A method for repairing a tire including: (a) providing a reamer, an insertion tool with a receiving opening, a tri-layer strip, and vulcanizing fluid; (b) inserting the reamer into a puncture hole of a tire to clear debris; (c) applying the vulcanizing fluid; (d) inserting the tri-layer strip into the insertion tool; (e) inserting the insertion tool and tri-layer strip into the puncture hole; wherein the insertion tool extends linearly from a first end of a center base of a first bilateral elongated tool member and a cavity encasing extending from a second end of the center base of the first bilateral elongated tool member in an opposite direction configured for housing a plurality of the tri-layer strips; and (f) removing the insertion tool from the puncture hole causing a center portion of the tri-layer strip to fold forming a four-layer seal within the puncture hole.

A method for repairing a part made of composite material includes producing a recessed section by removing the composite material at a damaged area, producing grooves extending on the two faces of the part from edges of the recessed section, producing orifices in the part opening out into the grooves, tree-dimensional weaving of a filling part fiber preforms including a central section having a shape corresponding to the shape of the recessed section and fiber bundles extending from the central section, placing the filling preforms respectively on either face of the part with the fiber bundles in the grooves on the faces of the part and in the orifices such that the fiber bundles open out into the grooves present on the opposite face of the part, impregnating the filling fiber preforms with a precursor resin of a matrix, transforming the resin into a matrix to obtain a filling part.

Systems and methods for actualizing simulated scarfing and patching for repair of composite laminates. A virtual environment is provided that enables engineers to optimize a repair design and provide the most robust repair solution that meets structural requirements, while minimizing the material removal and the impact to the composite structure. An optimization algorithm is configured to adjust contour offsets for pad-up plies and adjust scarf taper ratios in any direction to reduce the amount of material removed or avoid underlying structures. Scarf repair designs are subsequently transmitted to repair technicians for manual scarfing via printed templates or automated/robotic scarfing using converted computer-readable code. The technology also provides digital data for automated repair ply cutting.

Systems and methods for actualizing simulated scarfing and patching for repair of composite laminates. A virtual environment is provided that enables engineers to optimize a repair design and provide the most robust repair solution that meets structural requirements, while minimizing the material removal and the impact to the composite structure. An optimization algorithm is configured to adjust contour offsets for pad-up plies and adjust scarf taper ratios in any direction to reduce the amount of material removed or avoid underlying structures. Scarf repair designs are subsequently transmitted to repair technicians for manual scarfing via printed templates or automated/robotic scarfing using converted computer-readable code. The technology also provides digital data for automated repair ply cutting.

Methods and systems for characterizing holes in a combustor liner of a gas turbine engine, and associated repair methods are provided. One method comprises receiving first measured data of the combustor liner in an uncoated state. The method includes determining a first location and a first orientation of a first hole and a first location and a first orientation of a second hole in the combustor liner using the first measured data. The method includes receiving second measured data of the combustor liner in a coated state where the second hole is at least partially obstructed by a coating and the first hole is substantially unobstructed by the coating. The method includes inferring a second location of the second hole of the combustor liner in the coated state using a known spacing between the first location of the first hole and the first location of the second hole. The characterization of the holes may be used to re-drill the obstructed second hole.

Methods and systems for characterizing holes in a combustor liner of a gas turbine engine, and associated repair methods are provided. One method comprises receiving first measured data of the combustor liner in an uncoated state. The method includes determining a first location and a first orientation of a first hole and a first location and a first orientation of a second hole in the combustor liner using the first measured data. The method includes receiving second measured data of the combustor liner in a coated state where the second hole is at least partially obstructed by a coating and the first hole is substantially unobstructed by the coating. The method includes inferring a second location of the second hole of the combustor liner in the coated state using a known spacing between the first location of the first hole and the first location of the second hole. The characterization of the holes may be used to re-drill the obstructed second hole.

A method of repairing a composite beam having a longitudinal direction including: removing material from a damaged area of the composite beam to form a cut out region; machining a plurality of elongate slots into the composite beam, the elongate slots each having a length in the longitudinal direction of the composite beam and spanning across the damaged area, the elongate slots extending into the composite beam to a depth greater than a depth of the cut out region; introducing a plurality of reinforcing inserts into the respective elongate slots and fixing the reinforcing inserts into the slots with adhesive.

A method of repairing a composite beam having a longitudinal direction including: removing material from a damaged area of the composite beam to form a cut out region; machining a plurality of elongate slots into the composite beam, the elongate slots each having a length in the longitudinal direction of the composite beam and spanning across the damaged area, the elongate slots extending into the composite beam to a depth greater than a depth of the cut out region; introducing a plurality of reinforcing inserts into the respective elongate slots and fixing the reinforcing inserts into the slots with adhesive.

In order to repair any damage to an originally applied paint film, a method of the invention facilitates repair of the paint film by removing essentially only that portion of the paint film that is damaged. After removal of the damaged portion of the paint film, a series of abrading, application, and polishing steps results in a repaired portion of the paint film.

An automated wind turbine servicing system that includes a rover, and uses an active electro-mechanical gripping roller system to attach to a horizontally positioned airfoil and navigate along it in order to clean, inspect, service, or otherwise maintain the wind turbine airfoil. An electromechanical compression system adapts to various turbine airfoil profiles. Once secured to the airfoil, the rover activates a drive system that propels the rover along the airfoil as it travels along an upper edge, using wind pressure, the rover wheels' frictional adherence to the airfoil, and gravity to assist in coupling the rover to the airfoil. The rover, which preferably includes a robotic arm, is able to utilize multiple tools to perform various tasks such as inspecting, cleaning, sanding, repairing, painting and laying leading edge protection tape as well as vortex generators on the surface of the airfoil.