发明名称 |
Multihole patch for combustor liner of a gas turbine engine |
摘要 |
A liner for a combustor of a gas turbine engine, including a shell having a first end adjacent to an upstream end of the combustor and a second end adjacent to a downstream end of the combustor, wherein at least one discrete region is subject to distress from impingement of hot gases, a plurality of cooling slots formed in the shell through which air flows for providing a cooling film along a hot side of the shell, and a group of cooling holes formed in the shell in the discrete region to augment the cooling film and provide convective bore cooling to the discrete region.
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申请公布号 |
US2003200752(A1) |
申请公布日期 |
2003.10.30 |
申请号 |
US20020134283 |
申请日期 |
2002.04.29 |
申请人 |
MOERTLE GEORGE ERIC;MILLS BRUCE ERNEST;HOLMES JAMES PATRICK;LIND DAVID ALBIN;HARRIS TARIQ KAY |
发明人 |
MOERTLE GEORGE ERIC;MILLS BRUCE ERNEST;HOLMES JAMES PATRICK;LIND DAVID ALBIN;HARRIS TARIQ KAY |
分类号 |
F02C7/18;F23R3/06;F23R3/50;(IPC1-7):F23R3/06 |
主分类号 |
F02C7/18 |
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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