Gas turbine combustor with dynamics mitigation system
A gas turbine engine combustor includes: a head end section containing a fuel nozzle assembly and defining a head end air plenum; and a liner extending downstream from the head end section toward an aft frame and defining a combustion chamber therein. First injectors are disposed at a first axial location spaced apart from the head end section to direct a first fuel/air mixture through the liner. A dynamics mitigation system includes cold-side resonators disposed wholly within the head end air plenum, each resonator of the plurality of cold-side resonators having a resonator body with a closed end and an open neck extending from the resonator body opposite the closed end. Each resonator body defines a respective volume, and the open neck is in fluid communication with the head end air plenum. In some embodiments, quarter-wave tube dampers are installed within the fuel nozzle assembly of the head end section.
1. A combustor for a gas turbine engine, the combustor comprising:
a head end section containing a fuel nozzle assembly and defining a head end air plenum; a liner extending downstream from the head end section toward an aft frame and defining a combustion chamber therein;
a first plurality of injectors disposed at a first axial location spaced apart from the head end section to direct a first fuel/air mixture through the liner;
a dynamics mitigation system comprising a plurality of cold-side resonators disposed wholly within the head end air plenum, each resonator of the plurality of cold-side resonators having a resonator body with a closed end and an open neck extending from the resonator body opposite the closed end, wherein the resonator body defines a respective volume, and the open neck is in fluid communication with the head end air plenum, wherein the open neck of at least one resonator in the plurality of cold-side resonators has a smaller diameter than the closed end of the at least one resonator in the plurality of cold-side resonators, and wherein the plurality of cold-side resonators is axially oriented; and
an upstream inner barrel that partially surrounds the head air plenum, wherein the plurality of cold-side resonators is coupled to the upstream inner barrel.
2. The combustor of claim 1 , wherein the plurality of cold-side resonators comprises one or more sets of three resonators.
3. The combustor of claim 1 , wherein the dynamics mitigation system further comprises a plurality of hot-side dampers that extend through the liner and that define respective damper volumes in fluid communication with the combustion chamber.
4. The combustor of claim 3 , wherein at least one damper of the plurality of hot-side dampers is forward of the first plurality of injectors.
5. The combustor of claim 3 , further comprising a second plurality of injectors disposed at a second axial location different from the first plurality of injectors to direct a second fuel/air mixture through the liner; and wherein at least one damper of the plurality of hot-side dampers is between the first plurality of injectors and the second plurality of injectors.
6. The combustor of claim 3 , wherein at least one damper of the plurality of hot-side dampers is aft of the second plurality of injectors.
7. The combustor of claim 1 , wherein the fuel nozzle assembly is a bundled tube fuel nozzle assembly that comprises a forward plate facing the head end air plenum, an aft plate facing the combustion chamber, a plurality of premixing tubes extending from the forward plate to the aft plate, and a side wall extending circumferentially around the plurality of premixing tubes and extending axially from the forward plate to the aft plate, such that the forward plate, the aft plate, and the side wall define a fuel plenum; wherein the head end air plenum is in fluid communication with the combustion chamber, via the plurality of premixing tubes; wherein each premixing tube of the plurality of premixing tubes includes at least one fuel injection hole therethrough in fluid communication with the fuel plenum; and wherein the bundled tube fuel nozzle assembly spans an entire diameter of the head end section.
8. The combustor of claim 7 , wherein the bundled tube fuel nozzle assembly further comprises one or more quarter-wave tube dampers coupled to the aft plate, extending through the fuel plenum, and terminating in an end upstream of the forward plate, relative to a flow of fluids through the combustor chamber.
9. The combustor of claim 7 , wherein the bundled tube fuel nozzle assembly comprises an additively manufactured body; wherein at least one of one or more quarter-wave tube dampers includes a damper mounting body that is integrally connected to the forward plate and the aft plate and an extended damper body that is welded to the damper mounting body, the extended damper body extending into the head end air plenum.
10. The combustor of claim 9 , wherein the damper mounting body has a damper end that is distal to the forward plate; wherein the damper end comprises one or more apertures in fluid communication with the head end air plenum.
11. The combustor of claim 9 , wherein the damper mounting body of the at least one of the one or more quarter-wave tube dampers is surrounded by a bellows mounting body that projects from the forward plate into the head end air plenum; wherein the bellows mounting body extends a shorter distance from the forward plate than the damper mounting body; and wherein a bellows assembly is coupled to the bellows mounting body of the at least one of the one or more quarter-wave tube dampers.
12. The combustor of claim 9 , wherein the one or more quarter-wave tube dampers comprises multiple quarter-wave tube dampers; and wherein the multiple quarter-wave tube dampers have extended damper bodies of at least two different lengths to dampen dynamics of different frequencies.
13. A combustor for a gas turbine engine, the combustor comprising:
a head end section defining a head end plenum;
a liner extending downstream from the head end section toward an aft frame and defining a combustion chamber therein;
a bundled tube fuel nozzle assembly disposed in the head end section, the bundled tube fuel nozzle assembly comprising: an additively manufactured body, a forward plate facing the head end air plenum, an aft plate facing the combustion chamber, a plurality of premixing tubes extending from the forward plate to the aft plate, and a side wall extending circumferentially around the plurality of premixing tubes and extending axially from the forward plate to the aft plate, such that the forward plate, the aft plate, and the side wall define a fuel plenum; wherein the head end air plenum is in fluid communication with the combustion chamber, via the plurality of premixing tubes; wherein each premixing tube of the plurality of premixing tubes includes at least one fuel injection hole therethrough in fluid communication with the fuel plenum; and wherein the bundled tube fuel nozzle assembly spans an entire diameter of the head end section;
a first plurality of injectors disposed at a first axial location spaced apart from the head end section to direct a first fuel/air mixture through the liner; and
a dynamics mitigation system comprising one or more quarter-wave tube dampers coupled to the aft plate, extending through the fuel plenum, and terminating in an end upstream of the forward plate, relative to a flow of fluids through the combustor chamber, and wherein at least one of the one or more quarter-wave tube dampers includes a damper mounting body that is integrally connected to the forward plate and the aft plate and an extended damper body that is welded to the damper mounting body, the extended damper body extending into the head end air plenum.
14. The combustor of claim 13 , wherein the damper mounting body has a damper end that is distal to the forward plate; wherein the damper end comprises one or more apertures in fluid communication with the head end air plenum.
15. The combustor of claim 13 , wherein the damper mounting body of the at least one of the one or more quarter-wave tube dampers is surrounded by a bellows mounting body that projects from the forward plate into the head end air plenum; wherein the bellows mounting body extends a shorter distance from the forward plate than the damper mounting body; and wherein a bellows assembly is coupled to the bellows mounting body of the at least one of the one or more quarter-wave tube dampers.
16. The combustor of claim 13 , wherein the one or more quarter-wave tube dampers comprises multiple quarter-wave tube dampers; and wherein the multiple quarter-wave tube dampers have extended damper bodies of at least two different lengths to dampen dynamics of different frequencies.
17. The combustor of claim 13 , further comprising an upstream inner barrel that partially surrounds the head end air plenum; and wherein the dynamics mitigation system further comprises: a plurality of cold-side resonators coupled to the upstream inner barrel and disposed wholly within the head end air plenum, each resonator of the plurality of cold-side resonators having a resonator body with a closed end and an open neck extending from the resonator body opposite the closed end, wherein the resonator body defines a respective volume, and the open neck is in fluid communication with the head end air plenum.
18. The combustor of claim 17 , wherein the plurality of cold-side resonators comprises one or more sets of at least one resonator.
19. The combustor of claim 13 , wherein the dynamics mitigation system further comprises a plurality of hot-side dampers that extend through the liner and that define respective damper volumes in fluid communication with the combustion chamber.
20. A combustor for a gas turbine engine, the combustor comprising:
a head end section defining a head end plenum;
a liner extending downstream from the head end section toward an aft frame and defining a combustion chamber therein;
a bundled tube fuel nozzle assembly disposed in the head end section, the bundled tube fuel nozzle assembly comprising: a forward plate facing the head end air plenum, an aft plate facing the combustion chamber, a plurality of premixing tubes extending from the forward plate to the aft plate, and a side wall extending circumferentially around the plurality of premixing tubes and extending axially from the forward plate to the aft plate, such that the forward plate, the aft plate, and the side wall define a fuel plenum; wherein the head end air plenum is in fluid communication with the combustion chamber, via the plurality of premixing tubes; wherein each premixing tube of the plurality of premixing tubes includes at least one fuel injection hole therethrough in fluid communication with the fuel plenum; and wherein the bundled tube fuel nozzle assembly spans an entire diameter of the head end section;
a first plurality of injectors disposed at a first axial location spaced apart from the head end section to direct a first fuel/air mixture through the liner; and
a dynamics mitigation system comprising one or more quarter-wave tube dampers coupled to the aft plate, extending through the fuel plenum, and terminating in an end upstream of the forward plate, relative to a flow of fluids through the combustor chamber, wherein the damper mounting body of the at least one of the one or more quarter-wave tube dampers is surrounded by a bellows mounting body that projects from the forward plate into the head end air plenum, wherein the bellows mounting body extends a shorter distance from the forward plate than the damper mounting body, and wherein a bellows assembly is coupled to the bellows mounting body of the at least one of the one or more quarter-wave tube dampers.