The present disclosure relates to a housing for an engine component. The housing comprises a wall made of a light alloy. An epoxy primer coating having at least one layer of a primer containing at least 80 wt. % epoxy covering the wall. An intumescent paint coating having at least one layer of intumescent paint directly covering the epoxy primer. And, an epoxy top coat directly covering the intumescent paint coating, the epoxy top coat having at least one layer of a top coat containing at least 80 wt. % epoxy.

A device (26) for cooling an annular outer turbine casing (17) includes at least one circumferentially extending tube (27) having an air inlet intended for conveying cooling air, the tube having a radially inner wall provided with cooling air discharge openings and a radially outer wall arranged radially opposite each other, an air inlet manifold (28), the inlet of the tube opening into the manifold, the tube (27) including at least one intermediate wall extending over a circumferential portion of the tube from the air inlet, the intermediate wall being located radially between the radially inner wall and the radially outer wall, the radially inner wall and the intermediate wall forming a first air conveying duct, the radially outer wall and the intermediate wall forming a second air conveying duct extending circumferentially beyond the first air conveying duct, relative to the air inlet.

A turbine rotor wheel for an aircraft turbomachine includes a rotor disk, an annular shroud extending around the disk, and blades arranged between the disk and the shroud. The the root of each of the blades has two tabs configured for attachment to the disk. The tabs are arranged upstream and downstream, respectively, of a wall of the disk, relative to the axis. The tab arranged upstream is engaged in a first recess of the disk and configured to cooperate by abutment with a peripheral edge of the first recess. The tab arranged downstream is engaged in a second recess of the disk and is configured to cooperate by abutment with a peripheral edge of the second recess.

A method for the layer-by-layer additive manufacturing of a composite material having the selective irradiation of a base material to produce a first, dense material phase and to produce a second, porous material phase, wherein the production of the first material phase and the production of the second material phase take place alternately. A correspondingly produced composite material and to a component has the composite material.

Nozzle of a spacecraft engine, comprising a nozzle body extending along a main direction, from a proximal end secured to the engine of the spacecraft, and a free distal end, said nozzle body having a plurality of stiffeners extending from an outer surface of the nozzle body, radially with respect to the main direction, said nozzle comprising a thermal insulation system, comprising at least one strip of insulating material disposed so as to surround the outer surface of the nozzle body over at least part of the height of said nozzle body-, said thermal insulation system comprising a plurality of holding elements, each holding element being positioned so as to surround said strips of insulating material, and being disposed between two stiffeners of the nozzle body.

A method of assessing the quality of a bond coat for bonding a ceramic coating to a metallic substrate comprises determining a thresholded summit area for the bond coat.

A heat shield for a fuel nozzle of a gas turbine engine combustor. The heat shield includes a radial flange extending in radial and circumferential directions and has an opening therethrough at a radially inward end of the radial flange, and an annular conical wall extending in longitudinal and circumferential directions, the annular conical wall being connected to the radial flange at the radially inward end of the radial flange. The radial flange includes a flange forward side, and a flange aft side, and has a flange outer end portion. The flange outer end portion includes a flange rounded end portion on one of the flange forward side or the flange aft side, and a flange rounded protruding lip on the other of the flange forward side or the flange aft side, the rounded protruding lip extending in the longitudinal direction.

A variable geometry turbocharger (100) includes a bearing housing (10) including a bearing-housing side support portion (40) configured to support a radially outer portion (38) of a nozzle mount (16) from a side opposite to a scroll flow passage (4) in an axial direction of a turbine rotor (2), and wherein at least one of the following condition (a) or (b) is satisfied: (a) the bearing-housing side support portion (40) includes at least one bearing-housing side recess portion (46) formed so as to be recessed in the axial direction so as not to be in contact with the radially outer portion (38); (b) the radially outer portion (38) of the nozzle mount (16) includes at least one nozzle-mount side recess portion (62) formed so as to be recessed in the axial direction so as not to be in contact with the bearing-housing side support portion (40).

An assembly including a support panel of an internal fixed structure, a thermal protection element and a plurality of fastening systems. Each fastening system includes a female part secured to the support panel and which has, in its interior, a circular shoulder, and a male part including a sleeve pierced with a main bore, a slide movable in translation in the main bore and a plurality of balls. For each ball, the sleeve has a secondary bore, and each ball is movable along the secondary bore between a locking position and an unlocking position. The slide is movable in translation between a blocking position and an unlocking position. Such an assembly makes it possible to fasten the thermal protection element to the support panel in a simple and rapid manner, also permitting easy removal if necessary.

A hybrid three-layer system is presented. The hybrid three-layer system includes a two-layer composite system and an additively manufactured third layer comprising a lattice structure. The composite layer system includes a metallic substrate, a structured surface, and a thermal protection system. The structured surface may be additively manufactured onto the metallic substrate and includes structured surface features formed to project above the metallic substrate. Each of the structured surface features are separated from adjacent structured surface features by grooves. The thermal protection coating may be thermally sprayed onto the structured surface and is bonded to each of the structured surface features. The lattice structure is in contact with a surface of the metallic substrate of the composite layer system.