Entries |
Document | Title | Date |
20080196247 | METHOD AND APPARATUS TO FACILITATE INCREASING TURBINE ROTOR EFFICIENCY - A method facilitates assembling a turbine. The method includes coupling buckets to a turbine wheel. The method also includes coupling a first end of a cover plate to the turbine wheel such that at least one projection extending from the turbine wheel retains the cover plate in position relative to the turbine wheel and inserting a fastening mechanism through an opening defined in the turbine wheel to secure the cover plate against the turbine wheel. The cover plate facilitates reducing dovetail leakage across the buckets coupled to the turbine wheel. | 08-21-2008 |
20080271315 | METHOD AND APPARATUS FOR FABRICATING A PLURALITY OF TURBINE COMPONENTS - A method for fabricating a plurality of turbine components is provided. The method includes removably coupling at least one tab to a plate, wherein the at least one tab and the plate each include a plurality of apertures extending therein. The at least one tab is removably coupled to a first turbine component, and a tool is removably coupled to the plate such that the plate and the at least one tab substantially align the tool with respect to the first turbine component. The method further includes performing a fabrication operation on the first turbine component. The at least one tab is re-oriented with respect to the plate, and the at least one tab is removably coupled to a second turbine component. The tool is removably coupled to the plate such that the plate and the at least one tab substantially align the tool with respect to the second turbine component, and a fabrication operation is performed on the second turbine component. | 11-06-2008 |
20080301939 | Gas turbine and manufacturing process of gas turbine - The invention is intended to maintain turbine reliability when, based on a gas turbine designed for one desired cycle, a gas turbine for another different cycle is manufactured. A channel of a compressor is formed such that a mass flow of a fluid compressed by the compressor changes. Thus, when manufacturing, based on the gas turbine designed for one desired cycle, the gas turbine for another different cycle, turbine reliability can be maintained. | 12-11-2008 |
20090056126 | Component with tuned frequency response - A method of manufacturing a component ( | 03-05-2009 |
20090106978 | METHODS FOR OPERATING GAS TURBINE ENGINES - A method facilitates assembling a gas turbine engine assembly. The method comprises providing at least one propelling gas turbine engine that includes a core engine including at least one turbine, coupling an auxiliary engine to the propelling gas turbine engine such that during operation of the propelling gas turbine engine, such that at least a portion of the airflow entering the propelling gas turbine engine is extracted from the propelling gas and channeled to the auxiliary engine for generating power, and coupling a modulating valve in flow communication to the propelling gas turbine engine to control the flow of airflow from the propelling gas turbine engine to the auxiliary engine, wherein the modulating valve is selectively operable to control an extraction point of airflow from the propelling gas turbine engine. | 04-30-2009 |
20090119918 | METHOD FOR ATTACHING A BEARING SUPPORTING A ROTOR ON A TURBOMACHINE - The invention relates to a method for attaching a bearing ( | 05-14-2009 |
20090211090 | TURBINE ENGINE VALVE ASSEMBLY AND METHOD OF ASSEMBLING THE SAME - A method of assembling a crank assembly for a turbine engine. The turbine engine includes a valve assembly including an outer fairing and an inner fairing coupled to the outer fairing with a strut. The valve assembly further includes an annular slide valve coupled between the inner and outer fairings. The valve assembly is positioned within a duct having a radially outer duct wall and a radially inner duct wall. The method includes coupling a first arm of a crank assembly to the annular slide valve, and coupling a second arm of the crank assembly to the outer fairing such that the crank assembly controls movement of the annular slide valve and for moving the outer and inner fairings between a first operational position and a second operational position to facilitate regulating an amount of airflow channeled through the turbine engine. | 08-27-2009 |
20090211091 | NON-METALLIC COVER FOR A FIXTURE - An assembly includes a fixture including an opening shaped to receive a portion of a turbine engine component. A non-metallic cover is placed over at least a portion of the fixture. The cover facilitates reducing metal to metal contact of the fixture and the turbine engine component when the turbine engine component is installed in the fixture, and facilitates reducing scratching of the turbine engine component. | 08-27-2009 |
20090235525 | Method of Producing a Turbine Component with Multiple Interconnected Layers of Cooling Channels - A method for making a gas turbine component ( | 09-24-2009 |
20090255118 | METHOD OF MANUFACTURING MIXERS - A method for fabricating a unitary mixer is disclosed, said method comprising the steps of determining three-dimensional information of the unitary mixer having at least one swirler, converting the three-dimensional information into a plurality of slices that each define a cross-sectional layer of the unitary mixer, and successively forming each layer of the unitary mixer by fusing a metallic powder. Exemplary embodiments are disclosed, showing unitary mixer comprising an annular housing and a swirler having a unitary construction wherein unitary mixer is made by using a rapid manufacturing process. In one aspect of the invention, the rapid manufacturing process is a laser sintering process. | 10-15-2009 |
20090255119 | METHOD OF MANUFACTURING A UNITARY SWIRLER - A method for fabricating a unitary swirler is disclosed, the method comprising the steps of determining three-dimensional information of the unitary swirler having a plurality of vanes arranged in a circumferential direction on a body around a swirler axis and a wall extending between a rim and a portion of the body, converting the three-dimensional information into a plurality of slices that each define a cross-sectional layer of the unitary swirler, and successively forming each layer of the unitary swirler by fusing a metallic powder using laser energy. Exemplary embodiments are disclosed, showing a unitary swirler comprising a plurality of vanes extending from a hub having a unitary construction wherein unitary swirler is made by using a rapid manufacturing process. In one aspect of the invention, the rapid manufacturing process is a laser sintering process. | 10-15-2009 |
20090255120 | METHOD OF ASSEMBLING A FUEL NOZZLE - A method of assembling a fuel nozzle comprises the steps of forming a pilot assembly; coupling the pilot assembly to a unitary distributor such that the pilot assembly is in flow communication with a pilot flow passage in the unitary distributor; coupling a unitary swirler having an adaptor to the unitary distributor; coupling the adaptor to a stem housing; coupling the unitary distributor to the stem housing; and coupling a centerbody to the stem housing. | 10-15-2009 |
20090277009 | Method for manufacturing and/or machining components - A method for manufacturing and/or machining components, in particular gas turbine components such as blades, blade segments or integrally bladed rotors for an aircraft engine, is disclosed. In an embodiment, the method for manufacturing components, in particular gas turbine components, includes at least the following steps: a) providing a workpiece; b) milling the workpiece to provide a component to be manufactured; c) rounding the edges of the component and/or smoothing the surface of the component and/or hardening the surface of the component by a hydraulic method using a lubricant and/or coolant required for the milling. | 11-12-2009 |
20090282679 | CENTERING A PART INSIDE A SHAFT - A device for centering a tube inside a hollow shaft, the device comprising deformable means interposed between the tube and the hollow shaft and including bearing members for bearing against the inside surface of the shaft and suitable for being spaced away from the inside surface of the shaft in order to enable them to be moved inside the shaft, the deformable means being made of a shape-memory material suitable for deforming to press the bearing members against the inside surface of the shaft or to space them away therefrom on being subjected to a predetermined temperature. | 11-19-2009 |
20090293276 | ROTOR ASSEMBLY SYSTEM AND METHOD - A method and system are disclosed for use in assembling a plurality of rotatable elements in the assembly of a turbine engine. The system and method include an initialization unit, a measurement unit, and a processing unit. The initialization unit receives and stores initialization data in a computer datastore. The initialization data includes a first set of initialization data that is representative of characteristics of a first rotatable element, and a second set of initialization data that is representative of characteristics of a second rotatable element. The measurement unit receives measured data including a first set of measured data characteristic of measured features of the first rotatable element, and a second set of measured data characteristic of measured features of the second rotatable element. The processor unit determines an optimal order and rotational arrangement of the first and second rotatable elements with respect to one another responsive to the first and second sets of initialization data and the first and second sets of measured data. | 12-03-2009 |
20100005657 | METHODS AND SYSTEMS TO FACILITATE OVER-SPEED PROTECTION - A method of assembling a gas turbine engine is provided. The method includes coupling a first fuel system interface to a fuel delivery system, coupling a second fuel system interface to the fuel delivery system, coupling a first driver control system in communication with the first and second fuel system interfaces, and coupling a second driver control system in communication with the first and second fuel system interfaces. | 01-14-2010 |
20100011576 | Gas turbine transition duct coupling apparatus - An apparatus is provided for coupling a first portion of a gas turbine transition duct to a second portion of a gas turbine transition duct to reduce vibratory deflection. The apparatus may comprise: at least one first support structure attached to the gas turbine transition duct first portion; at least one second support structure attached to the gas turbine transition duct second portion; and at least one coupling mechanism configured to couple the at least one first support structure to the at least one second support structure so as to allow sliding movement between the at least one first support structure and the at least one second support structure when a movement force of the at least one first support structure and the at least one second support structure exceeds a predefined frictional force threshold value. | 01-21-2010 |
20100024214 | METHOD FOR THE MANUFACTURE OF METALLIC COMPONENTS - When manufacturing slender metallic components ( | 02-04-2010 |
20100126016 | Method for manufacturing multistage exhaust turbocharger - A method of manufacturing a multistage exhaust turbocharger having a high-pressure stage turbocharger and a low-pressure stage turbocharger reduced in pipe connection between the turbochargers thereby reducing the bulk of the multistage exhaust turbocharger, the number of parts for the connection, and assembling man-hours, and facilitating the mounting of an engine equipped with the multistage exhaust turbocharger in a narrow engine room of a vehicle. | 05-27-2010 |
20100223790 | BLADE OUTER SEAL ASSEMBLY - An outer seal assembly of a turbine rotor stage is secured within a circumferential groove of the turbine casing in such a manner as to both fix the outer seal assembly in its installed position and also provide for sealing around its outer periphery so as to thereby prevent the leakage of cooling air therearound. A plurality of arcuate elements having an angle-shaped cross sectional profile are provided to interface between radially extending arms of the outer seal assembly and the inner surface of the casing, with a locking mechanism then being applied to secure the two structures in their installed positions. Each of the arcuate elements includes a radially extending panel, a plurality of forwardly extending hooks that are disposed within a groove in the casing, and a second forwardly extending flange that engages the rear surface of the outer seal assembly arm. As the outer seal assembly arm is urged rearwardly during operation, the arcuate element is caused to rotate about a fulcrum in the circumferential groove such that a radially outer edge of the radially extending panel is urged against a casing inner surface so as to thereby enhance the sealing relationship therebetween. | 09-09-2010 |
20100229387 | MULTI-MATERIAL TURBINE ENGINE SHAFT - A turbine engine shaft comprising an end section thereof made of high temperature resistant super-alloy adapted for working in a hot section of the engine, and a remaining section of the shaft made of steel. The end section and the remaining section are directly joined together to form a single-piece shaft. | 09-16-2010 |
20100281688 | PROCESS FOR PRODUCING A ROTOR - A process is provided for producing a rotor which is made by welding together disk-shaped and/or drum-shaped elements, in particular disks, wherein a device is used to join the disks together axially in sequence along a longitudinal axis and the disks are welded in a two-stage welding process. As they are joined together, the disks are stacked axially in the vertical direction. A first welding process takes place in a vertical orientation of the stacked disks, followed by a second welding process in a horizontal orientation of the stacked disks. | 11-11-2010 |
20110010935 | COMBUSTOR HEAT SHIELD - A combustor heat shield comprises a heat shield member defining at least one opening for receiving a fuel nozzle. A louver is received in the opening. The louver has a flow diverting portion extending radially outwardly from the opening for directing air along the hot side of the heat shield member. | 01-20-2011 |
20110041333 | METHOD FOR MANUFACTURING A VARIABLE CAPACITY EXHAUST GAS TURBINE - Provided is a manufacturing method for a variable capacity exhaust gas turbine whereby, with variable capacity exhaust gas turbine component members produced using casting or other element molding and with which the final finished product is obtained using machining, the gap in a tongue section to allow an exhaust gas stream to flow smoothly into an inner circumferential scroll section can be formed at a minimum, and mounting of a cover section near a ring can be accomplished with high precision. The method is characterized in that: the component members are comprised of a cover section and a reduced-diameter plate section extending the inner diameter side in the direction of a plane perpendicular to the shaft following the gap between a bearing housing and the turbine rotor; the cover section and the reduced-diameter plate section are integrally formed using either casting, injection molding, or cold casting; a molded surface of the cover section is protruded to form a protrusion corresponding to the tongue section that is in the exhaust gas path in the turbine housing and that is formed in an intake equivalent portion of the inner circumferential scroll section of the cover section; and the protrusion undergoes cutting, and the cut surface and the tongue section are assembled maintaining the gap value therebetween. | 02-24-2011 |
20110072661 | METHOD OF MANUFACTURING A METAL COMPONENT FROM METAL POWDER - A method of manufacturing a metal component from metal powder comprises preparing ( | 03-31-2011 |
20110078902 | 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. | 04-07-2011 |
20110252644 | DEVICE FOR HEATING A CYLINDRICAL COMPONENT AND USE IN ASSEMBLING AN INTER-SHAFT BEARING IN A TURBOMACHINE - A device for heating a cylindrical component of given diameter is disclosed. The device includes at least two heaters each delivering a stream of hot gas and emerging in an annular chamber. The inside diameter of the annular chamber is slightly greater than the diameter of the cylindrical component. The device may be used for heating a metal journal in which a bearing ring for an inter-shaft bearing in a double-body turbomachine is mounted. | 10-20-2011 |
20110265327 | APPARATUS AND METHOD FOR AIRCRAFT ENGINE CORE EXCHANGE - A method and ground support equipment (GSE) for attaching an engine core to an engine fan module on an aircraft pylon. The GSE may comprise GSE supports and lifting components attached to the pylon, two suspension rails attached to the lifting components, two translating rails translatably attached to the two suspensions rails and fixedly attached to opposite sides of the engine core, and two alignment fittings fixed to the engine fan module. The method of using the GSE may comprise lifting the engine core vertically using the lifting components and anchoring the suspension rails to the alignment fittings. The translating rails and engine core may then be translated in an aft-to-forward direction such that portions of the translating rails engage portions of the alignment fittings to cooperatively guide the translating rails into a final forward position in which the engine core is aligned relative to the engine fan module. | 11-03-2011 |
20110296686 | ROTATIONALLY BALANCING A ROTATING PART - A method is provided of rotationally balancing a rotating part. A rotor hub or ring and a plurality of rotor blades for assembly onto the hub or ring are provided, each blade having an unfilled internal cavity. The respective masses and moment weights of the blades with filled internal cavities are then predicted. Next, the rotor blades are assembled onto the hub or ring to form the rotating part. The relative positions of the assembled blades are determined on the basis of their predicted masses and moment weights with filled internal cavities. The internal cavities of the assembled rotor blades are then filled. | 12-08-2011 |
20120096715 | NON-METALLIC COVER FOR A FIXTURE - An assembly used in performing a manufacturing process on a turbine engine component includes a turbine engine component and a fixture including an opening shaped to receive a portion of the turbine engine component. The assembly includes a non-metallic cover placed over at least a portion of an external surface of the fixture. The non-metallic cover is visible when positioned over the at least a portion of the external surface of the fixture and is visible when the turbine engine component is received in the fixture opening of the fixture. | 04-26-2012 |
20120279067 | COMPONENTS AND PROCESSES OF PRODUCING COMPONENTS WITH REGIONS HAVING DIFFERENT GRAIN STRUCTURES - Processes for fabricating components to have two or more regions with different grain structures, and components produced by such processes. First and second preforms are fabricated to comprise interface surfaces at which the preforms can be joined together. The first and second preforms are formed of first and second precipitation-strengthened alloys, respectively, and the first alloy differs from the second alloy by having a higher solvus temperature or a higher grain refiner content. The preforms are joined together to form an article comprising first and second portions formed by the first and second preforms, respectively, and corresponding to first and second regions of the component, respectively, and the interface surfaces of the preforms form a joint between the first and second portions of the article. A supersolvus heat treatment is performed on the article so that greater grain growth occurs in the second portion than in the first portion. | 11-08-2012 |
20130042475 | PANELS AND PROCESSES THEREFOR - Polymer-based materials and processes suitable for producing panels, for example, panels for use in a fan shroud abradable seal of a turbofan engine. Such a process includes introducing constituents of an expandable foam material into a continuous forming apparatus that continuously compounds the constituents into a partially-cured compounded polymeric material, which is then continuously formed with the continuous forming apparatus to produce a continuous form having a constant cross-sectional shape transverse to a continuous forming direction of the continuous forming apparatus. A portion of the continuous form is then deformed to produce a preform, and the preform is cured within a restricted volume to cause the preform to expand and produce the panel. | 02-21-2013 |
20130160292 | MACHINE TOOLS AND METHODS FOR MACHINING TURBINE ROTOR ASSEMBLIES - Machine tools and methods for machining turbine rotor assemblies are disclosed. Some machine tools include a drill arm that pushes off of a turbine stage that is adjacent to a turbine stage to be machined. Some machine tools include a clamping arm that secures the machine tool to a turbine stage to be machined and an adjacent turbine stage. Some methods include pushing-off of a turbine stage that is adjacent to a turbine stage to be machined. Some methods include securing a machine tool to a turbine stage that is adjacent to a turbine stage to be machined. Some methods include monitoring at least one of a current delivered to a first motor and a voltage applied to the first motor and controlling a second motor in response to the monitoring. Some methods include sequentially machining a turbine stage with cutting tools having increasing lengths and/or diameters. | 06-27-2013 |
20130247378 | GAS TURBINE ROTOR ASSEMBLY METHODS - Method of assembling a rotor assembly of a gas turbine engine having a plurality of components. The method comprises in one aspect calculating the bending forces due to the mass distribution along the rotor. In another aspect, an optimization routine iterates different rotor arrangements, comparing the calculated bending moments to determine a set of component positions that minimizes the bending forces. In another aspect, mass corrections are optimized to balance the rotor assembly. | 09-26-2013 |
20130291382 | Method for Working of Combustor Float Wall Panels - A method for working or repairing a combustor wall panel that may be damaged is disclosed. The method comprises providing a supplemental body to a combustor float wall panel, and attaching at least one cooling pin to the supplemental body. | 11-07-2013 |
20140137408 | METHODS OF FABRICATING AND COATING TURBINE COMPONENTS - In one aspect, a method of forming a hot gas path component is provided. The method includes forming at least one groove in an outer surface of a substrate, wherein the at least one groove has a base and a top. The method further includes filling the at least one groove with a filler. The method also includes applying at least one cover layer over at least a portion of the outer surface of the substrate such that the at least one groove and the at least one cover layer define at least one micro-channel for cooling the component. The filler is automatically removed from the at least one micro-channel during application of the at least one cover layer. Methods for coating a hot gas component and for assembling a turbine engine assembly are also provided. | 05-22-2014 |
20140173898 | METHOD OF MOUNTING A WIND TURBINE - An installation apparatus for handling a component of a wind turbine is provided. The installation apparatus includes a base, a support portion and an extensible arm having opposing ends connected to the support portion and the base, respectively. The extensible arm is adapted to move the support portion relative to the base and about a transverse axis of the installation apparatus between a transport position and an installation position. In the transport position the support portion rests on the base. In the installation position the support portion and the base form an angle. An assembly including such an installation apparatus and a method of mounting a wind turbine are also provided. | 06-26-2014 |
20140190011 | Method of Calculating Unsteady Force Acting on Rotor Blade or Stator Blade, Method of Designing Turbine and Method of Manufacturing Turbine - A turbine design method that can easily construct a turbine stage structure in which an unsteady force acting on a rotor blade can be reduced and degradation in performance and increase in rotor shaft length can be prevented is provided. Unsteady forces and exciting forces by the potential field interaction acting on the rotor blade are respectively obtained, exciting forces by the wake interaction acting on the rotor blade are obtained, the exciting forces by the potential field interaction and the wake interaction are mathematically expressed, the unsteady force acting on the rotor blade when the distance between stator and rotor blades is an arbitrary value is calculated, and the distance between stator and rotor blades is determined based on a calculation result. | 07-10-2014 |
20140215822 | METHOD FOR PRODUCING A COMPRESSOR BLADE - The invention relates to a method for producing a compressor blade, comprising the following steps: forging a blank made of an austenitic-ferritic steel; uniaxially stretching and plastically deforming the blank while at least the elongation and the deformation force of the blank are detected and monitored; and ending the stretching after a defined limit value for the stress has been reached. | 08-07-2014 |
20140230246 | THERMALLY FREE HANGER WITH LENGTH ADJUSTMENT FEATURE - A system for connecting spaced components of a gas turbine engine includes connecting one end of a T-bar to each of the spaced components. One component is attached to the crossbar portion of the T-bar by trapping the crossbar between the component and a bracket. The second component is attached to the shaft portion using a hanger nut connected to the shaft portion of the T-bar and bolted to the second component. The system may be installed by attaching the crossbar portion, then advancing the first component towards the second component until the shaft portion passes through an aperture in the second component. The hanger nut is attached to the shaft portion and the second component. | 08-21-2014 |
20140230247 | ONE-PIECE MANUFACTURING PROCESS - A method of making a turbomachine part, wherein the method can include machining a blank into a base having blades extending therefrom, the blades defining a channel therebetween. The method can also include forming a bridge constructed from refractory material in the channel between the blades, and forming a cover on the tops of the blades and over the channel, such that the base, the blades, and the cover form a single substantially homogenous turbomachine part once the bridge is removed. | 08-21-2014 |
20140317926 | FRONT CENTERBODY SUPPORT FOR A GAS TURBINE ENGINE - A method for maintaining a gas turbine engine includes providing access from a forward section of a front center body assembly to a flex support mounted to a front center body support. The flex support is mounted to a geared architecture. | 10-30-2014 |
20140373354 | METHOD FOR PRODUCING A TURBINE ROTOR OF AN EXHAUST GAS TURBOCHARGER, AND USE OF A TURBINE ROTOR - A method for producing a turbine rotor of an exhaust gas turbocharger, wherein the turbine rotor includes a turbine wheel with a hub and turbine blades that extend from the hub, and a shaft, includes the steps of: providing the turbine wheel and the shaft; forming a protective layer by applying or introducing a halogen on or in the surface of the turbine wheel and subsequently heat-treating the turbine wheel; and connecting the shaft to the hub of the turbine wheel after the protective coating is formed. | 12-25-2014 |
20150047191 | METHOD FOR BALANCING AND ASSEMBLING A TURBINE ROTOR - A method for balancing and assembling a turbine rotor | 02-19-2015 |
20150082633 | TOOL AND METHOD FOR FRONTAL UNSCREWING OF A LINK NUT IN A TWIN-SPOOL TURBINE - A method for unscrewing a link nut of an HP rotor of a twin-spool turbine, including a front fan, an intermediate casing, a HP module with a HP rotor, and a LP turbine module, the intermediate casing including a support bearing for the HP rotor, the rotor being retained in the bearing by the link nut, the method including: placing an unscrewing tool in front of the link nut after having removed the fan and released access to the nut from the front; with rotation of the HP rotor locked and the frontal unscrewing tool including a socket spanner including teeth having a shape that complements that of teeth of the link nut, attaching a mounting for the socket spanner to the intermediate casing, the socket spanner being rotatably mounted on the mounting, and applying an unscrewing torque to the socket spanner. An unscrewing tool implements the method. | 03-26-2015 |
20150107109 | GAS TURBINE ENGINE COMBUSTOR WITH CMC HEAT SHIELD AND METHODS THEREFOR - A combustor for a gas turbine engine is disclosed. The combustor is described as comprising a dome plate coupled to a liner thereof, with at least one heat shield comprised of a ceramic matrix composite coupled at the aft end of the dome plate. Also described is a method for assembling a combustor for a gas turbine engine, including releasing a metal alloy heat shield from a dome plate and providing a ceramic matrix composite heat shield as replacement. | 04-23-2015 |
20160090870 | 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. | 03-31-2016 |
20160102573 | ROTOR TIP CLEARANCE - A method of setting a clearance between a rotor and a stator of a rotor assembly for a turbine engine. The rotor assembly has a plurality of rotor-to-stator stages and the stator has a nominal centreline. Typically the stator is a casing or an array of vane tips. The method includes (i) correlating in-service rotor-to-stator rub patterns for a rotor-to-stator stage of a number of turbine engines, (ii) setting a position of a machining centreline relative to the nominal centreline of the stator, the position being towards a heavy rub, (iii) machining the stator about the machining centreline, (iv) repeating steps (i) to (ii) for each rotor-to-stator stage of the plurality of the rotor-to-stator stages, wherein the machined stator having been formed by at least two machining steps having different centre-lines. | 04-14-2016 |
20160375530 | METHOD FOR PRODUCING TURBINE ENGINE PARTS, AND RESULTING BLANK AND MOULD - The invention relates to a method for producing multiple metal turbine engine parts, comprising steps consisting in:
| 12-29-2016 |