| 发明名称 |
COMPRESSOR |
| 摘要 |
A compressor section for a gas turbine engine, the compressor section including a circumferential row of stator vanes, a circumferential row of rotor blades, and a casing arrangement. A row of bleed ports are provided in the casing arrangement. Each of the bleed ports extends radially and is curved such that an outlet of the port is rearward of and is circumferentially offset in a direction of rotation of the rotor blades from an inlet of the port. |
| 申请公布号 |
US2017108006(A1) |
申请公布日期 |
2017.04.20 |
| 申请号 |
US201615290476 |
申请日期 |
2016.10.11 |
| 申请人 |
ROLLS-ROYCE plc |
发明人 |
WILSHAW Johnathan H.;BOLGAR Crispin D. |
| 分类号 |
F04D29/54 |
主分类号 |
F04D29/54 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A compressor section for a gas turbine engine, the compressor section comprising:
a circumferential row of stator vanes; a circumferential row of rotor blades; a casing arrangement configured such that the rotors pass the casing arrangement during rotation in one axial region and the stator vanes are connected to the casing arrangement in another axial region; and a row of bleed ports provided in the casing arrangement, wherein each of the bleed ports extends radially and is curved such that an outlet of the port is rearward of and is circumferentially offset in a direction of rotation of the rotor blades from an inlet of the port. |
| 地址 |
London GB |
