United Technologies Corporation

Daniel M Stadtlander

William Bogue

Brian Kenneth Holland

Charles R Watson

Michael J Madel

Nicole Suulivan

Christopher S Leoni

William F Bogue

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

Acoustic panel repair methods and apparatus

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.

Torque protection device for fire blanket and associated method

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.

Repair of perforated acoustic skins by reverse pin transfer molding

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.

Plastic welding using fiber reinforcement materials

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.

Bond and stitch repair for delaminated composite

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.

Laminate air seal for a gas turbine 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.

Using a stiffener to repair a part for an aircraft engine

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.

Growing community of inventors

West Hartford, CT, United States of America

Daniel M Stadtlander