Entries |
Document | Title | Date |
20080201947 | Method For Repairing Turbo Machine Blades - A method is for repairing turbo machine blades, e.g., gas turbine blades on integrally bladed gas turbine rotors. The method includes at least the following steps: a) providing a turbo machine blade to be repaired or an integrally bladed rotor to be repaired having a damaged blade section; b) removing the damaged blade section from the turbo machine blade or from the integrally bladed rotor resulting in a blade stump; c) clamping the blade stump at least in the region of a flow leading edge and a flow trailing edge of the same in a cooling device; d) applying respectively a punctiform welding bead in the region of the flow leading edge and a flow trailing edge of the blade stump by laser powder build-up welding, the welding beads protruding at least over the flow leading edge and the flow trailing edge; e) applying material by laser powder build-up welding between the welding beads in the region of the or each removed blade section for restoring the respective blade section. | 08-28-2008 |
20080209726 | BRAZE REPAIR OF SHROUD BLOCK SEAL TEETH IN A GAS TURBINE ENGINE - An undersize repair region of a gas turbine engine stationary shroud is repaired with a sufficient mass of a repair material. The repair region includes a protruding portion that is undersized, and the repair includes machining of the protruding portion, grooving the resulting rub surface, inserting a replacement element, applying a brazing repair material, and brazing the article to form a repaired article. The repair material preferably includes a first fraction of a first powder of a first alloy component, and a second fraction of a second powder of a second alloy component. The first alloy component and the second alloy component have different solidus temperatures. The repair material is placed in the repair region. The repair material and the repair region are heated to melt the repair material but not the repair region, and thereafter the repair material and the repair region are cooled to solidify the repair material. | 09-04-2008 |
20080244905 | Method For Joining Blades to Blade Roots or Rotor Disks When Manufacturing and/or Repairing Gas Turbine Blades or Integrally Bladed Gas Turbine Rotors - A method is provided for joining blades to blade roots or rotor disks when manufacturing and/or repairing gas turbine blades or integrally bladed gas turbine rotors. A blade and a blade root or rotor disk that is to be joined to the blade are supplied, and provided with a thickening in sections that are to be joined together. The sections of the blade and the blade root or rotor disk that are to be joined together are machined so as to form recesses and; c) are then aligned relative to each other, opposite recesses defining at least one groove-shaped seam preparation. The blade and the blade root or rotor disk are joined in the area of the or each seam preparation by means of laser power build-up welding and the joined blade and blade root or rotor disk are machined so as to provide a gas turbine blade or an integrally bladed gas turbine rotor having a predefined geometrical profile. | 10-09-2008 |
20080263863 | Dimensional restoration of turbine blade knife edge seals - A turbine blade assembly comprising a knife edge seal having at least one seal member. The at least one seal member comprising a restored portion fused to a stub portion, where the restored portion comprises a plurality of fused layers of a restoration material, the restoration material being melted and deposited in a layer-by-layer manner to form the plurality of fused layers. | 10-30-2008 |
20080263864 | TURBOMACHINE BLADE AND TURBOMACHINE COMPRISING THIS BLADE - The present invention relates to a resurfacing method of repairing a surface portion of a moving turbomachine blade. The method is noteworthy in that metal particles are deposited on said surface by electrolysis. The latter is of the type comprising pad electrolysis, electrolysis in a bath or microbath, or a combination thereof. | 10-30-2008 |
20080289179 | Split vane repair - A method of repairing a vane cluster for a gas turbine engine includes attaching a first registration block to a salvageable airfoil segment of the vane cluster, machining a face of the first registration block relative to datum surfaces of the vane cluster, removing a damaged airfoil segment from the vane cluster, adding new material to the salvageable airfoil segment, joining a replacement airfoil segment having a second registration block to the salvageable airfoil segment to replace the damaged airfoil segment, removing the first registration block, and removing the second registration block. The respective first and second registration blocks of the salvageable airfoil segment and the replacement airfoil segment are aligned in a configuration substantially identical to a configuration of the vane cluster prior to undergoing repair. | 11-27-2008 |
20090038151 | METHOD FOR ESTABLISHING A LOCATION OF AN ELEVATED STRESS REGION - A method for use in repairing gas turbine engine components includes applying a stress to a first gas turbine engine component to cause surface cracking on the first gas turbine engine component and establishing a location of an elevated stress region of a second gas turbine engine component based upon the location of the surface cracking on the first gas turbine engine component. | 02-12-2009 |
20090049689 | METHOD REPAIR OF TURBINE BLADE TIP - A method of repair of a turbine blade involves inspecting a turbine blade having an internal cavity and a cap. The cap is removed and replaced with a replacement cap. The replacement cap has an opening. The opening provides access to the internal cavity of the internal blade so that the replacement cap may be attached to the turbine blade through the opening. | 02-26-2009 |
20090064500 | METHOD OF REPAIRING A TURBINE ENGINE COMPONENT - The inventive method involves the inspection of a turbine engine. A damaged component of the turbine engine is identified. Portions of the turbine engine component are removed from the damaged area to accommodate an overlay. The overlay is sized smaller than the turbine engine component. The overlay is then placed in a location previously occupied by the removed portion and attached to the turbine engine component. | 03-12-2009 |
20090094831 | METHOD FOR RESTORING AIRFOIL CONTOUR ON INTEGRALLY BLADED ROTORS - An integrally bladed rotor includes a central hub and a plurality of airfoils or blades. The blades are repaired by rebuilding their surfaces beyond the original shape, such as by adding weld material. The contour of the blade is then returned to the desired shape using superabrasive quills. | 04-16-2009 |
20090094832 | Heat treating apparatus and method of using same - An apparatus and method for heat treating the welded area of a repaired gas turbine engine component uses first and second heating elements. The heating elements each include an insulating tube supported by a support rod and wrapped with a conducing wire. One of the heating elements is sized to fit inside a recess in the gas turbine engine component, adjacent to the welded area, while the second heating element is placed outside the recess, but also adjacent to the welded area, thereby heating the welded area from two sides. | 04-16-2009 |
20090144980 | SYSTEM AND METHOD FOR ADAPTIVE MACHINING - A method of repair includes removing a deformed portion of a component to define a native component portion and adding a replacement portion to the native component portion. The replacement portion is adaptively machined based on one or more parameters of the native component portion and based on one or more original design parameters of the component. | 06-11-2009 |
20090241339 | METHOD FOR REPAIRING AN AIRFOIL - An example method of repairing an airfoil includes the steps of securing additional material to a worn airfoil and limiting movement of the additional material with a guide. | 10-01-2009 |
20090255114 | Methods for correcting twist angle in a gas turbine engine blade - A method of correcting a twist angle of a gas turbine engine blade includes measuring an existing twist angle of the blade, applying a first angular load to a first end of the blade; and measuring a repaired twist angle of the blade. The first angular load applied to the first end of the blade is based on an empirical correlation between a plurality of angular loads necessary to produce a plurality of twist angle correction values. | 10-15-2009 |
20090255115 | Method for developing a repair process to correct a deformed gas turbine engine component - A method of developing a repair process for a gas turbine engine component deformed during engine operation includes determining peak stress locations in a model of the component, applying loads to sample components based on the model to produce geometrical correction values in the samples, generating data from the samples including the loads applied and the geometrical correction values produced, destructively analyzing the samples at the peak stress locations for structural imperfections, and correlating the loads applied to the geometrical correction values produced to determine allowable loads necessary to produce target geometrical correction values in a used component substantially free of structural imperfections. | 10-15-2009 |
20090255116 | METHOD OF REPAIRING A FUEL NOZZLE - A method of repairing a fuel nozzle is disclosed comprising the steps of forming a pilot assembly; installing into a repair bore; inserting a primary adaptor into a repair bore such that the primary adaptor is in flow communication with a pilot flow passage and the pilot assembly; and coupling the primary adaptor to a distributor and the new pilot assembly. | 10-15-2009 |
20090255117 | GAS TURBINE HOT GAS COMPONENT REPAIR METHOD - A gas turbine engine hot gas component repair method for defects that do not extend through the thickness of the component is provided. First defects are removed by machining a cavity in the surface of a component. Coupons, fittable within the cavities are manufactured, are for example coated with brazing medium on an inner surface and then joined to the component by joining means such as laser metal forming. The joint holds the coupon during later heat treatment, thereby eliminating a need for holding aids. Before heat treatment, a further brazing medium can be applied to the surface of the coupon overlapping onto the component. A single heat treatment, brazing the coupon to the component and, brazing the brazing medium to the outer surface of the coupon can, then be used to complete the repair. | 10-15-2009 |
20090265932 | METHOD FOR REPAIRING A GUIDE VANE SEGMENT - A method for repairing a guide vane segment of a gas turbine, the guide vane segment including at least two guide vanes as well as an inner and an outer shroud. At least one guide vane is irreparably damaged and is separated from the guide vane segment while the guide vane segment is completed by joining at least one replacement vane. If the one irreparable guide vane is located in one half of the segment outside the circumferential center of the guide vane segment, or if the several irreparable guide vanes are located in the same half of the segment, the matching number of guide vanes to be separated from the segment and replacement vanes to be joined to the segment are determined first. The determined number of replacement vanes are then joined to the guide vane segment. The same number of guide vanes, including the at least one irreparable guide vane, are finally separated from the guide vane segment. | 10-29-2009 |
20090271983 | METHOD TO WELD REPAIR BLADE OUTER AIR SEALS - A method of repairing a blade outer air seal for a gas turbine engine includes the step of utilizing laser powder fusion materials to supply a metal powder filler into cracks in the blade outer air seal to repair the blade outer air seal for future service. Finally, a weld pass without deposition of powder metal is performed. | 11-05-2009 |
20090271984 | METHOD FOR REPAIRING A GAS TURBINE ENGINE COMPONENT - A method of repairing a stator assembly of a gas turbine engine includes removing a worn surface of the stator assembly to provide a revealed area, and securing additional material to the stator assembly utilizing gas metal arc welding. | 11-05-2009 |
20090271985 | REPAIR METHOD - The invention relates to a method of repairing moving blades of a gas turbine, with at least the following steps: a) preparation of a moving blade to be repaired; b) removal of at least one damaged section of a damaged blade tip of the moving blade to be repaired, forming a parting surface; c) successive building up of the, or each, removed section or the entire blade tip on the parting surface of the moving blade by means of a rapid manufacturing process, using three-dimensional CAD structural data on the moving blade. | 11-05-2009 |
20090282677 | COMPRESSOR STATOR CHORD RESTORATION REPAIR METHOD AND APPARATUS - A method for defining an airfoil with a radiused shape edge includes joining a filler material to the airfoil such that the filler material defines excess material that extends beyond an operational condition edge location of the edge of the airfoil, placing the airfoil within a barrel, providing an abrasive finishing media in the barrel with the airfoil, rotating the barrel to produce relative motion between the abrasive finishing media and the airfoil. Contact between the abrasive finishing material and the airfoil facilitates removing the excess material that extended beyond the operational condition edge location of the edge of the airfoil. | 11-19-2009 |
20090282678 | Methods of Maintaining Turbine Discs to Avert Critical Bucket Attachment Dovetail Cracks - Methods of to maintaining turbine discs prone to cracks in bucket attachment dovetails are disclosed. In one embodiment, wherein a turbine disc comprises a plurality of bucket attachment dovetail regions, one or more of the bucket attachment dovetail regions comprises a cooling slot, and each cooling slot comprises edges and adjacent surfaces, a method comprises inspecting the one or more of the bucket attachment dovetail regions comprising a cooling slot to confirm that each bucket attachment dovetail region meets predetermined minimum standards. The method further comprises blending the edges of the at least one of the cooling slots. The method further comprises polishing the edges of the at least one of the cooling slots. The method further comprises peening the edges of the at least one of the cooling slots. The method further comprises coating the edges and adjacent surfaces of at least one of the cooling slots. | 11-19-2009 |
20090313822 | METHODS AND APPARATUSES FOR CORRECTING TWIST ANGLE IN A GAS TURBINE ENGINE BLADE - The present invention includes a method of repairing a twist angle of a turbine blade, which method includes restraining a root of the blade, induction heating one or more portions of the blade, and applying an angular load to a tip of the blade. | 12-24-2009 |
20090313823 | IMPARTING DEEP COMPRESSIVE RESIDUAL STRESSES INTO A GAS TURBINE ENGINE AIRFOIL PERIPHERAL REPAIR WELDMENT - A gas turbine engine airfoil is repaired by machining away airfoil material along at least a portion of at least one of leading and trailing edges and a radially outer tip forming at least one cut-back area and forming a weldment by welding successive beads of welding material into the cut-back area. Desired finished dimensions of the repaired airfoil are obtained by machining away some of the weld bead material in the weldment and then deep compressive residual stresses are imparted in a pre-stressed region extending into and encompassing the weldment and a portion of the airfoil adjacent the weldment. The compressive residual stresses may be are imparted after either rough machining or final finishing thereafter of the weldment. The cut-back area may extend up to about 90% of the airfoil's span and have a maximum cut-back depth up to about 0.22 inches. | 12-24-2009 |
20090320287 | Compressor blade flow form technique for repair - A method for repairing a turbine engine component is provided. The method broadly comprises the steps of providing a turbine engine component having an airfoil portion, applying a coating to the airfoil portion, and restoring a tip portion, a chord, and surfaces of the airfoil portion to original dimensions in a single operation. A system for repairing the turbine engine component is also described. | 12-31-2009 |
20090320288 | Method for repairing a turbine - A method for facilitating turbine repair is disclosed. The method includes determining wear characteristics of a turbine blade based on at least one of turbine type or turbine application. The method also includes determining a delineated repair area on the turbine blade based on the determined wear characteristics of the turbine blade. The method additionally includes providing a replacement turbine blade part generally matching the size, shape, and material of the turbine blade. | 12-31-2009 |
20100005656 | A METHOD FOR FITTING THE ROTOR OF A WIND GENERATOR - Method of mounting the rotor of a wind turbine ( | 01-14-2010 |
20100011575 | METHOD OF REPLACING WIND TURBINE EQUIPMENT - A method of replacing wind turbine equipment, which can reduce the cost for replacing large equipment disposed in a nacelle, is provided. The method is characterized by including a winch-hoisting step for winching up to a nacelle a reciprocating winch that is used for replacing the wind turbine equipment disposed in the nacelle mounted atop a tower and a balance supporting the wind turbine equipment with an ordinarily-installed winch provided on a girder that moves in the nacelle; a wire-hoisting step for hoisting a wire that is used for the replacement of the wind turbine equipment to the nacelle from a drum disposed on the ground; a winch-replacing step for detaching the ordinarily-installed winch from the girder and attaching the winch for replacement to the girder; and a wire-arranging step for arranging the hoisted wire on the reciprocating winch and a movable pulley provided between the balance and the girder. | 01-21-2010 |
20100037459 | Method for Correcting Downstream Deflection in Gas Turbine Nozzles - A gas turbine nozzle can be refurbished to reduce downstream deflection. The outer shroud of the gas turbine nozzle is held in a fixture, and then the nozzle is heated. The heated nozzle is then reshaped by a force exerted upon the inner shroud of the gas turbine, reducing the downstream deflection of the nozzle. After the deformation of the nozzle, an aft hook of the nozzle that has been adjusted by previous refurbishment efforts can be rebuilt to remove the previous adjustments. | 02-18-2010 |
20100043228 | Method of Preparing an Engine for Ferry Flight - A method for preparing a gas turbine engine for a ferry flight, where the engine has a core gas turbine engine, a spinner, and a plurality of external fan blades powered by the core gas turbine engine. The core gas turbine engine has an annular splitter for directing a portion of incoming airflow into the core gas turbine engine. The method comprises the steps of: a) removing the spinner; b) removing the fan blades; and c) securing a fairing in sealing engagement with the core gas turbine engine. | 02-25-2010 |
20100050434 | Gas Turbine Airfoil Assemblies and Methods of Repair - Gas turbine airfoil assemblies and methods of repair are provided. In this regard, a representative method includes: separating the airfoil from the platform; forming a depression in the platform, the depression being sized and shaped to receive a replacement airfoil; and affixing the replacement airfoil within the depression such that the replacement airfoil is attached to the platform. | 03-04-2010 |
20100050435 | BLADE TIP REPLACEMENT METHOD - A gas turbine blade, a gas turbine blade airfoil repair method, and an airfoil corresponding to the product of the method are disclosed. The airfoil extends radially from a platform and includes a tip having a tip edge radially distant from the platform; a trailing edge; and a leading edge. The method includes forming a joining plane extending from the leading edge to the tip edge, wherein the joining plane forms at least one arc; forming a replacement tip fittable on the joining plane; and bonding the replacement tip to the airfoil. | 03-04-2010 |
20100064515 | METHOD FOR REPAIRING AND/OR REPLACING INDIVIDUAL ELEMENTS OF A GAS TURBINE COMPONENT - The present invention relates to a method for repairing and/or replacing individual elements of a gas turbine component ( | 03-18-2010 |
20100083499 | METHOD FOR REMOVING BLADE RING AND MEMBER FOR REMOVING BLAD RING - There are provided a method for removing a blade ring by pulling out the blade ring smoothly and surely while preventing damage to other components, and a member for removing a blade ring. By using a dummy blade ring, connection plates, and connecting bolts, work for removing and mounting a lower half section of the blade ring is performed. Thereby, work of rotation and the like can be performed while the lower half section of the blade ring and the dummy blade ring are connected to each other in both end portions. Therefore, during the work, the lower half section of the blade ring and the dummy blade ring are prevented from shifting from each other and therefore from interfering with the opposed rotor blade tip, a lower half section of a casing, and the like, thus preventing damage to the tip, distortion of the lower half section of the blade ring and the dummy blade ring, and the like. Consequently, a stator blade ring can be pulled out smoothly and surely. | 04-08-2010 |
20100095526 | METHOD OF REPAIRING MACHINED COMPONENTS SUCH AS TURBOMACHINE BLADES OR BLADES OF BLISKS - The invention relates to a method of using machining to repair a component workpiece ( | 04-22-2010 |
20100101086 | DEVICE AND PROCESS FOR RAPID DISASSEMBLY OF A ROTOR AND A NACELLE FROM THE MAST OF A WINDMILL, AS WELL AS A WINDMILL THAT IS EQUIPPED WITH SUCH A DEVICE - A crane-bearing assembly ( | 04-29-2010 |
20100126014 | REPAIR METHOD FOR TBC COATED TURBINE COMPONENTS - A method is provided for repairing a metallic turbine component which includes a thermal barrier coating system including a metallic bond coat and a ceramic top coat. The method includes: (a) removing the top coat using a mechanical process; (b) partially stripping the metallic bond coat from the component, such that substantially no material of the component is removed; (c) repairing at least one defect in the turbine component; (d) applying a new metallic bond coat to the turbine component; and (e) applying a new ceramic top coat over the metallic bond coat. | 05-27-2010 |
20100126015 | IMPELLER WELD RESTRAINING FIXTURE - The present invention provides an apparatus for use in automated welding repairs, particularly those repairs intended for impellers and similar structures. In one embodiment, the invention provides an impeller weld restraining fixture. The fixture includes a base plate and top ring. An impeller may be sandwiched between the base plate and the top ring. Tangs located on the top ring may be fitted to rest in the valley faces between airfoils on an impeller. Bolting the top ring to the base plate, with the impeller firmly secured therebetween, restrains the impeller so as to minimize warpage during welding repairs and heat treatments. | 05-27-2010 |
20100162565 | REFURBISHING METHOD AND SYSTEM FOR A MAIN ROTOR BLADE SPAR - A method of refurbishing a rotor blade utilizing a waterjet and an apparatus therefore. | 07-01-2010 |
20100199494 | METHOD AND APPARATUS FOR MICROPLASMA SPRAY COATING A PORTION OF A COMPRESSOR BLADE IN A GAS TURBINE ENGINE - A method and apparatus for microplasma spray coating a portion of a substrate, such as a gas turbine compressor blade, without masking any portions thereof. The apparatus includes a microplasma gun with an anode, cathode, and an arc generator for generating an electric arc between the anode and cathode. An arc gas emitter injects inert gas through the electric arc. The electric arc is operable for ionizing the gas to create a plasma gas stream. A powder injector injects powdered material into a plasma stream. A localized area of the compressor blade is coated with the powdered material without having to mask the compressor blade. | 08-12-2010 |
20100205805 | TURBINE ROTOR BLADE REPAIR METHOD - A turbine rotor blade repair method which reduces the occurrence of cracks due to welding is provided. A turbine rotor blade repair method for repairing damage of a fin at a tip of a turbine rotor blade includes overlaying a damaged portion of the fin with metal by welding (step S | 08-19-2010 |
20100223788 | METHOD OF MAINTAINING GAS TURBINE ENGINE COMPONENTS - An example method of maintaining a serviceable component of a gas turbine engine includes selecting a used component, using a fluid to move an abrasive against a surface of the used component, and removing material from the used component using the abrasive. In one example, the method moves the abrasive against the surface of the used component when the used component is installed within the gas turbine engine. | 09-09-2010 |
20100223789 | METHOD AND APPARATUS FOR REPAIRING TURBINE ROTOR - A method for repairing a rotor of a turbine includes providing a rotor having a groove portion defined by a circumferential portion of the rotor. The circumferential portion of the rotor is removed to create an opening to provide access to the groove such that the opening, immediately adjacent the groove, is narrower than the groove. A guide block may be extended into a receiving slot separating a first protruding surface from a second protruding surface of the rotor such that a weld area slot of the guide block extends over at least a portion of the opening. The opening may be welded adjacent the guide block to close at least a portion of the opening. | 09-09-2010 |
20100236067 | Hybrid welding repair of gas turbine superalloy components - Methods are provided for repairing a degraded section of a turbine blade, the turbine blade comprising a base material. In one embodiment, and by way of example only, the method includes the step of electro-spark depositing a first material on the turbine blade degraded section to form an intermediate layer thereon, the first material comprising a material that is substantially similar to the base material. Next, a second material is laser welded onto the intermediate layer to form a repaired section. This invention combines the low-heat input of electro-spark deposition with the high welding quality and high deposition rate of laser powder fusion welding. | 09-23-2010 |
20100257733 | High pressure single crystal turbine blade tip repair with laser cladding - Methods are provided for repairing a damaged section of an air-cooled turbine blade, the blade having a first wall, a second wall, a trailing edge, and a plurality of cooling holes, the plenum formed between the first and second walls and having a predetermined shape, and the plurality of cooling holes formed on the trailing edge in flow communication with the plenum and having predetermined shapes. In one embodiment, and by way of example only, the method includes the steps of injecting a filler material into the blade plenum and the plurality of blade cooling holes, the filler material capable of solidifying into the predetermined shapes of the blade plenum and blade cooling holes. Then, the damaged section of the blade is laser welded and machined to original dimensions. Next, the filler material is removed. | 10-14-2010 |
20100275442 | METHOD AND SYSTEM FOR DISENGAGING A SHRINK COUPLING ON A TURBINE GENERATOR - A system and associated method for disengaging a shrink coupling that secures a shaft to a drive train component, such as a gearbox, includes a reaction plate erected around the shaft at a location displaced from the shrink coupling, with the reaction plate being anchored in place relative to the shaft. A plurality of jacking devices, such as hydraulic jacks, are operationally disposed between the reaction plate and shrink coupling and spaced circumferentially around the shaft. The jacking devices have a first end engaged against the reaction plate and a second opposite end mechanically fastened to the shrink coupling. To remove the shrink coupling from the drive train component, the shrink coupling is released from its clamped state and the jacking devices are activated to exert a pulling force on the shrink coupling, which causes the shrink coupling to be pulled off of the drive train component and moved axially along the shaft to a resting position on the shaft. | 11-04-2010 |
20100293786 | METHOD AND APPARATUS FOR REBUILDING GAS TURBINE ENGINES - A method for repairing a turbine blade for a gas turbine engine is provided. The method includes securing the blade into a clamping fixture, obtaining a zero reference from a gauging surface on the clamping fixture, coupling the clamping fixture to a grinding machine, and grinding the blade based on the zero reference. | 11-25-2010 |
20100313419 | METHOD FOR RECONDITIONING A TURBINE BLADE - A method is provided for reconditioning a turbine blade. The turbine blade includes a blade airfoil which extends longitudinally and into the hollow inner space of which inserts can be inserted in the longitudinal direction of the blade for distribution and guiding cooling air which flows in the inner space. The inserts with a rib engage with sealing effect in a U-shaped sealing groove which is machined out on the inner wall of the blade airfoil and extend in the longitudinal direction of the blade. A damaged sealing groove is reconditioned by the sealing groove being removed from the inner wall of the blade airfoil, forming a slot, by an insertion strip, which is provided for sealing, being inserted into the slot, and by the insertion strip, which is seated in the slot, being connected in a materially bonding manner to the inner wall of the blade airfoil. | 12-16-2010 |
20110000086 | DEVICE AND METHOD FOR REPAIRING A FORWARD FRAME V-BLADE IN AN AIRCRAFT ENGINE - A repair device and method for repairing a forward frame v-blade on an aircraft engine are described in which the repair device replaces a section of the forward frame v-blade. In one embodiment, the repair device includes a supplemental part, which is secured to the forward frame v-blade. The supplemental part includes a central web and a pair of legs with a leg thickness that is greater than the thickness of corresponding flanges on the forward frame v-blade. Fasteners such as rivets are used to couple the supplemental part to the forward frame v-blade. | 01-06-2011 |
20110005075 | SOLID STATE RESISTANCE WELDING FOR AIRFOIL REPAIR AND MANUFACTURE - A method for bonding airfoil sections includes aligning upper and stub airfoil sections having upper airfoil pressure and suction sides and stub airfoil pressure and suction sides respectively, pressing together upper and stub airfoil cross sections at upper and stub airfoil distal ends of the upper and stub airfoil sections respectively, and then resistance welding, preferably solid state resistance welding, the upper and stub airfoil sections together along the upper and stub airfoil cross sections by passing electrical current across the upper and stub airfoil cross sections. The upper and stub airfoil sections may be clamped between pressure and suction side upper airfoil electrodes and between the stub airfoil pressure and suction sides respectively. The method may be performed while the stub airfoil section is attached to an airfoil carrier such as a rotor disk rim, a gas turbine engine drum, or a gas turbine engine blade platform. | 01-13-2011 |
20110138624 | CONSUMABLE COLLAR FOR LINEAR FRICTION WELDING OF BLADE REPLACEMENT FOR DAMAGED INTEGRALLY BLADED ROTORS - A method of repairing an integrally bladed rotor includes the steps of placing a support collar around at least a leading and trailing edge portions of the blade stub, and performing linear friction welding to add a replacement airfoil to the blade stub. The linear friction welding is generally along a direction between the leading and trailing edges. In addition, the support collar leading and trailing edge portions are connected together. | 06-16-2011 |
20110138625 | REPAIR OF INTEGRALLY BLADED ROTORS - A method is provided for repairing a damaged rotor blade on an integrally bladed rotor by removing a damaged portion of a damaged blade leaving a blade stub extending outwardly from the disk and performing a linear friction welding operation to attach a replacement blade segment to the blade stub. The rotor may be disposed operation using a linear friction welding apparatus. The method includes disposing a support collar about the blade stub and securing the support collar to the linear friction welding apparatus prior to a commencement of the bonding operation. A lower surface of the support collar is contoured to mate with a portion of an outer circumference surface of the rotor disk. | 06-16-2011 |
20110167633 | METHOD OF REPAIRING A WIND TURBINE BLADE - A method of repairing a wind turbine blade while mounted on a tower without removing the blade from the tower is provided. The method may begin by positioning the wind turbine blade in a substantially vertical orientation. Next, a blade reinforcement structure is secured to the blade to reduce stress on a portion of the blade. The blade is repaired by removing a damaged portion of the blade, and installing a repair portion to the blade where the damaged portion was removed. The method may conclude by removing the blade reinforcement structure from the blade. | 07-14-2011 |
20110167634 | COATED GAS TURBINE ENGINE COMPONENT REPAIR - A method of repairing a component of a gas turbine engine that includes a metallic substrate, an existing aluminide coating, and a diffusion layer formed in the metallic substrate adjacent to the coating. The method includes removing at least a portion of the existing aluminide coating, removing material forming the diffusion layer, applying a new metallic layer to the metallic substrate, and applying a new aluminide coating over the new metallic layer to form a new diffusion layer in the new metallic layer. The new metallic layer is a substantially homogeneous material that is substantially similar in chemical composition to that of the metallic substrate, and the new metallic layer forms a structural layer having a thickness selected to provide a specified contour to the component. | 07-14-2011 |
20110167635 | METHOD OF REPAIRING SHROUDED TURBINE BLADES WITH CRACKS IN THE VICINITY OF THE OUTER SHROUD NOTCH - A method of repairing a damaged notch fillet radius of a turbine blade shroud includes a replacement notch fillet radius and a hardface nugget. The damaged notch fillet radius is blended out and a hardface structure positioned proximate the damaged notch fillet radius is removed. A replacement notch fillet radius is formed with weld filler and the hardface nugget is welded to at least a portion of the replacement notch fillet radius. | 07-14-2011 |
20110173811 | Method Of Servicing The Outer Components Of A Wind Turbine Such As The Wind Turbine Blades And The Tower With A Work Platform And Work Platform - A method of servicing a wind turbine generally comprises rotating a rotor of the wind turbine until a blade extends downwardly next to the wind turbine tower. A work platform is positioned next to the tower with at least one steering wheel in contact with the tower. The work platform is connected to an upper part of the wind turbine with at least one cable and then moved vertically and horizontally to a first position. A section of the blade within reach is serviced in the first position, and then the work platform is moved vertically and horizontally to a second position for servicing a different section of the blade. The steering wheel is in contact with the tower when the work platform is moved. | 07-21-2011 |
20110179645 | REMOVAL OF STUCK BLADE IN A TURBINE ENGINE - An apparatus for dislodging stuck blades in a turbine engine. The apparatus includes a housing, cam structure, and impact structure. The housing is capable of being temporarily secured to a blade disc structure adjacent to a stuck blade to be dislodged. The cam structure is associated with the housing and is adapted to receive an input torque that rotates the cam structure, the cam structure capable of translating the input torque into an impact force, the impact force including a component in a desired direction. The impact structure is associated with the housing and is capable of receiving the impact force from the cam structure and exerting the impact force on a root area of the stuck blade for dislodging the stuck blade from the blade disc structure non-destructively. | 07-28-2011 |
20110209347 | METHOD FOR REPAIRING A WIND TURBINE BLADE - A procedure for repairing subsurface defects in a shell member laminate of a wind turbine blade includes detecting the location and boundary of the subsurface defect and drilling a fill hole from an external surface of the laminate into the defect proximate to a boundary of the defect. A vent hole is drilled from the external surface of the laminate into the defect proximate to an opposite boundary from the fill hole. A flowable bonding material is injected into the fill hole until the bonding material flows from the vent hole. The repair zone is reinforced with at least one mechanical fastener defined through the laminate either within the boundary of the defect or outboard of the boundary of the defect. | 09-01-2011 |
20110219616 | METHOD FOR REPLACING AN INNER DISK ELEMENT OF AN INTEGRALLY BLADED DISK - The present invention relates to a method for replacing an inner disk element of a blade integrated disk wherein the blade integrated disk has a plurality of recesses in the form of axial through-bores in the joining area. The method begins with filling the axial through-bores, after which the inner disk element of the blade integrated disk is separated from the remaining blade ring. Next a new inner disk element is inserted into the remaining blade ring and the new inner disk element and the remaining blade ring are joined. Finally the axial through-bores are restored. | 09-15-2011 |
20110225823 | Cobalt alloy and method for its manufacture - A cobalt alloy is proposed, made up of at least 30% by weight cobalt, 0 to 20% by weight nickel, 5 to 30% by weight chromium, 0.4 to 2.5% by weight carbon and at least one carbide-forming metal which forms carbides with the carbon, wherein the atomic ratio in the alloy of the carbide-forming metal to the carbon amounts to at least 0.8, wherein the alloy can furthermore optionally contain one or more of the elements molybdenum, tungsten, aluminum, titanium, niobium, iron, silicon, manganese, vanadium, boron, zirconium and contaminants. The carbides are present in the alloy in the form of a finely dispersed phase without a preferred direction. | 09-22-2011 |
20110296685 | Gas Turbine Blade and Manufacturing Method Thereof - In a gas turbine blade where a part of the γ′ phase precipitation strengthened type Ni-based alloy base material is composed of a weld metal, the weld metal is a Ni-based alloy containing Ta from 4.8 to 5.3 wt. %, Cr from 18 to 23 wt. %, Co from 12 to 17 wt. %, W from 14 to 18 wt. %, C from 0.03 to 0.1 wt. %, Mo from 1 to 2 wt. %, and Al of 1 wt. % or less, in which the oxygen content is 0 to 30 ppm, the Ti content from 0 to 0.1 wt. %, and the Re content from 0 to 0.5 wt. %. A blade base metal is manufactured by the step of stripping, the step of solution heat treatment where the γ′ phase is dissolved again, the step of welding in an inert gas chamber by a TIG method using a welding wire where the weld metal can be obtained, the step of HIP treatment at 1100° C. to 1150° C., and the step of an aging treatment at 835° C. to 855° C. | 12-08-2011 |
20110302781 | METHOD FOR PROVIDING RUB COATINGS FOR GAS TURBINE ENGINE COMPRESSORS - Rub coatings, and methods for applying rub coatings, are provided for compressor assemblies of gas turbine engine assemblies. The coating may be applied as an initial coating to a new surface of a component, as well as a repair and replacement corrosion resistant rub coating for applying to a previously coated component of a gas turbine engine assembly such as a compressor casing. The method includes the steps of providing a component of a gas turbine engine assembly, the component having predetermined dimensions and specifications for operational use in an engine assembly. The component has a surface having a damaged rub coating thereon, the damaged rub coating not in compliance with the predetermined dimensions and specifications. The method includes removing the non-compliant damaged rub coating to expose the surface. Next, a repair corrosion resistant rub coating comprising MCrAlX is applied to the surface. Finally, the repair corrosion resistant rub coating comprising MCrAlX is machined to restore the coated component to comply with the predetermined dimensions and specifications. | 12-15-2011 |
20110308085 | METHOD OF SERVICING AN AIRFOIL ASSEMBLY FOR USE IN A GAS TURBINE ENGINE - A method of servicing an airfoil for use in a gas turbine engine. The airfoil assembly is defined by a base material and includes an airfoil and a platform from which the airfoil extends. A predetermined amount of the base material is removed from the airfoil assembly proximate to a fillet area of the airfoil assembly via water jet material removal. The fillet area comprises a junction between the airfoil and the platform and is located at an intersection between the airfoil and the platform. A remainder of the base material comprising base material of the airfoil assembly other than proximate to the fillet area is left intact. | 12-22-2011 |
20120060370 | SYSTEM AND METHOD FOR REPAIRING A GAS TURBINE ENGINE COMPONENT - A method for repairing a defect in a component having a first major surface and a second major surface, a thickness defined between the major surfaces, and an edge adjoining both the major surfaces is characterized by forming a slot cut entirely through the thickness of the component between the first and second major surfaces, the slot extending inward from the edge of the component towards an interior of the component to a depth from the edge sufficient to remove at least a substantial part of the defect, the slot defining an open end at the edge of the component, a closed end within the component, a width, a radius formed by the closed end, and opposing chamfered edges at the open end. | 03-15-2012 |
20120073134 | Method and System for Servicing a Horizontal-Axis Wind Power Unit - A method and system for attaching a service device to a wind turbine of a wind power unit, using the wind turbine to rotate the service device into one or more service positions, and using the service device to perform servicing on the wind power unit. In some embodiments, a blade of the wind turbine is removed and the service device is mounted in its place. In other embodiments, the service device is mounted to a device mount approximately in a saddle region between adjacent blades. In one example, the service device is a crane. In another example, the service device is a stator module installation/removal tool. | 03-29-2012 |
20120084980 | Extending Useful Life of a Cobalt-Based Gas Turbine Component - A method of extending the useable life of a gas turbine component fabricated from a cobalt-based alloy is disclosed. The method includes applying a rejuvenation process to the alloy where the alloy is placed in a protected atmosphere and heated to three different elevated temperatures and held at the elevated temperatures for approximately four hours each. Application of the rejuvenation process allows gas turbine components to be returned to service for at least one more service interval of approximately 24,000 operating hours. | 04-12-2012 |
20120096713 | REPAIR OF A TURBINE ENGINE SURFACE CONTAINING CREVICES - A composition and method for cleaning turbine engine components ( | 04-26-2012 |
20120096714 | Method of Applying Abrasion Resistant Materials to Rotors - A process for applying a plurality of coats of abrasion resistant material to a substrate such as a rotor for an air-craft. The abrasion resistant material is composed of a first and a second material. The coats gradually transition from an abrasion resistant composition having a larger percentage part per volume of the first material to a larger percentage part per volume of the second material as additional coats are applied. | 04-26-2012 |
20120110847 | METHOD FOR SERVICING A TURBINE PART - According to one aspect of the invention, a method for in situ repair of a turbine part is provided. The method includes the steps of accessing the turbine part while assembled to other turbine components, wherein the turbine part comprises a region with a structural flaw near a hole in the turbine part, wherein the hole is configured to flow a cooling fluid and welding the structural flaw without performing a heat treatment of the turbine part, wherein welding the structural flaw comprises laser welding that maintains a structure of the region. | 05-10-2012 |
20120110848 | LOW AND EXTRA LOW SULFUR ALLOYS FOR REPAIR - A method for repairing, refurbishing, or replacing a turbine engine component or sub-component includes the steps of providing a turbine engine component or sub-component having a site to be repaired, refurbished, or replaced providing a repair or replacement material having a sulfur content, which sulfur content is less than 10 ppm, and applying the repair or replacement material to the site on the turbine engine component to effect the repair, the refurbishment, or the replacement. | 05-10-2012 |
20120151768 | Trammel Assembly for Rotor Pitch Links and Method of Using Same - Described is a trammel set tool designed to measure the center-to-center location of the bearings mounted on a pitch change link. Because pitch change links have two replaceable “lollypop” rod ends, it may be necessary at some point to replace an entire rod end, not just the bearing. The trammel set tool provides the operator the capability to remove an unserviceable rod end, and reinstall a new rod end to the same settings while taking into consideration | 06-21-2012 |
20120167389 | METHOD FOR PROVIDING A FILM COOLED ARTICLE - A method for providing a film cooled article is disclosed. A metallic article is provided having first and second wall surfaces and a cooling hole. The cooling hole includes a metering hole that extends from an inlet at the second wall surface to an outlet at the first wall surface. The method further includes exposing the first wall surface of the metallic article, applying a thermal barrier coating overlying the first wall surface and at least partially covering the outlet, boring through an outer surface of the applied thermal barrier coating to expose the metering hole, removing the thermal barrier coating from a trough portion of the outlet formed in the metallic article and forming a trough region in the thermal barrier coating that extends from the trough portion of the outlet formed in the metallic article to be flush with the outer surface of the thermal barrier coating. | 07-05-2012 |
20120180314 | COMPOSITE SHROUD AND METHODS FOR ATTACHING THE SHROUD TO PLURAL BLADES - The present invention relates to a method for balancing a wind turbine. The method includes the steps of a) measuring at least one property that is dependent on a motor workload of at least one yaw motor | 07-19-2012 |
20120216402 | REPAIR ALIGNMENT METHOD AND APPARATUS FOR TURBINE COMPONENTS - A turbine component repair apparatus includes: a first die having male and female halves for clamping a first section of a turbine blade with a platform and a root portion of an airfoil, the first die having a recess shaped to receive the root portion and retain a faying surface thereof in predetermined alignment; and a second die having male and female halves for clamping a repair section which defines a tip portion of the airfoil, the second die having a second recess shaped to receive the tip portion and retain a faying surface of the tip portion in predetermined alignment. The first and second dies have mating front faces configured to align their bottom surfaces in a common plane. A alignment device is removably attached to the second die to temporarily align the repair section in the absence of the male half of the second die. | 08-30-2012 |
20120222306 | METHODS FOR REPAIRING TURBINE COMPONENTS - A method is provided for repairing a turbine component with a distressed portion. The method includes machining the turbine component into a first intermediate turbine article such that the distressed portion is removed; and rebuilding the first intermediate turbine article into the turbine component with an additive manufacturing process. | 09-06-2012 |
20120240398 | METHOD AND APPARATUS FOR REPAIRING TURBINE ROTOR - A method for repairing a rotor of a turbine includes providing a rotor having a groove portion defined by a circumferential portion of the rotor. The circumferential portion of the rotor is removed to create an opening to provide access to the groove such that the opening, immediately adjacent the groove, is narrower than the groove. A guide block may be extended into a receiving slot separating a first protruding surface from a second protruding surface of the rotor such that a weld area slot of the guide block extends over at least a portion of the opening. The opening may be welded adjacent the guide block to close at least a portion of the opening. | 09-27-2012 |
20120255176 | METHOD FOR PRODUCING A METAL REINFORCEMENT FOR A TURBINE ENGINE BLADE - A method for creating a metal reinforcement for a leading or trailing edge of a turbine engine blade including a reinforcement foot and head, the method including: creating a plurality of V-shaped tapered elements that form different parts of the metal reinforcement so that the metal reinforcement is divided into a plurality of parts distributed between the foot and the head; positioning the parts on equipment that is shaped like the leading or trailing edge of the turbine engine blade; and rigidly connecting the different parts so as to form the complete profile of the one-piece metal reinforcement the by recombining the different parts. | 10-11-2012 |
20120272523 | METHOD OF REPAIRING A TURBINE ROTOR USING COLD SPRAYING - A method of repairing a damaged rotor comprising: (a) preparing a locally damaged portion of the rotor; (b) cold spraying alloy powder particles onto the locally damaged portion; (c) controlling the cold spraying in step (b) to restore the locally damaged portion to form a repaired portion having substantially the same properties and shape as originally manufactured; and (d) heat treating at least the repaired portion. | 11-01-2012 |
20120279065 | METHOD OF EXTRACTING BARREL NUTS - The present disclosure relates to a method for removing barrel nuts used for securing a plurality of studs to a turbine blade. Each stud is individually coupled to a respective barrel nut such that each barrel nut is anchored to a root end of the turbine blade. The barrel nut is heated to a predetermined temperature using a controller and a thermocouple. An adhesion between the barrel nut and the turbine blade is overcome and the barrel nut is extracted from the turbine blade. The barrel nut is removed from the turbine blade by connecting an extractor assembly or barrel nut removal device. This is accomplished from an interior surface of a root end of the turbine blade such that this method allows one to remove and replace barrel nuts while the turbine blade remains attached to the hub. | 11-08-2012 |
20120279066 | WELDING Ti-6246 INTEGRALLY BLADED ROTOR AIRFOILS - A method is disclosed for welding a first metal to a Ti-6246 alloy airfoil. The method consists of depositing weld metal by fusion welding and reshaping the airfoil to predetermined dimensions. A post weld heat treatment is applied to relieve residual stresses. Surface treatment such as laser shock peening introduces residual surface compressive stresses to enhance the mechanical integrity of the airfoil. | 11-08-2012 |
20120304465 | APPARATUS AND A METHOD OF SHAPING AN EDGE OF AN AEROFOIL - An apparatus for shaping an edge of an aerofoil comprising a brush and the brush comprises a plurality of bristles extending substantially parallel to each other. A motor rotates the brush about an axis. The axis is arranged substantially parallel to the bristles of the brush. A support structure holds the brush such that the axis intersects a first surface of the edge of the aerofoil or holds the brush such that the axis intersects a second surface of the edge of the aerofoil. There are means to move the brush such that the brush contacts the first surface of the edge or such that the brush contacts the second surface of the edge. There are means to produce relative movement of the brush and the aerofoil such that the first brush moves longitudinally along the edge of the aerofoil to shape the edge of the aerofoil. | 12-06-2012 |
20120317808 | METHOD AND APPARATUS TO REPAIR A TURBOMACHINE ROTOR WHEEL - A method of repairing a turbomachine rotor wheel including a first outer circumferential edge extending to a second outer circumferential edge through a circumferential surface, a dovetail interface extending across the outer circumferential surface between the first and second outer circumferential edges, and a bucket mounted to the dovetail interface includes identifying a defect on one of the first and second outer circumferential edges of the rotor wheel adjacent the bucket, securing the bucket in the dovetail interface to substantially constrain axial movement, and removing a portion of the one of the first and second outer circumferential edges to remove the defect. | 12-20-2012 |
20120317809 | METHOD OF REPAIRING A TURBINE NOZZLE SEGMENT IN A TURBINE ENGINE - A method for repairing a turbine nozzle having at least one vane disposed between an inner and an outer band. Embodiments of the method can comprise separating the inner band from the outer band and securing a replacement part to the inner band. In one embodiment, the methods accommodate replacement parts that include vanes with a base feature that comprises a non-airfoil shape and that integrates cooling features useful for operation of the turbine nozzle. | 12-20-2012 |
20130042474 | ROTOR SEAL WIRE GROOVE REPAIR - A method of repairing a seal wire groove is disclosed, the groove forming an annular structure having an outer surface and an inner surface and defining an original profile when new, comprising the steps of: removing a less-than-annular portion of the original profile of the groove to remove damaged portions of at least one of the inner and outer surfaces thereby forming a void; adding new material to the void; and shaping the new material to form a new profile of the groove. | 02-21-2013 |
20130074336 | METHOD FOR RECONDITIONING A ROTOR OF A TURBOMACHINE - A method is provided for reconditioning a turbomachine rotor, equipped with circumferentially extending grooves for accommodating blades retained in the grooves at a distance from each other by spacers. The method includes removing the blades and spacers from the grooves and hollowing out the exposed grooves, simultaneously widening the grooves to remove damage-inflicted material. At least one circumferentially extending lateral groove is introduced for accommodating a filler piece in the grooves to fill a gap between blades and hollowed-out rotor grooves. New spacers are provided which are matched to the hollowed-out grooves and have recesses which are matched to the introduced lateral grooves. Filler pieces are provided for inserting into the circumferentially extending lateral grooves and recesses of the new spacers. The blades and new spacers are inserted into the hollowed-out rotor grooves and corresponding filler pieces are inserted into the lateral grooves and matched recesses of the new spacers. | 03-28-2013 |
20130074337 | MULTIFUNCTIONAL PLATFORM OF WIND POWER GENERATING UNIT AND BLADE DISASSEMBLING METHOD - A multifunctional platform includes a platform frame including a base having an annular center hole and two parallel arms, a hoist mechanism including traction devices and moves the platform up and down, tower clamping mechanisms around the circumference of the annular center hole and preventing the platform frame from rotating, a moving dolly sliding on the two arms, two blade adjusting pedestals respectively provided on the protruding ends of the two arms, two set of blade drawing mechanisms, one end of each set of blade drawing mechanism is respectively connected with one blade adjusting pedestal. The blade disassembling method includes lifting the multifunctional platform to an appropriate height of the tower by the hoist mechanism, tying sling ropes at three positions of a blade, disassembling the blade and lowering it to a transport ship by a crane ship, and a fan maintenance crane, and the blade drawing mechanisms. | 03-28-2013 |
20130091704 | METHOD FOR REPAIRING ROTOR BLADES - In a method for repairing worn or damaged rotor blades of an aircraft engine, laser cladding for the reconstruction of the blade tips is not performed in a continuous welding process along the blade edge but during a cycle-by-cycle rotation of the rotor blades attached to a rotor disk, in only one limited section of the respective blade edge for each cycle. The method reduces time expenditure for the repair of the blades and improves the tribological properties of the blade material in the area of the repaired blade tip. | 04-18-2013 |
20130104397 | METHODS FOR REPAIRING TURBINE BLADE TIPS | 05-02-2013 |
20130133199 | METHOD FOR CLEANING WIND TURBINE BLADES - A fast and effective method for cleaning and repairing the shell-spar glue voids of a wind turbine blade, comprising the steps of detecting voids, raising the turbine blade at an incline, drilling holes into top and bottom ends of the void, injecting cleaning solution into the holes, and allowing the cleaning solution to drain out of the bottom holes and drain holes at the tip. The void is then inspected for oil by FTIR spectroscopy. If oil is detected, additional cleaning steps are performed comprising injection of a second cleaning solution into at least two holes of the void followed by a rest period, washing the holes with water via a pressure washer, and drying with compressed air. The blade is then inspected for oil and moisture, and when clean, adhesive is applied to the void through the holes. | 05-30-2013 |
20130139387 | METHOD OF REPAIRING A WIND TURBINE BLADE - A method of repairing a wind turbine blade while mounted on a tower without removing the blade from the tower is provided. The method may begin by positioning the wind turbine blade in a substantially vertical orientation. Next, a containment structure is suspended from a nacelle via a hoisting system that positions the containment structure at a damaged portion of the blade. The damaged portion is enclosed within the containment structure and the temperature of the air within the containment structure is controlled. The blade is repaired by removing a damaged portion of the blade, and installing a repair portion to the blade where the damaged portion was removed. The method may conclude by operating the hoisting system to remove the containment structure from the blade. | 06-06-2013 |
20130152389 | ROTOR BLADE REPAIR STRUCTURE AND METHOD - A method of repairing a damaged portion of a rotor blade includes filling the damaged portion with a filler material. A pre-cured patch assembly is applied over the damaged portion, the patch assembly including one or more laminate packs positionable at least one of an upper rotor blade surface and a lower rotor blade surface and one or more overwrap plies positionable over the upper rotor blade surface and the lower blade surface. A repair structure for a damaged portion of a rotor blade includes a volume of fill material disposed at the damaged portion. | 06-20-2013 |
20130180107 | METHOD FOR REFURBISHING A TURBO-MACHINE COMPONENT - A method for preparing to refurbish a turbo-machine component includes virtually refurbishing the turbo-machine component, actually refurbishing the turbo-machine component, and comparing the virtually refurbished turbo-machine component to the actually refurbished turbo-machine component. | 07-18-2013 |
20130185937 | METHOD OF SEALING COOLING HOLES - A method of selectively sealing at least one cooling hole provided on an aerofoil component ( | 07-25-2013 |
20130199039 | PROPELLER SERVICE METHOD - Disclosed is a method for maintenance of a ship propeller including the steps of: placing a flexible habitat having an open upper end over an uppermost blade and a portion of the propeller hub, and establishing a gas seal between the upper end of the habitat and the blade to close the habitat at its upper end. After fixing the lower end of the habitat relatively to the propeller, compressed gas is preferably introduced into the habitat to displace the water in the habitat. The apparatus for maintenance of a ship propeller under water comprises a flexible habitat with an open upper end. The habitat has a gas seal adapted to cooperate with a propeller blade surface to establish a gas seal to close the habitat at its upper end and fixing means adapted to fix the open lower end of the habitat relatively to the propeller. A means for introducing compressed gas into the habitat is provided. | 08-08-2013 |
20130199040 | Device and method for treatment of high-pressure turbine blades of a gas turbine - The present invention relates to a device and a method for in-situ treatment of turbine blades/vanes of a gas turbine, with the treatment device being insertable into a combustion chamber of the gas turbine via at least one access aperture and placeable on cooling-air recesses of the turbine blades, with the treatment device at its end including a tool head with at least one tool and at least one jet nozzle, with the jet nozzle being connected to a medium hose for externally supplying a treatment fluid, with the treatment device being provided with an actuating device for exactly guiding and/or placing and/or moving the tool head. | 08-08-2013 |
20130205589 | System and Method For Modifying A Rotor - A system for modifying a slot in a rotor includes a drill, a clamp connected to the drill and configured to engage with an interior surface of the slot, and means for supporting the drill from a stationary platform adjacent to the rotor. A method for modifying a slot in a rotor includes connecting a coupling to a stationary platform adjacent to the rotor, connecting a drill to the coupling, and locating the drill proximate to the slot. The method further includes inserting a clamp into the slot, engaging the clamp with an interior surface of the slot, and operating the drill to create a cavity in the slot. | 08-15-2013 |
20130219716 | METHOD FOR SERVICING A TURBINE ENGINE COVER PLATE ASSEMBLY - A holding structure associated with a lifting device for supporting a removed turbine engine cover plate assembly. The holding structure includes an upper support member and a lower support member. The upper support member is formed with a plurality of service areas, where each service area is configured for servicing a cover plate assembly. Each service area includes a plurality of slots extending inwardly from a peripheral edge of the upper support member to receive and support components of the cover plate assembly during a disassembly and service operation. | 08-29-2013 |
20130232792 | APPARATUS AND METHOD FOR SERVICING TURBOMACHINERY COMPONENTS IN-SITU - An apparatus adapted for servicing a turbomachine component includes a tool delivery mechanism adapted for delivering a tool to a desired location in a turbomachine. A tool support is adapted to be secured onto the body of the turbomachine, and is also configured to support the tool delivery mechanism. A machining tool is attached to the tool delivery mechanism, and includes an axial slide clamp configured to clamp to the turbomachine component, a radial slide slidably connected to the axial slide clamp, a spring connected to the axial slide clamp and the radial slide, the spring providing axial tension, and a machining bit retained at least partially within the radial slide. The apparatus is adapted to service the component of the turbomachine in-situ. | 09-12-2013 |
20130247377 | PROCESS OF REPAIRING A COMPONENT, A REPAIR TOOL FOR A COMPONENT, AND A COMPONENT - A process of repairing a component, a repair tool for a component, and a component are disclosed. The process includes removing material from a region of the component. The removing forms a through-cut in the component, forms a partial-frustoconical geometry in the component, forms a substantially partial-frustoconical geometry in the component, forms a partial-spherical geometry in the component, forms a substantially partial-spherical geometry in the component, forms a partial-elliptical geometry in the component, forms a substantially partial-elliptical geometry in the component, forms a partial-cylindrical geometry in the component, forms a substantially partial-cylindrical geometry in the component, is in a direction substantially perpendicular to a surface of the component, is in a direction substantially inclined with respect to the surface of the component, or a combination thereof. The repair tool includes a securing mechanism and a cutting portion for removing a region. The component includes a region formed by removing material. | 09-26-2013 |
20130269188 | INSTALLATION/DISMOUNTING OF A HUB TO/FROM A NACELLE OF A WIND TURBINE BY USING A BLADE PITCH ANGLE ADJUSTMENT DEVICE OF THE HUB FOR ORIENTATING THE HUB - Disclosed is a holding device for holding a hub to be installed at a nacelle. The holding device includes a carrier element with a first connection interface configured to connect the holding device to a lifting system, and a second connection interface configured to connect the device to a blade pitch bearing of the hub. Further disclosed is a pitch operating device for operating a blade pitch angle adjustment device of a hub to be mounted to a nacelle. The pitch operating device includes an actuating unit and a power interface for connecting the pitch operating device to the blade pitch angle adjustment device. Further disclosed is a hub installation system including such a holding device and such a pitch operating device. Further, a method for installing a hub at a nacelle and a method for dismounting a hub from a nacelle are described. | 10-17-2013 |
20130298400 | METHOD OF PROVIDING A TURBINE BLADE TIP REPAIR - A method of repairing a turbine blade having a radially extending outer wall defining an internal cavity width and a blade tip. The method comprises removing at least a portion of the blade tip to form a repair surface and providing a tip cap having a radially outer side with an outer width that may be less than the internal cavity width, and having a radially inner side with an inner width that is substantially equal to or greater than the internal cavity width. The tip cap is positioned at the repair surface, and the tip cap is welded to the repair surface using a ductile welding material. A cap peripheral portion is formed by build-up welding around the tip cap, and a squealer portion is formed by build-up welding on the cap peripheral portion. | 11-14-2013 |
20130326877 | METHOD OF WORKING AN AIRFOIL USING ELEVATED TEMPERATURE CMT WELDING - A method of adding base metal to a superalloy component is disclosed. The method comprises identifying a region deficient in base metal and preparing the region for base metal addition by exposing clean substrate metal in the site. Base metal is added to the site by cold metal transfer (CMT) gas metal arc welding. Successful addition of base metal is possible by performing the CMT gas metal arc welding on a preheated substrate. | 12-12-2013 |
20140041223 | STEAM TURBINE BUCKET TENON RESTORATION THROUGH SOLID STATE BONDING PROCESS - Tenons can be installed at the ends of turbine blades by applying a solid state bonding procedure such as a friction welding technique to join the tenons to the turbine blades. The tenons can be employed to assemble the turbine blades to one or more covers for the turbine blades. The tenons can be installed in connection with the restoration of tenons for turbine buckets in steam turbines and in connection with the renovation of rotor assemblies that include turbine blades secured to a common disk, tenons located at one end of respective turbine blades and one or more covers secured to the turbine blades by means of the tenons. In instances in which tenon remnants are present at the ends of the turbine blades, tenon enlargement elements can be joined to the tenon remnants by the solid state bonding procedure. The tenon installations can be carried out in situ. | 02-13-2014 |
20140068938 | METHOD OF CLOCKING A TURBINE WITH SKEWED WAKES - Clocking of downstream turbine airfoils can provide significant thermal and other performance benefits. The benefit from clocking the downstream airfoils is improved by skewing the airfoil wakes in the upstream turbine airfoils so that an increase in the amount of the radial spans of the clocked, downstream airfoils are impacted by the upstream wakes. This is achieved by skewing the upstream wakes using vortexing and restacking of the upstream airfoils so that the upstream wakes impact a mid-span portion of one clocked, downstream airfoil and two outer span portions of an adjacent clocked, downstream airfoil. | 03-13-2014 |
20140082939 | METHOD FOR CLEANING AND STRIPPING A TURBOSHAFT ENGINE BLADE USING A PULSED LASER - A method for cleaning a turboshaft engine blade comprising a superalloy body covered with a coating, in which the coating of the blade is at least partially machined using a pulsed laser. At least the feed rate of the pulsed laser and the pulse frequency of the pulsed laser are parameterised such that the machined surface of the blade has a roughness of 4 μm to 10 μm. | 03-27-2014 |
20140109407 | METHOD AND SYSTEM FOR REPLACING A SINGLE WIND TURBINE BLADE - A method of replacing a wind turbine blade includes suspending the wind turbine blade from support hub of a wind turbine, connecting one or more cable climbing members between the support hub and the wind turbine blade, and lowering the one or more cable climbing members and the wind turbine blade from the support hub. | 04-24-2014 |
20140137407 | METHOD OF EXTENDING LIFE OF ROTATING PARTS - A method of refurbishing a gas turbine engine rotor is disclosed and includes an initial step of inspecting a rotor for defects such as cracks. A strain is then generated around any detected cracks in the rotor to create enhanced plasticized zones about the detected defects that delay defect propagation. Strain is generated by rotating the rotor at speeds greater than operational speeds to induce the desired strain and delay the propagation of defects. | 05-22-2014 |
20140157597 | METHOD OF LOCALLY INSPECTING AND REPAIRING A COATED COMPONENT - A method of locally inspecting and repairing a coated component is provided. The method includes determining an area of interest on the coated component, wherein the area of interest has little to no visible damage. The method also includes removing a coating proximate the area of interest to expose a base material of the coated component. The method further includes inspecting the area of interest for damage to the base material. | 06-12-2014 |
20140202002 | METHOD OF REPAIRING A WIND TURBINE BLADE - A method of repairing a wind turbine blade while mounted on a tower without removing the blade from the tower is provided. The method includes positioning the wind turbine blade in a substantially vertical orientation. Next, a containment structure is positioned adjacent to a damaged portion of the blade. The damaged portion is at least partially enclosed by the containment structure and the temperature of the air within the containment structure heated. The blade is repaired by removing a damaged portion of the blade, installing a repair portion to the blade where the damaged portion was removed, and the repair portion is cured in the heated containment structure. | 07-24-2014 |
20140230245 | METHOD FOR REPAIRING SURFACE DAMAGE TO A TURBOMACHINE COMPONENT - A method for repairing surface damage to a turbomachine component that has a base material which has titanium with the base material having TiAl6V4 and/or pure titanium is provided. The method includes the following steps: mixing a solder that has a titanium-containing alloy and a powder which is distributed in the solder and which has the base material; applying the solder onto turbomachine component areas where the surface damage is located; introducing a quantity of heat into the solder and into the turbomachine component such that the alloy liquefies and the areas are thus wetted; and cooling the solder such that the alloy solidifies. | 08-21-2014 |
20140245607 | METHOD AND APPARATUS FOR REPAIRING TURBINE ROTOR - A method for repairing a rotor of a turbine includes providing a rotor having a groove portion defined by a circumferential portion of the rotor. The circumferential portion of the rotor is removed to create an opening to provide access to the groove such that the opening, immediately adjacent the groove, is narrower than the groove. A guide block may be extended into a receiving slot separating a first protruding surface from a second protruding surface of the rotor such that a weld area slot of the guide block extends over at least a portion of the opening. The opening may be welded adjacent the guide block to close at least a portion of the opening. | 09-04-2014 |
20140259665 | MECHANICAL REPAIR OF DAMAGED AIRFOIL STRUCTURE - A process is provided for repairing an airfoil structure adapted for use in a gas turbine engine comprising: providing an airfoil structure having a section with a defect; removing airfoil structure material comprising the section with the defect such that a through hole is created; providing a replacement element; providing interlocking structure; positioning the replacement element relative to the through hole; and securing the replacement element to the airfoil structure via the interlocking structure such that the through hole is covered. | 09-18-2014 |
20140259666 | METHODS FOR THE REPAIR OF GAS TURBINE ENGINE COMPONENTS USING ADDITIVE MANUFACTURING TECHNIQUES - In accordance with an exemplary embodiment, a method for repairing a damaged metallic component using additive manufacturing techniques includes separating a damaged portion of the damaged metallic component from an undamaged portion of the damaged metallic component, measuring the undamaged portion to determine the dimensions of the removed damaged portion, fabricating a replacement portion using additive manufacturing techniques in accordance with the determined dimensions of the removed damaged portion, and joining the replacement portion with the undamaged portion of the damaged metallic component to form a repaired metallic component. | 09-18-2014 |
20140259667 | SYSTEM, KIT AND METHOD FOR SURFACE REPAIR AND RECONDITIONING OF INDUSTRIAL SIZED FAN BLADES SUCH AS INCORPORATED INTO A COOLING TOWER - A system, kit and method for non-structural surface repair and reconditioning of industrial sized blades includes an initial evaluation and power washing step for identifying required repairs. A surface cleaning step combines power washing with application of muratic acid and various mechanical tools and techniques for removing environmental and chemical buildup. A succeeding step provides for non-structural surface repairs to the blades, such as including filling and reshaping the leading edges with the use of an impact resistant urethane and/or a fast cure epoxy and fiberglass cloth. A finish coating step includes applying a chemically resistant and submersible grade (i.e. water resistant) top coat epoxy. | 09-18-2014 |
20140259668 | TURBINE BLADE TIP REPAIR - A method for repairing a blade tip of a turbine blade based on a dual fusion weld process for portions of a tip plate and a mechanical locking bead over the tip plate. A damaged portion of blade is removed. The damaged portion is removed at an initial cut level. An undamaged portion of the turbine blade exists as a base below the initial cut level. A replacement section is rebuilt via laser cladding. The replacement section is machined to form a tip pocket. A tip plate is placed in the tip pocket. The tip plate comprises at least a first portion and a second portion. The tip plate is welded using a dual fusion weld process comprising a first weld process and a second weld process. A squealer tip is built using a welding process that forms a mechanical locking bead over the tip plate. | 09-18-2014 |
20140317925 | HEATING DEVICE OR METHOD FOR REPAIRING OR PRODUCING COMPONENTS OF A WIND POWER PLANT AND PARTS THEREOF, AND WIND POWER PLANT - There is provided a heating device for use in the repair or production of a component of a wind power installation, in particular a rotor blade of a wind power installation. The heating device has a mat with at least one peripherally extending passage open to one side, and a vacuum tube in the at least one passage. The at least one peripherally extending passage divides the mat into a first and a second portion. A heating unit is provided in the region of the first portion. The air in the region of the first portion can be sucked away through the vacuum tube in the at least one passage. | 10-30-2014 |
20140360015 | METHOD FOR LOWERING AND RAISING A WIND TURBINE BLADE - A method of lowering a wind turbine blade after removal from a wind turbine lowers the blade in a vertical position to a point near the ground, and rotates it to a horizontal position for emplacement on a cradle. A winch is situated in the nacelle of the wind turbine. A cable extends downward from the winch to the blade root where it may be secured to a load cell. A tip end shoe is placed around the lower portion of the blade, and includes a crane hook receiving component that is used when the blade orientation is being changed. Tag lines are attached to the root and the tip end shoe, and extend to points on the ground where technicians manipulate them to prevent the blade from being blown into the tower. | 12-11-2014 |
20140366374 | METHOD FOR CLOSING COOLING AIR BORES - Disclosed is a method for the manufacture or repair of a blade of a turbomachine, which blade has cooling air bores. In a machining step the cooling air bores are temporarily closed for their protection, a dual-cure epoxy resin being used for closing. | 12-18-2014 |
20150026979 | METHOD FOR REMOVING AND/OR INSTALLING A TURBINE BEARING AND A DEVICE FOR CARRYING OUT THE METHOD - A method and a device are provided for removing a turbine bearing or a bearing segment of a preferably stationary turbo engine, having a housing that may preferably be split in half while the housing is closed. The method includes: supporting the rotor to relieve the turbine bearing of the weight of the rotor, fastening a support plate to a turbine bearing housing, attaching two parallel, rail-like supports to the support plate and fastening a cross-beam to ends of supports, fastening a counter-bearing plate having at least two push/pull rods to the turbine bearing housing, and fastening the push/pull rods to the turbine bearing and detaching the fastening of the turbine bearing from the turbine bearing housing and pulling the turbine bearing located in the operating position thereof out of the turbine bearing housing with the aid of the push/pull rods. | 01-29-2015 |
20150026980 | METHOD FOR DISASSEMBLING A REINFORCEMENT FROM A PART - A method of disassembling reinforcement from a part, the method including: fastening at least one metal stud on one side wall of the reinforcement and at least one other metal stud on the other side wall of the reinforcement, the studs extending substantially perpendicularly to the side walls on which they are fastened; moving the studs apart from each other to space apart the side walls of reinforcement and disengage snap-fastener mechanisms thereof from complementary mechanisms of the part; and removing the reinforcement from the part. | 01-29-2015 |
20150033559 | REPAIR OF A SUBSTRATE WITH COMPONENT SUPPORTED FILLER - In a method of repairing a component substrate ( | 02-05-2015 |
20150033560 | AEROFOIL COMPONENT HANDLING TOOL - A handheld tool facilitates the removal of an aerofoil from an array of aerofoils for an axial flow machine includes a body portion, and first and second jaw members depending from the body portion. The first jaw member is shaped to be insertable between a first aerofoil and an adjacent aerofoil in the array so as to contact a first surface of the first aerofoil. The position of the first and/or second jaw member is adjustable to selectively grip the aerofoil in use. The second jaw member is adapted to contact a further portion as a trailing edge of the first aerofoil. The tool may allow for manual levering and/or impact forces to be applied to the aerofoil. A method of removal of aerofoils is also provided, involving a sequence of manual operations using the tool. The aerofoil array may be a stator vane array for a gas turbine engine. | 02-05-2015 |
20150040394 | REMOTE TURBINE COMPONENT REPLACEMENT APPARATUS AND METHOD OF REMOTELY REPLACING A TURBINE COMPONENT - A remote turbine component replacement apparatus for a turbine assembly includes an arm having a first end and a second end, the first end configured to be positioned at a user accessible region and the second end configured to extend to a remote location of the turbine assembly, the remote location in close proximity with a turbine material zone to be removed. Also included is a base portion proximate the second end, the base portion configured to engage a turbine component located at the remote location. Further included is a material removal tool disposed proximate the base portion. Yet further included is a debris removal component disposed proximate the base portion. | 02-12-2015 |
20150040395 | METHOD FOR REPAIRING WEAR MARKS ON A ROTOR SUPPORTING THE FAN OF A BYPASS ENGINE - A method for repairing a flange of a rotor, to a transverse surface of which a disk of a fan in an upstream turbo-fan engine is attached. The flange includes, in a form of a ring, openings for connecting to the disk and intermediate discharge openings. Wear marks are formed by friction of the fan blades on the flange. The method includes machining spot facings onto the flange, in areas with wear marks; placing anti-wear slugs in the discharge openings that can be covered by the blades during friction; and the spot facings extend between the connection openings and are circumferentially limited by clamping surfaces of the connection between the disk and the flange. | 02-12-2015 |
20150096174 | UPTOWER WIND TURBINE COMPONENT REPLACEMENT - A method for performing uptower maintenance of a wind turbine in order to replace the main bearing on the turbine shaft is disclosed. Embodiments of this method to perform maintenance may include installing a rotor lock to resist rotation of the main shaft during maintenance, providing a lifting device in order to elevate the main shaft, removing the main bearing from its main bearing housing, and installing a replacement split main bearing. A crane may also be installed uptower to assist in the maintenance. | 04-09-2015 |
20150107108 | METHOD AND APPARATUS FOR SUPPORTING BLADES - A method of supporting a cantilevered component prior to machining the cantilevered component, wherein the cantilevered component is mounted on a hub, the method comprising the step of providing an adhesive carrier, applying adhesive to the carrier and adhering the carrier to the cantilevered component and allowing the adhesive to cure. The carrier may rigid and braced against adjacent blades or against another carrier located on an opposing side of the aerofoil. Alternatively, the carrier may be a flexible fabric that can be wrapped around the blade. Advantageously, the blade can be machined through the carrier. | 04-23-2015 |
20150128417 | TURBINE BLADE REMOVAL TOOL AND METHOD THEREOF - An apparatus for removing a turbine blade, the apparatus including a main body having a front plate including at least one securing opening for receiving a securing bolt, a rear plate having a fixture groove, and first and second side plates, and a base block configured to slide along the fixture groove of the rear plate. | 05-14-2015 |
20150135535 | GAS TURBINE SPLITTING - A gas turbine engine fan stand ( | 05-21-2015 |
20150300175 | METHOD AND SYSTEM FOR SERVICING WIND TURBINE ROTOR - A method for enabling servicing of a wind turbine rotor includes coupling a support cable to the blade root, the support cable extends from the blade root to a hub of the wind turbine. A lowering step lowers a rotor blade relative to the hub using the support cable so the rotor blade is spaced apart from the hub by an initial vertical distance. An installing step installs a rotor blade sling on the rotor, the rotor blade sling supports the rotor blade. Other steps are used for coupling the rotor blade to the rotor blade sling, lowering the rotor blade such that the rotor blade is spaced apart from the hub by a distance greater than the initial vertical distance, de-coupling the support cable from the blade root, and interposing a rotor servicing fixture between the rotor blade and hub. The rotor servicing fixture is configured to transport a rotor part. | 10-22-2015 |
20150300313 | APPARATUS FOR MOVING BLADES OF A WIND TURBINE, METHOD FOR REPAIRING PITCH BEARINGS USING THE SAME, AND WIND TURBINE INCLUDING THE SAME - An apparatus for moving blades of a wind turbine is provided. The apparatus for moving blades for a wind turbine includes: wire connectors formed at a plurality of blades; and a pair of wires that are attachable and detachable to and from first to third wire connectors so as to connect the first and second wire connectors formed at first and second blades and a third wire connector formed at the third blade. | 10-22-2015 |
20150328728 | TURBOMACHINE BUCKET DISPLACEMENT APPARATUS AND METHOD OF USE - Various embodiments include apparatuses adapted to displace turbomachine components from a location within a turbomachine. In some embodiments apparatuses for displacing a turbine bucket from a turbomachine wheel slot include a body having at least two contacting portions for contacting the turbomachine wheel, a linear actuator coupled to the body, and an engagement arm for engaging the turbine bucket, the engagement arm coupled to the linear actuator and adapted to be actuated in a first axial direction by the linear actuator. | 11-19-2015 |
20150328729 | TURBOMACHINE COMPONENT DISPLACEMENT APPARATUS AND METHOD OF USE - Various embodiments include apparatuses adapted to displace components from a location within a turbomachine. In some embodiments an apparatus for displacing a component of a gas turbine from a first slot in a spacer disk includes a body including a mounting member configured to affixedly attach to a second slot of the spacer disk, a linear actuator coupled to the body and a displacement arm coupled to the linear actuator, the displacement arm actuatable in a first axial direction by the linear actuator to contact the component and displace the component relative to the first slot. | 11-19-2015 |
20150352617 | APPARATUSES AND METHODS FOR PRESSING - Embodiments of the present invention include systems and methods for the underwater or dry dock repair of damaged articles, including structural steel members and associated appendages, as well as propellers of vessels. The disclosed embodiments include a pressing apparatus including a structural body, a ram, a first fixture plate, a ballast tank having variable buoyancy control, and a working envelope. The ram is secured to the structural body and has a pressing surface. The first fixture plate is secured to the structural body at a location opposite the ram and has a first working surface. The ballast tank is formed within the structural body. The working envelope is located between the pressing surface and the first working surface. The ram is adjustable in a plane parallel or perpendicular to the first working surface. The first fixture plate is adjustable in a plane parallel to the pressing surface. | 12-10-2015 |
20160001404 | METHODS AND TOOLS FOR USE IN REPAIRING GAS ENGINE TURBINE BLADES - A repair tool and repair method for restoring gas turbine engine blade tips to a predetermined configuration is provided. The repair tool is an electrode that includes a tool body and a number of pins. The repair tool can be used to repair turbine blade tips through an electrical discharge machining process, such as a ram- or sink-type electrical discharge machining process. | 01-07-2016 |
20160010504 | Assembly Tool for Exhaust Turbochargers | 01-14-2016 |
20160010622 | METHOD AND DEVICE FOR BLADE REPLACEMENT IN WIND TURBINES | 01-14-2016 |
20160010660 | IMPELLER REMOVAL AND INSTALLATION | 01-14-2016 |
20160024925 | Turbine Disk Fatigue Rejuvenation - A process for rejuvenating a turbine disk having a plurality of slots includes the steps of determining a depth of a damaged layer containing M23C6 carbide dissolution; and removing the damaged layer from the slots in accordance with the determined depth. | 01-28-2016 |
20160025012 | METHOD AND APPARATUS FOR IMPROVED TURBINE BELLYBAND ROTOR SEAL MACHINING, INSTALLATION AND LIFE - A method and apparatus for improved turbine bellyband rotor seal machining, installation and life are disclosed. A fixture is provided which can be temporarily attached to the turbine disks in a position straddling the gap between the disks, without destacking the turbine rotor. The fixture accepts power tools including a drill and a mill, and positions the power tools to drill and grind a rectangular slot into the disks, where the slot has the exact size and shape needed to receive an anti-rotation block which is integral to the replacement bellyband. Measuring tools are also provided which enable precise location of each of the four slots which must be machined in the disks. The resulting slots have a uniform size and shape, and are equally spaced around the circumference of the disk, thereby facilitating installation of the service bellyband from four identical segments. | 01-28-2016 |
20160045982 | HYBRID WELDING/PRINTING PROCESS | 02-18-2016 |
20160047277 | METHOD OF ENGINE SPLIT AND REASSEMBLY - A method of axially separating an annular system, such as a gas turbine engine ( | 02-18-2016 |
20160053615 | METHOD FOR RESTORING A COVER PLATE PRETENSION - A method for repairing a blade row, wherein the blades have cover plates and a disruptive gap has occurred between the cover plates, wherein in a first method step, a bracing element is arranged in the gap between the cover plates and, in a second method step, the element and the plates are welded together. | 02-25-2016 |
20160069185 | METHOD FOR RECONDITIONING A HOT GAS PATH PART OF A GAS TURBINE - A method for reconditioning a hot gas path part of a gas turbine in order to flexibly adapt an operation regime of said gas turbine for subsequent operation intervals is disclosed. The method includes providing a hot gas path part to be reconditioned; removing a predetermined area of said hot gas path part, resulting in a cutout at said hot gas path part; and manufacturing a coupon for being inserted into said cutout to replace said removed area of said hot gas path part. The method further includes inserting said coupon into said cutout; and joining said hot gas path part with said inserted coupon. The coupon is manufactured by a selective laser melting (SLM) method resulting in a fine grain sized material with significantly improved low cycle fatigue (LCF) lifetime. The hot gas path part is coated, at least in an area comprising said inserted coupon, with a metallic overlay with improved thermo-mechanical fatigue (TMF) and oxidation lifetime. | 03-10-2016 |
20160076375 | SYSTEM AND METHOD FOR REPAIRING BLADES - A system and method for repairing a blade are provided. The system includes an induction heating coil configured for heating a platform and slash face of the blade. The induction heating coil extends under the platform and is adjacent to the slash face to provide substantially uniform localized heating to both the platform and slash face of the blade. The induction heating coil is configured so that the platform is visible during a repair or welding operation. | 03-17-2016 |
20160082523 | DRILLING TOOL AND METHOD FOR MODIFYING A BLIND HOLE - The present invention relates to a drilling tool and method for modifying a blind hole in a blade root insert of a wind turbine. The invention further relates to an apparatus and method for cleaning a blind hole. The method for modifying a blind hole comprises: removing a blade screw located in the blind hole, inserting a drilling tool into the blind hole, fixing the drilling tool in a drill, recessing the blind hole by a predetermined depth, with a maximum diameter of the end section and of the hole bottom after recessing being smaller than or equal to a diameter of the end section prior to recessing and a transition from the end section to the hole bottom being round after recessing, removing the drilling tool and the drill, mounting the blade screw in the modified blind hole. | 03-24-2016 |
20160146183 | METHOD AND SYSTEM FOR SERVICING WIND TURBINE ROTOR - A system for enabling servicing of a rotor of a wind turbine is provided. A rotor servicing fixture attaches to a first and second rotor blade, and contacts a wind turbine tower. A clamp assembly is connected to the rotor servicing fixture, and clamps onto a third rotor blade. The clamp assembly lowers the third rotor blade from a hub and raises it back to the hub. A lifting assembly is connected to the rotor servicing fixture and the clamp assembly, and is configured for raising and lowering the third rotor blade via the clamp assembly. A slide assembly is connected to the rotor servicing fixture, and is configured to support the rotor part and to slidably move the rotor part away from or towards the wind turbine. The system enables the rotor part to be removed or replaced without requiring the rotor to be removed from the wind turbine. | 05-26-2016 |
20160158901 | SYSTEM AND METHOD FOR REMOVING STATOR VANES FROM A CASING OF A ROTARY MACHINE - A stator vane removal system includes a reaction platform configured to couple between opposing sides of a slot defined in an inner surface of a casing of a rotary machine. At least one stator vane is retained in the slot. The reaction platform includes at least one wedge surface. The system also includes an actuator configured to couple to the reaction platform. The at least one wedge surface facilitates inducing a coupling force exerted by the reaction platform to the opposing sides of the slot when the actuator applies a pushing force to the at least one stator vane in the slot. | 06-09-2016 |
20160169010 | DISMANTLING DEVICE FOR BLADES AND CORRESPONDING DISMANTLING METHOD | 06-16-2016 |
20160375527 | DEEP TRAILING EDGE REPAIR - A method for repairing a blade tip of a turbine blade based on welding below and above a designated depth recommended for repair of turbine blades. A damaged portion of the turbine blade is inspected to identify a standard cut portion and an angled cut portion. The standard cut portion is damaged above a standard cut line and the angled cut portion is damaged below the standard cut line. The damaged portion of the turbine blade is removed. The standard cut portion is removed using a first removal process and the angled cut portion is removed using a second removal process. The angled cut portion is built up with a first weld repair process. The angled cut portion is built up to the standard cut portion. The standard cut portion and the angled cut portion are built up with a second weld repair process. | 12-29-2016 |
20170234132 | System and Method for In Situ Repair of Turbine Blades of Gas Turbine Engines | 08-17-2017 |
20190145262 | BALANCING METHOD FOR A TURBOCHARGER | 05-16-2019 |
20190145283 | EXTRACTION DEVICE OF A PLATFORM FOR HOLDING A BLADE AND METHOD USING THIS DEVICE | 05-16-2019 |