发明名称 |
Hybrid prefilming airblast, prevaporizing, lean-premixing dual-fuel nozzle for gas turbine combustor |
摘要 |
A dual fuel nozzle for a gas turbine combustor includes a hub defining a fuel inlet and a plurality of liquid fuel jets disposed at a downstream end of the hub. The fuel jets are oriented to eject liquid fuel radially outward from the hub. An annular air passage includes a swirler that imparts swirl to air flowing in the annular air passage, and a splitter ring is disposed in the annular air passage and surrounds the plurality of liquid fuel jets. The nozzle allows liquid fuels to be injected into a swirling annular airstream and then atomized, dispersed and vaporized inside a lean premixing dual fuel nozzle for a gas turbine combustor. |
申请公布号 |
US8671691(B2) |
申请公布日期 |
2014.03.18 |
申请号 |
US20100787990 |
申请日期 |
2010.05.26 |
申请人 |
BOARDMAN GREGORY ALLEN;CHILA RONALD JAMES;HUGHES MICHAEL JOHN;STEWART JASON THURMAN;GENERAL ELECTRIC COMPANY |
发明人 |
BOARDMAN GREGORY ALLEN;CHILA RONALD JAMES;HUGHES MICHAEL JOHN;STEWART JASON THURMAN |
分类号 |
F02C1/00;F02G3/00 |
主分类号 |
F02C1/00 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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