Cluster of swirled mini-mixers for fuel-staged, axially staged combustion
AssigneeRtx Corporation
InventorsGregory Boardman, Stephen Kramer
Life of this patent
Estimating the term…
Abstract
A main injector can include multiple sub-element mixers. A first sub-element mixer includes a first main air nozzle circumscribing a first main fuel nozzle. A second sub-element mixer includes a second main air nozzle circumscribing a second main fuel nozzle. An annular combustor can include a circumferential array of main injectors disposed proximate a pilot injector. Each main injector of the array of main injectors can be oriented with first sub-element mixers proximate to the pilot injector and second sub-element mixers spaced axially downstream relative to first sub-element mixers in a staged configuration.
Claims15
A main injector for a continuous combustion chamber extending along an engine axis, the main injector comprising:
- a plurality of sub-element mixers arranged in a cluster, the plurality of sub-element mixers comprising a plurality of main air nozzles and a plurality of main fuel nozzles, each main air nozzle of the plurality of main air nozzles circumscribing a different main fuel nozzle of the plurality of main fuel nozzles, the plurality of sub-element mixers comprising:
- a first sub-element mixer comprising a first main air nozzle circumscribing a first main fuel nozzle;
- and
- a second sub-element mixer comprising a second main air nozzle circumscribing a second main fuel nozzle;
- wherein the first main fuel nozzle and the first main air nozzle are operatively associated with a first air-fuel ratio that is different than a second air-fuel ratio operatively associated with the second main fuel nozzle and the second main air nozzle, and
- wherein each main air nozzle of the plurality of main air nozzles is proximate at least one adjacent main air nozzle of the plurality of main air nozzles, and
- wherein each main air nozzle of the plurality of main air nozzles includes an inlet end coinciding with respective inlet passages of the plurality of main fuel nozzles, and
- wherein a first inlet end of the first main air nozzle is offset from a second inlet end of the second main air nozzle with respect to the engine axis.
An annular combustor for a gas turbine engine comprising:
- an outer combustor liner assembly;
- an inner combustor liner assembly spaced radially from the outer combustor liner assembly relative to an engine axis to form a combustion chamber;
- a forward assembly joining the outer combustor liner assembly to the inner linear assembly;
- a pilot injector extending into the forward assembly and configured to direct a pilot air-fuel mixture into the combustion chamber;
- and
- a main injector extending through the outer combustor liner assembly;
- wherein the main injector includes:
- a plurality of sub-element mixers arranged in a cluster, the plurality of sub-element mixers comprising a plurality of main air nozzles and a plurality of main fuel nozzles, each main air nozzle of the plurality of main air nozzles circumscribing a different main fuel nozzle of the plurality of main fuel nozzles, the plurality of sub-element mixers comprising:
- a first sub-element mixer comprising a first main air nozzle circumscribing a first main fuel nozzle;
- and
- a second sub-element mixer comprising a second main air nozzle circumscribing a second main fuel nozzle.
Dependencies are inferred from the claim text.