A method of manufacturing an assembly including a first structure which is arranged to be rigidly connected to a housing of a turbojet engine; a second annular structure surrounding the first structure; and a hyperstatic trellis of connecting rods which maintains the first structure relative to the second structure, is provided. The method includes mounting the connecting rods of the hyperstatic trellis between the structures; and pre-stressing at least one of the connecting rods to a pre-determined level, which is carried out before the mounting thereof between the structures.

The present invention provides an apparatus for providing a balancing weight in a groove on a rotor disk in a gas turbine engine. The apparatus comprises an elongate reservoir for housing a hardenable material and an inflatable balloon in fluid communication with the distal end of the elongate reservoir. An actuator is provided for forcing the hardenable material from the elongate reservoir to inflate the inflatable balloon with hardenable material within the groove on the rotor disk. A sealing device for sealing the inflated inflatable element to form the balancing weight is also provided.

The present invention relates to a turbomachine element (1), comprising at least one blade (2) obtained by additive manufacturing, the blade (2) having a skin (4) and an internal lattice (6) allowing air circulation in the blade (2) and having an additive manufacturing support function for the skin (4).

The invention relates to an element (1) for compensation of tolerances and/or gap widths of a device, having a main body (2) which has at least one annular cross-sectional portion (3), wherein the cross-sectional portion (3) has, in its peripheral direction (4), at least one auxetic portion (5) which exhibits auxetic behavior in a radial direction (6) of the main body (2). The invention also relates to an engine (20) which comprises the element (1), to an assembly method for a shaft/hub connection (19) which has at least one element (1), and to an adaptation method for adapting a tolerance and/or a gap width in the engine (20).

An auxetic (NPR) structure includes a plurality of vertical intersecting dimpled sheets, each dimpled sheet exhibiting a negative Poisson's ratio, each dimpled sheet intersects two adjacent dimpled sheets creating a rectangular tubular structure, and having a portion of each dimpled sheet projecting outward from its intersection with an adjacent dimpled sheet, the amplitude of each dimple on the plurality of dimpled sheets is such that no overhanging surface of the dimpled sheet exceeds an angle threshold for printability without support structures.

A vane of a low pressure compressor of an axial turbine engine. The vane can be connected to the rotor or to the stator. The vane includes an airfoil forming a body in composite material with an organic matrix, and a reinforcing frame. This frame displays a base of a vane intended to be welded to the compressor drum, an upstream portion extending from the base and forming the leading edge of the vane, and a stiffener. The stiffener is situated at a central position of the base and remains enveloped in the airfoil of the vane. In the core, it forms a strip with orifices. The frame also has a cut-out separating the upstream portion from the stiffener, the upstream portion extending from the base along the height of the stiffener. This architecture reduces the mass of the frame, while preserving the general stiffness.

A gas turbine engine component includes a substrate having first surface and a second surface disposed opposite the first surface, a plurality of holes extending through the substrate from the first surface to the second surface, the holes defined by a plurality of respective walls each extending from the first surface to the second surface, a metallic bond coat disposed on the first surface, and an aluminide coating disposed on the first surface, the second surface, and the walls. The metallic bond coat is disposed between the first surface and the aluminide coating and the walls are free of the metallic bond coat.

A gas turbine engine component includes a substrate having first surface and a second surface disposed opposite the first surface, a plurality of holes extending through the substrate from the first surface to the second surface, the holes defined by a plurality of respective walls each extending from the first surface to the second surface, a metallic bond coat disposed on the first surface, and an aluminide coating disposed on the first surface, the second surface, and the walls. The metallic bond coat is disposed between the first surface and the aluminide coating and the walls are free of the metallic bond coat.

A rotor blade for a gas turbine engine is provided. The rotor blade includes a blade body formed of a first material; and a spar within a portion of the blade body, the spar formed of a second material that is different than the first material, the spar having an elongate body including a notch. The notch, weakened geometric feature, or other reduction in cross-section defines a frangible portion of the spar that is used to control a fracture of a rotor blade.