发明名称 |
Combustors with complex shaped effusion holes |
摘要 |
A combustor is provided for a turbine engine. The combustor includes a first liner having a first side and a second side and a second liner having a first side and a second side. The second side of the second liner forms a combustion chamber with the second side of the first liner, and the combustion chamber is configured to receive an air-fuel mixture for combustion therein. The first liner defines a plurality of effusion cooling holes configured to form a film of cooling air on the second side of the first liner. The plurality of effusion cooling holes including a first effusion cooling hole extending from the first side to the second side with a non-linear line of sight. |
申请公布号 |
EP2759772(B1) |
申请公布日期 |
2016.04.27 |
申请号 |
EP20140150504 |
申请日期 |
2014.01.08 |
申请人 |
HONEYWELL INTERNATIONAL INC. |
发明人 |
GAGE, RAYMOND;RUDRAPATNA, NAGARAJA S. |
分类号 |
F23R3/00;F23R3/06;F23R3/16;F23R3/50 |
主分类号 |
F23R3/00 |
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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