Multi-walled structure for a gas turbine engine

An assembly for a gas turbine engine, comprising:

• a combustor wall comprising a shell, a heat shield and a cooling cavity;
• the shell comprising a shell surface having one or more apertures;
• the heat shield including a first panel and a second panel;
• the first panel extending longitudinally a first longitudinal length between a first panel first end and a first panel second end, the first panel including a first panel base and a first panel rail that projects out from the first panel base and engages the shell surface, the first panel first end is spaced a first panel longitudinal first distance from the first panel rail, the first panel second end is spaced a first panel longitudinal second distance from the first panel rail, the first panel longitudinal first distance is greater than the first panel longitudinal second distance, and the first panel base extends straight and linearly from the first panel first end to the first panel second end;
• the second panel extending longitudinally a second longitudinal length between a second panel first end and a second panel second end, the second panel including a second panel base and a second panel rail that projects out from the second panel base and engages the shell surface, and the second panel base extends straight and linearly from the second panel first end to the second panel second end;
• and
• the cooling cavity extending within the combustor wall from the shell surface to the first panel and the second panel;
• wherein at least one of the one or more apertures is configured to direct a jet of cooling fluid between the shell surface and the second panel first end and within a portion of the cooling cavity between the shell surface and the second panel first end;
• wherein the second panel first end projects longitudinally into a vertical gap formed between the shell surface and the first panel second end;
• wherein at least a portion of the shell surface completely longitudinally overlaps the first panel along an entirety of the first longitudinal length and the second panel along an entirety of the second longitudinal length, and at least the portion of the shell surface has a straight, linear sectional geometry;
• wherein the second panel rail is spaced a second panel longitudinal first distance from the second panel first end;
• wherein the second panel rail is spaced a second panel longitudinal second distance from the second panel second end;
• and
• wherein the second panel longitudinal first distance is greater than the second panel longitudinal second distance.

An assembly for a gas turbine engine, comprising:

• a wall comprising a shell, a heat shield, a first cooling cavity and a second cooling cavity;
• the heat shield including a first panel, a second panel and a third 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 first panel first end is spaced a first panel longitudinal first distance from the first panel rail, the first panel second end is spaced a first panel longitudinal second distance from the first panel rail;
• the second panel extending longitudinally between a second panel first end and a second panel second end, the second panel first end arranged between the shell and the first panel second end, such that
• the second panel first end is spaced from the shell in a radial direction to form a first air gap,
• the second panel first end is spaced from the first panel second end in the radial direction to form a second air gap, and
• the second panel first end is spaced from the first panel rail of the first panel in an axial direction,
• the second panel including a second panel base and a second panel rail;
• the second panel base comprising and extending between a second panel uninterrupted interior surface and a second panel uninterrupted exterior surface, the second panel uninterrupted interior surface extending longitudinally from the second panel rail to the second panel first end, and the second panel uninterrupted exterior surface extending longitudinally from the second panel first end to the second panel second end;
• the first cooling cavity longitudinally bounded by the first panel rail and the second panel rail;
• the first cooling cavity continuously extending from the first air gap to the second air gap, and the second air gap forming a first cooling cavity outlet;
• the third panel extending longitudinally between a third panel first end and a third panel second end, the third panel first end arranged between and spaced from the shell and the second panel second end, the third panel including a third panel base and a third panel rail;
• the third panel base comprising and extending between a third panel uninterrupted interior surface and a third panel uninterrupted exterior surface, the third panel uninterrupted interior surface extending longitudinally from the third panel rail to the third panel first end, and the third panel uninterrupted exterior surface extending longitudinally from the third panel first end to the third panel second end;
• the second cooling cavity longitudinally bounded by the second panel rail and the third panel rail.