发明名称 |
Integrated Combustor and Stage 1 Nozzle in a Gas Turbine and Method |
摘要 |
An integrated combustor and stage one nozzle in a gas turbine includes a combustion chamber that receives premixed fuel and air from at least one fuel nozzle group at separate axial locations. The combustion chamber includes a liner and a transition piece that deliver hot combustion gas to the turbine. The stage one nozzle, the liner and the transition piece are integrated into a single part. At least one of the axial locations of the one or more fuel nozzle groups includes a plurality of small scale mixing devices that concentrate heat release and reduce flame length.
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申请公布号 |
US2010115953(A1) |
申请公布日期 |
2010.05.13 |
申请号 |
US20080269411 |
申请日期 |
2008.11.12 |
申请人 |
DAVIS JR LEWIS BERKLEY;ZIMINSKY WILLY STEVE;MCMAHAN KEVIN WESTON;CHILA RONALD JAMES;MESHKOV SERGEY ANATOLIEVICH |
发明人 |
DAVIS, JR. LEWIS BERKLEY;ZIMINSKY WILLY STEVE;MCMAHAN KEVIN WESTON;CHILA RONALD JAMES;MESHKOV SERGEY ANATOLIEVICH |
分类号 |
F23R3/42;F02C3/14;F02C7/22 |
主分类号 |
F23R3/42 |
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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