| 发明名称 |
ULTRA HIGH BYPASS RATIO TURBOFAN ENGINE |
| 摘要 |
An ultra high bypass ratio turbofan engine includes a variable pitch fan, a low pressure turbine, a reduction gearbox, and a plurality of outlet guide vanes. The ultra high bypass ratio turbofan engine has a bypass ratio between about 18 and about 40. The variable pitch fan and the low pressure turbine are coupled together by the reduction gearbox. The reduction gearbox reduces the speed of the variable pitch fan relative to the low pressure turbine. The plurality of outlet guide vanes are spaced aft of the variable pitch fan and are axially swept. The variable pitch fan and the low pressure turbine are configured to generate a fan pressure ratio between about 1.15 and about 1.24. |
| 申请公布号 |
US2014363276(A1) |
申请公布日期 |
2014.12.11 |
| 申请号 |
US201314101438 |
申请日期 |
2013.12.10 |
| 申请人 |
Rolls-Royce Corporation ;Rolls-Royce North American Technologies, Inc. |
发明人 |
Vetters Daniel K.;Karam Michael;Fulayter Roy D. |
| 分类号 |
F02K3/075 |
主分类号 |
F02K3/075 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. An ultra high bypass ratio turbofan engine comprising
a bypass ratio between about 18 and about 40; a variable pitch fan; a low pressure turbine; the variable pitch fan and the low pressure turbine coupled together by a reduction gearbox that reduces the speed of the variable pitch fan relative to the low pressure turbine; and a plurality of outlet guide vanes that are spaced aft of the variable pitch fan and are axially swept; the variable pitch fan and the low pressure turbine being configured to generate a fan pressure ratio between about 1.15 and about 1.24. |
| 地址 |
Indianapolis IN US |
