A manufacturing method is provided. During this method, a preform component is provided for a turbine engine. The preform component includes a substrate. A meter section of a cooling aperture is formed in the substrate. An internal coating is applied onto a surface of the meter section. An external coating is applied over the substrate. A diffuser section of the cooling aperture is formed in the external coating and the substrate to provide the cooling aperture.

A rotor for a turbomachine includes a disc and a plurality of blades fixed to the disc. Each blade of the plurality of blades is fixed to the disc via a lattice structure configured so that a tensile force applied to the lattice structure induces a change in the angle of incidence of the blade. The blades and the lattice structures are configured so that: (i) when the rotor is stationary, the distribution of the angles of incidence of the blades around the disc is aperiodic, and (ii) when the rotor is rotating at a predetermined rotational speed, the angles of incidence of the blades are identical.

A rocket engine section includes a combustion chamber body having an inner wall and a channel carrying a cooling medium extending outside and along the inner wall. The rocket engine section further comprises a porous portion integrally formed with the inner wall and integral with the inner wall and adapted to allow the cooling medium carried in the channel to pass from the channel to the interior of the combustion chamber body. A porosity of the porous portion determines a volume flow rate and/or mass flow rate of the cooling medium let through into the interior of the combustion chamber body.

A field configurable autonomous vehicle includes modular elements and attachable components. The vehicle can be assembled from these modular elements and components to meet desired mission and performance characteristics without the need to purchase specially designed vehicles for each mission. The vehicle can include a modular propulsion system with magnetic drive.

Sacrificial inserts for use in gas turbine engines to reduce friction and wear damage between compressor fan blades and the fan rotors are disclosed. The consumable metallic shims have low friction and reduce fretting and galling on fan blade roots and fan rotor dovetail slots thereby increasing their operating lives, as well as reduce engine noise and improve engine efficiency. The electroformed, compliant, multi-purpose shims may have variable thickness and, when positioned between the blade dovetail root and the rotor disk dovetail slot, prevent movement and slippage between air foil blades and the rotor.

The invention relates to a method for producing a part by means of a laser beam, with a nozzle (1) that sprays a metal powder towards a substrate (5). Initially, the trajectory of the nozzle is defined in a pre-determined manner, and then, during the production of the part (7): a theoretical reference distance D0 that has been previously recorded and a real distance which is then measured are compared, and
the trajectory of the nozzle is modified on the basis of a deviation threshold between said distances.

A method of sealing one or more openings provided in a wall of an aerofoil for a gas turbine engine, the aerofoil comprising at least one cavity which is at least partly filled with a vibration damping material, the method comprising steps to provide a metallic material onto the wall of the aerofoil in order to cover the opening and bond the metallic material to the wall of the aerofoil to seal the opening.

An impeller for a rotary machine includes: a base material of the impeller comprising Al or an Al alloy; a surface layer for the impeller formed by an electroless plating layer comprising a Ni—P based alloy; and an under layer disposed between the base material and the surface layer, the under layer having a smaller Vickers hardness than the surface layer.

Ceramic matrix composite articles include, for example a first plurality of plies of ceramic fibers in a ceramic matrix defining a first extent, and a local at least one second ply in said ceramic matrix defining a second extent on and/or in said first plurality of plies with the second extent being less than said first extent. The first plurality of plies has a first property, the at least one second ply has at least one second property, and said first property being different from said at least one second property. The different properties may include one or more different mechanical (stress/strain) properties, one or more different thermal conductivity properties, one or more different electrical conductivity properties, one or more different other properties, and combinations thereof.

The present disclosure generally relates to methods for additive manufacturing (AM) for fabricating multi-walled structures. A multi-walled structure includes a first wall having a first surface and a second wall having a second surface facing the first surface to define a passage having a width between the first surface and the second surface in a first direction. The multi-walled structure also includes an enlarged powder removal feature connecting the first wall and the second wall. The enlarged powder removal feature has an inner dimension greater than the width in the first direction and at least one open end in a direction transverse to the first width.