Film cooled multi-walled structure with one or more indentations

1. An assembly for a turbine engine, the assembly comprising:

a shell and a heat shield with a cooling cavity between the shell and the heat shield,

the heat shield defining a plurality of cooling apertures and an indentation in a side of the heat shield opposite the cooling cavity,

wherein the plurality of cooling apertures are fluidly coupled with the cooling cavity,

wherein the indentation is configured such that cooling air directed out of the cooling cavity from a first of the plurality of cooling apertures at least partially circulates against the side of the heat shield, and

wherein the heat shield comprises a surface that defines the indentation with a circular peripheral geometry.

2. The assembly of claim 1 , wherein

the plurality of cooling apertures in the heat shield are effusion apertures; and

the shell defines a plurality of impingement apertures that are fluidly coupled with the effusion apertures by the cooling cavity.

3. The assembly of claim 1 , wherein the heat shield includes a first surface and a second surface with the first surface defining an outlet of the first of the plurality of cooling apertures and the second surface defining the indentation, and wherein the first and second surfaces are adjacent and contiguous with one another.

4. The assembly of claim 1 , wherein the first of the plurality of cooling apertures has an outlet that is separated by a distance from the indentation.

5. The assembly of claim 1 , wherein the first of the plurality of cooling apertures has an outlet that intersects the indentation.

6. The assembly of claim 1 , wherein the first of the plurality of cooling apertures is circumferentially aligned with the indentation.

7. The assembly of claim 1 , wherein the first of the plurality of cooling apertures is circumferentially offset from the indentation.

8. The assembly of claim 1 , wherein a second of the plurality of cooling apertures is configured to direct cooling air away from the cooling cavity, and the indentation is further configured such that cooling air directed from the second of the plurality of cooling apertures at least partially circulates against the side of the heat shield.

9. The assembly of claim 1 , wherein

the heat shield further defines a second indentation in the side of the heat shield, and

the second indentation is configured such that cooling air directed from a second of the plurality of cooling apertures at least partially circulates against the side of the heat shield.

10. The assembly of claim 1 , wherein the heat shield includes an arcuate panel in which the first of the plurality of cooling apertures and the indentation are defined.

11. The assembly of claim 1 , further comprising a tubular combustor wall that includes the shell and the heat shield, and the heat shield configured to form a peripheral boundary of a combustion chamber.

12. An assembly for a turbine engine, the assembly comprising:

a shell; and

a heat shield attached to the shell with a cooling cavity extending between the heat shield and the shell, the heat shield defining a plurality of cooling apertures and an indentation in a side of the heat shield opposite the cooling cavity,

wherein the plurality of cooling apertures are fluidly coupled with the cooling cavity, and an outlet of a first of the plurality of cooling apertures is located on an edge of the indentation, and

wherein the indentation is configured such that cooling air directed out of the cooling cavity from the outlet at least partially circulates against the side of the heat shield.

13. The assembly of claim 12 , wherein

the heat shield extends between a chamber surface and a cavity surface that defines a portion of the cooling cavity;

a point of an indentation surface that defines the indentation is located a distance from the cavity surface; and

the distance is between fifty percent and ninety percent of a thickness of the heat shield measured between the cavity and the chamber surfaces.

14. The assembly of claim 12 , wherein a cross-sectional area of the outlet is between one percent and fifty percent of an area of an indentation surface that defines the indentation.

15. The assembly of claim 12 , wherein

the plurality of cooling apertures in the heat shield are effusion apertures; and

the shell defines a plurality of impingement apertures that are fluidly coupled with the effusion apertures by the cooling cavity.

16. An assembly for a turbine engine, the assembly comprising:

a shell and a heat shield with a cooling cavity between the shell and the heat shield;

the heat shield configured with a plurality of cooling apertures and a plurality of indentations in a side of the heat shield opposite the cooling cavity;

the plurality of indentations comprising a first indentation and a second indentation located downstream of the first indentation;

the plurality of cooling apertures fluidly coupled with the cooling cavity;

the first indentation configured such that cooling air directed out of the cooling cavity from a first of the plurality of cooling apertures at least partially circulates in the first indentation against the side of the heat shield; and

the second indentation configured such that cooling air directed out of the cooling cavity from a second of the plurality of cooling apertures at least partially circulates in the second indentation against the side of the heat shield downstream of the first indentation.

17. The assembly of claim 16 , further comprising a surface that defines the indentation with an oval peripheral geometry.

18. The assembly of claim 16 , further comprising a surface that defines the indentation, wherein the indentation has a peripheral geometry with one or more concave sections and one or more convex sections.

19. The assembly of claim 16 , wherein an annular surface of the heat shield defines the indentation.