| 发明名称 |
GAS TURBINE ENGINE COMBUSTOR WITH TAILORED TEMPERATURE PROFILE |
| 摘要 |
A method of tailoring a combustor flow for a gas turbine engine includes controlling an airflow into a swirler to be generally uniform and controlling an airflow into a quench zone to provide a desired pattern factor. |
| 申请公布号 |
US2014338351(A1) |
申请公布日期 |
2014.11.20 |
| 申请号 |
US201213725137 |
申请日期 |
2012.12.21 |
| 申请人 |
United Technologies Corporation |
发明人 |
Snyder Timothy S.;McKinney Randal G.;Hoke James B. |
| 分类号 |
F23R3/00;F23R3/28 |
主分类号 |
F23R3/00 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A method of tailoring a combustor flow for a gas turbine engine, comprising:
controlling an airflow into a swirler; and controlling an airflow into a quench zone to provide a desired pattern factor. |
| 地址 |
US |
