Film cooling a combustor wall of a turbine engine
An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall including a shell and a heat shield. The combustor wall defines first and second cavities between the shell and the heat shield. The heat shield defines a first outlet and an elongated second outlet. The first outlet is fluidly coupled with the first cavity. The second outlet is fluidly coupled with the second cavity. The combustor wall defines one of the cavities with a tapered geometry.
1. An apparatus for a combustor of a turbine engine, the apparatus comprising:
a combustor wall comprising a heat shield and a rail, the combustor wall configured with a first cavity, a second cavity and a quench aperture that extends through the heat shield, and the rail axially between the first cavity and the second cavity;
the heat shield including an exterior surface configured to form a peripheral boundary of a combustion chamber within the combustor;
the heat shield configured with a plurality of first cooling apertures and a plurality of second cooling apertures;
each of the plurality of first cooling apertures extending through the heat shield to the exterior surface and configured to direct a jet of cooling air into the combustion chamber, a first of the plurality of first cooling apertures having a circular cross-sectional geometry in a first plane, and the first of the plurality of first cooling apertures fluidly coupled with the first cavity; and
each of the plurality of second cooling apertures extending through the heat shield to the exterior surface and configured to direct a film of cooling air into the combustion chamber, a first of the plurality of second cooling apertures extending along a second cooling aperture centerline that is acutely angled relative to the exterior surface, the first of the plurality of second cooling apertures configured to direct a respective film of cooling air into the combustion chamber along a trajectory towards the quench aperture, the first of the plurality of second cooling apertures having a non-circular cross-sectional geometry in a second plane that is parallel to the first plane, and the first of the plurality of second cooling apertures fluidly coupled with the second cavity.
2. The apparatus of claim 1 , wherein
the first of the plurality of first cooling apertures is configured as an effusion aperture; and
the first of the plurality of second cooling apertures is configured as an elongated slot.
3. The apparatus of claim 2 , wherein the elongated slot is configured with a laterally elongated outlet in the exterior surface.
4. The apparatus of claim 1 , wherein as the first of the plurality of first cooling apertures extends along a first cooling aperture centerline that is acutely angled relative to the exterior surface.
5. The apparatus of claim 1 , wherein as the first of the plurality of first cooling apertures is configured to direct a respective jet of cooling air into the combustion chamber and the first of the plurality of second cooling apertures is configured to direct the respective film of cooling air into the combustion chamber along a common direction.
6. The apparatus of claim 1 , wherein a second of the plurality of second cooling apertures is configured to direct a respective film of cooling air into the combustion chamber along a trajectory towards the quench aperture.
7. The apparatus of claim 1 , wherein
the combustor wall further comprises a shell; and
the heat shield is attached to the shell.
8. The apparatus of claim 7 , wherein a thickness of the shell changes as the combustor wall extends longitudinally along the one of the first cavity and the second cavity.
9. The apparatus of claim 1 , wherein
the combustor wall further comprises a second rail;
one of the first cavity and the second cavity extends axially between the first rail and the second rail; and
a height of the one of the first cavity and the second cavity decreases as the heat shield extends from the first rail towards the second rail.
10. The apparatus of claim 1 , wherein
the rail defines a downstream axial end of the first cavity; and
the rail defines an upstream axial end of the second cavity.
11. The apparatus of claim 1 , wherein the rail fluidly isolates the first cavity from the second cavity within the combustor wall.
12. An apparatus for a combustor of a turbine engine, the apparatus comprising:
a combustor wall comprising a heat shield;
the heat shield including an interior surface and an exterior surface configured to form a peripheral boundary of a combustion chamber within the combustor;
the heat shield configured with a plurality of first cooling apertures and a plurality of second cooling apertures;
each of the plurality of first cooling apertures extending through the heat shield to the exterior surface, and a first of the plurality of first cooling apertures configured with a circular cross-sectional geometry in a first plane;
each of the plurality of second cooling apertures extending through the heat shield to the exterior surface, a first of the plurality of second cooling apertures configured with a non-circular cross-sectional geometry in a second plane that is parallel to the first plane, the first of the plurality of second cooling apertures extending along a second cooling aperture centerline from a second cooling aperture inlet in the interior surface to a second cooling aperture outlet in the exterior surface, and an entirety of the second cooling aperture centerline between the second cooling aperture inlet and the second cooling aperture outlet acutely angled relative to the exterior surface;
wherein a quench aperture extends through the heat shield; and
wherein the first of the plurality of second cooling apertures circumferentially overlaps and is upstream of the quench aperture.
13. The apparatus of claim 12 , wherein
the first of the plurality of first cooling apertures is configured to direct a jet of cooling air into the combustion chamber in a first direction; and
the first of the plurality of second cooling apertures is configured to direct a film of cooling air into the combustion chamber along the first direction.
14. The apparatus of claim 12 , wherein the first of the plurality of first cooling apertures extends through the heat shield from a first cooling aperture inlet in the interior surface to a first cooling aperture outlet in the exterior surface.
15. The apparatus of claim 12 , wherein an axial width of the first of the plurality of second cooling apertures continuously increases as the first of the plurality of second cooling apertures extends through the heat shield panel from the second cooling aperture inlet to the second cooling aperture outlet.
16. An apparatus for a combustor of a turbine engine, the apparatus comprising:
a combustor wall comprising a heat shield, the heat shield comprising a heat shield panel, and the combustor wall configured with a quench aperture that extends through the heat shield panel;
the heat shield including an interior surface and an exterior surface configured to form a peripheral boundary of a combustion chamber within the combustor; and
the heat shield panel configured with a plurality of cooling apertures that extend through the heat shield panel from the interior surface to the exterior surface, and a first of the plurality of cooling apertures comprising a laterally elongated slot upstream of the quench aperture;
wherein a lateral width of the laterally elongated slot is greater than a lateral width of the quench aperture, and the lateral width of the laterally elongated slot is less than a lateral width of the heat shield panel;
wherein an axial width of the laterally elongated slot continuously increases as the laterally elongated slot extends through the heat shield panel from an inlet in the interior surface to an outlet in the exterior surface; and
wherein a second of the plurality of cooling apertures comprises an effusion aperture, and the effusion aperture has a circular cross-sectional geometry.