| 发明名称 |
GAS TURBINE COMBUSTION CHAMBER WITH MODIFIED WALL THICKNESS |
| 摘要 |
A gas turbine combustion chamber, including at least one combustion chamber wall in which mixed air holes are formed in a predefined area that extends around the combustion chamber in a ring-shaped manner with respect to the central axis of the combustion chamber in a central area of the same, characterized in that the combustion chamber wall has a greater thickness in the ring-shaped area of the mixed air holes than in the areas that are not provided with mixed air holes. |
| 申请公布号 |
US2016178198(A1) |
申请公布日期 |
2016.06.23 |
| 申请号 |
US201514972850 |
申请日期 |
2015.12.17 |
| 申请人 |
Rolls-Royce Deutschland Ltd & Co KG |
发明人 |
GERENDAS Miklos |
| 分类号 |
F23R3/04;F23R3/00 |
主分类号 |
F23R3/04 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. Gas turbine combustion chamber, comprising at least one combustion chamber wall in which mixed air holes are formed in a predefined area that extends around the combustion chamber in a ring-shaped manner with respect to the central axis of the combustion chamber in a central area of the same, wherein the combustion chamber wall has a greater thickness in the ring-shaped area of the mixed air holes than in the areas that are not provided with mixed air holes. |
| 地址 |
Blankenfelde-Mahlow DE |
