the second joint segment each further have a joint interface end, a blade interface end, and a length therebetween. The joint interface end of the first joint segment and the joint interface end of the second joint segment are configured to couple the first joint segment and second joint segment together. | 12-08-2011 |
20110305581 | CEILING FAN VANE STRUCTURE - An improved ceiling fan vane structure minimizes the weight of vanes to reduce to loads and achieve a power saving effect without affecting the structural strength of the vanes. The structural design includes the vanes, each being formed by combining a plurality of laminated plates, in which a middle laminated plate has a hollow slot, and a hollow chamber is created after the vanes are formed. The hollow chamber is maintained hollow or filled with a lightweight material such as glass fiber, cotton, or foam to achieve the effect of reducing the weight of the vanes, so that when a motor of the fan is operated to drive the vanes to rotate and produce air turbulence, the lightweight vanes can reduce the load of the motor to improve its operation efficiency, and achieve the effects of saving power and extending the lifespan of the motor. | 12-15-2011 |
20110318190 | WIND TURBINE BLADES WITH IMPROVED BOND LINE - A wind turbine blade includes an upper shell member and a lower shell member defining an internal cavity therebetween. The shell members are joined with a bond paste along bond lines at the leading edge and trailing edge of the blade. A seal member is disposed between the upper and lower shell members at a designed width of the bond line along at least one of the trailing or leading edges. The seal member comprises a dam on each of the lower and upper shell members that overlap in a mated configuration of the shell members. | 12-29-2011 |
20120213642 | SEGMENTED WIND ROTOR BLADE FOR WIND TURBINE GENERATOR SYSTEM AND ASSEMBLYING METHOD THEREOF - A segmented wind rotor blade for a wind turbine generator system and the assembling method thereof are disclosed. The segmented wind rotor blade includes a blade root section adjacent to a hub and at least one radial blade. Main girders are embedded inside both the blade root section and the radial blades. The blade root section and each radial blade are connected end to end through the main girders connecting one by one. The effects of great connection intensity and less aerodynamic loss can be realized by the segmented wind rotor blade. | 08-23-2012 |
20120219426 | BLADE FOR A TURBINE - The present disclosure provides a blade for a wind turbine. The wind turbine has an axis about which in use the blade rotates. The blade is arranged for orientation along the axis and has a predetermined twisted shape. The blade has a first and an opposite second side portion. The first and second side portions have edges and are coupled together at the edges. The first and second side portions are shaped such that a blade body is formed that is shaped such that maintaining the predetermined twisted shape of the blade is facilitated. | 08-30-2012 |
20120237356 | WIND TURBINE BLADE AND ITS PRODUCING METHOD - The present invention provides a wind turbine blade of hybrid material composition, wherein the blade comprises a structural box mainly made of a epoxy based prepreg and a shell manufactured by resin infusion technique using polyester or vinylester, and the box and the shell are bonded using an adhesive that is not a polyester, a vinylester and an epoxy. The present invention also provides a method for producing such a blade. | 09-20-2012 |
20120257984 | METHOD OF PRODUCING A COMPOSITE SHELL STRUCTURE - A method of producing a composite shell structure in the form of a wind turbine blade shell part having a reinforced fibre material embedded in a cured resin includes: providing a mould part having a contour defining the outer surface of the composite shell structure; providing a preform forming part shaped complementary to the mould part moulding surface; forming a preform of dry fibre material on the surface of the preform forming part; arranging the mould part and the preform forming part in an assembled position with the mould part moulding surface facing the preform forming surface; releasing the preform from the preform forming surface so that it is received on the mould part moulding surface; removing the preform forming part from the mould part; forming a mould cavity by means of a second mould part arranged on the preform; providing resin in the mould cavity; and curing the resin. | 10-11-2012 |
20120321480 | METHOD OF MANUFACTURING AN OBLONG SHELL PART AND SUCH SHELL PART - A plurality of fibre layers is stacked to form a fibre insertion extending in a longitudinal direction of the shell part to be manufactured, whereby a core element having a tapered edge section is arranged along the fibre insertion. The fibre layers are stacked so that the tapered edge section of the core element is wedged into the fibre insertion. The core element is composed by a first and a second core part that are arranged along each other. The first core part forms at least part of the tapered edge section of the core element. The surface of the first core part has a higher permeability to liquid polymer than that of the surface of the second core part so that, during infusion, liquid polymer penetrates the surface of the first core part more readily than it penetrates the surface of the second core part. | 12-20-2012 |
20130164145 | METHOD FOR MANUFACTURING A HOLLOW VANE - A method for manufacturing a hollow structural turbomachine vane, the method including forming a first cavity in a first face of a first block; assembling by diffusion bonding the first block and a second block, the first face of the first block being positioned facing a second face of the second block, the first cavity thus forming a closed cavity; machining the block resulting from the assembly of the first block and the second block so as to obtain a vane including the closed cavity. | 06-27-2013 |
20130177436 | WIND TURBINE ROTOR BLADES WITH REDUCED RADAR CROSS SECTIONS - Wind turbine rotor blades with a reduced radar cross sections include a shell having a leading edge opposite a trailing edge, a structural support member that supports the shell and is disposed internal the wind turbine rotor blade between the leading edge and the trailing edge and extends for at least a portion of a rotor blade span length, wherein the structural support member comprises carbon fiber, one or more cavities internal the wind turbine rotor blade, and a lightweight broadband radar absorbing filler material disposed in at least one of the one or more cavities to provide the reduced radar cross section. | 07-11-2013 |
20130183161 | Low-Cost Molded Wind Turbine Blade - An optimally-shaped single part molded wind turbine blade is provided for small wind turbines. Two mold bodies are brought together to form a cavity, and a third retractable mold body is inserted into the cavity. A flowable material such as filled thermoplastic resin is introduced into the space between the mold bodies and solidified. The retractable mold body is retracted and the mold is opened to reveal a single-part wind turbine blade with a hollow root region. | 07-18-2013 |
20130309097 | VIBRATION DAMPER - Vibration damping is important with regard to such components as hollow turbine blades in gas turbine engines. Traditionally damping has occurred through damping elements secured at the root or tip of such blades. Such damping is not optimised and results in potential problems with wear in operational life. By providing a tube of deformable material which can be located within a hollow cavity it is possible to provide an element which through friction engagement can absorb vibration energy and therefore damp such vibration. The tube incorporates a number of cuts and/or grooves in an appropriate pattern in order to define a deformation profile once the tube is expanded in location. The tube is secured in position internally upon an expandable element which is typically an inflatable device. Once in position the tube is retained in its expanded deformable profile and the engagement between the tube and the hollow cavity wall surface results in energy absorption through vibration episodes. It is also possible to provide a tube formed from a shape memory alloy which will expand of its own right in location to engage the hollow cavity wall surfaces for energy absorption during vibration episodes. | 11-21-2013 |
20140199174 | METHOD OF FORMING A CERAMIC MATRIX COMPOSITE COMPONENT, A CERAMIC MATRIX COMPOSITE COMPONENT AND A TIP MEMBER - A method of forming a ceramic matrix composite (CMC) component, a CMC component and a tip member are provided. The method of form the CMC component includes providing a component preform having a first end, a second end, and a cavity, the cavity having a pre-determined shape and a first engagement surface. The method includes forming a tip member from a pre-consolidated composite material, the tip member having a second engagement surface generally conforming to the first engagement surface. The method includes directing the second engagement surface to the first engagement surface. The method includes consolidating the component preform and tip member. The ceramic matrix composite component is formed having a desired geometry and the tip member stays in place in the cavity during operation of the ceramic matrix composite component. | 07-17-2014 |
20150017014 | CORE FOR CASTING A HOLLOW COMPONENT | 01-15-2015 |
20150037165 | TURBINE BLADE WITH SECTIONED PINS - A turbine blade is provided and includes pressure and suction surfaces connected to define an interior through which coolant is passable and first and second pedestal arrays, each of the first and second pedestal arrays including pedestals respectively coupled to radially outboard portions of respective interior faces of one of the pressure and suction surfaces. The pedestals of the first pedestal array are separated from pedestals of the second pedestal array by gaps respectively defined therebetween. | 02-05-2015 |
20150078912 | CERAMIC CORE COMPOSITIONS, METHODS FOR MAKING CORES, METHODS FOR CASTING HOLLOW TITANIUM-CONTAINING ARTICLES, AND HOLLOW TITANIUM-CONTAINING ARTICLES - The disclosure relates generally to core compositions and methods of molding and the articles so molded. More specifically, the disclosure relates to core compositions and methods for casting hollow titanium-containing articles, and the hollow titanium-containing articles so molded. | 03-19-2015 |
20150308451 | FAN BLADE EDGE - The invention relates to the blades of a fan wheel. The invention particularly relates to a hollow profiled blade for a fan wheel. A hollow profiled blade according to the invention for a fan wheel is made from a planar semi-finished product and has a leading edge and a trailing edge as well as a compression side and a suction side. A hollow area is formed in the interior of the hollow profiled blade whereby the part of the planar semi-finished product forming the one side of the hollow profiled blade extends over the part of the planar semi-finished product forming the other side of the hollow profiled blade. | 10-29-2015 |
20150354371 | TURBINE BLADE MACHINING METHOD, MACHINING TOOL, AND TURBINE BLADE - Provided are a turbine blade machining method and a machining tool, which allow efficient machining of a through-hole running from the surface of a turbine blade to the interior thereof, and a turbine blade. This turbine blade machining method, whereby a through-hole is machined in a turbine blade with a protective film formed on a surface of a substrate, has: an insertion step of inserting a machining tool, including a grinding region provided at a tip thereof, into the through-hole with such an orientation that the grinding region faces the surface of the through-hole; and a removal step of grinding the protective film laminated in the through-hole with the grinding region of the machining tool inserted into the through-hole, to remove the protective film laminated in the through-hole. | 12-10-2015 |
20150361801 | FLUID DAMPER AND METHOD OF MAKING - An airfoil includes an airfoil structure defining a damping network that includes a first cavity, a second cavity, a flow passage connecting the first and second cavities. The airfoil further includes a damping material configured to flow through the damping network. A method of forming an airfoil includes forming an airfoil body having a damping network that includes a first cavity, a second cavity, and a flow passage connecting the first and second cavities. The method further includes adding a damping material configured to flow through the damping network. | 12-17-2015 |
20150377029 | GAS TURBINE ENGINE COMPONENT HAVING CURVED TURBULATOR - A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a wall that forms a portion of an outer periphery of at least one cavity and at least one curved turbulator that extends from said wall. | 12-31-2015 |
20150377031 | COVERS FOR CAVITIES IN AIRCRAFT FAN BLADES - Hollow fan blades for gas turbine engines are disclosed. The hollow fan blades include a body having a convex side and a concave side wherein the convex side has a cavity formed therein. The cavity is covered by two covers including an inner cover that may be adhered to the body of the fan blade assembly and an outer cover that may be adhered to the inner cover and/or the body of the fan blade assembly. The covers may be made of titanium, more than two covers may be employed and more than one cavity may be employed. | 12-31-2015 |
20160090842 | ADDITIVE MANUFACTURING METHOD FOR FABRICATING A COMPONENT - Provided are a component and an additive manufacturing method for fabricating a component. The additive manufacturing method for fabricating a component includes providing a first wire segment and a second wire segment, the first and second wire segments each having a cross-sectional stackable geometry; positioning the first wire segment into an alignment with the second wire segment to form a workpiece stack, the alignment aligning adjacent surfaces in a line of sight direction; and directing an energy beam toward the first wire segment and the second wire segment along the alignment to weld the first wire segment to the second wire segment to form a welded stack. The component includes a workpiece stack comprising a plurality of wire segments welded together along aligned adjacent surfaces. | 03-31-2016 |
20160177745 | ABRASIVE TIPS FOR CERAMIC MATRIX COMPOSITE BLADES AND METHODS FOR MAKING THE SAME | 06-23-2016 |
416233000 | Having brace means bridging cavity | 26 |
20080232971 | Coated turbine blade - The invention refers to a coated turbine blade for a gas turbine, having blade walls divided into sections with locally adapted material temperatures. The cooler material temperatures of the blade walls are at the points where the support ribs merge into the blade walls. The regions with higher material temperatures of the blade walls are at the positions where cavities are arranged inside the blade walls. This is achieved via a ceramic thermal barrier coating having different layer thicknesses that allow different material temperatures. The region of the surface of the blade wall which faces the working medium and lies opposite an internal rib has a thicker thermal barrier coating than a region of the surface of the blade wall which is cooled via a cooling medium that flows in the cavities. This results in homogenization of the material temperature in the connecting regions, which results in prolonged blade life. | 09-25-2008 |
20090196758 | LIGHTWEIGHT COMPOSITE TRUSS WIND TURBINE BLADE - A lightweight wind turbine blade formed with a truss support structure assembly of composite truss joints including composite spar and cross members attached to and supporting in spaced relation a spine of lightweight rib panels. The rib panels are oriented in parallel spaced relation from one another and individually molded with perimeters defining individual areas of curvature for the finished blade assembly. The truss support structure is covered with a lightweight fiberglass or hardened fabric skin attached to and fitted on respective rib panel edges forming an airfoil structure. | 08-06-2009 |
20100008789 | REINFORCED BLADE FOR WIND TURBINE - The present invention relates to a reinforced blade for a wind turbine, and in particular to a wind turbine blade comprising a shell having a section with an aerodynamic profile, and at least one internal reinforcing floor connected inside the shell and extending substantially along the profile chord in order to increase the strength of the blade and to prevent or reduce deformations of the surface of the blade caused by edgewise and flapwise loading of the blade structure. | 01-14-2010 |
20100092300 | REINFORCED BLADE FOR WIND TURBINE - The invention introduces a reinforcement of a box girder of a wind turbine blade. The reinforcement prevents the transverse shear distortion of the blade structure, when the blade is loaded during operation. The reinforcement connects the corners diagonally opposite inside the girder, and fixes them in relation to each other. The reinforcement increases the blade's resistance to overall collapse. The reinforcement comprises one or more individual element, such as rods or plates. | 04-15-2010 |
20100143146 | FLATBACK INSERT FOR TURBINE BLADES - A blade for the use in the generation of power has a leading edge and a trailing edge. A first shell portion of the blade extends from the leading edge to the trailing edge. A second shell portion of the blade also extends from the leading edge to the trailing edge. A root portion of the blade is positioned proximate the wind turbine and a tip portion which extends from the root portion away from the wind turbine. A trailing edge insert is positioned between the first shell portion and the second shell portion proximate the root portion. The trailing edge insert has a surface which extends between and separates the first shell portion from the second shell portion at the trailing edge, such that the insert provides a high lift profile for increased blade efficiency. | 06-10-2010 |
20100247322 | INTERNALLY SUPPORTED AIRFOIL AND METHOD FOR INTERNALLY SUPPORTING A HOLLOW AIRFOIL DURING MANUFACTURING - A hollow airfoil and a method for manufacturing a hollow airfoil is provided. The method includes the steps of: providing a first airfoil portion, which first portion has a wall with an interior surface and an exterior surface, and one or more ribs extending out from the interior surface; providing a second airfoil portion having a wall with an interior surface and an exterior surface; wherein the first airfoil portion and the second airfoil portion have mating geometries in which the one or more ribs extend between the interior surfaces of the walls of the first and second airfoil portion to form at least one internal cavity defined by the interior surface of the first portion wall, one or more of the ribs, and the interior surface of the second portion wall, and wherein the airfoil includes at least one exterior port disposed in one of the first airfoil portion or the second airfoil portion, or is formed between the first and second airfoil portions, which at least one exterior port is in fluid communication with the at least one cavity; disposing a support material within the at least one internal cavity allowing the support material to be in contact with the one or more ribs, which support material is operative to structurally support the one or more ribs; attaching the first and second airfoil portions together; and removing the support material from the at least one internal cavity through the at least one exterior port. | 09-30-2010 |
20110008175 | ROTOR BLADE FOR A WIND TURBINE AND METHOD FOR ITS PRODUCTION - A rotor blade for a wind turbine comprising at least one pair of girders lying opposite each other which extend in the longitudinal direction of the rotor blade and carry forces acting on the rotor blade, and at least one shear web which has two front surfaces, each of which is facing one of the two girders, and two lateral surfaces, wherein that shear web extends between the two girders in the longitudinal direction of the rotor blade and is permanently joined to the two girders, wherein at least one connecting profile having a single- or multi-piece cross-section is running in the longitudinal direction of the rotor blade and comprises a collet, into which the at least one shear web is inserted, wherein a first surface of the connecting profile is glued to one of the girders and a second surface of the connecting profile is glued to a lateral surface of the at least one shear web. | 01-13-2011 |
20110058949 | Turbine Airfoil Fabricated From Tapered Extrusions - An airfoil ( | 03-10-2011 |
20110081249 | HOLLOW TURBINE BLADE - A blade for a turbine engine made by the diffusion-bonding/superplastic-forming (DB/SPF) process has a hollow skin made of front and back panels | 04-07-2011 |
20110103965 | WIND TURBINE BLADES - A rotor blade for a wind turbine that includes an airfoil comprising a shell that includes an outer skin disposed around a plurality of fiber ribs. The fiber ribs may comprise resin-infused linear rib-like structures of substantially unidirectional fiber. The fiber ribs may be configured to include a plurality of junctions, the junctions comprising an intersection of two or more fiber ribs. The fiber ribs may be configured to form a repeating pattern along the inner surface of the outer skin. | 05-05-2011 |
20110135487 | ROTOR BLADE FOR USE WITH A WIND TURBINE AND METHOD FOR ASSEMBLING ROTOR BLADE - A method for assembling a rotor blade for use with a wind turbine. The method includes providing a blade sidewall at least partially defining a cavity extending from a blade root towards a blade tip of the rotor blade, the blade sidewall having a leading edge and a trailing edge. A structural support assembly is positioned at least partially within the cavity and extends from the blade root towards the blade tip. The structural support assembly includes a root end and an opposing tip end. At least one support member is coupled to the blade sidewall and to the structural support assembly. | 06-09-2011 |
20110176928 | WIND TURBINE BLADE WITH ANGLED GIRDERS - The present invention relates to a reinforced blade for a wind turbine, particularly to a blade having a new arrangement of two or more girders in the blade, wherein each of the girders is connected to the upper part and the lower part of the shell and forms an angle with another girder thereby strengthening the shell against transverse shear distortion. | 07-21-2011 |
20110293436 | TURBINE BLADE WITH PRESSURE SIDE STIFFENING RIB - A turbine blade comprising a root portion, and an airfoil portion extending outward from the root portion and defining a blade tip at an outermost end thereof. The airfoil portion having a pressure side and a suction side opposite the pressure side, and including a stiffening rib at the blade tip. The stiffening rib extends in a substantially tangential direction on the pressure side of the airfoil portion of the turbine blade. | 12-01-2011 |
20120020803 | TURBINE BLADES, SYSTEMS AND METHODS - 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 having a pressure side surface and the suction side having a suction side surface, the pressure side surface and suction side surface for providing 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 surfaces, the pressure side and suction side extending from a root portion to a tip portion of the turbine blade. In some situations, the root portion is non-aerodynamic. The aerodynamics of such a blade is improved with the aid of pneumatic blowing through one or more blown passages for providing pressurized air (or other fluid) to a suction side and/or pressure side of the blade. | 01-26-2012 |
20120070302 | TURBINE AIRFOIL VANE WITH AN IMPINGEMENT INSERT HAVING A PLURALITY OF IMPINGEMENT NOZZLES - A turbine airfoil vane usable in a turbine engine and including at least one cooling system with an impingement plate having one or more impingement nozzles is disclosed. The turbine vane impingement nozzles may extend towards an outer wall forming the turbine vane and may reduce the mixing of cooling fluids and impingement jets found in conventional configurations. Instead, the nozzles terminate within close proximity of the outer wall, thereby reducing the effect of cooling fluid cross flow. | 03-22-2012 |
20120082555 | EFFICIENT WIND TURBINE BLADES, WIND TURBINE BLADE STRUCTURES, AND ASSOCIATED SYSTEMS AND METHODS OF MANUFACTURE, ASSEMBLY AND USE - Wind turbine systems and methods are disclosed herein. A representative system includes a wind turbine blade having an inner region that has an internal load-bearing truss structure, and an outer region that has an internal, non-truss, load-bearing structure. In particular embodiments, the truss structure can include a triangular arrangement of spars, and/or can include truss attachment members that connect components of the truss without the use of holes in the spars. Spars can be produced from a plurality of pultruded composite members laminated together in longitudinally extending portions. The longitudinally extending portions can be connected at joints that interleave projections and recesses of each of the spar portions. The blades can include fan-shaped transitions at a hub attachment portion, formed by laminated layers and/or a combination of laminated layers and transition plates. | 04-05-2012 |
20120141286 | MULTI-SEGMENT WIND TURBINE ROTOR BLADE WITH SPAN-WISE OFFSET JOINTS - A wind turbine blade includes a first blade segment and a second blade segment, with each of the blade segments having a pressure side shell member, a suction side shell member, and internal support structure. The first and second blade segments have respective adjacent ends with complimentary joint sections that are joinable at a chord-wise joint. Each of the joint sections includes a joint profile that is offset in a span-wise direction from the pressure side shell member to the suction side shell member such that the joint sections are joinable to each other along their respective joint profiles and overlie each other in a span-wise direction. | 06-07-2012 |
20120301316 | BONDING METHOD FOR A WIND TURBINE MULTI-PANEL BLADE - A method for bonding a first and a second prefabricated parts of a wind turbine blade comprising the steps of: disposing bands ( | 11-29-2012 |
20130108455 | WIND TURBINE BLADE FOR A ROTOR OF A WIND TURBINE | 05-02-2013 |
20130115095 | Notch-Reduced Composite Joint - A wind turbine blade comprising a profiled hollow contour, at least one reinforcing beam ( | 05-09-2013 |
20130236324 | WIND TURBINE BLADE STRUCTURES, LIFTING ASSEMBLIES AND METHODS OF BLADE HANDLING - A wind turbine blade | 09-12-2013 |
20140119937 | WIND TURBINE ROTOR BLADE WITH FABRIC SKIN AND ASSOCIATED METHOD FOR ASSEMBLY - A rotor blade for a wind turbine includes an internal support structure extending span-wise from a blade root to a blade tip. A plurality of ribs are fixed to and spaced along the internal support structure, with each rib extending in a generally chord-wise direction and having a generally aerodynamic blade contour. A plurality of chord-wise oriented fabric strips are affixed to the ribs in a tensioned state, wherein the fabric strips define an aerodynamic outer skin of the rotor blade. | 05-01-2014 |
20140140855 | SEGMENTED WIND TURBINE BLADES WITH TRUSS CONNECTION REGIONS, AND ASSOCIATED SYSTEMS AND METHODS - Segmented wind turbine blades with truss connection regions, and associated systems and methods are disclosed. A wind turbine system in accordance with a particular embodiment includes a wind turbine with a first segment having a first position along the longitudinal axis and having a first internal load-bearing structure for which non-truss structure elements carry at least 90% of the shear loads in the first segment. The blade further includes a second segment having a second position along the longitudinal axis and having a second internal load-bearing structure for which non-truss structure elements carry at least 90% of the shear loads in the first segment. A connection region between the first and second segments includes an internal load-bearing truss structure connected between the first internal load-bearing structure and the second internal load-bearing structure. | 05-22-2014 |
20140241897 | ALUMINUM BRAZING OF HOLLOW TITANIUM FAN BLADES - A fan blade includes first and second titanium portions that are secured to one another with an aluminum alloy braze. A method of manufacturing a fan blade includes providing first and second titanium portions, applying an aluminum alloy braze to at least one of the first and second titanium portions, and heating the fan blade to melt the aluminum alloy braze and join the first and second portions to one another to provide a fan blade with an airfoil exterior contour. | 08-28-2014 |
20140286785 | METHOD OF PRODUCING A HOLLOW AIRFOIL - A method of producing an airfoil is provided. The method includes forming a steel airfoil preform with a pocket on at least one of the pressure and suction surfaces, forming a cover plate for the pocket and welding the cover plate over the pocket. | 09-25-2014 |
20160123155 | MANUFACTURING METHOD - A method of manufacturing an aerofoil blade includes the steps of providing: an aerofoil sub-assembly having a pair of aerofoil skins, wherein at least one of the skins is formed to have on its outer face an outer primary relief feature formed proud of the adjacent region of the outer face and an outer secondary relief feature projecting from the outer primary relief feature; arranging the aerofoil sub-assembly in a cavity die mould; and performing a hot forming process to form an internal cavity between the respective aerofoil skins by inflating the sub-assembly to conform the outer faces of the respective skins to the cavity die mould, whereby in conforming the respective outer faces of the skins to the cavity die mould, the outer primary and secondary relief features are transferred to the inner face of the respective skin to form respectively inner primary and secondary relief features. | 05-05-2016 |