Patent application number | Description | Published |
20080248300 | Processes for repairing erosion resistant coatings - A process for applying erosion resistant coatings includes the steps of applying a fluoroelastomer based solution to at least a portion of at least one perforated surface of an article, at least one perforated surface includes a plurality of perforations, and each of the perforations has a pre-coating diameter of no less than about 0.025 inches and no greater than about 0.075 inches; drying at least one perforated surface coated with the fluoroelastomer based solution; and curing at least one perforated surface coated with the fluoroelastomer based solution to form an erosion resistant coating. | 10-09-2008 |
20090243220 | FLUID BARRIERS WITH FLEXIBLE BACKING MATERIAL AND METHODS OF REPAIRING AND MANUFACTURING THE SAME - A component to be repaired includes a relatively rigid plate. On a surface that may have been subject to fracture, a resin material is first laid down, then a relatively flexible material is positioned outwardly of the resin material to repair the barrier. A part may also be formed initially with the flexible material. In another feature of this application, a method of forming a barrier includes providing a composite material, and applying a relatively flexible material on a surface of the composite material, and concurrently molding the relatively flexible material with the composite material using a composite mold. | 10-01-2009 |
20090263622 | REPAIR OF COMPOSITE SANDWICH STRUCTURES WITH UNEVEN BOND SURFACES - A method of restoring a section of a component having a honeycomb bonded to a skin includes the steps of separating a first honeycomb from the skin, wherein the honeycomb includes an uneven surface. At least a portion of the uneven surface is removed to form a bonding surface on the skin. A conformable layer is bonded to the uneven surface. Then a replacement honeycomb is then bonded to the conformable layer. | 10-22-2009 |
20100155251 | HARD ANODIZE OF COLD SPRAY ALUMINUM LAYER - A process for repairing components includes the steps of providing a component having an affected area on a surface of a component to be repaired; depositing a repair material over the affected area on the surface of the component so that the repair material plastically deforms without melting and bonds to the affected area upon impact with the affected area and thereby covers the affected area; providing a sulfuric acid based anodizing solution; anodizing a deposited repair material on the surface of said component in the sulfuric acid based anodizing solution; consuming only a portion of the deposited repair material to form a hard anodized coating layer upon the deposited repair material to form a hard anodized coated component; providing a corrosion resistant sealant solution; and contacting a hard anodized coated component with the corrosion resistant sealant solution to form a corrosion resistant sealant coating on the hard anodized coated component. | 06-24-2010 |
20100310873 | PLASTIC WELDING USING FIBER REINFORCEMENT MATERIALS - A method of reinforcing a thermoplastic part includes softening a portion of the thermoplastic part to form a pool, embedding fibers in the softened pool, and re-solidifying the pool embedded with fibers into a weld that strengthens the thermoplastic part. | 12-09-2010 |
20110000086 | DEVICE AND METHOD FOR REPAIRING A FORWARD FRAME V-BLADE IN AN AIRCRAFT ENGINE - A repair device and method for repairing a forward frame v-blade on an aircraft engine are described in which the repair device replaces a section of the forward frame v-blade. In one embodiment, the repair device includes a supplemental part, which is secured to the forward frame v-blade. The supplemental part includes a central web and a pair of legs with a leg thickness that is greater than the thickness of corresponding flanges on the forward frame v-blade. Fasteners such as rivets are used to couple the supplemental part to the forward frame v-blade. | 01-06-2011 |
20110138574 | HINGE ARM REPAIR - A hinge arm having a hinge pin hole having a worn bore, for example a hinge arm of a hinge assembly of an access door on a gas turbine engine, is repaired by forming in the worn hinge arm a new hole with a keyway extending outwardly from the new hole. A keyed bushing is provided having a cylindrical body having a central bore extending axially therethrough and a key extending outwardly from the cylindrical hole. The keyed bushing is inserted into the new hole and keyway formed in the hinge arm thereby preventing rotation of the bushing relative to the hinge arm. | 06-16-2011 |
20110177285 | REPAIR OF COMPOSITE SANDWICH STRUCTURES - A method of restoring a section of a composite includes the steps of removing an undesirable section of a composite and securing a repair section in the location of the removed undesirable section. One or more covers are secured on at least a portion the repair section to prevent or resist peeling of the repair section. | 07-21-2011 |
20110241295 | METHOD OF FORMING A SEAL ELEMENT - A method is provided for forming a seal element on a substrate surface. A layer of base material is formed on the substrate surface and a plurality of crenellations are formed in the layer of base material prior to forming a layer of seal material on the crenellated layer of base material. The method may be applied to making an original seal element or to repairing an existing seal element. The resulting seal includes a layer of base material bonded to a substrate and having a plurality of crenellations formed in a face surface of the layer of a base material and a layer of a seal material bonded thereto, the seal material filling the crenellations. | 10-06-2011 |
20120132447 | TORQUE PROTECTION DEVICE FOR FIRE BLANKET AND ASSOCIATED METHOD - A fire blanket assembly includes a thermal insulation material defining an opening, a metallic foil layer positioned along a first surface of the thermal insulation material and over at least a portion of the opening, an insert disc positioned adjacent to a second surface of the thermal insulation material opposite the first surface and further being positioned at the opening in the thermal insulation material, and a detail. The detail includes a base positioned at least partially within the opening in the thermal insulation material, a sidewall extending from the base, and a flange extending from the sidewall at a location spaced from the base, a perimeter of the flange turned at least partially away from the metallic foil layer. | 05-31-2012 |
20120160664 | CATHODIC ARC VAPOR DEPOSITION COATINGS FOR DIMENSIONAL RESTORATION OF SURFACES - A process for repairing a workpiece includes the steps of: providing a workpiece having at least one interior surface requiring restoration; providing a source of repair material; and depositing the repair material onto the at least one interior surface using a technique which is a near non-line of sight technique. | 06-28-2012 |
20120272637 | REPLACING AN APERTURE IN A LAMINATED COMPONENT - An example method of replacing an aperture in a component includes placing layers of a filler material into a first aperture. The layers of the filler material arranged in a stacked relationship relative to each other within the first aperture. The method cures the filler material and establishes a second aperture that is at least partially defined by the filler material. | 11-01-2012 |
20120304646 | METHOD AND APPARATUS FOR REPAIRING AN ENGINE COMPONENT - A shim is provided for repairing damage in a surface of a mechanical piece at or near an outer edge of a bore in the surface. The damage may penetrate a given distance within the surface and the bore is in close proximity to an attachment hole. The shim has a body having a first side and a second side and a thickness therebetween that is equal to or greater than the depth of the damage penetrating the given distance and contiguous to the attachment opening, wherein the body fits within an area machined into an outer surface surrounding the bore. | 12-06-2012 |
20120328427 | FIRESHIELD FASTENER HOOD - A fireshield fastener hood and method of bonding a cover to a substrate therefor. | 12-27-2012 |
20140096350 | NON-DESTRUCTIVE TEST INSPECTION METHOD FOR EVALUATING THERMAL DEGRADATION OF BISMALEIMIDE RESIN - A non-destructive method for determining an amount of temperature exposure to a Bismaleimide Resin (BMI) matrix substrate, the method includes determining component data of a Bismaleimide Resin (BMI) matrix component via fourier transform infrared (FTIR) spectroscopy; correlating the component data to model data to determine a structural debit from temperature exposure; and bounding a structurally damaged area in response to the correlating. | 04-10-2014 |
20140166255 | Closure of Cooling Holes with a Filing Agent - 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. | 06-19-2014 |
20140174092 | Closure of Cooling Holes with a Filling Agent - 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 extending through 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 with a polyimide, curing the polyimide to block the passage of cooling fluid through the plurality of first cooling holes, and applying a thermal bather coating over the outer surface of the component. The method may further include the step of installing a second plurality of cooling holes in the wall of the component wherein the plurality of second cooling holes penetrate the thermal barrier coating and the wall of the component and allow cooling fluid to pass therethrough. | 06-26-2014 |
20150030440 | FIRESHIELD FASTENER HOOD - A fireshield fastener hood and method of bonding a cover to a substrate therefor. | 01-29-2015 |
Patent application number | Description | Published |
20080233346 | Repair of a composite sandwich structure having a perforated skin - A method of restoring a section of a composite having a honeycomb bonded to a perforated skin includes the steps of separating a first honeycomb from the perforated skin to expose a portion of the perforated skin, inserting pins through perforations in the perforated skin, extending the pins through a repair material, attaching the repair material to the exposed portion of the perforated skin, and attaching a second honeycomb to the repair material. The method may include removing material from the exposed portion of the perforated skin, prior to inserting pins through the perforations, to create a more even bonding surface for attaching the repair material. | 09-25-2008 |
20080263844 | Using a stiffener to repair a part for an aircraft engine - A method of repairing a part, which has a first side, a second side opposite of the first side, and an aperture that makes the part susceptible to cracking, includes the steps of forming a slot in the first side of the part near the aperture, inserting a stiffener into the slot, and attaching at least one repair ply onto the first side of the part to cover the stiffener. | 10-30-2008 |
20090038739 | Replacement of a lubricant layer bonded to a part of a gas turbine engine - A method and system is described herein for repairing a part used in a gas turbine engine, which has a damaged or worn lubricant layer bonded to a surface of the part. After removing the damaged or worn lubricant layer, a polymeric adhesive may be used to attach a replacement lubricant layer to the metal surface. The polymeric adhesive may be a film or a paste. In some embodiments, the adhesive includes a non-metallic filler. The polymeric adhesive is stable at an operating temperature of the part to which it is attached. In one embodiment, the adhesive is polyimide, which is well-suited for use in a high pressure compressor of the gas turbine engine that operates at high temperatures. In other embodiments, the adhesive is bismaleimide (BMI) or cyanate ester. | 02-12-2009 |
20090148275 | Laminate air seal for a gas turbine engine - A laminate air seal for a gas turbine engine includes at least one fabric layer made of fiberglass, ceramic fiber, basalt and/or carbon, and a polymeric resin that is stable at an operating temperature of the gas turbine engine. The resin may be preimpregnated into the fabric layers, or introduced into the fabric during assembly and formation of the laminate. The resin may be polyimide, bismaelimide (BMI) or cyanate ester. A particular resin selected may depend, in part, on the operating temperatures in that region of the gas turbine engine. In some embodiments, the laminate seal may include a coating to increase lubricity of the seal. In one embodiment, the laminate air seal is used to seal a gap between a pylon fairing and an exhaust nozzle of the turbine engine. | 06-11-2009 |
20090165926 | Method and assembly for bonding metal layers in a gas turbine engine using a polyimide adhesive - A method and system is described herein for using a polyimide adhesive to bond a first metal layer to a second metal layer used in a gas turbine engine. The polyimide adhesive may be a film or a paste and is able to withstand operating temperatures in excess of 600 degrees Fahrenheit (315 degrees Celsius). In an exemplary embodiment, the second metal layer is an outer face skin of an exhaust nozzle and the first metal layer is a metal doubler configured to cover a damaged portion of the outer face skin. In some embodiments, the first and second metal layers may be formed of titanium. | 07-02-2009 |
20090258185 | Metallic doubler for repair of a gas turbine engine part - A method and system of repairing an engine part having a cracked metal skin bonded to a honeycomb core includes removing a portion of the honeycomb that corresponds to a cracked portion of the metal skin. A crack in the metal skin originates from an edge of the engine part. A portion of the honeycomb is removed to form a slot in the honeycomb beginning at the edge of the part. A doubler is inserted into the slot in the honeycomb and is attached to an underside of the metal skin to form a lap joint between the doubler and the metal skin. In one embodiment, the portion of the metal skin that includes the crack remains. In an alternative embodiment, the cracked portion of the metal skin is removed and a metal patch is attached to the doubler such that the patch replaces the removed metal skin. | 10-15-2009 |