| 发明名称 |
AUXILIARY DEVICE FOR THREE AIR FLOW PATH GAS TURBINE ENGINE |
| 摘要 |
A gas turbine engine has a fan rotor including at least one stage, with the at least one stage delivering a portion of air into a low pressure duct, and another portion of air into a compressor. The compressor is driven by a turbine rotor, and the fan rotor is driven by a fan drive turbine. A channel selectively communicates air from the low pressure duct across a boost compressor. |
| 申请公布号 |
US2015267551(A1) |
申请公布日期 |
2015.09.24 |
| 申请号 |
US201414458619 |
申请日期 |
2014.08.13 |
| 申请人 |
United Technologies Corporation |
发明人 |
Roberge Gary D. |
| 分类号 |
F01D15/08;F01D1/18 |
主分类号 |
F01D15/08 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A gas turbine engine comprising:
a fan rotor including at least one stage, with said at least one stage delivering a portion of air into a low pressure duct, and another portion of air into a compressor, said compressor being driven by a turbine rotor, and said fan rotor being driven by a fan drive turbine; and a channel selectively communicating air from said low pressure duct across a boost compressor. |
| 地址 |
Hartford CT US |
