Multi-walled structure for a gas turbine engine

An assembly for a gas turbine engine, comprising:

• a wall comprising a shell, a heat shield and a cooling cavity;
• the heat shield including a first panel and a second panel;
• the first panel extending longitudinally between a first panel first end and a first panel second end, and the first panel including a first panel base and a first panel rail;
• the second panel extending longitudinally between a second panel first end and a second panel second end, the second panel at the second panel first end arranged between and spaced from the shell and the first panel at the first panel second end, the second panel including a second panel base and a second panel rail, and the second panel base comprising an uninterrupted surface that extends longitudinally from the second panel rail to the second panel first end;
• the cooling cavity longitudinally bounded by the first panel rail and the second panel rail;
• and
• the shell comprising a first aperture configured to direct a first jet of cooling fluid at a surface of the first panel base longitudinally between the first panel rail and the first panel second end, and a centerline axis of the first aperture angularly offset from an interior surface of the shell by a first acute angle.