| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 029889710 | Composite blade | 34 |
| 20080250641 | System for forming a gas cooled airfoil for use in a turbine engine - A turbine airfoil system for forming a turbine airfoil that is usable in a turbine engine. The airfoil may be formed from a porous material shaped into an outer airfoil shape. The porous material may include an inner central spar capable of supporting the turbine airfoil an outer porous region and an outer coating. The porous material facilitates efficient cooling of the turbine airfoil. | 10-16-2008 |
| 20080263865 | Method for the Production of an Armor Plating for a Blade Tip - A method for producing a blade tip armor plating on a blade of a turbomachine, in particular on a high-pressure compressor rotary blade of a gas turbine, having the following steps: a) provision of a blade made of a nickel base material; b) application of a solder to a blade tip of the blade, the solder being a nickel base solder; c) application of hard material particles of cubic boron nitride to the solder, the hard material particles of cubic boron nitride being coated with titanium or with a titanium base material; d) fusion of the solder in a vacuum in order to form a matrix that at least partially surrounds the hard material particles; and e) fixing of the blade tip armor plating through cooling. | 10-30-2008 |
| 20090077802 | METHOD FOR MAKING A COMPOSITE AIRFOIL - A method of manufacturing a composite airfoil includes the step of providing a core made of a metal or ceramic material. A plastic airfoil portion is molded to envelope at least a portion of the core. | 03-26-2009 |
| 20090193656 | STEAM TURBINE BUCKET WITH EROSION DURABILITY - A method for forming a bucket for a steam turbine includes forming a leading edge on at least one airfoil. The leading edge is comprised of an erosion resistant material and is bonded to the airfoil. | 08-06-2009 |
| 20090313824 | METHOD OF MAKING A FAN BLADE - A method of making a fan blade includes: a) providing a blade body having a top surface, a bottom surface opposite to the top surface, and a peripheral wall interconnecting the top and bottom surfaces; b) drilling a blind hole in the blade body that extends from one side of the peripheral wall of the blade body and between the top and bottom surfaces of the blade body; and c) inserting a reinforcing rib into the blind hole. | 12-24-2009 |
| 20100180439 | METHOD FOR MANUFACTURE OF WIND VANES - The invention relates to a method for the manufacture of wind vanes, consisting of: formation of a single foam core ( | 07-22-2010 |
| 20110078903 | Method and arrangement for a spray coating process - A method for preparing a blade of a turbomachine for a spray coating process is provided. The method includes providing a sheet of flexible material which is shaped such that, when the sheet is bent circumferentially around a blade root of the blade along a longitudinal axis of the blade, the sheet forms a circumferential cover on the surface of the blade root, and bending the sheet around the blade root to form the cover. The sheet is positioned on the blade root up to a platform between an airfoil and the blade root. The sheet is placed on the blade root such that the sheet forms a circumferentially closed structure around the blade root. Further, an arrangement for a spray coating process is provided. | 04-07-2011 |
| 20110146075 | METHODS FOR MAKING A TURBINE BLADE - Methods for making a turbine blade involving casting an internal skeleton having a plurality of internal ribs which form a plurality of open cooling channels, applying a filler material to the open cooling channels, and applying an outer wall about the internal skeleton having the filler material applied to the open cooling channels. | 06-23-2011 |
| 20110296687 | METHOD OF MACHINING ROTOR BLADE WEAR INDICATORS, AND ROTOR BLADE PLUG FOR IMPLEMENTING THE METHOD - A method for machining at least one aircraft gas turbine engine rotor ( | 12-08-2011 |
| 20120055020 | BLADE MODULE, A MODULAR ROTOR BLADE AND A METHOD FOR ASSEMBLING A MODULAR ROTOR BLADE - A method for assembling a modular wind turbine rotor blade, includes aligning a first blade module and a second blade module such that a first receptacle of the first blade module and a second receptacle of the second blade module are co-axial; and forming a detachable mechanical connection between a first inlay of the first blade module and a second inlay of the second blade module using a threaded fastener that extends into the first receptacle and into the second receptacle. | 03-08-2012 |
| 20120151769 | METHOD FOR DETERMINING OPTIMUM VORTEX GENERATOR PLACEMENT FOR MAXIMUM EFFICIENCY ON A RETROFITTED WIND TURBINE GENERATOR OF UNKNOWN AERODYNAMIC DESIGN - A method of optimizing performance of a wind turbine electric generator (WTG) comprises the steps of measuring the performance of a wind turbine electric generator, defining an area on a blade of the WTG, placing stall flags within said defined area, monitoring the behavior of the stall flags when the WTG is operating, determining a stall line based upon the stall flags during operation, installing vortex generators on the blade adjacent to and upwind of said stall line, monitoring the behavior of said stall flags during operation with vortex generators installed on all blades, and measuring the performance of the WTG to detect improved performance. If there is little or no improvement, repeating the steps on a second WTG using different placement within the defined area for the vortex generators. | 06-21-2012 |
| 20120167390 | AIRFOIL FOR GAS TURBINE ENGINE - One embodiment of the present invention is a unique method for producing a turbomachine airfoil. Other embodiments include unique methods for manufacturing an airfoil for a gas turbine engine. Still other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for airfoils for gas turbine engines and other turbomachinery. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith. | 07-05-2012 |
| 20120174401 | Highly Reliable, Low Cost Wind Turbine Rotor Blade - A wind turbine rotor blade and a wind turbine incorporating the rotor blade include a first and second composite skin. A first and a second spar pultrusion having a base and a plurality of integral ribs generally normal to base are attached to the inside surface of the first and second composite skins and extend the span of the rotor blade. At least one shear web connects a rib of the first spar pultrusion to a corresponding rib of the second spar pultrusion. The width of the spar pultrusions decreases in a step-wise fashion along the span of the rotor blade from the root to the tip. The leading or trailing edge of the rotor blade may be selectably opened for inspection and repair. | 07-12-2012 |
| 20120246931 | METHODS OF MANUFACTURING WIND TURBINE BLADES - An elongate web is attached to the root end of a spar of a wind turbine rotor blade to provide additional support along the width of the blade. The root end is formed by a winding operation, and a recess is then cut into the surface of the spar. The recess is defined by a relatively large first, cylindrical surface, which is coaxial with the longitudinal axis of the root end, and a relatively small second, conical surface. A tapered end of the elongate web is attached within the recess of the root end using a layer of suitable adhesive and an array of pins. Resilient spacer elements are arranged within the recess so as to surround the pins. The large area of the cylindrical surface causes the tensile and compressive stresses which arise along the elongate web in use to be transmitted to the spar as shear stresses. | 10-04-2012 |
| 20120317810 | METHOD FOR MAKING A METAL REINFORCEMENT FOR THE BLADE OF A TURBINE ENGINE - A method for making a metal reinforcement for the leading edge or trailing edge of the blade of a turbine engine that includes making a metal insert defining the base of the metal reinforcement; positioning the metal insert at the end of a blank of a shaping tool, the blank repeating the shape of the turbine-engine blade; shaping a planar metal sheet on the metal insert and the blank of the shaping tool using a superplastic hot-shaping method. | 12-20-2012 |
| 20130008027 | METHOD FOR PRODUCING A METAL INSERT TO PROTECT A LEADING EDGE MADE OF A COMPOSITE MATERIAL - A method for producing a metal insert for protecting a leading or trailing edge of a compressor vane of an aeronautical machine made of a composite material, by stamping sheets and diffusion bonding between the sheets. The method includes: initially shaping the sheets by stamping to approximate the sheets to a shape of a suction side and pressure side of the insert; producing a core shaped inner cavity of the metal insert to be manufactured, one of the surfaces thereof reproducing an inner shape of the suction side of the insert and the other surface reproducing an inner shape of the pressure side of the insert; positioning the sheets around the core and securing the assembly; applying a vacuum and sealing the assembly by bonding; assembling the assembly by hot isostatic compression; cutting the assembly to extract the core and separate the insert; producing an outer profile of the insert by a final machining. | 01-10-2013 |
| 20130180108 | METHOD FOR TREATING TURBINE BLADES AND DEVICE THEREFOR - A method is provided for treating turbine blades having holes for discharging cooling air. A protective layer is provided and then the holes that are partly or completely closed by the protective layer are opened again. Coordinates concerning the position of the holes are acquired before the protective layer is applied using a laser triangulation sensor using a light source generating a light beam and a light detector. The data obtained is used after application of the protective layer to control a removal device for removing protective layer partly or wholly covering the holes. Each hole is measured by the light beam being shone into the hole in different positions in relation to the longitudinal mid-axis of the latter. The light beam is shone into the respective hole in a plane at at least three different angles to the longitudinal mid-axis thereof. | 07-18-2013 |
| 20130185938 | METHOD FOR MANUFACTURING A METAL PART - A method for making a metallic part, includes positioning at least one metallic coil formed from flexible metal foil including a plurality of notches, on a shaping tool, the at least one coil being manually deformable when cold along three directions in space (X, Y, Z); hot isostatic pressing the at least one metallic coil in a tool causing compaction of the metallic coil so as to obtain the metallic part. | 07-25-2013 |
| 20130199043 | METHOD OF MANUFACTURING A TURBINE BLADE, SYSTEM FOR MANUFACTURING A TURBINE BLADE, INTERMEDIATE MEMBER FOR MANUFACTURING A TURBINE BLADE, AND TURBINE BLADE MANUFACTURED BY MEANS OF THE AFOREMENTIONED METHOD - A method of manufacturing a turbine blade is provided. The described method includes providing an elongate core, surrounding the elongate core with a textile structure, arranging the elongate core surrounded by the textile structure in a mold, pressing at least a part of the textile structure against the mold, and injecting a curing agent into the mold to interact with the textile structure, thereby forming the turbine blade. Also, a system and an intermediate member for manufacturing a turbine blade by means of the described method is provided. | 08-08-2013 |
| 20130219718 | BLADE INSERT FOR A WIND TURBINE ROTOR BLADE AND RELATED METHODS - A method for retrofitting a rotor blade of a wind turbine is disclosed. The method may generally include cutting the rotor blade at a specified location in order to form a root segment and a tip segment and positioning a blade insert between the root segment and the tip segment | 08-29-2013 |
| 20130312261 | METHOD FOR PRODUCING A REINFORCED METAL PART, SUCH AS A REINFORCEMENT FOR A TURBINE-ENGINE BLADE - A method for producing a reinforced metal part, includes: cutting out a plurality of metal foils from at least one flexible metal sheet, the foils substantially corresponding to the blank of said metal part to be produced; rigidly connecting at least one metal reinforcing wire to at least one metal foil, the metal wire being positioned depending on the orientation of the desired structural reinforcement; making a plurality of reinforced metal pockets, each metal pocket being made from two reinforced metal foils; positioning the plurality of reinforced metal pockets in shaping equipment; performing a isostatically hot-pressing of the reinforced metal pockets, causing the metal pockets and the metal reinforcing wire to be bonded together so as to produce the metal part incorporating the structural reinforcement. | 11-28-2013 |
| 20130333215 | PROCESS FOR MAKING A METAL PART SUCH AS A TURBINE ENGINE BLADE REINFORCEMENT - A process for manufacturing a metal part such as a metal reinforcement for the blade of a turbine engine, which includes: manufacturing a three-dimensional metal structure made up of an insert which exhibits properties which allow superplastic forming and diffusion welding to be carried out, and of multiple metal wires encircling the periphery of the insert, where the metal structure forms a preform of the metal part; positioning the metal structure in a forming tool and hot-pressing the three-dimensional metal structure which causes agglomeration of the metal structure so as to obtain the compact metal part. | 12-19-2013 |
| 20130340252 | METHOD FOR MANUFACTURING WIND TURBINE BLADES, BLADES FOR PROPELLORS, WINGS, OR SIMILAR STRUCTURES, AND STRUCTURE IN THE FORM OF A BLADE OBTAINED BY MEANS OF THIS PROCEDURE - The invention relates to a method for manufacturing wind turbine blades, blades for propellers, wings or similar structures, and to a structure in the shape of a blade produced by means of said method, including: use a female mold of the leading edge ( | 12-26-2013 |
| 20140020247 | METHOD FOR MAKING A CEILING FAN BLADE - A method for making a ceiling fan blade comprises the steps of cutting, inside drying, surface wetting, surface spraying, and surface forming. The method is capable of reducing production cost and loss rate, reducing the harm to human health, preventing environmental pollution, and preventing the ceiling fan blades from perishing and deformation by dehydrating the ceiling fan blades. | 01-23-2014 |
| 20140165398 | METHODS OF MANUFACTURING DIVIDED BLADES OF TURBOMACHINES BY ADDITIVE MANUFACTURING - The method is used for manufacturing a turbomachine blade that comprises an airfoil portion and is divided into two parts at an intermediate region of the airfoil portion; each of the two parts of the airfoil portion is obtained by additive manufacturing; the two parts are joined by brazing. | 06-19-2014 |
| 20140237821 | TURBOMACHINE BLADE PRODUCTION METHOD - A method of producing a turbomachine blade having a coupling root, and an airfoil-shaped oblong member cantilevered from the coupling root; the airfoil-shaped oblong member having a main plate-like element connected directly to the coupling root, and a cover plate for sealing a hollow weight-reducing seat formed in one of the two major faces of the main plate-like element; the main plate-like element being divided into a lower connecting fin cantilevered from the coupling root, and a plate-like body butt welded to the lower connecting fin to form an extension of the lower connecting fin; the method being characterized by including the steps of twisting and curving a flat plate of constant thickness greater than the maximum thickness of the plate-like body of the blade, to obtain a blank plate, in which the three-dimensional shape of the centerline surface of the blank plate substantially matches the three-dimensional shape of the centerline surface of the plate-like body of the main plate-like element. | 08-28-2014 |
| 20140259669 | SYSTEM AND METHOD FOR INSTALLING A BLADE INSERT BETWEEN SEPARATE PORTIONS OF A WIND TURBINE ROTOR BLADE - A system for installing a blade insert between a root portion and a tip portion of a rotor blade of a wind turbine is disclosed. The system may include a root cradle assembly configured to support the root portion of the rotor blade and a tip cradle assembly configured to support the tip portion of the rotor blade. At least one of the tip cradle assembly or the root cradle assembly may be movable relative to the other of the tip cradle assembly or the root cradle assembly to allow the tip portion to be spaced apart from the root portion after the rotor blade has been divided between the root and tip portions. In addition, the system may include an insert cradle assembly configured to support a blade insert for the rotor blade. The insert cradle assembly may be configured to be positioned between the root cradle assembly and the tip cradle assembly so as to position the blade insert between the root portion and the tip portion. | 09-18-2014 |
| 20150033561 | LASER MELT PARTICLE INJECTION HARDFACING - A method for hardfacing a surface including: depositing a powder ( | 02-05-2015 |
| 20150040396 | METHOD OF FABRICATING A COMPOSITE MATERIAL TURBINE ENGINE VANE WITH INCORPORATED PLATFORMS - Multilayer weaving is used to form a fiber blank having a longitudinal direction corresponding to the longitudinal direction of the vane to be made and comprising across its thickness a first woven portion with a plurality of layers of yarns interlinked by weaving, and also a second and third woven portions. The first portion is situated between the second and third portions and interlinked thereto by weaving over only a fraction of its longitudinal dimension. A preform for the vane is formed by folding out, on either side of the first portion, segments of the second and third portions not interlinked with the first portion, by shaping the first portion to form a preform portion for the airfoil of the vane, and by shaping the folded-out segments of the second and third portions to form preform portions for the inner and outer platforms of the vane to be fabricated. | 02-12-2015 |
| 20150082634 | METHOD AND APPARATUS FOR ROTOR BLADE BALANCE - A method of assembling a rotor blade assembly includes determining a first spanwise moment of a first component of the rotor blade assembly and comparing the first spanwise moment to a target first spanwise moment. The first spanwise moment of the first component is adjusted based on a result of the comparison. A second spanwise moment of a second component of the rotor blade assembly is determined and compared to a target second spanwise moment. The second spanwise moment of the second component is adjusted based on a result of the comparison. The first component is assembled to the second component, resulting in a rotor blade assembly meeting a target spanwise moment of the rotor blade assembly. | 03-26-2015 |
| 20150292475 | METHOD FOR PRODUCING A ROTOR BLADE - The invention relates to a method for producing a rotor blade of a wind turbine in a two-story producing building with a ground floor level for the production of a first part of a rotor blade, and an upper floor level, which is disposed above the ground floor level, for the production of a second part, for example semifinished products for the rotor blade. | 10-15-2015 |
| 20150345312 | DUAL ELEMENT TURBINE BLADE - A method of manufacturing a turbine blade includes providing a core element having a base portion, a tip portion, and an intermediate portion extending between the base portion and the tip portion. The intermediate portion has a non-uniform cross-section and is a high-strength fiber material. The method also includes surrounding the core element with a shell, the volume between the core element and the shell forming a void. | 12-03-2015 |
| 20160377048 | MODULAR WIND TURBINE ROTOR BLADES AND METHODS OF ASSEMBLING SAME - The present disclosure is directed to a method for assembling a modular rotor blade of a wind turbine. The method includes providing a pre-formed blade root section and a pre-formed blade tip section of the rotor blade. Further, the blade root section includes one or more spar caps extending in a generally span-wise direction. Another step includes providing at least one pre-formed blade segment of the rotor blade. The method also includes mounting the at least one blade segment around the one or more spar caps of the blade root section, wherein the at least one blade segment includes a chord-wise cross-section having multiple joints, wherein at least one joint is located on at least one of a pressure side surface or a suction side surface. In addition, the method also includes joining the blade tip section to at least one of the one or more spar caps or the at least one blade segment. | 12-29-2016 |
| 20190143396 | CORE FOR HIGH-TEMPERATURE SHAPING OF A METAL PART AND MANUFACTURING PROCESS | 05-16-2019 |
