Turbine engine support structure with airflow ports
An assembly is provided for a turbine engine. This engine assembly includes a combustor, an engine case, a support structure and a monolithic body. The combustor includes a combustor wall and a combustion chamber within the combustor. The combustor wall forms a peripheral boundary of the combustion chamber. The engine case forms a peripheral boundary of a plenum along the combustor. The support structure extends radially from the combustor wall to the engine case. The monolithic body includes the combustor wall, the engine case, the support structure and a plurality of ports arranged circumferentially about an axis. Each of the ports is fluidly coupled with the plenum and projects axially through the support structure. The ports include a first port. The first port includes a cross-sectional geometry that laterally tapers as the first port extends radially outward within the monolithic body.
1. An assembly for a turbine engine, comprising:
a combustor including a combustor wall and a combustion chamber within the combustor, the combustor wall forming a peripheral boundary of the combustion chamber;
an engine case forming a peripheral boundary of a plenum along the combustor;
a support structure extending radially from the combustor wall to the engine case;
a monolithic body including the combustor wall, the engine case, the support structure and a plurality of ports arranged circumferentially about an axis, each of the plurality of ports fluidly coupled with the plenum and projecting axially through the support structure, the plurality of ports comprising a first port, and the first port comprising a cross-sectional geometry that laterally tapers as the first port extends radially outward within the monolithic body;
a vane array structure including a first platform, a second platform and a plurality of vanes extending radially between and connected to the first platform and the second platform; and
a cavity formed by and located radially between the combustor wall and the first platform, each of the plurality of ports further fluidly coupled with the combustion chamber through the cavity.
2. The assembly of claim 1 , wherein
a radial outer portion of the cross-sectional geometry laterally tapers as the first port extends radially outward within the monolithic body; and
a radial inner portion of the cross-sectional geometry laterally tapers as the first port extends radially inwards within the monolithic body.
3. The assembly of claim 1 , wherein the first port comprises the cross-sectional geometry at an outlet from the first port.
4. The assembly of claim 3 , wherein
the combustor wall and the support structure extend axially to an end surface;
the outlet is disposed in the end surface; and
the cross-sectional geometry has a hexagonal shape.
5. The assembly of claim 3 , wherein the first port laterally tapers as the first port projects axially into the support structure from the outlet.
6. The assembly of claim 1 , wherein
an interior surface of the combustor wall forms the peripheral boundary of the combustion chamber; and
an outlet from the first port includes a notch in the interior surface.
7. The assembly of claim 6 , wherein the notch laterally tapers as the notch projects axially into the interior surface.
8. The assembly of claim 6 , wherein the notch has a triangular shape in the interior surface.
9. The assembly of claim 1 , wherein
the monolithic body further includes a plurality of struts arranged circumferentially about the axis;
each of the plurality of struts is between a respective circumferentially neighboring pair of the plurality of ports; and
each of the plurality of struts extends radially from the combustor wall to the engine case.
10. The assembly of claim 9 , wherein
the plurality of struts comprise a first strut forming a lateral side of the first port; and
the first strut laterally tapers as the first strut extends axially towards an inlet into the first port from the plenum.
11. The assembly of claim 10 , wherein
a first portion of the first strut laterally tapers as the first strut extends axially towards an inlet into the first port from the plenum;
a second portion of the first strut laterally tapers as the first strut extends axially towards an outlet from the first port; and
the second portion of the first strut is axially between the first portion of the first strut and the outlet from the first port.
12. The assembly of claim 1 , wherein a longitudinal centerline of the first port is parallel with the axis.
13. The assembly of claim 1 , wherein a longitudinal centerline of the first port is angularly offset from the axis.
14. The assembly of claim 1 , wherein the combustor is radially outboard of and circumscribes the engine case and the support structure.
15. The assembly of claim 1 , wherein the vane array structure is radially outboard of and axially overlaps the support structure and the plurality of ports.
16. The assembly of claim 1 , wherein the monolithic body further includes the first platform.
17. The assembly of claim 1 , further comprising:
a compressor section;
a turbine section; and
a flowpath extending through the compressor section, the plenum, the combustion chamber and the turbine section from an inlet into the flowpath to an exhaust from the flowpath.