Fuel injector device
US-2016290648-A1 · Oct 6, 2016 · US
US8966909B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-8966909-B2 |
| Application number | US-201213590302-A |
| Country | US |
| Kind code | B2 |
| Filing date | Aug 21, 2012 |
| Priority date | Aug 21, 2012 |
| Publication date | Mar 3, 2015 |
| Grant date | Mar 3, 2015 |
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Official abstract text for this publication.
A system and method for reducing combustion dynamics includes first and second combustors arranged about an axis, and each combustor includes a plurality of tubes that extend axially through at least a portion of the combustor and a combustion chamber downstream from the plurality of tubes. A fuel injector extends through each tube to provide fluid communication into each tube at a fourth axial distance from the combustion chamber. The fourth axial distance in the first combustor is different than the fourth axial distance in the second combustor.
Opening claim text (preview).
What is claimed is: 1. A gas turbine, comprising: a. a plurality of combustors annularly arranged about an axial centerline of the gas turbine, the plurality of combustors including a first combustor and a second combustor; b. wherein the first combustor comprises a plurality of bundled tube fuel nozzles annularly arranged about a centerline of the first combustor, each bundled tube fuel nozzle including a fuel plenum and a plurality of tubes which extend therethrough, each tube…
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