Patent application number | Description | Published |
20130042668 | HOT GAS PATH MEASUREMENT - A hot gas path measurement apparatus is provided and includes a substrate having a coating applied on a surface thereof such that the coating is interposed between the substrate and a hot gas path; and a measurement device fixed in a recess formed in the substrate, the measurement device including a sensor, and a holder configured to position the sensor in an alignment condition with a plane of a surface of the coating or at least partially within a span of the hot gas path. | 02-21-2013 |
20140260287 | GAS TURBINE FIRING TEMPERATURE OPTIMIZATION BASED ON SULFUR CONTENT OF FUEL SUPPLY - Gas turbine firing temperature optimization based on a measured sulfur content of a fuel supply of the gas turbine system is provided. In one embodiment, a system includes a diagnostic system configured to determine a maximum firing temperature for a combustor of a gas turbine system. The diagnostic system may determine the maximum firing temperature based on a predetermined sulfur content to maximum firing temperature correlation and an actual sulfur content of a fuel supplied to the combustor. The diagnostic system may also be configured to provide an indicator for a change in an actual firing temperature in the combustor of the gas turbine system. The diagnostic system may provide the indicator in response to the determined maximum firing temperature differing from the actual firing temperature of the combustor of the gas turbine system. | 09-18-2014 |
20150068213 | METHOD OF COOLING A GAS TURBINE ENGINE - A method of cooling a gas turbine engine is provided. The method includes removing a load from the gas turbine engine. The method also includes operating the gas turbine engine at a rated speed of the gas turbine engine. The method further includes modulating an angle of at least one stage of inlet guide vanes disposed proximate an inlet of a compressor section of the gas turbine engine, wherein modulating the angle modifies a flow rate of an inlet flow for reducing a cooling time of the gas turbine engine. | 03-12-2015 |
20150075265 | MEASUREMENT DEVICE AND METHOD FOR EVALUATING TURBOMACHINE CLEARANCES - Measurement devices and methods for evaluating clearances between adjacent components in turbomachines are provided. A measurement device may include a tool and a controller. The tool and controller may determine the clearance by measuring the distance between the adjacent components. The controller may compare the clearance to a predetermined engineering clearance limit and/or a previously measured clearance. A method may include measuring the clearance with a device which includes a controller. The method may further include comparing the clearance in the controller to a predetermined engineering clearance limit and/or a previously measured clearance. | 03-19-2015 |
20150078892 | ECCENTRIC COUPLING DEVICE AND METHOD FOR COUPLING MATING CASINGS IN A TURBOMACHINE - Turbomachines, coupling devices and methods for coupling a first casing and an second casing together are provided. The first casing and second casing include mating bore holes defined in mating flanges thereof, which may be misaligned. The coupling device may include a bushing insertable and positionable within one of the mating bore holes, and a pin insertable and positionable within the bushing and the other of the mating bore holes. The bushing and pin may each include eccentric features which may facilitate insertion into the mating bore holes when the bore holes are misaligned, thus coupling the first casing and second casing together. | 03-19-2015 |
Patent application number | Description | Published |
20120328451 | PLATFORM COOLING PASSAGES AND METHODS FOR CREATING PLATFORM COOLING PASSAGES IN TURBINE ROTOR BLADES - A method for creating a platform cooling passage in a turbine rotor blade, wherein the turbine rotor blade comprises a platform at an interface between an airfoil and a root, wherein the platform includes a platform topside along an outboard surface. The method may include the steps of forming a recessed area along the platform topside; forming a coverplate; and affixing the coverplate to the platform topside. The coverplate may be configured to correspond to the shape of the recessed area such that, when affixed to the platform topside in a desired manner, the coverplate substantially encloses the recessed area to form the platform cooling passage therein. | 12-27-2012 |
20130167870 | PRESSURE MASKING SYSTEMS AND METHODS FOR USING THE SAME - Methods of pressure cleaning a target surface of an article comprising one or more passageways include fluidly connecting a pressure masker comprising pressurized masking fluid to a first side of at least one passageway, passing the pressurized masking fluid through the at least one passageway from the first side to a second side comprising the target surface, and, cleaning the target surface using a cleaning material, wherein the pressurized masking fluid passing through the at least one passageway prevents the cleaning material from permanently altering a cross sectional area of the at least one passageway. | 07-04-2013 |
20130174923 | PRESSURE MASKERS AND PRESSURE MASKING SYSTEMS - Pressure maskers for masking at least one passageway of an article include a body portion that surrounds at least a portion of the article around the at least one passageway, at least one fluid inlet connected to the body portion that provides a conduit for pressurized masking fluid to pass from an exterior of the pressure masker to an interior of the pressure masker, wherein the article is at least partially disposed within the interior of the pressure masker, and at least one seal that seals the body portion at least partially around the article such that the pressurized masking fluid that enters the interior of the pressure masker is at least partially forced through the at least one passageway. | 07-11-2013 |
20130336801 | ROTATING AIRFOIL COMPONENT WITH PLATFORM HAVING A RECESSED SURFACE REGION THEREIN - A rotating airfoil component of a turbomachine, in which the component has an airfoil aligned in a spanwise direction of the component, a shank, and a platform therebetween oriented transverse to the spanwise direction. The platform has an outer radial surface adjacent the airfoil, and at least one recessed region defined in its outer radial surface. The recessed region extends opposite the spanwise direction from a platform plane that contains portions of the outer radial surface that are upstream and downstream from the recessed region. The recessed region is contiguous with an end wall of the platform and extends therefrom toward the airfoil. The recessed region defines a surface shape whose boundary is contained by the platform plane, and has a profile shape that extends from the end wall toward the airfoil. The recessed region is sized and shaped to increase the stiffness of the platform. | 12-19-2013 |
20140193664 | RECOATING PROCESS AND RECOATED TURBINE BLADE - Recoating process and recoated turbine blade are disclosed. The recoating process includes providing a coated turbine blade, then removing a portion of the thermal barrier coating system to form a partially-stripped turbine blade, then applying a bond recoat to the stripped region of the partially-stripped turbine blade; and then applying a thermal barrier recoat to the bond recoat to form a recoated turbine blade. The recoated turbine blade comprises the bond coating portion abutting the bond recoat, the thermal barrier coating portion abutting the thermal barrier recoat, and the stepped configuration. The coated turbine blade has a thermal barrier coating system positioned on a substrate. The partially-stripped turbine blade has a stripped region, a bond coating portion, a thermal barrier coating portion, and a stepped configuration. | 07-10-2014 |
20150030460 | METHODS FOR MODIFYING COOLING HOLES WITH RECESS-SHAPED MODIFICATIONS AND COMPONENTS INCORPORATING THE SAME - Methods for modifying a plurality of cooling holes of a component include disposing a recess-shaped modification in a recess of the component comprising a plurality of cooling hole outlets, wherein the recess-shaped modification is formed to substantially fill the recess and comprising a plurality of modified cooling holes passing there through. The method further includes aligning the plurality of modified cooling holes of the recess-shaped modification with the plurality of cooling hole outlets of the component, and, bonding the recess-shaped modification disposed in the recess to the component, wherein the plurality of modified cooling holes of the recess-shaped modification is fluidly connected with the plurality of cooling holes of the component. | 01-29-2015 |
20150064008 | TURBOMACHINE BUCKET HAVING ANGEL WING FOR DIFFERENTLY SIZED DISCOURAGERS AND RELATED METHODS - A turbomachine bucket may include an airfoil, a shank coupled to the airfoil, and an angel wing coupled to the shank, the angel wing having an axially extending tip sized to seal with a plurality of discouragers, each discourager having a different axial extent. Various methods for modifying an angel wing to accommodate different sized discouragers are also disclosed. | 03-05-2015 |
20150090303 | SYSTEM AND METHOD FOR CONFORMAL CLEANING - A system includes a plurality of nozzles, a pump configured to pump a fluid through the nozzles, and a manifold configured to arrange the plurality of nozzles to substantially match a shape of a workpiece. Each nozzle of the plurality of nozzles is configured to impinge upon a section of the workpiece with the fluid. | 04-02-2015 |
20150107341 | METHOD AND SYSTEM FOR DETECTING SURFACE FEATURES ON TURBINE COMPONENTS - A system for locating at least one surface feature, such as a cooling aperture, on a turbine component is provided. The system includes at least one feature marker configured for placement adjacent to the at least one surface feature. The system also includes at least one sensor configured for non-visual detection of the at least one feature marker. The system also includes a control device coupled to the at least one sensor for receiving signals from the at least one sensor, wherein the signals represent data indicative of one of a presence of the at least one feature marker and an absence of the at least one feature marker. | 04-23-2015 |
20150140239 | METHOD FOR MODIFYING AN APERTURE AND SYSTEM FOR MODIFYING FLOW THROUGH A COMPONENT - A method for modifying an aperture in a component, a system for modifying flow through a component, and a turbine component are disclosed. The method includes providing a substrate having at least one aperture having an electrically-conductive surface, providing a deposition device including an ESD torch, the ESD torch including an aperture penetrating electrode including a conductive material, inserting the aperture penetrating electrode at least partially into the aperture, and generating an arc between the aperture penetrating electrode and the electrically-conductive surface to deposit electrode material within the aperture. The system includes the ESD torch removably supported in an electrode holder. The turbine component includes at least one aperture having an electrospark deposited material along an electrically-conductive surface, the electrospark deposited material providing modified fluid flow through the turbine component. | 05-21-2015 |
20150158044 | AUTOMATED MASKING OF COOLING APERTURES - A system including: a masking applicator; and at least one computing device coupled with the masking applicator, the at least one computing device configured to provide instructions to the masking applicator to apply a masking material according to a masking plan for masking at least one cooling aperture in a turbomachine component during a cooling aperture coating process, the masking plan based upon at least one characteristic of the plurality of cooling apertures, the masking plan including masking the at least one cooling aperture using a first mask type. | 06-11-2015 |
20150159254 | COATING METHODS AND A COATED SUBSTRATE - Coating methods and a coated substrate are provided. The coating method includes providing a component having an aperture formed in a surface thereof, arranging and disposing a hollow member on a portion of the surface to define a hollow space above the aperture corresponding to a shape of the aperture at the surface, applying at least one coating over the surface of the component and the hollow member to form an applied coating having an applied coating thickness, and removing at least a portion of the hollow member to expose the hollow space through the applied coating. The coated substrate includes a component having an aperture formed in a surface thereof, a hollow member arranged and disposed on the surface to define a hollow space above the aperture, and an applied coating over the surface of the component, the hollow space being exposed through the applied coating. | 06-11-2015 |
20150160644 | REPAIR METHOD, SYSTEM FOR AUTOMATIC LOCATING AND CLEARING AND TOOL FOR AUTOMATED LOCATING AND MODIFYING - A repair method is provided and includes deriving, from a model of a component, drilling vectors respectively associated with fluid flow passages of the component, obtaining location data of each of the fluid flow passages at least partially from a source other than the model and relying upon the derived drilling vectors and the obtained location data of each of the fluid flow passages to position a tool configured to modify each of the fluid flow passages. | 06-11-2015 |
20150174837 | TURBINE COMPONENT PATCH DELIVERY SYSTEM - A turbine component patch delivery system can include a support arm and a deposition tool supported by the support arm. The deposition tool can include a reservoir configured to house a turbine component patch material and a dispenser configured to dispense the turbine component patch material from the reservoir onto a surface of a turbine component. | 06-25-2015 |
20150254817 | METHOD AND SYSTEM FOR DIMENSIONAL ANALYSIS OF AN OBJECT - The invention relates generally to the measurement and dimensional analysis of an object and, more particularly, to the correction of distortion in volumetric data of the object using dimensional data of the object. In one embodiment, the invention provides a method of analyzing an object, the method comprising: acquiring volumetric data of an object using an X-ray computed tomography (CT) imaging system; acquiring dimensional data of the object using a vision-based system; determining whether the volumetric data include a distortion; and in the case that the volumetric data are determined to include a distortion, correcting the distortion in the volumetric data using the dimensional data. | 09-10-2015 |
20150375322 | BRAZE METHODS AND COMPONENTS WITH HEAT RESISTANT MATERIALS - Braze methods include providing a substrate comprising a pre-sintered preform disposed thereon, wherein the pre-sintered preform comprises a mixture comprising a base alloy comprising about 30 weight percent to about 90 weight percent of the mixture and a second alloy comprising a sufficient amount of melting point depressant to have a lower melting temperature than the base alloy. Braze methods further include at least partially covering the pre-sintered preform with a heat resistant material, wherein a melt temperature of the heat resistant material is higher than a melt temperature of the pre-sintered preform, and heating the pre-sintered preform on the substrate. | 12-31-2015 |
20160047253 | SELECTIVE LOCALIZED COATING DEPOSITION METHODS AND SYSTEMS FOR TURBINE COMPONENTS - Methods for selective localized coating deposition for a turbine component include providing the turbine component comprising an exterior surface with one or more surface features and selectively coating at least a portion of the exterior surface using a localized coating deposition apparatus based on a location of at least one of the one or more surface features. | 02-18-2016 |
20160089692 | TURBINE COMPONENT COATING PROCESSES AND TURBINE COMPONENTS - Turbine component coating processes include applying a malleable masking material to one or more apertures of one or more fluid flow passages within a turbine component surface and then applying a first coating over the malleable masking material and on the turbine component surface. The turbine component coating processes further include locally applying a local masking material to the one or more apertures of the one or more fluid flow passages and then applying a second coating over the local masking material and on the first coating. | 03-31-2016 |
20160090843 | TURBINE COMPONENTS WITH STEPPED APERTURES - Turbine components include at least one fluid flow passage at least one aperture disposed on a surface of the turbine component and fluidly connected to the at least one fluid flow passage. The at least one aperture includes a floor extending from the at least one fluid flow passage to the surface; and, a step disposed between an inner portion of the floor and an outer portion of the floor such that the inner portion of the floor and the outer portion of the floor do not comprise a single planar surface. | 03-31-2016 |
Patent application number | Description | Published |
20090179146 | FLUIDICS DEVICE - The present invention contemplates various devices that are configured to separate a sample, which contains more than one unique species, into any desired number of sub-samples by passing the sample across a like number of separation media configured for a first separation protocol. Each of the sub-samples may be further separated by an additional separation protocol, thereby creating a plurality of mini-samples, each of which may be further separated and/or analyzed. The invention also contemplates using a simple method of using conduits to form a fluid path that passes through a plurality of separation media, each of which media is configured to isolate a particular sub-sample. After various sub-samples of the sample are isolated by the various separation media, the conduits may be removed, thereby enabling each of the isolated sub-samples to be further separated and/or analyzed independent of any other sub-sample. | 07-16-2009 |
20110250167 | METHOD FOR PURIFYING PROTEINS - The present invention provides methods and kits for purifying a target protein group. The method comprises the steps of contacting a sample comprising at least 95% of the target protein group and at most 5% of contaminating proteins with a library of binding moieties having different binding moieties, binding the contaminating proteins and a minority of the target protein group to the library of binding moieties, separating the unbound target protein group from the proteins bound to the library of binding moieties and collecting the unbound target protein. The collected target protein is more pure than the target protein group in the sample. | 10-13-2011 |
20120309644 | FLUIDICS DEVICE - The present invention contemplates various devices that are configured to separate a sample, which contains more than one unique species, into any desired number of sub-samples by passing the sample across a like number of separation media configured for a first separation protocol. Each of the sub-samples may be further separated by an additional separation protocol, thereby creating a plurality of mini-samples, each of which may be further separated and/or analyzed. The invention also contemplates using a simple method of using conduits to form a fluid path that passes through a plurality of separation media, each of which media is configured to isolate a particular sub-sample. After various sub-samples of the sample are isolated by the various separation media, the conduits may be removed, thereby enabling each of the isolated sub-samples to be further separated and/or analyzed independent of any other sub-sample. | 12-06-2012 |
20140004533 | MULTI-PROTEIN QUANTITATION STANDARD | 01-02-2014 |