| Entries |
| Document | Title | Date |
|---|
| 20090013530 | METHOD OF PRODUCING EFFUSION HOLES - A method of producing a plurality of effusion holes in a wall of a combustor of a gas turbine engine comprises: determining a hole pattern definition which provides a functional relationship of the spacing between each adjacent hole within the row of holes; using the hole pattern definition to identify individual positions of the effusion holes to be produced; and using a hole producing system to produce the effusion holes at the identified positions. | 01-15-2009 |
| 20090056123 | Friction lock design for adjustable pump head to allow for 360.degree. rotation - A method and apparatus are provided for coupling a pump head ( | 03-05-2009 |
| 20090126190 | METHOD FOR PRODUCING A TURBINE CASING - A method for producing a turbine casing for a rotating machine is provided. The casing is manufactured by a casting process, and is cast in two casing halves which are separated by a parting plane which passes axially through the turbine casing. Each casing half is first cast in one piece in each case, and each casing half is separated into at least two casing sections which are joined together for forming a casing half in each case. | 05-21-2009 |
| 20090172942 | INTEGRATED HYDRAULIC HYBRID DRIVE MODULE AND METHOD OF INSTALLING SAME - A method of installing a hybrid drive system in a drive train system includes the preliminary step of providing a cradle, a plurality of components of a hybrid drive system, and a drive train system. The cradle and the plurality of components are initially assembled together to provide an integrated cradle and hybrid drive module. Then, the integrated cradle and hybrid drive module are subsequently installed in the drive train system. The hybrid drive system may be actuated hydraulically, electrically, or otherwise as desired. | 07-09-2009 |
| 20090313821 | Method of manufacturing an inflator - At the time of manufacturing an inflator, a blocking body is first disposed at an opening so as to allow the interior and the exterior of a housing to communicate with each other. The blocking body is abutted against a peripheral edge of the opening so as to ensure sealability between the blocking body and the peripheral edge of the opening. A filling nozzle injecting a pressurized gas is then pressed against a periphery of an inlet port of the blocking body, and the pressurized gas is injected from the filling nozzle so as to fill the pressurized gas into the housing through a filling channel. Subsequently, to block the filling channel, the blocking body is energized with a resistance-welding current to resistance-weld an inner peripheral portion of the filling channel. At the same time, the blocking body is fixed to the peripheral edge of the opening by resistance-welding so as to maintain sealability, thereby manufacturing the inflator. | 12-24-2009 |
| 20100307000 | METHOD AND APPARATUS TO REMOVE OR INSTALL COMBUSTION LINERS - A method and apparatus for removing and installing combustion liners in a combustion case of a turbine is provided. The apparatus includes an elongated handle having a pin disposed at one end, and a bracket attached to the elongated handle. A tower clamp, for attaching to a flange of a combustion case, includes a tower portion having a plurality of notches for receiving the pin of the elongated handle. | 12-09-2010 |
| 20100313417 | Method, System and Device for Contributing to the Assembly of a Wind Turbine - A contribution is made to the assembly of a wind turbine intended to comprise, in a final assembly condition, a tower ( | 12-16-2010 |
| 20110072660 | MANUFACTURE OF A PORTION OF A METAL PART USING THE MIG METHOD WITH PULSED CURRENT AND WIRE - The invention relates to a method for manufacturing at least a portion of a metal part of a turbine engine having a width L. The method is characterised in that said portion is manufactured by metal deposition using a MIG welding apparatus including a pulsed current generator and a pulsed deposition-wire flow, and used for varying said current and said flow, the manufacture being carried out in the form of metal beads ( | 03-31-2011 |
| 20110088260 | BRAZING REPAIR MATERIAL AND BRAZING REPAIRING METHOD USING THE MATERIAL - In a brazing repair material | 04-21-2011 |
| 20110099809 | METHODS FOR REPAIRING A GAS TURBINE COMPONENT - A method for repairing a gas turbine component includes:
| 05-05-2011 |
| 20110099810 | METHOD FOR REPAIRING A GAS TURBINE COMPONENT - A method for repairing an ex-service gas turbine component ( | 05-05-2011 |
| 20110131809 | SYSTEM AND METHOD FOR ARRANGING WIND TURBINE BLADES - A system for arranging wind turbine blades includes first and second root cradles and a first tip cradle proximate to the second root cradle, wherein the first tip cradle is angled approximately 30 to 60 degrees with respect to a horizontal line. The system also includes a second tip cradle proximate to the first root cradle, wherein the second tip cradle is angled approximately 30 to 60 degrees with respect to the horizontal line. A method for arranging wind turbine blades includes transferring a first wind turbine blade to a first root cradle and transferring a second wind turbine blade to a second root cradle. The method further includes rotating at least a portion of the first wind turbine blade about at least a portion of the second wind turbine blade. | 06-09-2011 |
| 20110185568 | METHODS AND APPARATUS FOR REPLACING OBJECTS ON HORIZONTAL SHAFTS IN ELEVATED LOCATIONS - An apparatus for stabilizing a shaft in an essentially horizontal position while an anchoring object at one end of the shaft is replaced without removal of an object at the opposite end of the shaft that would otherwise tend to destabilize the shaft from its essentially horizontal position includes a half-spool member configured to clamp above and around the shaft to resist torque around the rotor, under supports configured to attach to the half-spool member and clamp an underside of the shaft below the half-spool member, and a hydraulic or mechanical brake configured to resist torque on the shaft when the brake is engaged. | 08-04-2011 |
| 20110239460 | APPARATUS AND METHOD FOR TRANSPORTING VERTICAL AXIS WIND TURBINE - The invention relates to a vertical axis wind turbine, and in particular to an apparatus and method for transporting the vertical axis wind turbine. The method for transporting the vertical axis wind turbine, including the steps of: employing an apparatus to be a box or frame; situating a generator horizontally in the apparatus; fixing an upper flange and lower flange to a vertical shaft; fixing the base of the generator on the corresponding surface of the apparatus through holes at the base of the generator; and supporting the other end of the vertical shaft by a supporting object. | 10-06-2011 |
| 20110308083 | DEVICE FOR REPAIRING THE CASING HOLDER OF AN AERONAUTICAL ENGINE - A device for repairing a casing holder of an aeronautical engine extending radially relative to the engine rotational axis and including a plurality of lips, each having a hole drilled therein and evenly distributed on the circumference of the holder. The device includes at least one reinforcement holder that can be attached to clean lips of the case holder via through-holes or blind-holes, the reinforcement holder having two orthogonal planes of symmetry. The device further includes a reconditioning holder mounted on the reinforcement holder via a first part using attachment means positioned in one of the planes of symmetry of the reinforcement holder. | 12-22-2011 |
| 20120073132 | Weld bead cutting device and method of removing radial pin of steam turbine - A radial pin | 03-29-2012 |
| 20120079718 | Positive Displacement Injection Pump - A reciprocating drive mechanism having a housing with upper and lower internal chambers with a spool slidably positioned inside the upper internal chamber. There is at least one fluid inlet and fluid exhaust communicating with the upper internal chamber and at least one slide valve positioned within the upper internal chamber and traveling with the spool. A piston positioned in the lower internal chamber divides the lower internal chamber into an upper and lower cylinder space. A valve stem is connected to the piston and includes a bore communicating with the upper internal chamber and an exhaust passage is positioned between the upper and lower internal chambers. | 04-05-2012 |
| 20120124832 | TURBINE COMPONENTS WITH COOLING FEATURES AND METHODS OF MANUFACTURING THE SAME - The present disclosure is directed to the use and manufacture of cooling features within a component used in a hot gas path, such as within a turbine. In one embodiment, channels are formed within an external surface of the component and filled with a removable material. The external surface and channels may then be coated with one or more layers, such as a structural layer and/or top coat. The removable material may then be removed to leave the channels free of the removable material. | 05-24-2012 |
| 20120167388 | SYSTEM AND METHOD FOR DISASSEMBLING TURBINE COMPONENTS - Systems and methods are provided for disassembling turbine components. A system is provided that includes a turbine tool. The turbine tool is configured to loosen an interference fit between a first component and a second component of a turbine system. The turbine tool is also configured to apply a thermal medium to an inner portion of the first component of the turbine system. | 07-05-2012 |
| 20120240397 | METHOD OF REMOVING RETAINER OF JET PUMP AND JET PUMP - A retainer provided at lower portion of a pump beam of a jet pump for circulating cooling water to a reactor core or a bolt for fastening the retainer is cut through an underwater-remote control to remove the bolt and the retainer is removed through the underwater-remote control. | 09-27-2012 |
| 20120279064 | GAS TURBINE ENGINE MODULE ADAPTER TO A CARRIER - An engine mounting arrangement is provided for supporting a gas turbine engine. The mounting arrangement comprises a module adaptor mounted to an overhead or a ground based carrier for rotation about a substantially horizontal axis. The module adaptor extends horizontally from a base to an axially-opposed distal end having a first mounting interface configured for attachment to a module of the engine. The module adaptor holds the engine by the module to which it is attached and with the other engine modules projecting in a cantilever fashion from the supported module. | 11-08-2012 |
| 20130025123 | WORKING A VANE ASSEMBLY FOR A GAS TURBINE ENGINE - A method of working a vane assembly for a gas turbine engine involves a collar and an engine operated cooling baffle. The collar is connected to the cooling baffle and installed into the interior cavity of the vane assembly. A braze is applied to both a portion of the collar that interfaces with the cooling baffle and to a second portion of the collar that interfaces with the vane assembly. In one embodiment, the connection between the replacement collar and both the cooling baffle and vane assembly is accomplished by fitting the cooling baffle into the collar and by slipping a portion of the cooling baffle with a smaller cross-sectional area though the collar. | 01-31-2013 |
| 20130061473 | METHOD FOR CENTERING ENGINE STRUCTURES - A method for centering an engine structure such as a bearing housing is provided which may be used, for example, during assembly of a mid turbine frame or other engine case structure. In one aspect, the method includes using spacers with respective radial spokes which connect inner and outer portions of the case. In another aspect, centring may be provided by machining selected contacting surfaces of selected components. | 03-14-2013 |
| 20130081269 | SYSTEMS AND METHODS FOR REPAIRING HOLES - A system for repairing holes in a turbine engine component is provided. The system includes a turbine engine component including a front surface, a back surface, and a tapered surface extending from the front surface to the back surface, the tapered surface circumscribing the hole. The system further includes a plug configured to be welded to the turbine engine component, the plug including at least one tapered portion configured to contact the tapered surface when the plug is welded to the turbine engine component, and a die plate positioned on the back surface of the turbine engine component and including an aperture defined therethrough that is configured to collect flash generated when the plug is welded to the turbine engine component. | 04-04-2013 |
| 20130081270 | COMBUSTION SYSTEM AND METHOD OF ASSEMBLING THE SAME - A method of assembling a combustion system for a gas turbine engine includes providing a combustion chamber frame, an inner casing structure, and an outer casing structure. The method also includes mounting the combustion chamber frame between the inner casing structure and the outer casing structure such that the combustion chamber frame is coupled to the inner casing structure and the outer casing structure. | 04-04-2013 |
| 20130133194 | METHOD OF FABRICATING A TURBINE ENGINE DRUM - A method of fabricating a turbine engine drum including at least two rotor disks, the method including: positioning the two disks on a common axis spaced apart from each other and in a predetermined angular position relative to each other; placing a wall forming a body of revolution between the two disks coaxially about their common axis; driving the wall in rotation about its axis; and moving the disks axially towards the wall so as to put the disks into contact with ends of the wall and thus welding the disks to the wall by inertial friction welding. | 05-30-2013 |
| 20130232788 | Apparatus for Installing a Turbine Case - An apparatus for installing a turbine casing including a first drive subassembly and a member coupled to the first drive subassembly configured for engaging a first segment of the turbine casing. The apparatus may also include a second member coupled to the second drive subassembly configured for engaging the first segment of the turbine casing. The apparatus may be provided with a first retainer connected to the first member and configured for engaging a second segment of the turbine casing, and a second retainer connected to the second member and configured for engaging the second segment of the turbine casing. | 09-12-2013 |
| 20130263449 | CHECK VALVE DIAPHRAGM MICROPUMP - A micropump device including a first wafer and a second wafer attached to the first wafer. The first and second wafers are configured to define a chamber therebetween having a predetermined volume. A third wafer is attached to the second wafer to define an inlet section and an outlet section in fluid communication with the chamber. At least one of the second and third wafers are formed to define a moveable diaphragm configured to change the predetermined volume of the chamber for pumping a fluid between the inlet section and the outlet section. | 10-10-2013 |
| 20130312260 | METHOD AND DEVICE FOR MODIFYING A SECONDARY AIR SYSTEM IN A GAS TURBINE ENGINE - A method and device for modifying a gas turbine engine is disclosed herein. The method for modifying a gas turbine engine includes accessing a first outward end of a first tube installed in the gas turbine engine, the first tube having a tube axis. Then attaching an extraction tool to the first outward end of the first tube, and applying an axial force to the first tube using the extraction tool, the axial force relative to the tube axis, thus breaking a first interference seal between a first interface surface on a first inward end of the first tube and a receiving member of the gas turbine engine. The method continues with removing the first tube from the gas turbine engine. | 11-28-2013 |
| 20140013598 | METHOD FOR RETROFITTING A DOUBLE FLOW STEAM TURBINE - The method for retrofitting a double flow steam turbine includes opening an outer casing of the steam turbine, removing the blade carriers and the stator blades, removing the inner casing with inlet belt, removing the double flow rotor and the rotor blades. Thus, the method includes the further steps of providing a new single flow rotor and new rotor blades different from the rotor blades connected to the double flow rotor, providing balancers connected to the single flow rotor, to balance the axial thrust, providing new stator blade carriers and new stator blades different from the stator blades associated to the double flow rotor, providing a new inner casing with inlet belt, providing a passage between the inner casing and the outer casing, closing the outer casing. | 01-16-2014 |
| 20140130351 | VARIABLE GEOMETRY TURBOMACHINE - A method for assembling a variable geometry turbomachine with a bearing housing, an adjacent turbine housing, a turbine wheel rotating in the turbine housing about a turbine axis; an inlet passage upstream of the turbine wheel between inlet surfaces of first and second wall members, one wall member moveable along the turbine axis to vary the inlet passage size; vanes across the inlet passage connected to a first wall member; an array of vane slots defined by the second wall member to receive the vanes for relative movement between the wall members; the second wall member comprising a shroud defining vane slots; the second wall member supported by a support member retained by a mounting feature; the mounting feature being one of the bearing housings, the turbine housing, or the actuation element; and the shroud is fixed to the support member. | 05-15-2014 |
| 20140157595 | MASK SYSTEM FOR GAS TURBINE ENGINE COMPONENT - A system to install a mask onto a component of a gas turbine engine includes a drive movable along an axis with respect to a movable base. | 06-12-2014 |
| 20140259661 | VARIABLE AREA FAN NOZZLE WITH WALL THICKNESS DISTRIBUTION - A method of controlling flutter of a fan nozzle includes, for a given design of a fan nozzle, determining a vibration mode that causes a flutter characteristic of the fan nozzle and, in response to the determined vibration mode, establishing a wall thickness distribution of at least one wall of the fan nozzle to include local thick portions and local thin portions that alter the flutter characteristic. | 09-18-2014 |
| 20140259662 | PROCESS AND APPARATUS TO RESTORE DISTORTED FEATURES ON GAS TURBINE VANES - A method and apparatus for restoring displaced features on a turbine vane segment for a gas turbine engine, such as a vane segment in a low pressure turbine, and more specifically, the inner shroud thereof relative to the outer shroud thereof to meet the original design position and dimensions. | 09-18-2014 |
| 20140331496 | INTERMEDIATE STRUCTURE FOR INDEPENDENTLY DE-MOUNTABLE PROPULSION COMPONENTS - An intermediate structure of an aircraft configured to mechanically attach an engine core and an engine fan module to each other and to the aircraft. The intermediate structure may have a ring-shaped portion and/or an elongated mount beam extending substantially perpendicularly from the ring-shaped portion. The ring-shaped portion may have a forward edge and an aft edge opposite of the forward edge, and may include a first attachment portion for attaching to a flange of the engine core, a second attachment portion for attaching to a flange of the engine fan module, and a mounting portion configured for mounting directly to a pylon or airframe of an aircraft. The engine core and/or the engine fan module may independently mechanically attach to and detach from the intermediate structure. The intermediate structure may have a gearbox mounted thereto for interfacing with rotary components of the engine core and the engine fan module. | 11-13-2014 |
| 20140352146 | METHOD OF FABRICATING A TURBINE ENGINE SHAFT - A method of fabricating a turbine engine shaft from a metal billet of generally cylindrical shape, the method including drilling the billet to form a through axial cylindrical bore therein, engaging a cylindrical insert in the bore, the insert being made of a material having yield stress close to that of the material of the billet so that the materials of the insert and of the billet have substantially the same behavior during forging, hot forging the billet to form a forged blank of length greater than that of the billet, withdrawing the insert, and machining the blank. | 12-04-2014 |
| 20150013158 | ALTERNATIVE METHOD FOR DISMANTLING SOLID-PROPELLANT MOTORS - A method is provided for solid-propellant engines to be dismantled safely and in accordance with environmental standards having been scrapped. For each engine to be dismantled, it is mounted on a static test rig, immersed in a tank filled with water and started such that propellant is used up under the water. The soluble part of the combustion products (gases or condensates) thus remains trapped in the water in the tank while the non-soluble solid products drop to the bottom of the tank. The body of the engine emptied of its fuel in this way and rendered pyrotechnically inert is then taken apart or disassembled. Periodically, the water in the tank is withdrawn and the tank stripped of its deposits such that subsequent dismantling operations can be carried out under proper conditions. All of the combustion products recovered are sent to appropriate reprocessing plants. The method allows high dismantling rates. | 01-15-2015 |
| 20150033558 | METHOD FOR RETROFITTING A GAS TURBINE POWER PLANT - A method for retrofitting an already existing gas turbine power plant is provided. The method features at least the following steps: fluidically connecting a gas turbine to a flue gas duct which is suitable for conducting flue gas which is produced by the gas turbine; connecting the flue gas duct to a steam generating unit which is fluidically connected to a water-steam cycle, and via which water-steam cycle a power generating facility can be operated; fluidically connecting a CO2 separation apparatus to the flue gas duct for separating the CO2 from the flue gas in the flue gas duct; and electrically connecting the power generating facility to the CO2 separation apparatus, preferably for the essentially energy-autonomous operation of the CO2 separation apparatus. | 02-05-2015 |
| 20150089808 | Structures and Methods for Forcing Coupling of Flow Fields of Adjacent Bladed Elements of Turbomachines, and Turbomachines Incorporating the Same - Turbomachines having close-coupling flow guides (CCFGs) that are designed and configured to closely-couple flow fields of adjacent bladed elements. In some embodiments, the CCFGs may be located in regions extending between the adjacent bladed elements, described herein as coupling avoidance zones, where conventional turbomachine design would suggest no structure should be added. In yet other embodiments, CCFGs are located upstream and/or downstream of rows of blades coupled to the bladed elements, including overlapping one of more of the rows of blades, to improve flow coupling and machine performance. Methods of designing turbomachines to incorporate CCFGs are also provided. | 04-02-2015 |
| 20150113805 | METHOD OF ASSEMBLING A GAS TURBINE ENCLOSURE - A method of assembling an enclosure of a gas turbine is provided. The method includes disposing gas turbine equipment in an interior of a frame at a first site, connecting wall panels to the frame to form a pre-assembled module at the first site, shipping the pre-assembled module from the first site to a second site and disposing the pre-assembled module proximate to the gas turbine such that the gas turbine equipment is exposed for connection to the gas turbine and a portion of the wall panels form a portion of an outer enclosure of the gas turbine and the gas turbine equipment. | 04-30-2015 |
| 20150345452 | Stepped Orifice Hole - An orifice plate used as part of a fuel injector. The orifice plate has a base portion, an offset portion integrally formed with the base portion, a flow entry side and a flow exit side, where the base portion and the offset portion are part of the flow entry side and the flow exit side. A plurality of exit apertures is integrally formed with the offset portion. Each of the plurality of exit apertures includes a plurality of stepped portions, and at least one inner diameter, and each exit aperture is disposed at an angle relative to a central axis extending through the orifice plate. Each exit aperture is of a depth that is about twice the size of the inner diameter, providing optimal atomization of the fluid as the fluid flows through the exit apertures. | 12-03-2015 |
| 20160024967 | TOOL FOR FITTING AN INNER BEARING RACE CARRYING A BEARING CAGE AND SCREWS FOR RETAINING IN A TURBOMACHINE - The disclosure relates to a tool for fitting an inner bearing race carrying a bearing cage and rollers and screws in a turbomachine, comprising two sectored cylindrical casings which respectively cover an upstream end part of the race and the bearing cage, a cylindrical annulus which surrounds the second casing, and a locking ring which is fitted on an upstream part of the first casing and which has means for axially pressing against the annulus and for axially clamping the second casing between the annulus and the heads of the screws carried by the flange. | 01-28-2016 |
| 20160040730 | CLUTCH UNIT ASSEMBLY METHOD - A clutch unit includes a one-way clutch including a plurality of engaging elements which restrict relative rotation of an outside rotating body toward one side of a circumferential direction relative to an inside rotating body by engagement with the outside rotating body and which allow relative rotation toward the other side of the circumferential direction by releasing the engagement. An assembly method for this clutch unit includes: a first step of mounting an engaging member including the engaging elements to the inside rotating body; and a second step of mounting, after the first step, the outside rotating body to a radial outside of the engaging elements while the outside rotating body is rotated relative to the inside rotating body toward the other side of the circumferential direction. | 02-11-2016 |
