This invention relates to a multi-part kit system to repair damaged products used in industrial applications, comprising a part A which comprises A1) MDI prepolymer, A2) fumed silica and A3) plasticizer; a part B which comprises B1) hydroquinone di-(2-hydroxyethyl)ether and B2) plasticizer; and a part C which comprises C1) polyol, C2) optionally catalyst and C3) optionally plasticizer.

A method of repairing a through-hole formed in a structure having at least one composite material includes filling at least a portion of the through-hole with a potting compound, inserting a portion of a cartridge heater into the through-hole, and curing the potting compound with the cartridge heater.

A method of repairing a through-hole formed in a structure having at least one composite material includes filling at least a portion of the through-hole with a potting compound, inserting a portion of a cartridge heater into the through-hole, and curing the potting compound with the cartridge heater.

The present invention provides a composition as well as a method for repairing deep scratches, gouges, etc. and which is particularly useful for aircraft and aerospace transparency repair. The composition is a blend of a polishable two-part, solvent-free, polyurethane coating composition for repairing the transparencies and which, after application, cures to a thermoset polyurethane. An optical grid is emplaced over the area to be repaired prior to applying the blend.

The present invention provides a composition as well as a method for repairing deep scratches, gouges, etc. and which is particularly useful for aircraft and aerospace transparency repair. The composition is a blend of a polishable two-part, solvent-free, polyurethane coating composition for repairing the transparencies and which, after application, cures to a thermoset polyurethane. An optical grid is emplaced over the area to be repaired prior to applying the blend.

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.

Provided herein is a method to reinforce a junction of fiber-composite aircraft components forming an elongate conduit. The method comprises (a) abrading the junction and (b) applying sealant along the junction from a tool moveable through the conduit, the tool exerting force on an interior surface of the conduit opposite the junction.

A conditioning agent (typically for use in repairing a flaw in a glazing panel) is contained in a sealed container which is itself disposed internally of a flexible outer walled container. Pressure applied to the outer flexible walled container can cause release of the conditioning agent from the internal conditioning agent container. The conditioning agent preparation may comprise a hygroscopic solvent (such as acetone) combined with one or more primer additives to prime the surface of the glazing panel for repair.

A method of redefining an opening in a composite component comprises filling the opening with a filling material, where the opening is defined in a body of the composite component and opens onto a surface defined by the composite component, and redefining the opening such that the opening extends into the body. Some methods comprise removing an existing coating from the surface of the composite component prior to filling the opening with the filling material and applying a new coating to the surface prior to redefining the opening such that the opening extends through the new coating and into the body. An exemplary composite component comprises a body, a surface with a coating thereon, an original opening defined through the body and filled with a filling material, and a new opening defined through the coating into the body, which may be defined at a new location from the original opening.

A method of repairing a core stiffened structure, including removing a damaged portion of the core stiffened structure; bonding a shelf onto a first core member; bonding a second core member to a shelf; and securing a skin patch over the second core member.