Abstract: A manufacturing method is provided. During this method, a preform component is provided for a turbine engine. The preform component includes a substrate comprising electrically conductive material having an outer coating comprising non-electrically conductive material applied over a surface of the substrate. A preform aperture is formed in the preform component using an electrical discharge machining electrode. The preform aperture includes a meter section of a cooling aperture in the substrate. The preform aperture also includes a pilot hole in the outer coating. A diffuser section of the cooling aperture is formed in at least the outer coating using a second machining process.

Abstract: In some examples, a method including applying a wet bond coat slurry to a damaged area of a coating system on a metal substrate, the bond coat slurry including a liquid binder, glass and/or glass-ceramic particles, and ceramic oxide particles; depositing fibers onto the wet bond coat slurry, wherein the fibers include metallic and/or ceramic fibers; applying a ceramic composite slurry on the bond coat while the bond coat is wet or at least partially dried to form a ceramic composite layer, the bond coat including a plurality of partially exposed fibers, wherein, following the application of the ceramic composite slurry, a first portion of fibers of the plurality of fibers are embedded in the bond coat and a second portion of fibers of the plurality of fibers extend into the layer of the ceramic composite slurry; and heating the bond coat and the ceramic composite layer to form a repaired portion of the coating system on the metal substrate, wherein heating the bond coat melts the glass particles and/or the gl

Abstract: A coated, highly transparent film based on cellulose triacetate, is proposed that includes a) a support film acting as support layer and a cellulose triacetate or a mixture of cellulose esters and cellulose triacetate as main component, the cellulose triacetate or mixture being defined by a haze value of <0.5%, measured on the cellulose triacetate or mixture drawn out to a film after having been dissolved in dichloromethane or acetone, and b) a multi-functional coating applied in a coating solution to one or both sides of the support film. A dissolver medium can also be used as an enclosure medium. The highly transparent films of the invention can be used as window film, sunglasses film, laminating film, furniture foil, enclosing film, slide film for microscopy, cover slip replacement film and/or protective film, adhesive to glass, wood, metal, ceramic, cellulose derivative films or plastics following incipient dissolution or heat treatment.

Abstract: An article includes a substrate and a structure of additive manufacturing material of predetermined thickness attached to the substrate, the structure of additive manufacturing material formed by providing a metal alloy powder, forming an initial layer having a preselected thickness and a preselected shape including at least one aperture, with the metal alloy powder, sequentially forming an additional layer with the metal alloy powder over the initial layer, each of additional layers having an additional preselected thickness and an additional preselected shape including an aperture corresponding to the aperture in the initial layer, and joining each of the additional layers to the initial layer or any previously joined additional layers, forming a structure having a predetermined thickness and shape, and an aperture having a predetermined profile. The article includes a passageway through the structure including the aperture and a corresponding metering hole.

Abstract: An article includes a substrate and a structure including direct metal laser melted material of predetermined thickness attached to the substrate, the structure formed by providing and depositing a metal alloy powder to form an initial layer having a preselected thickness and shape including at least one aperture, melting the metal alloy powder with a focused energy source, transforming the powder layer to a sheet of metal alloy, sequentially depositing an additional layer of the metal alloy powder over the sheet of metal alloy, the additional preselected shape including an aperture corresponding to the aperture in the initial layer, and melting each additional layer of the metal alloy powder with the focused energy source, increasing the thickness of the sheet and forming at least one aperture having a predetermined profile, the article further including a passageway through the structure including the aperture and a corresponding metering hole.

Abstract: A method of fabricating and repairing a gas turbine component having a plurality of cooling holes defined therein is provided. The method includes determining a parameter of a first cooling hole defined in the gas turbine component, and generating a tool path for forming a protective cap around the first cooling hole. The tool path is based at least partially on the parameter of the first cooling hole. The method also includes directing a robotic device to follow the tool path, and discharging successive layers of ceramic slurry towards the gas turbine component as the tool path is followed such that the protective cap is formed around the first cooling hole.

Abstract: A gas shield arrangement for a gas turbine engine includes a first gas shield that is arranged to cover an inlet of a gas flow path of the gas turbine engine and a second gas shield that is arranged to cover a first outlet of the gas flow path of the gas turbine engine. The gas shield arrangement further includes a reservoir that holds fluid and a pump that pumps the fluid from the reservoir to one of a first valve and a second valve and that returns at least some of the pumped fluid to the reservoir from the other of the first valve and the second valve.

Abstract: A process is described for laser welding a sheet metal workpiece having an anti-corrosion pre-coat on at least one major surface thereof and having first and second opposite side edges. The sheet metal workpiece is arranged such that the first and second side edges are in contact with one another and such that the at least one major surface faces outwardly. A laser beam having a first beam spot-size, is used to form a laser weld joint between the first and second side edges. Subsequently, a localized anti-corrosion surface layer is formed on the laser weld joint. To this end, a laser beam having a second beam spot-size larger than the first beam spot-size is scanned along the laser weld joint. During the scanning, a flow of a powdered anti-corrosion surface layer material is directed toward a portion of the laser weld joint that is being irradiated by the laser beam. The laser beam melts the material, which subsequently solidifies to form a layer adhering to the laser weld joint.

Abstract: A treatment composition is disclosed including a carrier and a sacrificial oxide-forming material suspended within the carrier. The sacrificial oxide-forming material is selected from the group consisting of tin oxide, magnesium oxide, antimony pentaoxide, and combinations thereof. A treatment process for a gas turbine component including an abradable ceramic coating is disclosed. The process includes contacting the abradable ceramic coating with the treatment composition. The sacrificial oxide-forming material is infused into the abradable ceramic coating to form sacrificial oxide-forming deposits within the abradable ceramic coating. A rejuvenation process is disclosed including contacting the hot gas path surface of a gas turbine component with a rinse composition comprising water and the treatment composition to form the sacrificial oxide-forming deposits within the abradable ceramic coating.

Abstract: Light weight fan blades for turbofan jet engines are disclosed. The fan blades may be fabricated from an aluminum alloy. To enhance the hardness of the leading edge of the fan blade, a titanium sheath may be attached to the leading edges of the fan blades. To prevent galvanic coupling between the titanium and the aluminum, a polymeric liner may be disposed between the protective titanium sheath and the aluminum fan blade. The liner may be fabricated from a polymer material, such as a polyimide or another high performance polymer.

Abstract: A containment sheet mounting device for holding containment sheeting in a sealed engagement to a mounting surface. The device has a base which is removably engageable to the mounting surface which has one or a pair of connecting members extending from the base. The connecting members have an adhesive surface which engages with the sides of the containment sheeting to hold it in position adjacent the mounting surface.

Abstract: A heatable roller suitable for a machine for producing and/or upgrading a web of material, in particular a fibrous material web such as a paper, paperboard or tissue web. The roller has a main element with a metallic and cylindrical roller wall which is heatable by suitable means and on the radially outer side of which there is, at least in sections, a coating. When the roller is used as intended, the coating provides a web contact side which can be brought into contact with the web of material. The coating includes, or is formed by, at least one metallic or metal-carbidic layer with a first layer component providing a matrix and a second layer component distributed in the matrix. The first layer component has a higher abrasion resistance than the second layer component and the second layer component has a greater thermal conductivity than the first layer component.

Abstract: Functionally graded materials can be prepared through additive manufacturing by determining the path that a head of 3D printer can follow while extruding a material mix of a required composition at required points of a layer of an FGM. Each point within the layer is evaluated regarding the directions within which the printing head can move into from that point while extruding the material mix of a required composition. Based on the evaluation, a multitude of polygons are defined within the polygonal shape that are guaranteed to be printable. A path can be designed for the printing head to follow to print all of the defined polygons, and consequently, to print the entire polygonal layer. Material extrusion commands are generated for the printing head.

Abstract: The invention relates to a method and system for forming a layer of oxide on a pervious component made of a material or a stack of materials that are stable at 400° C., said component including an outer surface to be coated and at least one pore with a diameter of 50 to 1000 ?m leading onto said outer surface.

Abstract: A coating process for applying a bifurcated coating to an article is disclosed including applying an aluminizing slurry to a first portion of the article, applying a chromizing slurry to a second portion of the article, and simultaneously heat treating the article, the aluminizing slurry, and the chromizing slurry. Heat treating the aluminizing slurry forms an aluminide coating on the first portion of the article and an aluminide diffusion zone between the article and the aluminide coating. Heat treating the chromizing slurry forms a chromide coating on the second portion of the article and a chromide diffusion zone between the article and the chromide coating. The first portion and the second portion are both maintained in an unmasked state while applying the aluminizing slurry and the chromizing slurry and during the heat treating.

Abstract: A method of producing cooling apertures in a combustion chamber head includes mechanically drilling a plurality of cooling apertures through the combustion chamber head from the downstream side of the combustion chamber head. A tool is inserted through at least one aperture for a fuel injector from the downstream side of the combustion chamber head and the tool is rotated about its axis while within the aperture for a fuel injector. Fluid is supplied from the drilling machine through the tool and jets of fluid are directed from nozzles in the tool with at least a radial component towards the cooling apertures on the upstream side of the combustion chamber head to remove burrs and/or caps adjacent the cooling apertures. The present disclosure enables cooling apertures to be drilled through a combustion chamber head using conventional mechanical drilling in a viable and cost effective manner.

Abstract: The present disclosure is directed to a waterborne coating composition having neutral pH that is low foaming and forms dry coating layer that has high hardness and high gloss. This disclosure is further directed to a coating composition comprising a crosslinking component comprising: (a) one or more alkylated melamines that are essentially unreactive to a polyisocyanate; and (b) a polyisocyanate. The coating composition can be particularly suitable for vehicle coatings and other industrial or consumer applications.

Abstract: A wet on wet coating application method. The method includes contacting a polyol-containing layer including a polyol in an amount of 10 to 70 percent by weight and a isocyanate-catalyst-containing layer including an isocyanate and a catalyst to form a boundary layer between the layers being the reaction product of the polyol and isocyanate catalyzed by the catalyst and carried out at 68° F. to 75° F.

Abstract: A method is provided for repairing an area of damaged coating on a component of a turbine module in a gas turbine engine, the component formed of a base material having a diffusion coating applied to the base material. The repair may be accomplished in place by directly heating the area to which a touch-up coating material has been applied with a hot gas plasma without the need to place the component in an oven for curing and heat treatment of the touch-up coating applied to the damaged area.

Abstract: A paste contains at least one monomer for radical polymerization, at least one polymer that is soluble in said at least one monomer for radical polymerization, and at least one filling agent that is poorly soluble or insoluble in said at least one monomer for radical polymerization. The filling agent is a particulate inorganic calcium salt comprising the following properties: at least 90% by weight of the particulate inorganic calcium salt have a particle size of less than 63 ?m, as determined by means of sieve analysis; and the solubility in water of the particulate inorganic calcium salt at 20° C. is less than 8.5 g per liter. A kit and the paste is usable for mechanical fixation of articular endoprostheses, for covering skull defects, for filling bone cavities, for femuroplasty, for vertebroplasty, for kyphoplasty, for the manufacture of spacers or for the production of carrier materials for local antibiotics therapy, as well as a form body.

Abstract: A sintered product having an average chemical composition such that, in weight percentages on the basis of the oxides: Cr2O3=80.0-99.0%; 0.5%?TiO2?9.0%; 0.2%?MgO?3.0%; and ZrO2?5.0%, provided that the ratio of TiO2/MgO is between 1.5 and 9.0 and the molar ratio TiO2/Cr2O3 is less than 0.12.

Abstract: A method of repairing a damaged rotor comprising: (a) preparing a locally damaged portion of the rotor; (b) cold spraying alloy powder particles onto the locally damaged portion; (c) controlling the cold spraying in step (b) to restore the locally damaged portion to form a repaired portion having substantially the same properties and shape as originally manufactured; and (d) heat treating at least the repaired portion.

Abstract: A material mixture for dissolving a coating system from a work piece comprises an aqueous, alkaline solution containing between 3 and 8 weight percent KMnO4 and at the same time having an alkaline fraction of between 6 and 15 weight percent. The alkaline fraction is formed in one embodiment by KOH or NaOH, wherein the pH of the solution is above 13. A method according to the present invention uses the above-described material mixture for wet-chemical delaminating of hard material coatings of the group: metallic AlCr, TiAlCr and other AlCr alloys; nitrides, carbides, borides, oxides thereof and combinations thereof.

Abstract: A component of a rotary wing aircraft is provided including a surface configured to contact another component of the rotary wing aircraft such that the surface is susceptible to corrosion and/or pitting. The surface has an area from which a portion of material was removed. A structural deposit is formed by cold spraying one or more layers of powdered material within the area. The structural deposit is configured to carry a load applied to the component.

Abstract: A magnesium component of a rotary wing aircraft is provided including a groove including a first sidewall and a second sidewall arranged on opposing sides of a recessed opening. The first sidewall includes a deposit positioned adjacent the recessed opening. The deposit is formed by cold spraying one or more layers or powdered material within an area of the first sidewall from which material was removed.

Abstract: A method of coating a metal substrate such as the components in second and third stages of gas turbine engines in order to increase the oxidation and corrosion resistance of the metal substrate under high temperature operating conditions, the method including the steps of forming a powdered mixture of a high-melt superalloy or MCrAlY component, where M comprises Fe, Ni and/or Co, and a low-melt component containing about 2-5 wt. % silicon, boron or hafnium, applying the powdered mixture to the surface of the metal substrate at room temperature using an atomized spray to form a uniform surface coating, and then heating the coated substrate surface under vacuum conditions to a temperature in the range of about 1900° F. to 2275° F. to obtain a uniform coating composition providing oxidation resistance to the underlying substrate.

Abstract: A plunger for fuel injection assembly is provided. The plunger includes a nitrided surface. The nitrided surface includes a damaged area. An electroless material is coated on the damaged area.

Abstract: A method for non-destructive evaluation of an article of manufacture (30) by coating the article with a temperature-sensitive coating (34), stimulating the article with energy (18) to induce temperature changes in the article responsive to features of the article, then evaluating (24) a resulting topography of energy-induced changes (50, 52, 53) in the coating (34). The energy imparted to the article may be, for example, electromagnetic, magnetic, or sonic energy that produces localized changes in temperature in the article (30) in response to features (32) of the article such as flaws or other discontinuities. The coating (34) may be a suspension of liquid crystals in a liquid, and the energy may be an application of sonic energy. The coating may be a material that hardens (42, 54) or softens (44, 56) upon a slight increase in temperature. Layers (34, 35) of different energy-sensitive coatings (38, 40) may be applied to indicate different aspects of features of the article.

Abstract: The present invention relates to a slip for producing an aluminum diffusion layer which comprises an Al-containing powder and an Si-containing powder and a binder, the slurry further comprising an Al-containing powder the powder particles of which are coated with Si. The invention further relates to a process for producing an aluminum diffusion layer, comprising the following steps: providing a slurry according to any one of the preceding claims, applying the slurry to a component surface on which the aluminum diffusion layer is to be created, drying and/or curing by way of a heat treatment at a first temperature, and diffusion annealing at a second temperature.

Abstract: The present invention relates to methods for repairing a structural weakness in an aircraft fuselage, or preventing the advancement of a structural weakness in an aircraft fuselage. Cold spray methods such as supersonic particle deposition have been shown to positively affect structural characteristics of sheet metal and lap joints as used in fuselage construction.

Abstract: A method of repairing a component removes a prior coating from an underlying metal substrate. Small cooling air holes extend through the substrate and the coating that is to be removed. A new coating layer is placed on the metal substrate, and over the existing cooling air holes. The location of the cooling air holes is identified by inspecting the coated component for the location of indicators of the coating passing over the cooling air holes. The identified location of the indicators is used to control a cutting tool to remove any new coating from the cooling air holes. The basic method may also benefit new manufacture.

Abstract: A method of applying a nanocrystalline metal coating to a titanium or titanium alloy blade of a gas turbine engine is described. The method includes selecting an intermediate bond coat from the group consisting of nickel, nickel alloy, P, B, Tl and combinations thereof, and applying the intermediate bond coat to at least a portion of the blade. A nanocrystalline metal coating having an average grain size of between 10 nm and 500 nm is then applied to the portion of the blade overtop of the intermediate bond coat.

Abstract: A method for creating a textured surface (52) of bond coat material (18) for improving the performance of a thermal barrier coating system (12). A plurality of columns (62) of bond coat material are formed by spraying (52) the material through a corresponding plurality of openings (32) in a mask (30) applied to a surface (40) to be textured. The openings may be formed in only a region (34) of the mask in response to an image of the surface to be textured. The mask and excess material (54) applied over the mask are then removed to reveal the textured surface.

Abstract: The present disclosure is related to a component. The component may include a cast iron base and an intermediate layer covering a least a portion of the cast iron base. The intermediate layer may include aluminum and at least one of nickel, cobalt, chromium, silicon, or iron. The component may also include an outer layer covering the intermediate layer. The outer layer may include steel.

Abstract: In various embodiments, a sputtering target initially formed by ingot metallurgy or powder metallurgy and comprising a sputtering-target material is provided, the sputtering-target material (i) comprising a metal, (ii) defining a recessed furrow therein, and (iii) having a first grain size and a first crystalline microstructure. A powder is spray-deposited within the furrow to form a layer therein, the layer (i) comprising the metal, (ii) having a second grain size finer than the first grain size, and (iii) having a second crystalline microstructure more random than the first crystalline microstructure. Spray-depositing the powder within the furrow forms a distinct boundary line between the layer and the sputtering-target material.

Abstract: A method of applying a nanocrystalline coating to a gas turbine engine component is described. The method comprises the steps of applying an intermediate bond coat to at least a portion of the component, and then applying the nanocrystalline coating to at least the portion of the component overtop of the intermediate bond coat. The component may include, for example, a blade of which a dovetail portion of the blade root is protected by applying the intermediate bond coat and the nanocrystalline coating thereto.

Abstract: A refurbishment process for a volumetric screw compressor of the ‘oil-free’ type, which comprises a male rotor and a female rotor, is described. The process comprises visually checking the wear condition of the rotors, treating their surface for removing the previous coating, and applying a new coating on the surface.

Abstract: A plunger for fuel injection assembly is provided. The plunger includes a nitrided surface. The nitrided surface includes a damaged area. An electroless material is coated on the damaged area.

Abstract: A method of repairing a component comprises identifying a non-compliant surface of the component, wherein the non-compliant surface is not within an allowable tolerance, cold spraying a powder comprising a metal onto the non-compliant surface, and forming a coating comprising the metal over the non-compliant surface, wherein an outer surface of the coating is within an allowable tolerance. In an embodiment, the method of repairing an outer component further comprises machining the outer surface of the coating. In an embodiment, the component is a shaft, a rotor mast, an input quill, or a bearing. In an embodiment, the component contains electronic equipment during the cold spraying, and wherein the cold spraying does not damage the electronic equipment. In an embodiment, the component is repaired without subjecting the component to a hydrogen embrittlement bake.

Abstract: A low sludge trivalent chromium based conversion coating bath is provided which forms corrosion resistant coatings on aluminum and aluminum alloys by contact with the bath, which is suitable for use as a rinseable or dry-in place conversion coating for metal, that comprises trivalent chromium cations, fluorometallate anions, guanidinium ions and at least one organic anti-corrosion additive, and other optional components, as well as methods of making and using same, and metals coated using the compositions, the coated aluminum serving as an effective base for paint primers.

Abstract: A method of repairing or manufacturing a superalloy component (50) by depositing a plurality of layers (22, 24, 26, 28) of additive superalloy material having a property that is different than an underlying original superalloy material (30). The property that is changed between the original material and the additive material may be material composition, grain structure, principal grain axis, grain boundary strengthener, and/or porosity, for example. A region (60) of the component formed of the additive material will exhibit an improved performance when compared to the original material, such as a greater resistance to cracking (58).

Abstract: A method of manufacturing a component suitable for use in a gas turbine engine, comprising the steps of forming the component from a substrate having a first surface and a second surface, forming at least one aperture through the substrate from the first surface to the second surface having a first open area, applying a first coating to at least one of the first surface and the second surface adjacent to the at least one aperture, the aperture remaining at least partially unobstructed by the first coating, applying a second coating to the first coating adjacent to the at least one aperture, the aperture remaining at least partially unobstructed by the second coating, and removing the second coating from the aperture, leaving most or all of the first coating to define a second open area which is smaller than the first open area.

Abstract: 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.

Abstract: A method is disclosed for the repair of a component of a turbomachine, in particular a rotor of an aircraft gas turbine, with blades taken up in at least one groove and with at least one support region for limiting a blade tilt angle, whereby at least one segment, which has been subjected to wear, of the support region of the component is removed, and a coating that can be introduced in the unit on at least one supporting surface of at least one blade is formed on the component for limiting the blade tilt angle. In addition, a component of a turbomachine, in particular a rotor of an aircraft gas turbine, with at least one such repair site is disclosed.

Abstract: A method for filling cooling holes in a component of a gas turbine engine is disclosed. The component may include a plurality of first cooling holes penetrating the wall of the component. The method may comprise the steps of exposing the outer surface of the component, filling the plurality of first cooling holes of the component with a filling agent, curing the filling agent to block the passage of air through the cooling holes, and applying a thermal barrier coating over the surface of the component. The method may further include installing a second plurality of cooling holes, the second plurality of cooling holes penetrating the thermal barrier coating and the wall of the component and allow air to pass therethrough.

Abstract: A method for controlled removal of a portion of a diffusion coating from a coated superalloy component and a method for rejuvenating a coated superalloy component are provided. The methods include providing the component having an oxide layer, an additive layer between the oxide layer and a diffusion zone, the diffusion zone being between the additive layer and a superalloy substrate of the superalloy component. The methods include selectively removing the oxide layer and a portion of the additive layer by grit blasting, wherein removing creates an exposed portion. Rejuvenating includes applying an aluminide coating to the exposed portion and heat treating at a preselected elevated temperature to form a rejuvenated protective aluminide coating on the superalloy component.

Abstract: A deposition chamber shield having a stainless steel coating of from about 100 microns to about 250 microns thick wherein the coated shield has a surface roughness of between about 300 microinches and about 800 microinches and a surface particle density of less than about 0.1 particles/mm2 of particles between about 1 micron and about 5 microns in size and no particles below about 1 micron in size, and process for production thereof is disclosed.

Abstract: The method according to the invention for reprocessing the worn surface of grinding rollers (2) of a material bed roller mill comprises the following method steps: a. providing a mobile processing station (6) which is arranged in a container (8) and comprises at least one machine tool (9) and a drive (10) for rotating the grinding roller, b. removing the complete roller unit (A) containing the grinding roller to be reprocessed from the material bed roller mill, c. positioning the complete roller unit in front on the mobile processing station and coupling the drive to the shaft (1) of the grinding roller, d. producing a new cylindrical surface (2h) using the machine tool, and e. producing a new wear protection comprising new profiled bodies (2c) and/or build-up welding.

Abstract: Provided are an automatic lithium target regenerating apparatus and an automatic lithium target regenerating method, which are equipped with a measurement function of a lithium film thickness of a lithium target, and may automatically regenerate the consumed lithium target by moving a vapor deposition source to the lithium target. An automatic lithium target regenerating apparatus (106) is allowed to automatically regenerate lithium of a lithium target. The automatic lithium target regenerating apparatus (106) includes a lithium vapor deposition unit (1) for vapor-depositing the lithium on the lithium target. The lithium vapor deposition unit (1) is allowed to vapor-deposit the lithium on the lithium target by moving to the lithium target side.

Abstract: A thermal barrier coating method forms a thermal barrier coating by spray coating over the surface of a component where cooling holes are made. The thermal barrier coating is formed by spray coating after masking pins, which do not protrude above the surface of the component, are inserted into the cooling holes or masking pins protruding above the surface of the component are inserted and get shrunk due to heat while spray coating, obtaining the protruding amount equal to or less than the thickness of the thermal barrier coating after shrinkage, which characterizes the method. By way of this method, a thermal barrier coating can be formed all over the surface without clogging the cooling holes.