| 发明名称 |
CENTRIFUGAL COMPRESSOR WITH AXIAL IMPELLER EXIT |
| 摘要 |
A gas turbine engine includes a centrifugal compressor having an improved impeller structure. The impeller structure includes a near axial discharge configuration thus reducing the overall size of the envelop surrounding the compressor assembly. The impeller structure may have axial exit vanes. |
| 申请公布号 |
US2014271173(A1) |
申请公布日期 |
2014.09.18 |
| 申请号 |
US201314133275 |
申请日期 |
2013.12.18 |
| 申请人 |
Rolls-Royce North American Technologies, Inc. |
发明人 |
Bryan William B. |
| 分类号 |
F04D29/44;F04D17/10 |
主分类号 |
F04D29/44 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A gas turbine engine comprising:
a centrifugal compressor having a rotational axis; and a rotating impeller structure having an inlet and a discharge, the inlet has a first central axis that may be parallel to the rotational axis or at an angle, the discharge has a central axis that is substantially parallel to the rotational axis. |
| 地址 |
Indianapolis IN US |
