Cooling an aperture body of a combustor wall

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

a combustor wall including a shell, a heat shield and an annular body having an inner surface that at least partially defines a first aperture through the shell and the heat shield;

wherein the annular body further defines a plurality of second apertures through which air is directed into the first aperture and provides non-uniform cooling to the annular body;

wherein the annular body defines each of the second apertures with a respective path that extends from a respective inlet to a respective outlet with a respective trajectory through the annular body;

wherein the respective outlets of the second apertures are arranged in axial alignment on the inner surface of the annular body relative to a centerline of the first aperture;

and wherein a geometry of the trajectory of the path of one of the second apertures is different than a geometry of the trajectory of the path of another one of the second apertures.

2. The assembly of claim 1 , wherein

the annular body defines each of the second apertures with a respective length therethrough; and

the length of one of the second apertures is different than the length of another one of the second apertures.

3. The assembly of claim 1 , wherein

the annular body defines each of the second apertures with a respective width therewithin; and

the width of one of the second apertures is different than the width of another one of the second apertures.

4. The assembly of claim 1 , wherein

the respective outlets of the second apertures are disposed around and fluidly coupled with the first aperture;

a first of the outlets is between and adjacent to a second and a third of the outlets; and

a distance between the first and the second of the outlets is different than a distance between the first and the third of the outlets.

5. The assembly of claim 1 , wherein at least a portion of one of the plurality of second apertures at the inner surface extends substantially radially relative to the centerline of the first aperture.

6. The assembly of claim 1 , wherein at least a portion of one of the plurality of second apertures at the inner surface extends substantially tangentially relatively to the inner surface.

7. The assembly of claim 1 , wherein at least a portion of one of the plurality of second apertures at the inner surface extends acutely relative to the inner surface.

8. The assembly of claim 1 , wherein the annular body extends laterally between an outer surface and the inner surface; and one of the plurality of second apertures extends through the annular body between the outer surface and the inner surface.

9. The assembly of claim 1 , wherein the annular body extends vertically to an exterior surface and laterally to the inner surface; and one of the plurality of second apertures extends through the annular body between the exterior surface and the inner surface.

10. The assembly of claim 9 , wherein the exterior surface is funnel-shaped and defines a portion of the first aperture.

11. The assembly of claim 1 , wherein the annular body includes a shelf surface and the inner; and the shelf surface and the inner surface define a peripheral inner channel in the annular body.

12. The assembly of claim 1 , wherein

the annular body extends vertically through a cooling cavity that is defined vertically between the shell and the heat shield; and

the cooling cavity fluidly couples one or more shell cooling apertures defined in the shell with one or more heat shield cooling apertures defined in the heat shield.

13. The assembly of claim 1 , wherein the heat shield includes a plurality of panels that are attached to the shell, and the annular body is connected to one of the panels.

14. A grommet for a turbine engine combustor wall through which a quench aperture vertically extends, the grommet comprising:

an annular body extending vertically between interior and exterior surfaces and laterally between an inner surface and an outer surface, the inner surface at least partially defining the quench aperture;

wherein the annular body defines a plurality of cooling apertures to direct air into the quench aperture that extend through the annular body from respective inlets to respective outlets in the inner surface with a respective trajectory, wherein the outlets are axially aligned relative to a centerline of the quench aperture;

and wherein the annular body defines a first of the plurality of cooling apertures with a different trajectory geometry than that of a second of the plurality of cooling apertures.

15. The grommet of claim 14 , wherein

the annular body defines each of the cooling apertures with a respective length therethrough; and

the length of the first of the cooling apertures is different than the length of the second of the cooling apertures.

16. The grommet of claim 14 , wherein the annular body is operable to direct air through the cooling apertures to non-uniformly cool the annular body.

17. A grommet for a turbine engine combustor wall through which a quench aperture vertically extends, the grommet comprising:

an annular body extending vertically between interior and exterior surfaces and laterally between an inner surface and an outer surface, the inner surface at least partially defining the quench aperture;

wherein the annular body defines a plurality of cooling apertures to direct air into the quench aperture that respectively extend through the annular body from a plurality of respective inlets to a plurality of respective outlets in the inner surface with a respective trajectory;

wherein the outlets are disposed in axial alignment around the quench aperture relative to a centerline of the quench aperture;

wherein the annular body defines a first of the plurality of cooling apertures with a different trajectory geometry than that of a second of the plurality of cooling apertures;

and wherein a first of the outlets is between and adjacent to a second and a third of the outlets, and a distance between the first and the second of the outlets is different than a distance between the first and the third of the outlets.

18. The grommet of claim 17 , wherein the annular body is operable to direct air through the cooling apertures to non-uniformly cool the annular body.