A method of remanufacturing a liner panel for a gas turbine engine includes removing a bushing from a damaged component; and molding the bushing with a material charge. A liner panel for a gas turbine engine includes a forward fan exit case liner panel with a donor bushing from a damaged forward fan exit case liner panel. A liner panel for a gas turbine engine includes a forward fan exit case liner panel molded from a material charge that includes a multiple of layers. At least one of the multiple of layer includes a discontinuity.

A method of remanufacturing a liner panel for a gas turbine engine includes removing a bushing from a damaged component; and molding the bushing with a material charge. A liner panel for a gas turbine engine includes a forward fan exit case liner panel with a donor bushing from a damaged forward fan exit case liner panel. A liner panel for a gas turbine engine includes a forward fan exit case liner panel molded from a material charge that includes a multiple of layers. At least one of the multiple of layer includes a discontinuity.

A method of modifying or repairing a fluid conduit assembly includes scanning a sealing feature of a fluid conduit, the sealing feature including an abnormality, creating a 3D model of a sealing member configured to provide a fluid seal with the sealing feature, and utilizing the 3D model to form the sealing member via additive manufacturing. The method may include modifying the sealing feature of the fluid conduit to reduce or remove the abnormality and provide the sealing feature with modified dimensions. Scanning the sealing feature may include determining the modified dimensions of the sealing feature.

In an example, a mandrel for a composite part includes an upper-mandrel portion, a lower-mandrel portion, and a mid-mandrel portion between the upper-mandrel portion and the lower-mandrel portion. The mandrel also includes a cavity and an exterior surface defined by the upper-mandrel portion, the lower-mandrel portion, and the mid-mandrel portion. An actuator is movable in the cavity between a first position and a second position. The exterior surface can support the composite part. A perimeter of the exterior surface has a first length when the actuator is in the first position and the perimeter has a second length when the actuator is in the second position. The first length is greater than the second length such that the mandrel is in an expanded state when the actuator is in the first position and the mandrel is in a contracted state when the actuator is in the second position.

In an example, a mandrel for a composite part includes an upper-mandrel portion, a lower-mandrel portion, and a mid-mandrel portion between the upper-mandrel portion and the lower-mandrel portion. The mandrel also includes a cavity and an exterior surface defined by the upper-mandrel portion, the lower-mandrel portion, and the mid-mandrel portion. An actuator is movable in the cavity between a first position and a second position. The exterior surface can support the composite part. A perimeter of the exterior surface has a first length when the actuator is in the first position and the perimeter has a second length when the actuator is in the second position. The first length is greater than the second length such that the mandrel is in an expanded state when the actuator is in the first position and the mandrel is in a contracted state when the actuator is in the second position.

The present disclosure provides repair systems, repair components, and methods for repairing composite structure systems using a set number of prefabricated repair components including a repair component and various shims which are fabricated to repair multiple composite members in a composite structure system.

The present disclosure provides repair systems, repair components, and methods for repairing composite structure systems. The repair systems include using a set number of prefabricated repair components which are fabricated to repair multiple composite members in a composite structure system.

A repair for a structural element made from a composite material includes a bracket defining a first surface and a second surface. The first surface is adapted for facing the structural element. A chamfer is located on a first end of the bracket. An angle is defined between a plane of the chamfer and a plane of the first surface, the first surface of the bracket being adapted to be disposed adjacent to a side of the structural element. The repair also includes a sealant material between the bracket and the structural element, where the sealant material occupies a space established between the chamfer and the structural element.

A repairing method for a repaired composite material and a composite material using this method, which are capable of readily repairing, in a short time, a gap due to delamination generated between layers of completely hardened composite material. In the repairing method for composite material, a hole (4) is formed through the delamination (3) generated between layers (1a, 1b) of hardened composite material, and a joining member (6) is inserted into the hole (4) so as to join the delamination (3) generated between the layers (1a, 1b) of the hardened composite material.

A repairing method for a repaired composite material and a composite material using this method, which are capable of readily repairing, in a short time, a gap due to delamination generated between layers of completely hardened composite material. In the repairing method for composite material, a hole (4) is formed through the delamination (3) generated between layers (1a, 1b) of hardened composite material, and a joining member (6) is inserted into the hole (4) so as to join the delamination (3) generated between the layers (1a, 1b) of the hardened composite material.