Combustor wall aperture body with cooling circuit

1. An assembly for a turbine engine, comprising:

a combustor wall including an aperture body between a shell and a heat shield;

the aperture body at least partially forming a cavity and an aperture that extends through the combustor wall;

an inlet passage extending in the combustor wall to the cavity; and

an outlet passage extending in the combustor wall from the cavity to the aperture;

wherein the combustor wall is configured to direct air through the inlet passage to impinge against a first surface of the heat shield forming a side of the cavity;

wherein the heat shield further includes a second surface and a third surface;

wherein the first surface extends radially between the second surface and the third surface;

wherein a channel extends between the aperture body and the shell, and the channel is in fluid communication with the cavity through the inlet passage; and

wherein the channel extends axially between the shell and the heat shield, and is adjacent the aperture body; and

wherein the aperture is configured as a quench aperture.

2. The assembly of claim 1 , wherein the first surface is textured to augment convective heat transfer between the air and the combustor wall.

3. The assembly of claim 1 , further comprising one or more heat transfer augmentors extending into the cavity.

4. The assembly of claim 1 , wherein the aperture extends along an axis through the combustor wall, and the inlet passage extends axially to the cavity.

5. The assembly of claim 1 , wherein the aperture extends along an axis through the combustor wall, and the outlet passage extends radially from the cavity to the aperture.

6. The assembly of claim 1 , wherein the inlet passage is one of a plurality of inlet passages that extend in the combustor wall to the cavity.

7. The assembly of claim 1 , wherein the outlet passage is one of a plurality of outlet passages that extend in the combustor wall from the cavity to the aperture.

8. The assembly of claim 1 , wherein the cavity comprises an annular cavity.

9. The assembly of claim 1 , wherein

the aperture body at least partially forms a second cavity;

a second inlet passage extends in the combustor wall to the second cavity; and

a second outlet passage extends in the combustor wall from the second cavity to the aperture.

10. The assembly of claim 1 , wherein the inlet passage is within the aperture body and/or the outlet passage is within the aperture body.

11. The assembly of claim 1 , wherein the aperture is partially formed by an inner surface and a shelf surface that extends radially out to the inner surface, and the outlet passage extends to an outlet in the inner surface.

12. The assembly of claim 1 , wherein

a gap extends radially between the aperture body and the shell; and

the channel extends axially into the aperture body and fluidly couples the gap with the inlet passage.

13. The assembly of claim 1 , wherein the aperture body includes a tapered flange that partially forms the aperture through the combustor wall.

14. The assembly of claim 1 , wherein the aperture body is formed integral with the heat shield.

15. The assembly of claim 1 , further comprising a second combustor wall and a combustor bulkhead that extends radially between the combustor wall and the second combustor wall, wherein the combustor wall, the second combustor wall and the bulkhead form an annular combustion chamber therebetween.

16. The assembly of claim 1 , wherein

the cavity extends into the heat shield from the second surface to the first surface; and

the aperture body is disposed on and contacts the second surface.

17. The assembly of claim 1 , wherein the first surface meets the second surface at a first corner and the first surface meets the third surface at a second corner.

18. The assembly of claim 1 , wherein

the heat shield further includes a fourth surface and a fifth surface;

the fourth surface forms a side of a cooling cavity and is contiguous with the third surface;

the fifth surface partially forms a peripheral boundary of a combustion chamber;

a first distance between the fifth surface and first surface is less than a second distance between the fifth surface and the fourth surface.