| 发明名称 |
GAS TURBINE ENGINE |
| 摘要 |
There is disclosed a gas turbine engine comprising a bypass duct defined between a radially inner wall and a radially outer wall. A support radially extends across the bypass duct. The upstream end of the support acts as a source region. A sink region is provided adjacent to and upstream from the source region to at least partly compensate for aerodynamic effects caused by the source region. |
| 申请公布号 |
US2017096909(A1) |
申请公布日期 |
2017.04.06 |
| 申请号 |
US201615196978 |
申请日期 |
2016.06.29 |
| 申请人 |
ROLLS-ROYCE plc |
发明人 |
PARRY Anthony B. |
| 分类号 |
F01D25/14;F01D9/04;F01D25/28 |
主分类号 |
F01D25/14 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A gas turbine engine comprising:
a bypass duct defined between a radially inner wall and a radially outer wall; and a support radially extending across the bypass duct, the upstream end of the support acting as a source region; wherein a sink region is provided adjacent to and upstream from the source region to at least partly compensate for aerodynamic effects caused by the source region, and wherein at least one of the walls comprises a recessed section which forms at least a part of the sink region and wherein the or each recessed section extends to an axial position downstream of the downstream end of the support. |
| 地址 |
London GB |
