Abstract: In a method for processing an acoustic panel (22), the panel comprises: a sheet (42) having a first face (44), a second face (46), and apertures (48) open to the first face and second face; and a mesh (60) along the first face. The method comprises forcing the mesh into a plurality of the apertures.

Abstract: In a method for processing an acoustic panel (22), the panel comprises: a sheet (42) having a first face (44), a second face (46), and apertures (48) open to the first face and second face; and a mesh (60) along the first face. The method comprises forcing the mesh into a plurality of the apertures.

Abstract: 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.

Abstract: A method of restoring a section of a composite includes the steps of removing an undesirable section of a perforated composite and depositing a repair material in the location of the removed, undesirable section. The repair material is then cured. Before completing the curing step, one or more opening are formed through the repair material to produce one or more perforations through the repair material upon completing the curing step.

Abstract: 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.

Abstract: A method of repairing delaminated plies of a composite includes drilling a plurality of holes in the plies, stitching one or more tows into the plurality of holes, and tensioning the tows. The holes are disposed across an area of the plies that is delaminated. The method introduces a resin into the area of the plies that is delaminated and cures the resin. Curing of the composite can be performed prior to the stitching and the tensioning of the one or more tows and can be performed by the tensioning of the one or more tows. Optionally, one or more additional plies can be applied to the repaired area and/or a portion of the one or more tows that extends above a surface the plies can be removed.

Abstract: A method of repairing delaminated plies of a composite includes drilling a plurality of holes in the plies, stitching one or more tows into the plurality of holes, and tensioning the tows. The holes are disposed across an area of the plies that is delaminated. The method introduces a resin into the area of the plies that is delaminated and cures the resin. Curing of the composite can be performed prior to the stitching and the tensioning of the one or more tows and can be performed by the tensioning of the one or more tows. Optionally, one or more additional plies can be applied to the repaired area and/or a portion of the one or more tows that extends above a surface the plies can be removed.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: The present invention relates to a method for bonding a component, such as a bushing, into a part, such as a panel. The method broadly comprises attaching a vacuum chamber to a surface of the part, seating the component into a slot in the part, and applying an adhesive material about a circumference of the component while drawing a vacuum in the vacuum chamber to allow the adhesive material to flow between the part and the component.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: A method of restoring a section of a composite includes the steps of removing an undesirable section of a perforated composite and depositing a repair material in the location of the removed, undesirable section. The repair material is then cured. Before completing the curing step, one or more opening are formed through the repair material to produce one or more perforations through the repair material upon completing the curing step.

Abstract: The present invention relates to a method for bonding a component, such as a bushing, into a part, such as a panel. The method broadly comprises attaching a vacuum chamber to a surface of the part, seating the component into a slot in the part, and applying an adhesive material about a circumference of the component while drawing a vacuum in the vacuum chamber to allow the adhesive material to flow between the part and the component.

Abstract: The present invention relates to a method for bonding a component, such as a bushing, into a part, such as a panel. The method broadly comprises attaching a vacuum chamber to a surface of the part, seating the component into a slot in the part, and applying an adhesive material about a circumference of the component while drawing a vacuum in the vacuum chamber to allow the adhesive material to flow between the part and the component.