| 发明名称 |
CIRCUMFERENTIALLY AND AXIALLY STAGED CAN COMBUSTOR FOR GAS TURBINE ENGINE |
| 摘要 |
A combustor section for a gas turbine engine includes a can combustor with a combustion chamber. A pilot fuel injection system is in axial communication with the combustion chamber. A main fuel injection system is in radial communication with the combustion chamber. The main fuel injection system includes a multiple of first main fuel nozzles that circumferentially alternate with a multiple of second main fuel nozzles. |
| 申请公布号 |
US2016298852(A1) |
申请公布日期 |
2016.10.13 |
| 申请号 |
US201415025827 |
申请日期 |
2014.10.20 |
| 申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
Snyder, III Timothy S. |
| 分类号 |
F23R3/34;F23R3/12 |
主分类号 |
F23R3/34 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A combustor section for a gas turbine engine, comprising:
a can combustor including a combustion chamber; a pilot fuel injection system in axial communication with the combustion chamber; and a main fuel injection system in radial communication with the combustion chamber, the main fuel injection system including a multiple of first main fuel nozzles that circumferentially alternate with a multiple of second main fuel nozzles. |
| 地址 |
Farmington CT US |
