Combustion section with a primary combustion chamber and a secondary combustion chamber
A combustion section of a turbine engine having a primary combustion chamber and a secondary combustion chamber. The primary combustion chamber is defined, at least in part, by a combustor liner and a dome wall. A primary fuel nozzle having an outlet is located at the dome wall, wherein the outlet of the primary fuel nozzle is fluidly coupled with the primary combustion chamber. At least one opening located in an outer liner axially aft of the dome wall fluidly couples the secondary combustion chamber and the primary combustion chamber. A set of secondary fuel nozzles are fluidly coupled with the secondary combustion chamber.
1. A combustion section for a turbine engine, the combustion section comprising:
a primary combustor liner including an inner liner and an outer liner;
a dome wall extending between the inner liner and the outer liner;
a primary combustion chamber defined at least in part by the inner liner, the outer liner, and the dome wall, wherein the outer liner defines at least one opening aft of the dome wall;
a primary fuel nozzle having an outlet at the dome wall, wherein the outlet of the primary fuel nozzle is fluidly coupled with the primary combustion chamber;
a secondary combustion chamber defined at least in part by a secondary combustor liner, the secondary combustion chamber fluidly coupled to the primary combustion chamber at the at least one opening;
a set of secondary fuel nozzles comprising multiple mixer tubes having outlets at the secondary combustor liner, wherein the outlets of the mixer tubes are fluidly coupled with the secondary combustion chamber;
a first igniter at least partially located in the primary combustion chamber; and
a second igniter at least partially located in the secondary combustion chamber.
2. The combustion section of claim 1 , wherein at least one mixer tube of the multiple mixer tubes is a pilot tube.
3. The combustion section of claim 1 , wherein the secondary combustion chamber is a set of circumferentially spaced combustion chambers and the at least one opening is a plurality of circumferentially spaced openings, where each secondary combustion chamber of the set of circumferentially combustion chambers fluidly couples to the primary combustion chamber at each opening of the plurality of circumferentially spaced openings.
4. The combustion section of claim 1 , wherein the secondary combustion chamber is an annular combustion chamber defined in part by the outer liner.
5. The combustion section of claim 4 , wherein a cluster of secondary mixer tubes are circumferentially spaced about the annular combustion chamber.
6. The combustion section of claim 1 , wherein a first centerline defined by the primary fuel nozzle intercepts with a second centerline defined by the at least one opening.
7. The combustion section of claim 1 , wherein a primary combustor defined by the primary combustion chamber and the primary fuel intercepts is a rich burn system.
8. The combustion section of claim 7 , wherein the secondary combustion chamber is a plurality of secondary combustion chambers, and a set of secondary combustors are defined by the plurality of secondary combustion chambers and the set of secondary fuel nozzles is a lean burn system.
9. The combustion section of claim 1 , wherein the multiple mixer tubes form a cluster of mixer tubes.
10. The combustion section of claim 1 , wherein the primary combustion chamber includes a primary combustor length measured from the dome wall to a primary combustor outlet and a primary combustion height measured radially across the primary combustion chamber from the inner liner to the outer liner, wherein the primary combustion height is in a range from 1.1 to 10 times a dome inlet diameter measured across a dome inlet.
11. The combustion section of claim 10 , wherein the at least one opening is located at an end of the secondary combustion chamber, where the end is an axial distance from the dome wall, and wherein the axial distance is in a range of 0% to 70% of the primary combustor length.
12. The combustion section of claim 10 , wherein the primary combustion chamber includes a primary outlet centerline defined by the primary combustor outlet, and wherein a radially distance between the at least one opening and the primary outlet centerline is in a range of 30% to 100% of the primary combustion height.
13. The combustion section of claim 1 , wherein the primary fuel nozzle defines a rich cup and a cluster of secondary mixer tubes define a plurality of lean cups.
14. The turbine engine of claim 1 , further comprising dilution openings located downstream from the secondary combustion chamber in the outer liner or the inner liner.
15. A turbine engine comprising:
a compressor section, a combustion section, and a turbine section in serial flow arrangement along an engine centerline, the combustion section comprising:
a primary combustor liner including an inner liner and an outer liner;
a dome wall extending between the inner liner and the outer liner;
a primary combustion chamber defined at least in part by the inner liner, the outer liner, and the dome wall, wherein the outer liner defines at least one opening aft of the dome wall;
a primary fuel nozzle having an outlet at the dome wall, wherein the outlet of the primary fuel nozzle is fluidly coupled with the primary combustion chamber;
a secondary combustion chamber defined at least in part by a secondary combustor liner, the secondary combustion chamber fluidly coupled to the primary combustion chamber at the at least one opening; and
a set of secondary fuel nozzles comprising multiple mixer tubes having outlets at the secondary combustor liner, wherein the outlets of the mixer tubes are fluidly coupled with the secondary combustion chamber, and wherein each fuel nozzle of the set of secondary fuel nozzles contributes to a flame of a plurality of flames located, at least in part, in the secondary combustion chamber.
16. The turbine engine of claim 15 , wherein the secondary combustion chamber extends from the outer liner in a radially outward direction.
17. The turbine engine of claim 15 , wherein the primary combustion chamber or the secondary combustion chamber have a phi (equivalence ratio) in a range from 0.4 to 2.
18. The turbine engine of claim 15 , wherein the plurality of flames are a cluster or array of micro flames.
19. The combustion section of claim 15 , wherein at least one mixer tube of the multiple mixer tubes is a pilot tube.
20. The combustion section of claim 15 , wherein the multiple mixer tubes form a cluster of mixer tubes.