| 发明名称 |
GAS TURBINE ENGINE COMBUSTOR LINER |
| 摘要 |
A gas turbine engine variable porosity combustor liner has a laminated alloy structure. The laminated alloy structure has combustion chamber facing holes on one side and cooling plenum facing holes on a radially opposite side. The combustion chamber facing holes are in fluid communication with the cooling plenum facing holes via axially and circumferentially extending flow passages sandwiched between metal alloy sheets of the laminated alloy structure. Porous zones having respective different cooling flow amounts are formed in the laminated alloy structure based on at least one of an arrangement of the combustion chamber facing holes, an arrangement of the cooling plenum facing holes, and an arrangement of the flow passages. |
| 申请公布号 |
US2014260282(A1) |
申请公布日期 |
2014.09.18 |
| 申请号 |
US201314136705 |
申请日期 |
2013.12.20 |
| 申请人 |
Rolls-Royce Corporation ;Rolls-Royce North American Technologies, Inc. |
发明人 |
Pinnick Donald E.;Froemming Kenneth W.;Varney Bruce E. |
| 分类号 |
F23R3/06 |
主分类号 |
F23R3/06 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A gas turbine engine variable porosity combustor liner comprising:
a laminated alloy structure having combustion chamber facing holes on one side and cooling plenum facing holes on a radially opposite side, the combustion chamber facing holes being in fluid communication with the cooling plenum facing holes via axially and circumferentially extending flow passages sandwiched between metal alloy sheets of the laminated alloy structure; wherein porous zones having respective different cooling flow amounts are formed in the laminated alloy structure based on at least one of an arrangement of the combustion chamber facing holes, an arrangement of the cooling plenum facing holes, and an arrangement of the flow passages. |
| 地址 |
Indianapolis IN US |
