Patent application number | Description | Published |
20080219835 | ABRADABLE COMPONENT FOR A GAS TURBINE ENGINE - A gas turbine engine component includes an airfoil having a radial outward end and a radial inward end. A seal member is positioned adjacent to the radial inward end of the airfoil. A tip of the radial inward end of the airfoil is coated with an abradable material. The seal member is coated with an abrasive material. | 09-11-2008 |
20080226879 | Low stress metallic based coating - A composition for deposition as a coating includes a matrix material having a molten fraction of between about 33% and about 90% by volume and a filler material interspersed within the matrix. | 09-18-2008 |
20090053422 | MASKING FIXTURE FOR A COATING PROCESS - A masking fixture for use in a coating process includes a first fixture plate for supporting a first work piece, a second fixture plate spaced from the first fixture plate for supporting a second work piece, and at least one spacer secured between the first fixture plate and the second fixture plate. | 02-26-2009 |
20090053554 | THERMAL BARRIER COATING SYSTEM FOR THERMAL MECHANICAL FATIGUE RESISTANCE - A composite article includes a substrate including a first metallic material having a nominal composition, and a bond coat disposed on the substrate. The bond coat includes a second metallic material having the nominal composition of the first metallic material. A ceramic top coat is disposed on the bond coat. | 02-26-2009 |
20090060747 | ORIENTED FIBER CERAMIC MATRIX COMPOSITE ABRADABLE THERMAL BARRIER COATING - A method of manufacturing a gas turbine engine component includes the steps of forming a ceramic workpiece having oriented ceramic reinforcement, and severing the ceramic workpiece to produce a ceramic member having a desired orientation of the ceramic reinforcement. The ceramic member is then attached to a turbine engine component as a thermal barrier layer for the turbine engine component. | 03-05-2009 |
20090097970 | Systems and Methods Involving Abradable Air Seals - Systems and methods involving air seals are provided. In this regard, a representative air seal for a gas turbine engine comprises a layer of ceramic exhibiting patterned surface features, wherein a substrate supporting the layer of ceramic lacks the patterned surface features. | 04-16-2009 |
20090110536 | Blade outer air seal with improved thermomechanical fatigue life - A blade outer air seal for a gas turbine has an abradable coating with a substantially uniform thickness during service use. Prior to being placed in service, the abradable coating has a central portion with a greater thickness than leading and trailing portions. When placed in service, the blade outer air seal is positioned so that the central portion of the abradable coating with the greater thickness is located in a blade rub path of the turbine blades. As a result of abrasion in the blade rub path, the thickness of the central portion of the abradable coating is reduced so that it becomes substantially similar to the thickness of the leading and trailing portions. | 04-30-2009 |
20090110831 | METHOD OF SPRAYING A TURBINE ENGINE COMPONENT - A method of spraying a component involves disposing a component near a spray coating device. The component has a first mating feature that is formed as part of the component. A first mask is disposed over a portion of the component and has a second mating feature. The first mating feature is resiliently connected to the second mating feature. The component is then sprayed. | 04-30-2009 |
20090130424 | CLOSED PORE CERAMIC COMPOSITE ARTICLE - A composite article includes a substrate and a thermal barrier secured to the substrate. The thermal barrier includes a plurality of closed pores within a ceramic matrix. For example, the closed pores comprise 20 vol % to 80 vol % of the thermal barrier. | 05-21-2009 |
20090136345 | SEGMENTED CERAMIC LAYER FOR MEMBER OF GAS TURBINE ENGINE - A turbine seal member for use in a gas turbine engine includes a turbine seal substrate having a gas-path side and a ceramic layer disposed on the gas-path side that includes a plurality of mechanical indentations. | 05-28-2009 |
20090136740 | ARTICLE HAVING COMPOSITE LAYER - A composite article includes a substrate and a layer attached to the substrate. The layer includes a metal phase, a first ceramic phase, and a second ceramic phase. | 05-28-2009 |
20090274848 | IMPINGEMENT PART COOLING - This disclosure relates to a thermal spray coating system including a table that is configured to support a component. A spray torch is configured to direct a thermal spray at a component surface. A cooling device is arranged adjacent to spray torch and configured to be in close proximity to the component surface. The cooling device includes a manifold that is connected to an air supply. The manifold has a face with multiple impingement holes less than one-eighth inch (3.1 mm) in diameter that are configured to direct cooling air on the component surface. In one example, the diameter of the impingement holes is approximately 0.059 inch (1.5 mm) and provide cooling air at a velocity of at least 400 ft per second (122 meters per second). The face is arranged within one inch (25 mm) of the component surface, in one example. Accordingly, the above cooling device uses less air and yields more consistent results in thermal coating of the component. | 11-05-2009 |
20090304494 | Counter-vortex paired film cooling hole design - An apparatus for use in a gas turbine engine includes a wall defining an exterior face, a first film cooling passage extending through the wall for providing film cooling to the exterior face of the wall, and a second film cooling passage extending through the wall adjacent to the first film cooling passage for providing film cooling to the exterior face of the wall. The first film passage includes a first vortex-generating structure for inducing a vortex in a first rotational direction in a cooling fluid passing therethrough, and the second film passage includes a second vortex-generating structure for inducing a vortex in a second rotational direction in a cooling fluid passing therethrough. The first and second rotational directions are substantially opposite one another. | 12-10-2009 |
20090304499 | Counter-Vortex film cooling hole design - An apparatus for use in a gas turbine engine includes a wall defining an exterior face, a first film cooling passage extending through the wall to a first outlet along the exterior surface of the wall for providing film cooling, and first and second rows of vortex-generating structures. The first film cooling passage defines a first interior surface region and a second interior surface region. The first row of vortex-generating structures is located along the first interior surface region, and the second row of vortex-generating structures is located along the second interior surface region. The first and second rows of vortex-generating structures are configured to inducing a pair of vortices in substantially opposite first and second rotational directions in a cooling fluid passing through the first cooling passage prior to reaching the first outlet. | 12-10-2009 |
20100021716 | THERMAL BARRIER SYSTEM AND BONDING METHOD - A composite article includes a substrate, a ceramic member on the substrate and a ceramic bond coat for securing the substrate and the ceramic member together. A method of securing the ceramic member and the substrate together includes pyrolyzing a ceramic precursor, such as a ceramic powder, between the substrate and the ceramic member to form the ceramic bond coat. | 01-28-2010 |
20100136258 | METHOD FOR IMPROVED CERAMIC COATING - A method of manufacturing an article having a ceramic topcoat includes the steps of forming the ceramic topcoat on the article, heating the ceramic topcoat, and establishing a desired thermal gradient through the ceramic topcoat to induce segmentation cracking in the ceramic topcoat. | 06-03-2010 |
20100159149 | APPARATUS FOR REDUCING STRESS WHEN APPLYING COATINGS, PROCESSES FOR APPLYING THE SAME AND THEIR COATED ARTICLES - A process for applying a coating to an axially split component includes the steps of installing at least one expansion or contraction device to at least one half of an axially split component; expanding at least one half to change a radius and maintain a constant curvature of at least one masked piece; applying a coating to the half; and, removing at least one expansion or contraction device from at least one half. | 06-24-2010 |
20100247291 | GAS TURBINE ENGINE ARTICLE HAVING COLUMNAR MICROSTRUCTURE - A gas turbine engine article includes a substrate extending between two circumferential sides, a leading edge, a trailing edge, an inner side for resisting hot engine exhaust gases, and an outer side. A gaspath layer is bonded to the inner side of the substrate and includes a metallic alloy having a columnar microstructure. | 09-30-2010 |
20110027573 | Lubricated Abradable Coating - A coated article has a metallic substrate. A coating layer comprises at least 33% by volume ceramic, at least 5% by volume of a lubricant selected from the group consisting of hexagonal boron nitride (hBN), clay, graphite, and mixtures thereof. The coating layer lacks a metal phase of more than 5% by volume. | 02-03-2011 |
20110116920 | SEGMENTED THERMALLY INSULATING COATING - A gas turbine article includes a substrate, a plurality of geometric surface features that protrude from the substrate, and a thermally insulating topcoat disposed over the plurality of geometric surface features. The thermally insulating topcoat includes segmented portions that are separated by faults that extend through the topcoat from the geometric surface features. | 05-19-2011 |
20110243715 | ABRADABLE TURBINE AIR SEAL - An abradable seal for a gas turbine engine includes a metal alloy and a plurality of pores in the metal alloy. The plurality of pores have a diameter of approximately 1 to 10 microns. | 10-06-2011 |
20110243716 | BLADE OUTER AIR SEAL WITH IMPROVED EFFICIENCY - An air seal for use with rotating parts in a gas turbine engine has a matrix of agglomerated fine hBN (hexagonal boron nitride) powder, the particles of which having a first dimension, and of a fine metallic alloy powder, the particles of which having a second dimension. An hBN (hexagonal boron nitride) powder, the particles of which have a third dimension that is greater than the first dimension, is mixed with the matrix. | 10-06-2011 |
20110256321 | ARTICLE HAVING COMPOSITE LAYER - A composite article includes a substrate and a layer attached to the substrate. The layer includes a metal phase, a first ceramic phase, and a second ceramic phase. | 10-20-2011 |
20120063888 | ABRADABLE COATING WITH SAFETY FUSE - An abradable coating for interaction with tips of airfoils (such as vanes or blades of a compressor of a gas turbine engine) includes a metal bond coat thermal, a ceramic layer, and an abradable layer. The ceramic layer on the metal bond coat provides insulation and acts as a fuse that is adapted to spall off upon high rub interaction. The abradable coating on the ceramic layer contacts the tips of the airfoils during operation of the compressor. The abradable coating is sufficiently abradable to roundup the coating by contact with the airfoil tips. | 03-15-2012 |
20120099968 | ABRASIVE ROTOR SHAFT CERAMIC COATING - An abrasive coating on a rotor shaft interacts with cantilevered vanes to form an abradable air seal in a turbine engine. The abrasive coating includes a metal bond coat, and an abrasive layer containing a plurality of abrasive grit particles in a ceramic matrix. The grit particles may be selected from cubic boron nitride (CBN), zirconia, alumina, silicon carbide, diamond and mixtures thereof. | 04-26-2012 |
20120099970 | FRIABLE CERAMIC ROTOR SHAFT ABRASIVE COATING - An abrasive coating on a rotor shaft interacts with cantilevered vanes to form an abradable air seal in a turbine engine. The abrasive coating includes a metal bond coat, and an abrasive layer containing a plurality of abrasive CBN grit particles in a ceramic matrix. | 04-26-2012 |
20120099971 | SELF DRESSING, MILDLY ABRASIVE COATING FOR CLEARANCE CONTROL - An abrasive coating for rotor shafts that interact with cantilevered vanes to form an abradable air seal in a turbine engine. The abrasive coating including a metal bond coat layer on the rotor shaft, and an abrasive top coating bond coat layer for contact with vanes during operation of the rotor shaft, the abrasive coating including a plurality of abrasive grit particles in a matrix. the abrasive grit particles are selected from the group consisting of cubic boron nitride (CBN), zirconia, alumina, silicon carbide, diamond and mixtures thereof. | 04-26-2012 |
20120099972 | ROUGH DENSE CERAMIC SEALING SURFACE IN TURBOMACHINES - An abrasive coating is formed on a rotor shaft that rotates with respect to cantilevered vanes. The coating is formed by thermal spray techniques and comprises a ceramic layer on a metal bond coat. The coating surface is roughened by crush grinding or by grit blasting to increase the abradability of the surface. | 04-26-2012 |
20120099973 | LOW DENSITY ABRADABLE COATING WITH FINE POROSITY - A low density abradable coating for use as a seal material is formed by depositing a metal bond coat followed by depositing a low density, porous, abradable metal seal layer on the bond coat. The seal layer is formed by co-depositing metallic sponge particles and metal precursor particles. The metal precursor particles decompose during heat treatment leaving fine pores distributed throughout the microstructure. | 04-26-2012 |
20120099985 | ABRASIVE CUTTER FORMED BY THERMAL SPRAY AND POST TREATMENT - A seal for a gas turbine engine component having an airfoil with a radial outward end and a radial inward end, one of which is bare metal. A seal member is adjacent to the bare metal end of the airfoil wherein the seal member is coated with a abrasive layer having a laser engraved surface with the top of the surface has less than about 5% of the surface area of the base of the abrasive layer. | 04-26-2012 |
20120099992 | ABRASIVE ROTOR COATING FOR FORMING A SEAL IN A GAS TURBINE ENGINE - A compressor rotor seal includes a bare radial inward end of a rotor vane in proximity to a rotor surface coated with an abrasive material. | 04-26-2012 |
20120132138 | DIMENSIONALLY STABLE DURABLE THERMAL SPRAY MASKING SYSTEM - A masking system protects portions of a part, such as a turbine engine component, to be coated. The masking system has a base, a conduit positioned on said base, a part to be coated being positioned over the conduit, and an annular plate positioned over the conduit and resting on a first portion of the part. | 05-31-2012 |
20120141680 | METHOD OF SPRAYING A TURBINE ENGINE COMPONENT - A method of spraying a component involves disposing a component near a spray coating device. The component has a first mating feature that is formed as part of the component. A first mask is disposed over a portion of the component and has a second mating feature. The first mating feature is resiliently connected to the second mating feature. The component is then sprayed. | 06-07-2012 |
20120177840 | Process for Forming an Improved Durability Thick Ceramic Coating - A process for forming a ceramic coating on a substrate, such as a turbine engine component includes the steps of providing a substrate, creating a plasma which preheats the substrate, and forming a ceramic coating by injecting a powder feedstock into the plasma. The ceramic coating forming step comprises depositing ceramic particles having a mean size in the range of from 100 to 150 microns at constant particle morphology. | 07-12-2012 |
20120189434 | COATING WITH ABRADABILITY PROPORTIONAL TO INTERACTION RATE - A seal in a gas turbine engine component between an airfoil with a radial outward end and a seal member adjacent it coated with an abrasive layer having a ceramic component in a matrix of a metal alloy with hexagonal BN. The ceramic component is selected from silica, quartz, alumina, zirconia and mixtures thereof and the metal is selected from nickel, cobalt, copper and iron. The ceramic ranges from about 1% to about 10% and the amount of nickel, cobalt, copper or iron will range from about 30% to about 60% by volume, and the balance is hBN. | 07-26-2012 |
20130004301 | SPALL RESISTANT ABRADABLE TURBINE AIR SEAL - An abrasive coating for a rotor shaft, the abrasive coating having a metal bond coat layer on the rotor shaft and an abrasive layer over the bond layer for contact with vanes during operation of the rotor shaft. The abrasive coating includes a matrix containing a low strength filler having an increased concentration radially outward from the bond layer to the outer surface of the abrasive layer. The matrix may be ceramic or metal. | 01-03-2013 |
20130017338 | PROCESS FOR FORMING A CERAMIC ABRASIVE AIR SEAL WITH INCREASED STRAIN TOLERANCEAANM Strock; Christopher W.AACI KennebunkAAST MEAACO USAAGP Strock; Christopher W. Kennebunk ME USAANM Richard; Robert D.AACI SpringvaleAAST MEAACO USAAGP Richard; Robert D. Springvale ME USAANM Lemay; StevenAACI WaterboroAAST MEAACO USAAGP Lemay; Steven Waterboro ME US - A plasma spray gun comprises a nozzle, an upstream powder injector, and a downstream powder injector. The upstream powder injector is disposed outside the nozzle and axially adjacent a nozzle outlet. The downstream powder injector is disposed axially downstream of the first upstream powder injector. The downstream powder injector is operative in a first coating mode, and the upstream powder injector is operative in a second coating mode. | 01-17-2013 |
20130043325 | DEVICE FOR SPRAY APPLICATIONS INCLUDING AT LEAST ONE CLEANING PORT - An exemplary device for spray applications includes a nozzle configured to emit a first fluid stream in a downstream direction away from the nozzle. At least one feed port situated near the nozzle introduces an agent into the first fluid stream to be carried by the first fluid stream in the downstream direction. At least one cleaning port situated near the nozzle emits a second fluid stream in a generally upstream direction toward at least one of the nozzle or the feed port. | 02-21-2013 |
20130068415 | MOLD FOR CASTING A WORKPIECE THAT INCLUDES ONE OR MORE CASTING PINS - A mold for casting a workpiece that includes a casting shell, a casting core and casting pin that supports the core within the shell. The casting shell includes an interior shell surface. The casting core is located within the shell, and includes a sidewall extending between a first core surface and a second core surface. The casting pin includes an intermediate segment connected between a first support segment and a second support segment. The intermediate segment contacts the sidewall. The first support segment extends from the first core surface to a first side of the interior shell surface. The second support segment extends from the second core surface to a second side of the interior shell surface that is opposite the first side. | 03-21-2013 |
20130071235 | LIGHT WEIGHT ABRADABLE AIR SEAL - An air seal for use with rotating parts includes an abradable layer adhered to a substrate. The abradable layer comprises a matrix of agglomerated hexagonal boron nitride and an oxide ceramic. Another hexagonal boron nitride is interspersed with the matrix. | 03-21-2013 |
20130078085 | BLADE AIR SEAL WITH INTEGRAL BARRIER - An air seal for use with rotating parts includes a thermal barrier coating layer adhered to a substrate. An abradable layer is adhered to the thermal barrier coating layer. The abradable layer comprises a matrix of agglomerated hexagonal boron nitride and a metallic alloy. Another hexagonal boron nitride is interspersed with the matrix. | 03-28-2013 |
20130136864 | PASSIVE TERMPERATURE CONTROL OF HPC ROTOR COATING - A method and fixture for holding a part being spray coated at an elevated temperature by placing the part between a base forming an insulating cover and an upper insulation board. The space therebetween forms an area for positioning a part to be sprayed. The cover and board are sized to retain heat in the part at a steady predetermined temperature when the part is spray coated. The part is heated for sufficient time to uniformly bring the part to temperature, followed by applying a spray to coat the part. | 05-30-2013 |
20130186920 | FEED RATE CONTROLLER FOR GRANULATED MATERIALS - The flow of granulated materials from a supply hopper to a transport tube is controlled. A material feed friction tube is positioned to receive material from the hopper. The friction tube receives material independent from hopper pressure and the material moves to an orifice. The orifice discharges material to a pickup tube from the orifice and includes a transfer tube for receiving material from the pickup tube. The pickup tube has a source of carrier gas sufficient to move the material into the transfer tube for further use. | 07-25-2013 |
20130333392 | TURBINE COMPRESSOR BLADE TIP RESISTANT TO METAL TRANSFER - A gas turbine engine having an engine casing extending circumferentially about an engine centerline axis; and a compressor section, a combustor section, and a turbine section within said engine casing. At least one of said compressor section and said turbine section includes at least one airfoil and at least one seal member adjacent to the at least one airfoil, wherein a tip of the at least one airfoil is metal having a thin film ceramic coating and the at least one seal member is coated with an abrasive. | 12-19-2013 |
20140065408 | THERMAL BARRIER COATING FOR GAS TURBINE ENGINE COMPONENTS - A component for a gas turbine engine according to an exemplary embodiment of the present disclosure can include a substrate, a thermal barrier coating deposited on at least a portion of the substrate, and an outer layer deposited on at least a portion of the thermal barrier coating. The outer layer can include a material that is reactive with an environmental contaminant that comes into contact with the outer layer to alter a microstructure of the outer layer. | 03-06-2014 |
20140093360 | ALUMINUM BASED ABRADABLE MATERIAL WITH REDUCED METAL TRANSFER TO BLADES - A turbomachine has a seal which mates to a plurality of airfoils. The seal is formed from an abradable aluminum based material having a plurality of hard phase particles embedded therein and having a melting point higher than a melting point of the melting point of the abradable coating matrix alloy. | 04-03-2014 |
20140220324 | THERMAL BARRIER COATING HAVING OUTER LAYER - A component according to an exemplary aspect of the present disclosure includes, among other things, a substrate, a thermal barrier coating deposited on at least a portion of the substrate, and an outer layer deposited on at least a portion of the thermal barrier coating. The outer layer includes a material that absorbs energy in response to an impact event along at least a portion of the outer layer. | 08-07-2014 |