A method refurbishes structured surfaces of a component having a damaged subregion with material detachment. The method comprising: determining a reference region having a similar surface structure as the subregion; while pressing a die material onto the reference region: curing the die material to form a transparent die which is separable from the reference region without leaving residues and has a negative shape of the surface structure of the reference region; filling the damage location with electromagnetic irradiation curable material; placing the die onto the curable material in the damage location with an alignment of the negative shape of the transparent die corresponding to a desired surface structure at the damage location; while the die is being pressed onto the damage location: irradiating the curable material with electromagnetic irradiation through the transparent die until the material is cured; and removing the die from the cured material without leaving residues.

A UV-cured exothermic self-adhesive repair sheet having two components that may be combined in equal sizes. The first component comprises Polyester Resin (25-40%), Glass Fiber (15-25%), Styrene Monomer (<20%) and Inorganic Filler (25-40%). The second component comprises Acrylic Adhesive (75-95%) and Non-Woven Fabric (5-25%).

A method of repairing a composite blade. The composite blade includes a metal work bonded to a composite part through an adhesive layer. The method includes determining a locally damaged portion of the metal work, and removing a bullet portion corresponding to the locally damaged portion. The method further includes detaching, debonding, and removing a first wing portion from the composite part to obtain a first exposed surface portion. The method further includes detaching, debonding, and removing a second wing portion from the composite part to obtain a second exposed surface portion. The method further includes reconditioning the first and second exposed surface portions to obtain first and second reconditioned surface portions, respectively, and applying first and second adhesive layers to the first and second reconditioned surface portions respectively. The method further includes bonding a metal work patch to the first and second adhesive layers.

A method of repairing a composite blade. The composite blade includes a metal work bonded to a composite part through an adhesive layer. The method includes determining a locally damaged portion of the metal work, and removing a bullet portion corresponding to the locally damaged portion. The method further includes detaching, debonding, and removing a first wing portion from the composite part to obtain a first exposed surface portion. The method further includes detaching, debonding, and removing a second wing portion from the composite part to obtain a second exposed surface portion. The method further includes reconditioning the first and second exposed surface portions to obtain first and second reconditioned surface portions, respectively, and applying first and second adhesive layers to the first and second reconditioned surface portions respectively. The method further includes bonding a metal work patch to the first and second adhesive layers.

A heat blanket system including a blanket including a first sub-area and a second sub-area. The heat blanket system also includes heating elements printed on the blanket. First spacings between first ones of the heating elements in the first sub-area varies relative to second spacings between second ones of the heating elements in the second sub-area. The first spacings and the second spacings vary according to a design. The design is configured for use on a uniquely defined rework area on a uniquely defined composite material object including a third area including a heat sink region and a fourth area including a non-heat sink region. The first sub-area is sized and dimensioned to be placed over the third area. The second sub-area is sized and dimensioned to be placed over the fourth area.

A heat blanket system including a blanket including a first sub-area and a second sub-area. The heat blanket system also includes heating elements printed on the blanket. First spacings between first ones of the heating elements in the first sub-area varies relative to second spacings between second ones of the heating elements in the second sub-area. The first spacings and the second spacings vary according to a design. The design is configured for use on a uniquely defined rework area on a uniquely defined composite material object including a third area including a heat sink region and a fourth area including a non-heat sink region. The first sub-area is sized and dimensioned to be placed over the third area. The second sub-area is sized and dimensioned to be placed over the fourth area.

Described are methods and systems for repair of composite components without the use of vacuum bagging. The systems described herein include a composite repair structure with a repair laminate and a film sealant. The film sealant covers the repair laminate to prevent intrusion of air and other volatiles during bonding of the composite repair structure to the composite being repaired. As the film sealant prevents intrusion of air and other volatiles, the composite repair structure can be bonded to the structure to be repaired without the use of a vacuum bag. Thus, vehicle components can be repaired without disassembly from the vehicle.

The present invention relates to a method for repairing a damaged thermal protection covering a nacelle structure for an aircraft turbojet engine by adding a repair thermal insulation blanket as well as a repair sheet onto the damaged part.

The present invention relates to a method for repairing a damaged thermal protection covering a nacelle structure for an aircraft turbojet engine by adding a repair thermal insulation blanket as well as a repair sheet onto the damaged part.

A coke plant includes multiple coke ovens where each coke oven is adapted to produce exhaust gases, a common tunnel fluidly connected to the plurality of coke ovens and configured to receive the exhaust gases from each of the coke ovens, multiple standard heat recovery steam generators fluidly connected to the common tunnel where the ratio of coke ovens to standard heat recovery steam generators is at least 20:1, and a redundant heat recovery steam generator fluidly connected to the common tunnel where any one of the plurality of standard heat recovery steam generators and the redundant heat recovery steam generator is adapted to receive the exhaust gases from the plurality of ovens and extract heat from the exhaust gases and where the standard heat recovery steam generators and the redundant heat recovery steam generator are all connected in parallel with each other.