Reverse-flow annular combustor for reduced emissions

1. A reverse flow annular combustor for a gas turbine engine with an engine centerline, comprising:

an inner liner;

an outer liner circumscribing the inner liner;

a combustor dome having a first edge coupled to the inner liner and a second edge coupled to the outer liner, the combustor dome forming a combustion chamber with the inner liner and the outer liner; and

a fuel injector coupled to the outer liner and configured to inject a stream of fuel into the combustion chamber in a tangential direction relative to the engine centerline;

wherein the combustion chamber comprises a rich burn zone, a quench zone, and a lean burn zone to support combustion of fluid flow through the inner liner and the outer liner;

wherein the combustion chamber further comprises a convergent section located upstream of the quench zone and configured to decrease a passage height of the combustion chamber from the combustor dome to the quench zone;

wherein the combustor dome is configured to bifurcate the fluid flow at the combustor dome into a first combustor stream directed to the inner liner and a second combustor stream directed to the outer liner; and

wherein the first combustor stream and the second combustor stream comprise air flow, fuel, and combustion gases.

2. The annular combustor of claim 1 , wherein the combustor dome is configured to bifurcate the air flow such that the first combustor stream and the second combustor stream have flow rates approximately equal to one another.

3. The annular combustor of claim 1 , wherein the inner liner folds radially towards the outer portion of an exit plane, and wherein the outer liner folds radially towards the inner portion of an exit plane.

4. The annular combustor of claim 1 , further comprising:

a first row of air admission holes in the inner liner, configured to admit a first set of quench jets into the quench zone; and

a second row of air admission holes in the outer liner, configured to admit a second set of quench jets into the quench zone;

wherein the first row of air admission holes is circumferentially offset relative to the second row of air admission holes.

5. The annular combustor of claim 4 , further comprising:

a third row of air admission holes in the inner liner, configured to admit a first set of dilution jets into the lean burn zone; and

a fourth row of air admission holes in the outer liner, configured to admit a second set of dilution jets into the lean burn zone.

6. A combustor for a gas turbine engine, comprising:

an annular inner liner;

an annular outer liner circumscribing the annular inner liner; and

a combustor dome having a first edge coupled to the annular inner liner and a second edge coupled to the annular outer liner, the combustor dome forming a combustion chamber with the annular inner liner and the annular outer liner;

wherein the combustion chamber accommodates fluid flow through the annular inner and annular outer liners;

wherein the combustion chamber converges in the direction of the fluid flow to reduce a diameter of the combustion chamber;

wherein the combustor dome is configured to bifurcate the fluid flow at the combustor dome into a first combustor stream directed to the annular inner liner and a second combustor stream directed to the annular outer liner; and

wherein the first combustor stream and the second combustor stream comprise air flow, fuel, and combustion gases.

7. The combustor of claim 6 , further comprising a fuel injector coupled to the annular outer liner and configured to inject a stream of fuel into the combustion chamber in a tangential direction relative to an engine centerline.

8. The combustor of claim 6 , wherein the combustion chamber comprises at least a rich burn zone and a quench zone.

9. The combustor of claim 8 , wherein the combustion chamber further comprises a dilution zone downstream from the quench zone.

10. The combustor of claim 8 , wherein the converging of the combustion chamber is located upstream from the quench zone.

11. The combustor of claim 10 , wherein the converging of the combustion chamber is limited to the rich burn zone.

12. The combustor of claim 6 , wherein:

the combustion chamber comprises a converging section downstream from the combustor dome;

the combustor dome has a dome diameter; and

the converging section has a minimum diameter that is no more than 85% of the combustor dome diameter.

13. The combustor of claim 12 , wherein:

the converging section has a maximum diameter that is no more than 50% of the combustor dome diameter.

14. A combustor for a gas turbine engine with an engine centerline, comprising:

an inner liner;

an outer liner circumscribing the inner liner;

a combustor dome having a first edge coupled to the inner liner and a second edge coupled to the outer liner, the combustor dome forming a combustion chamber with the inner liner and the outer liner; and

a fuel injector coupled to the outer liner and configured to inject a stream of fuel into the combustion chamber in a tangential direction relative to the engine centerline;

wherein the combustion chamber comprises a primary zone and a secondary zone to support combustion of fuel and fluid flow through the inner liner and the outer liner; and

wherein a passage height in the primary zone converges to reduce a radial distance between the inner liner and the outer liner;

wherein the combustor dome is configured to bifurcate the fluid flow at the combustor dome into a first combustor stream directed to the inner liner and a second combustor stream directed to the outer liner; and

wherein the first combustor stream and the second combustor stream comprise air flow, the fuel, and combustion gases.

15. The combustor of claim 14 , wherein the primary zone is located upstream of the secondary zone.

16. The combustor of claim 15 , wherein the primary zone is configured to operate under fuel rich conditions and the secondary zone is configured to transition a primary zone mixture into a fuel lean stage.

17. The combustor of claim 16 , wherein the combustion chamber further comprises a tertiary zone, located downstream from the secondary zone and configured to provide a desired temperature distribution.

18. The combustor of claim 14 , wherein the inner liner ramps upward within the primary zone to form an incline, wherein the incline reduces the radial distance between the inner liner and the outer liner.

19. The combustor of claim 14 , wherein the outer liner ramps downward within the primary zone to form an incline, wherein the incline reduces the radial distance between the inner liner and the outer liner.

20. The combustor of claim 14 , wherein:

the inner liner ramps upward within the primary zone to form a first incline; and

the outer liner ramps downward within the primary zone to form a second incline;

wherein the first incline and the second incline reduce the radial distance between the inner liner and the outer liner.