A manufacturing method of an abradable coating consisting of depositing, on a substrate surface a filament of a thermosetting material while providing both a relative displacement between the substrate and the filament along a predetermined deposition path and solidification of the filament in order to create a three-dimensional scaffold of filaments, consisting of superimposed layers of which the filaments of a given layer are not contiguous and can be oriented differently from those of an adjacent layer, so as to confer upon it acoustic wave absorption properties, the thermosetting material being a thixotropic mixture free of solvent and consisting of a polymer base and a cross-linking agent in a weight ratio of a polymer base to a cross-linking agent comprised between 1:1 and 2:1, and of a flowing component, typically a petroleum jelly present between 5 and 15% by weight of the total weight of the thixotropic mixture.

An assembly for forming a gas turbine engine according to an example of the present disclosure includes, among other things, a layup tool including a main body extending along a longitudinal axis and a flange extending radially from the main body, the flange defining an edge face slopes towards the main body to an axial face. At least one compression tool has a tool body having a first tool section and a second tool section extending transversely from the first tool section. The first tool section is translatable along a retention member in a first direction substantially perpendicular to the edge face such that relative movement causes the second tool section to apply a first compressive force on a composite article trapped between the axial face of the flange and the second tool section. A method of forming a gas turbine engine component is also disclosed.

Compaction systems and methods of compacting components are provided. In one aspect, a laminate of a component can be laid up on a tool of a compaction system. The laminate defines a cavity. A noodle is positioned relative to or in the cavity. A noodle ring is then positioned relative to the noodle. For instance, the noodle ring can be placed over the noodle. A cross section of the noodle ring can be shaped complementary to a cross section of the noodle. A plunger of the compaction system is moved so that it engages the noodle ring. Particularly, the plunger is moved in such a way that a force is applied on the noodle ring so that the noodle ring compacts the noodle into the cavity.

A mold for manufacturing a turbomachine fan casing made of composite material, includes a main axis mandrel around which a fibrous preform of a fan casing is intended to be wound; a plurality of counter-mold angular sectors assembled on the outer contour of the mandrel which are intended to close the mold and to compact the fibrous preform wound on the mandrel; wherein a flat seal with a main elongation axis directed along the main axis is arranged between each angular sector, the flat seal being compressed between two adjacent angular sectors, a first angular sector including a sealing portion passing below a lower face of the flat seal while a second angular sector including a sealing portion passing above an upper face of the flat seal.

A method may comprise: laying up a first plurality of plies of material comprising thermoplastic resin and fiber to form an inner skin preform, the inner skin preform being a continuous sheet including alternating peaks and valleys; laying up a second plurality of plies of material comprising thermoplastic resin and fiber to form an outer skin preform; and joining the inner skin preform to the outer skin preform.

An assembly for forming a gas turbine engine according to an example of the present disclosure includes, among other things, a layup tool including a main body extending along a longitudinal axis and a flange extending radially from the main body, the flange defining an edge face slopes towards the main body to an axial face. At least one compression tool has a tool body having a first tool section and a second tool section extending transversely from the first tool section. The first tool section is translatable along a retention member in a first direction substantially perpendicular to the edge face such that relative movement causes the second tool section to apply a first compressive force on a composite article trapped between the axial face of the flange and the second tool section. A method of forming a gas turbine engine component is also disclosed.

A tooling assembly for mounting a plurality of components, such as compressor blades, in a powder bed additive manufacturing machine to facilitate a repair process is provided. The tooling assembly includes component fixtures configured for receiving each of the compressor blades, a mounting plate for receiving the component fixtures, and a magnet assembly operably coupling the component fixtures to the mounting plate in a desired position and orientation to facilitate an improved printing process.

An insert (105) for a wind turbine blade root. The insert (105) has a bushing (40) and an outer surface with circumferential annular grooves (68). A transition layer (102) is built up around the bushing (40). The transition layer (102) has fibrous material sheet layers and filamentary material windings (80) in the grooves which alternate with fibrous plies (98) covering the grooves (68). Each fibrous ply (98) is anchored into the grooves (68) by the windings (80). Fibrous battens (148) are fitted around the transition layer (102) to form an insert body (108). Each batten (148) has a deltoid cross-section so that the battens give the insert a quadrilateral or trapezoidal cross-section.

A method of debonding a first layer from a second layer, wherein the first layer is bonded to the second layer by an adhesive located between the first and second layers. The method includes inserting a blade of a cleaving tool between the first and second layers, and exerting a controlled force on the cleaving tool to move the cleaving tool so as to de-bond the first and second layers in a region. The force exerted is controlled to match a de-bonding force calculated for the region, and such that the movement of the cleaving tool stops when the calculated force is less than a force required to move the cleaving tool, and continues when the calculated force is higher than or equal to the force required to move the cleaving tool.

An injection mold for the manufacture of an axisymmetric part of composite material including a mandrel supporting a fibrous preform and including an annular wall, and a plurality of counter-mold angular sectors assembled on the mandrel and intended to close the mold and to compact the fibrous preform wound on the mandrel. Each angular sector includes an annular base intended to come into contact with the fibrous preform. The annular base extends between the first and second lateral edges in a circumferential direction, the first lateral edge of the annular base of an angular sector being in contact with a second lateral edge of the annular base of an adjacent angular sector.