| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 029889210 | Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member | 34 |
| 20080256795 | WIND TURBINE BLADE HAVING CURVED CAMBER AND METHOD OF MANUFACTURING SAME - A wind turbine blade for a vertical axis wind turbine (VAWT) having a curved camber and a method of manufacturing same is disclosed. The method of manufacturing a turbine blade comprises determining the profile of an airfoil of the blade and forming the blade having the airfoil with the translated profile. The step of determining the profile of an airfoil of the blade comprises selecting a symmetrical airfoil having a straight mean camber line and a desired chord length; selecting a circular segment having the same radius as a path traveled by the blade around a hub of the VAWT and locating the circular segment to contact the mean camber line at at least one point; translating the mean camber line of the symmetrical airfoil such that it overlaps with the circular segment; and determining the profile of the airfoil blade by translating the profile of the symmetrical airfoil to correspond with the translated mean camber line of the symmetrical airfoil. | 10-23-2008 |
| 20090113708 | Method for joining components - A method for joining components, in particular for joining a rotor blade to a rotor base body in the manufacture and/or repair of an integrally bladed gas turbine rotor, is disclosed. The method includes the following steps: a) providing two components that are to be connected, i.e., joined together; b) providing a joining part; c) aligning the two components and the joining part that are to be joined together such that the joining part is arranged as an insert between the two components that are to be joined together; d) connecting the two components with the intermediate arrangement of the joining part by moving the joining part with respect to the two stationary components that are to be joined together and in particular by exerting a compression force on the joining zones between the two stationary components and the joining part via the two stationary components. | 05-07-2009 |
| 20090265933 | Method for the manufacture of turbine or compressor rotors for gas-turbine engines - With the manufacture of turbine engine rotor drums, the opposite joining surfaces of rotor disks are brought into contact and at least one of the two rotor disks clamped into a fixture is set in a circular movement until the joining areas reach a pasty state due to the frictional heat. The circular movement of the rotor disks, in which the axis of the rotor disk moves along a circular path, is optically recorded and deviations due to imbalance are corrected by weight compensation at the fixture. Upon reaching the pasty material state the joining areas weld together, with the rotor disks being at rest and in axial alignment. Manufacture is cost-effective and guarantees precise axial alignment of the rotor disks and a long service life of the engine rotor drums. | 10-29-2009 |
| 20100126017 | METHOD OF MANUFACTURE - A method of fixturing a plurality of dissimilar blade assemblies, wherein each assembly undergoes one or more manufacturing steps to bring it to a finished form, the method comprising the step of providing on each of the articles a datum feature, wherein each datum feature is of identical form and dimension, in turn a) locating the datum feature of a first one of the articles in a complimentary fixture to secure the dissimilar article, b) performing at least one manufacturing step on the secured dissimilar article, c) removing the dissimilar article from the fixture, d) locating the datum feature of another of the articles in the complimentary fixture to secure the dissimilar article, e) performing at least one manufacturing step on the secured dissimilar article, f) removing the dissimilar article from the fixture. | 05-27-2010 |
| 20100139093 | METHOD AND ASSEMBLY FOR MOUNTING ROTOR BLADE BEARINGS OF A WIND TURBINE - A method and an assembly for fastening at least one screw nut to be tightened of a rotor blade bearing of a wind turbine are provided. A screw nut driver assembly is provided at a rotatable portion of the rotor blade bearing, the screw nut driver assembly being adapted to automatically tighten the at least one screw nut. The screw nut driver assembly is aligned with the screw nut to be tightened by rotating the rotatable portion with a pitch drive of the wind turbine. Then the screw nut is tightened using the screw nut driver assembly. | 06-10-2010 |
| 20100154214 | TURBINE WHEEL AND SHAFT JOINING PROCESSES - A process for joining a turbine wheel and a turbine shaft of a turbocharger comprising the steps of: providing a turbine wheel; providing a turbine shaft; holding the turbine shaft in a welding device; contacting the turbine shaft to the turbine wheel; energizing a pilot current; lifting the shaft a predetermined height from the turbine wheel to draw a pilot arc; energizing a weld arc current locally melting the shaft weld end and forming a weld pool on the wheel; plunging the shaft toward the wheel into the weld pool; turning off the current; and removing the welding device from the welded shaft. | 06-24-2010 |
| 20100281689 | METHODS AND APPARATUS FOR FABRICATING A TURBINE NOZZLE ASSEMBLY - An apparatus enables a turbine nozzle, including at least two turbine nozzle singlets to be fabricated. Each singlet includes inner and outer bands and a vane extending therebetween. The vane also includes first and second sidewalls coupled together at a leading edge and a trailing edge. The apparatus comprises a fixture, and at least two support members extending from the fixture. Each support member has first and second abutment surfaces, wherein a first of the at least two support members contacts at least one of the leading and trailing edges of a first of the vanes. At least two locating features extend from the fixture, wherein a first of the locating features contacts one of the first and second sidewalls of the first vane. At least two biasing members are coupled to the fixture, wherein a first of the biasing members biases the first vane against the first locating feature. | 11-11-2010 |
| 20110179646 | TURBINE DISK SLOT BOTTOM MACHINING - A method for forming a slot in a rotor disk includes a finishing step using a tool rotating at angle off normal in direction opposite a direction that the tool is driven through the slot. A finish profile is obtained in part by removing material from a bottom surface with a tool rotating about an axis off normal. | 07-28-2011 |
| 20120192421 | GAS TURBINE ENGINE AIRFOIL - A method of designing an airfoil for a gas turbine engine according to one embodiment of this disclosure can include localizing a sweep angle at a leading edge of a tip region of the airfoil, and localizing a dihedral angle at the tip region of the airfoil. The dihedral angle can be applied by translating the airfoil in direction normal to a chord of the airfoil. | 08-02-2012 |
| 20120210579 | BLADE PRELOADING SYSTEM AND METHOD - A removable fan blade of a turbofan engine includes a blade root at one end thereof. A rotor disk has a retention slot having dimensions corresponding for receiving the root of the fan blade in the slot. An elongated resilient member extends within the retention slot in a lengthwise direction between the root of the fan blade and the bottom of the retention slot and an elongated member extends lengthwise between the root of the fan blade and the elastomeric member to compress the resilient member and provide a radial preload to the fan blade. | 08-23-2012 |
| 20130104398 | ROTOR BLADE ASSEMBLY TOOL FOR GAS TURBINE ENGINE | 05-02-2013 |
| 20140026415 | GAS TURBINE ROTOR ASSEMBLY METHOD - Methods of assembling a rotor assembly of a gas turbine engine having a plurality of components. The method comprises, in one aspect, determining a static unbalance force of each component using the mass and the center of mass location, and determining an optimum assembly arrangement minimizing static unbalance forces. Optimal component stacking positions, among other things, may then be established. | 01-30-2014 |
| 20140101939 | METHOD OF FABRICATING INTEGRALLY BLADED ROTOR AND STATOR VANE ASSEMBLY - A method of fabricating an integrally bladed rotor of a gas turbine engine according to one aspect, includes a 3-dimensional scanning process to generate a 3-dimensional profile of individual blades before being welded to the disc of the rotor. A blade distribution pattern on the disc is then determined in a computing process using data of the 3-dimensional profile of the individual blades such that the fabricated integrally bladed rotor is balanced. | 04-17-2014 |
| 20140173899 | GAS TURBINE ROTOR ASSEMBLY METHODS - Method of assembling a rotor assembly of a gas turbine engine having a plurality of components. The method comprises in one aspect calculating the bending forces due to the mass distribution along the rotor. In another aspect, an optimization routine iterates different rotor arrangements, comparing the calculated bending moments to determine a set of component positions that minimizes the bending forces. In another aspect, mass corrections are optimized to balance the rotor assembly. | 06-26-2014 |
| 20140237820 | Turbine Blade Insertion Tool - Turbine blade insertion tool ( | 08-28-2014 |
| 20140304989 | ROTOR BLADE ASSEMBLY TOOL FOR GAS TURBINE ENGINE - A rotor blade assembly tool for coupling a plurality of circumferentially spaced rotor blades to a rotor disc of a turbine rotor assembly, includes a base ring with an array of circumferentially spaced resilient fingers axially extending from the base ring. The resilient fingers are configured each to radially abut a blade seal, damper or other engine component against radially inner facing surfaces of platforms of the respective blades when the blades are being seated onto the disc during an assembly procedure | 10-16-2014 |
| 20140310958 | Assembly Method of Wind Power Generation System - Provided is an assembly method of a wind power generation system that can enhance the safety of an assembly work, and which can reduce a working time. In order to solve the above problem, the assembly method of a wind power generation system of the present invention includes assembly of the wind power generation system which includes a rotor with a hub and blades, a nacelle for accommodating therein at least a generator connected to the rotor via a main shaft connected to the hub, and a tower supporting the nacelle on a top portion thereof, and having an opposite side thereof to the top portion fixed to a foundation, the tower including separated tower parts. When assembling the wind power generation system, the nacelle and the tower are laterally assembled together by using a carriage, and the rotor is fixed to the laterally-facing nacelle. | 10-23-2014 |
| 20140317927 | METHOD FOR ASSEMBLING AND TRANSPORTING AN OFFSHORE WIND TURBINE - A method for assembly and installation of an offshore wind turbine, where components such as a nacelle, one or more tower sections and/or blades for at least one wind turbine is manufactured, assembled at or transported to a harbor area, where said components are loaded onto a transport and installation vessel and subsequently transported to an erection site. The method involves at least the steps of assembling at least one nacelle for a two-bladed wind turbine having hub with two sets of blade installation interfaces facing in a radial direction, the blade installation interfaces having a 180 degree angular distance therebetween, installing at least one, but preferably two inner blade parts to the hub, and arranging the at least one nacelle with the at least one inner blade part attached to the hub on the deck of a transport and installation vessel. | 10-30-2014 |
| 20140325842 | Linear Friction Welding Apparatus and Method - The apparatus and method allows multiple components to be simultaneously bonded to a central shaft or tube using linear friction welding in a single welding process. The method involves simultaneously pressing the work pieces radially against the central shaft or tube at the desired locations while the shaft is vibrated axially. The weld is facilitated by the use of a linear friction welding machine, which includes a number of fixtures and press assemblies to hold and press the various work pieces against the central shaft or tube and a vibrating assembly for vibrating the central shaft or tube. | 11-06-2014 |
| 20140338193 | BALANCING METHOD - A method of balancing a set of retaining and locking plates used to retain a row of gas turbine engine aerofoil blades in attachment to a rotor disc, includes: (i) providing a weighing plate having a circular track; (ii) providing a non-rotating, static balancing apparatus capable of detecting unbalance in the weighing plate; (iii) positioning the weighing plate on the static balancing apparatus, and positioning the set of retaining and locking plates on the track in an arrangement corresponding to a possible arrangement for the set of plates in use in the engine; and (iv) repositioning the retaining and locking plates on the track to arrive at a balanced arrangement for the set of plates. | 11-20-2014 |
| 20150052749 | METHOD OF FABRICATING INTEGRALLY BLADED ROTOR USING SURFACE POSITIONING IN RELATION TO SURFACE PRIORITY - A method of fabricating an integrally bladed rotor for gas turbine engines according to one aspect includes a step of positioning a blade on a hub in a joining procedure by using a priority surface of the blade as a reference surface. The priority surface is determined in relation to importance of surface functionality of the blades during engine operation | 02-26-2015 |
| 20150292330 | METHOD OF MAKING A TURBOMACHINE - A turbomachine is made by first providing a stepped shaft having a large-diameter cylindrical portion, an intermediate-diameter cylindrical portion, and a small-diameter cylindrical portion all centered on a common axis. A separately manufactured a one-piece and annular first impeller wheel is then permanently mounted on the large-diameter portion with a back face of the first wheel facing axially toward the intermediate-diameter portion and carrying a rotor bearing half of an axial magnetic bearing. A rotor ring of a radial bearing is then detachably mounted on the intermediate-diameter portion of the shaft, and finally a one-piece and annular second impeller wheel is detachably mounted on the small-diameter portion of the shaft with a back face of the second wheel facing axially toward the first wheel and carrying a rotor bearing half of another axial magnetic bearing. | 10-15-2015 |
| 20150292364 | AID DEVICE - An aid device ( | 10-15-2015 |
| 20150306713 | A METHOD OF FABRICATING A ROTOR OF A TURBOFAN ENGINE - A method of fabricating a disk assembly for a turbofan engine is disclosed and includes the steps of forming a first and second disk and welding the second disk to the first disk to form a weld joint. A portion of the first disk and the second disk are removed along the weld joint on at least one surface to reduce a size of a heat affected zone and substantially reduce possible formation of material inconsistencies. | 10-29-2015 |
| 20150321309 | METHOD OF MACHINING A SHROUD AND GRINDING WHEEL THEREFOR - A method of machining a turbine shroud segment including inserting an annular flange of a grinding wheel through a first gap defined between the shroud retention elements and into a second gap defined between the shroud platform and an axially extending, radially inwardly facing arcuate inner surface of one of the retention elements. The wheel flange is inserted with its supporting leg and the wheel body remaining out of contact with the shroud segment and with the wheel flange remaining out of contact with the platform. The inner surface is ground through contact with an annular outer grinding surface of the wheel flange. The wheel leg and body remain out of contact with the shroud segment and the wheel flange remains out of contact with the platform during grinding. | 11-12-2015 |
| 20150345465 | WIND TURBINE BLADE LIFTING DEVICE AND A METHOD FOR LIFTING A WIND TURBINE BLADE - A wind turbine blade lifting device having a length, a width and a height and is suitable for lifting and handling a wind turbine blade or a part of a wind turbine blade, also having a length, a width and a height, where the lifting device has a chassis with at least one set of connection means for coupling to a lifting apparatus, and a mechanism for engaging a wind turbine blade or blade part. Also, a method for installing at least a part of a wind turbine blade, e.g., a full wind turbine blade or an inner blade part for a partial pitch wind turbine blade having an inner blade part and an outer blade part. | 12-03-2015 |
| 20150369050 | ROTOR BLADE MANUFACTURE - A method is provided of processing one or more blades of a row of blades which forms part of a rotor for a gas turbine engine. The method includes: providing a rotor disc having a slot for mounting one or more blades; applying tape at one or both sides of the slot such that when the blades are loaded in the slot the tape reduces a range of tilt angles which can be adopted by the blades; loading the blades in the slot; and performing a processing operation on the loaded blades. | 12-24-2015 |
| 20150369051 | ROTOR BLADE MANUFACTURE - A method is provided of processing one or more blades of a row of blades which forms part of a rotor for a gas turbine engine. The method includes: providing a rotor disc having a slot for mounting one or more blades; loading the blades in the slot and loading the wax blocks in or adjacent the slot, the wax blocks being configured and positioned such that, on loading, the blades shear material from the wax blocks, the sheared wax blocks reducing a range of tilt angles which can be adopted by the blades; and performing a processing operation on the loaded blades. | 12-24-2015 |
| 20150369070 | Multi-Airfoil Split and Rejoin Method - A method for working an airfoil cluster is disclosed. The method may include attaching a first datum to a first portion of the airfoil cluster, and joining a second portion of the airfoil cluster to the first portion, the second portion having a second datum substantially aligned with the first datum in a common plane spaced away from the first and second portions. | 12-24-2015 |
| 20150377331 | METHOD OF MANUFACTURING IMPELLER AND TURBINE ASSEMBLIES - A method of manufacturing an impeller and turbine assembly of a transmission includes providing an impeller housing and a turbine housing. An impeller blade defining an impeller receptor and a turbine blade defining a turbine receptor are provided. The impeller blade is mated to the impeller housing by deforming a portion of said impeller housing into the impeller receptor. The turbine blade is mated to the turbine housing by deforming a portion of the turbine housing into the turbine receptor. In this manner, the impeller blade is secured to the impeller housing and the turbine blade is secured to the turbine housing. | 12-31-2015 |
| 20160017718 | TURBINE BUCKET PLENUM FOR COOLING FLOWS - A casted turbine bucket having at least one machined plenum including a plenum chamber and at least one plenum passage connected to a plenum inlet at a root portion of turbine bucket, and a method to feed cooling flow to the turbine bucket using the machined plenum that receives cooling flow from the root portion of the turbine bucket. | 01-21-2016 |
| 20160146182 | WIND TURBINE ELEVATOR FOR HOISTING A NACELLE ALONG A TOWER AND PIVOTING THE NACELLE AT A TOP OF THE TOWER - A method for assembling a wind turbine includes: unloading a nacelle and hub from a truck; connecting the nacelle and hub to a carriage of an elevator in a vertical position; connecting blades to the hub, thereby forming a rotor; raising the carriage, nacelle, and rotor along a tower to a top of the tower; and pivoting the carriage, nacelle, and rotor to a horizontal position at the top of the tower. | 05-26-2016 |
| 20160169190 | ROTOR BLADE SURFACE FEATURE INSTALLATION SYSTEMS AND METHODS | 06-16-2016 |
| 20180021899 | METHODS OF MANUFACTURING A TANDEM GUIDE VANE SEGMENT | 01-25-2018 |
