Apparatus and methods for manufacturing and repairing fibre-reinforced composite materials are disclosed. In various embodiments, the apparatus and methods disclosed herein use a resin retaining/releasing device comprising resin having a viscosity that is temperature dependent for infusion into a region of a part. The resin retaining/releasing device may include a first sheet and an opposite second sheet at least partially enclosing the quantity of resin. The first sheet and the second sheet may be gas-permeable. The second sheet may be substantially resin-impermeable when the viscosity of the resin is above a threshold viscosity and resin-permeable when the viscosity of the resin is below the threshold viscosity.

A method of correcting, in a composite component, an inappropriate countersink with an inappropriate maximum diameter and/or depth, the inappropriate countersink being provided in the composite component at a fixation opening having a first opening diameter, the method comprising at least the steps of: Preparing a repair patch; Arranging the repair patch on the composite component in an area surrounding the inappropriate countersink; Pressing the repair patch at least partly into the inappropriate countersink by means of an associated pressure tool; and Fixing the repair patch in the inappropriate countersink.

A method of correcting, in a composite component, an inappropriate countersink with an inappropriate maximum diameter and/or depth, the inappropriate countersink being provided in the composite component at a fixation opening having a first opening diameter, the method comprising at least the steps of: Preparing a repair patch; Arranging the repair patch on the composite component in an area surrounding the inappropriate countersink; Pressing the repair patch at least partly into the inappropriate countersink by means of an associated pressure tool; and Fixing the repair patch in the inappropriate countersink.

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.

The invention relates especially to a self-adhesive film 1 for fixing an elastomer patch 10 during a vulcanization of an elastomer component. The elastomer component can in particular be a motor vehicle tire 40 or a cavity lining 120. The film 1 can comprise a supporting layer 2 and an adhesive layer 3. The adhesive layer 2 can have a predetermined manufacturing adhesiveness at room temperature and ambient pressure and a predetermined peel strength at a vulcanization pressure and a vulcanization temperature.

The invention relates especially to a self-adhesive film 1 for fixing an elastomer patch 10 during a vulcanization of an elastomer component. The elastomer component can in particular be a motor vehicle tire 40 or a cavity lining 120. The film 1 can comprise a supporting layer 2 and an adhesive layer 3. The adhesive layer 2 can have a predetermined manufacturing adhesiveness at room temperature and ambient pressure and a predetermined peel strength at a vulcanization pressure and a vulcanization temperature.

A method for repairing a damaged aircraft fuselage outer skin part, the damaged skin part comprising a static pressure port around which is arranged a stopper fastened to a structure of the fuselage at which a pipe of the static pressure port opens, the method including removing the stopper from the static port, fitting a patch including an opening for housing the stopper, and re-fitting the stopper on an adjustable-thickness spacer. A repair assembly configured to apply the repair method is also provided. Advantageously, it is thus possible to recreate an aerodynamic profile in accordance with the requirements for taking static pressure of the aircraft, with a reduced down-time of the aircraft.

A method for repairing a damaged aircraft fuselage outer skin part, the damaged skin part comprising a static pressure port around which is arranged a stopper fastened to a structure of the fuselage at which a pipe of the static pressure port opens, the method including removing the stopper from the static port, fitting a patch including an opening for housing the stopper, and re-fitting the stopper on an adjustable-thickness spacer. A repair assembly configured to apply the repair method is also provided. Advantageously, it is thus possible to recreate an aerodynamic profile in accordance with the requirements for taking static pressure of the aircraft, with a reduced down-time of the aircraft.

Aspects of the present disclosure are directed to a doped composite rework material including a fiber-containing material, a resin-containing material, and a dopant, with the dopant configured to impart an identifying characteristic to the doped composite rework material; and methods for precluding rework of a previously reworked composite material.

Aspects of the present disclosure are directed to a doped composite rework material including a fiber-containing material, a resin-containing material, and a dopant, with the dopant configured to impart an identifying characteristic to the doped composite rework material; and methods for precluding rework of a previously reworked composite material.