Gas turbine engine dilution chute geometry

1. A combustor for a gas turbine engine, the combustor comprising:

a combustor liner; and

a dilution chute integral and conformal with the combustor liner to provide an outlet into the combustor for fuel, the dilution chute including a plurality of walls;

the plurality of walls extending longitudinally along a longitudinal centerline of the dilution chute into an interior of the combustor, the plurality of walls terminating at a tapered edge with a vertex, and the plurality of walls including a first wall and a second wall; and

the tapered edge comprising a longitudinal peak at a corner between the first wall and the second wall.

2. The combustor of claim 1 , wherein the dilution chute has four walls and a substantially square shaped opening.

3. The combustor of claim 1 , wherein the tapered edge has a knife edge shape.

4. The combustor of claim 1 , wherein the tapered edge has a castellation shaped edge.

5. The combustor of claim 1 , wherein the tapered edge has a saw tooth shaped edge.

6. The combustor of claim 1 , wherein the tapered edge has an angle of inclination of substantially 45 degrees.

7. The combustor of claim 1 , wherein the tapered edge is configured to reduce carbon deposit formation on an exterior surface of the dilution chute.

8. A gas turbine engine comprising:

a compressor section;

a combustor section in fluid communication with the compressor section, the combustor section comprising the combustor of claim 1 ;

a turbine section in fluid communication with the combustor section; and

an exhaust section in fluid communication with the turbine section.

9. The combustor of claim 1 , wherein the dilution chute extends longitudinally along the longitudinal centerline into the interior of the combustor to the longitudinal peak.

10. The combustor of claim 1 , wherein

the plurality of walls further include a third wall; and

the tapered edge further comprises a second longitudinal peak at a corner between the second wall and the third wall.

11. The combustor of claim 10 , wherein

a portion of the tapered edge extends along the second wall between the longitudinal peak and the second longitudinal peak; and

the portion of the tapered edge is recessed longitudinally from the longitudinal peak and the second longitudinal peak towards the combustor liner.

12. The combustor of claim 11 , wherein the portion of the tapered edge is castellated.

13. The combustor of claim 1 , wherein the longitudinal peak comprises a triangular geometry.

14. The combustor of claim 1 , wherein the dilution chute comprises metal.

15. A combustor for a gas turbine engine, the combustor comprising:

a combustor liner; and

a dilution chute connected to the combustor liner and including a plurality of walls;

the plurality of walls extending longitudinally along a longitudinal centerline of the dilution chute into an interior of the combustor to a tapered edge, and the plurality of walls including a first wall and a second wall;

the tapered edge comprising a longitudinal peak at a corner between the first wall and the second wall.

16. The combustor of claim 15 , wherein dilution chute is formed integral with the combustor liner.

17. The combustor of claim 15 , further comprising a fuel line configured to direct fuel into the dilution chute for wetting a surface of the dilution chute.

18. The combustor of claim 15 , wherein

the plurality of walls further include a third wall; and

the tapered edge further comprises a second longitudinal peak at a corner between the second wall and the third wall.

19. The combustor of claim 18 , wherein

a portion of the tapered edge extends along the second wall between the longitudinal peak and the second longitudinal peak; and

the portion of the tapered edge is longitudinally setback from the longitudinal peak and the second longitudinal peak towards the combustor liner.