A method for repairing a part made of composite material includes producing a recessed section by removing the composite material at a damaged area, producing grooves extending on the two faces of the part from edges of the recessed section, producing orifices in the part opening out into the grooves, tree-dimensional weaving of a filling part fiber preforms including a central section having a shape corresponding to the shape of the recessed section and fiber bundles extending from the central section, placing the filling preforms respectively on either face of the part with the fiber bundles in the grooves on the faces of the part and in the orifices such that the fiber bundles open out into the grooves present on the opposite face of the part, impregnating the filling fiber preforms with a precursor resin of a matrix, transforming the resin into a matrix to obtain a filling part.

A rotor shroud for a rotary machine in a cabin air compressor includes a disk portion centered on a central axis of the rotor shroud, a frustoconical portion extending from the disk portion, a flared portion extending from the frustoconical portion, and a variable lattice structure in an interior of the rotor shroud. The variable lattice structure includes a first region of the rotor shroud having a first lattice structure and a second region of the rotor shroud having a second lattice structure. The second lattice structure of the second region is denser than the first lattice structure of the first region. The second region is a deflection region, a stress region, or an energy containment region of the rotor shroud.

A gas passage for a gas turbine engine, which allows for quicker and easier determination of the condition of a liner within the gas passage without the need for dismantling the entire gas passage, or irreparably damaging large sections of the liner. The gas passage comprises a casing with one or more plugs which are at least partly coated in a material matching the material composition of the lining, which can be removed from the gas passage in order to analyse the condition of the lining material.

A gear reduction reduces a speed of a fan rotor relative to a speed of a fan drive turbine. A fan case surrounds the fan rotor. A core engine has a compressor section and includes a low pressure compressor. The fan rotor delivers air into a bypass duct defined between the fan case and the core engine. A rigid connection between the fan case and the core engine includes a plurality of aft connecting members rigidly connected to the fan case, and to the core engine. A plurality of fan exit guide vanes are rigidly connected to the fan case, with the fan exit guide vanes including structural fan exit guide vanes which are rigidly connected to the core engine, and non-structural fan exit guide vanes, and the non-structural fan exit guide vanes being provided with an acoustic feature to reduce noise.

A steam turbine includes a rotor, a casing, a partition plate, and a center guide pin. The center guide pin has a positioning portion. In a state of being attached to a pin attachment portion formed in one of the casing and the partition plate, the positioning portion is disposed in a groove portion formed in the other of the casing and the partition plate. The positioning portion includes a plurality of abutment portions capable of abutting on an inner side surface of the groove portion, around a pin axis. The plurality of abutment portions is formed to have different horizontal distances from the pin axis.

A hanger for a turbine engine can include a first surface confronting a cooling airflow, a second surface facing a heated airflow, and a third surface radially outward of the first surface. The hanger can also include a cyclonic separator with a dirty air inlet and a clean air outlet, as well as a cooling air circuit extending through the cyclonic separator.

An engine housing of a gas turbine engine includes a plurality of leg members. An air intake space is formed between the plurality of leg members. A shroud case supported by the engine housing is disposed in the air intake space. A rotary electric machine housing of a rotary electric machine system includes a rectifying member. The rectifying member includes a distal end facing toward the shroud case, and the distal end is inserted inside the shroud case.

Aspects of the disclosure regard a fan case assembly for a gas turbine engine, the fan case assembly comprising a fan case having an inner surface and an outer surface, a front acoustic panel having an outer surface, and attachment means attaching the front acoustic panel outer surface to the fan case inner surface. The attachment means comprise a sliding arrangement allowing the front acoustic panel to be slid axially into the fan case. The sliding arrangement comprises a first longitudinal member and a second longitudinal member, one of the members being attached to the fan case inner surface and the other member being attached to the front acoustic panel outer surface. The attachment means further comprise removable fastening means fixing the first longitudinal member and the second longitudinal member in the axial direction.

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 for manufacturing a metal component includes the following steps: a shell made of a titanium-based material is provided, the shell having a first surface and a second surface remote from the first surface; a covering layer made of a titanium fire-resistant material is produced by additive manufacturing on the shell such that the covering layer at least partially covers the first surface and/or the second surface; and, after the additive manufacturing step, the metal component is heat treated at a temperature of between 200° C. and 1000° C.