Abstract:
The present disclosure provides a nozzle for an aircraft turboprop engine with an unducted fan, including: an inner wall, an outer wall radially spaced apart from the inner wall and concentric with the inner wall, a junction area of the inner and outer walls including an opening contained in a plane transverse to a longitudinal axis of the nozzle. In particular, the junction area of the inner and outer walls includes two connecting plates and a member to secure the two connecting plates together, or in another form, the junction area includes a pad secured to the inner wall, and a pad secured to the outer wall, facing the pad of the inner wall of the nozzle.
Abstract:
A setup for assembling, by brazing, a composite panel including at least two parts separated by a filler material and joined together by brazing. The setup includes a furnace to achieve a brazing temperature for brazing the panel, and an assembly device which has a form having a shape similar to the final shape of the panel to be brazed. In particular, the assembly device further includes a pressing device to apply mechanical pressure to at least part of the surface of the panel in a direction allowing the panel to be permanently deformed into a shape which matches that of the form. The pressing device is moved under the action of a spring, and the forces applied by the spring being determined so that, at the brazing temperature, the spring applies the force necessary for deforming the panel against the form.