Combustor with dilution openings
A gas turbine engine including a compressor section and a combustion section in serial flow arrangement along an engine centerline, the combustion section having a combustor liner, a dome wall coupled to the combustor liner, and a dome inlet located in the dome wall, a fuel injector fluidly coupled to the dome inlet, a combustion chamber fluidly coupled to the fuel injector and defined at least in part by the combustor liner and the dome wall, and at least one set of dilution openings located in the dome wall and fluidly coupled to the combustion chamber.
1. A gas turbine engine comprising:
a compressor section and a combustion section in serial flow arrangement along an engine centerline, the combustion section comprising:
a combustor liner;
a dome wall coupled to the combustor liner, and a dome inlet located in the dome wall, wherein the dome wall defines a conic portion forming an obtuse angle with the combustor liner;
a fuel injector fluidly coupled to the dome inlet, wherein the dome wall extends radially between the fuel injector and the combustor liner to define a flat portion, wherein the flat portion and the conic portion meet at a first junction;
a flare cone disposed around the fuel injector, wherein the flare cone meets the conic portion at a second junction and wherein the conic portion extends between the first junction and the second junction;
a combustion chamber fluidly coupled to the fuel injector and defined at least in part by the combustor liner and the dome wall; and
at least one set of dilution openings located in the dome wall and fluidly coupled to the combustion chamber, the at least one set of dilution openings circumferentially arranged about the engine centerline;
wherein the at least one set of dilution openings forms one of a segmented annulus about a circumference of the engine centerline or an annulus about the circumference of the engine centerline.
2. The gas turbine engine of claim 1 wherein the at least one set of dilution openings is a first set of dilution openings and a second set of dilution openings concentric with respect to each other.
3. The gas turbine engine of claim 2 wherein the first set of dilution openings forms the annulus and the second set of dilution openings forms a second annulus about the circumference of the engine centerline.
4. The gas turbine engine of claim 2 wherein both the first and second set of dilution openings are segmented dilution openings defining the segmented annulus.
5. The gas turbine engine of claim 1 wherein the at least one set of dilution openings extends between a dilution inlet and a dilution outlet at the dome wall.
6. The gas turbine engine of claim 5 , further comprising at least one vane disposed within the at least one set of dilution openings between the dilution inlet and the dilution outlet.
7. The gas turbine engine of claim 6 where in the at least one vane is one of a radial flow vane or an axial flow vane.
8. The gas turbine engine of claim 1 wherein the dome inlet defines a dome centerline and the at least one set of dilution openings defines a dilution centerline.
9. The gas turbine engine of claim 8 wherein the dilution centerline is a first centerline angled toward a longitudinal axis and intersecting with the dome centerline to define a dilution angle.
10. The gas turbine engine of claim 1 wherein the at least one set of dilution openings is located in the flat portion.
11. The gas turbine engine of claim 10 wherein the flat portion extends between the first junction and the combustor liner.
12. The gas turbine engine of claim 1 further comprising a purge passage disposed around the flare cone.
13. The gas turbine engine of claim 1 further comprising at least one axial deflector.
14. The gas turbine engine of claim 1 wherein the dome wall comprises a deflector and an impingement wall spaced apart to define an intermediate plenum.
15. The gas turbine engine of claim 1 wherein the at least one set of dilution openings are circumferentially disposed about the dome inlet.