| 发明名称 |
SYSTEM AND METHOD FOR BLADE TIP CLEARANCE CONTROL |
| 摘要 |
A system includes a turbomachine rotor having a shaft and turbomachine blades coupled to the shaft. The system also includes a turbomachine stator having a shroud surrounding the turbomachine blades of the turbomachine rotor. Further, the system includes a cooling channel having at least a first portion of the cooling channel extending upstream of a final stage of a compressor of the system, where the cooling channel is configured to receive cooled compressed air from the compressor and direct the cooled compressed air adjacent to the turbomachine rotor to reduce thermal expansion and/or axial displacement of the turbomachine rotor. |
| 申请公布号 |
US2016097296(A1) |
申请公布日期 |
2016.04.07 |
| 申请号 |
US201414507659 |
申请日期 |
2014.10.06 |
| 申请人 |
General Electric Comapny |
发明人 |
Ballard, JR. Henry Grady;Klingler Brett Darrick |
| 分类号 |
F01D11/24 |
主分类号 |
F01D11/24 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A system, comprising:
a turbomachine rotor comprising a shaft and turbomachine blades coupled to the shaft; a turbomachine stator comprising a shroud surrounding the turbomachine blades of the turbomachine rotor; and a cooling channel having at least a first portion of the cooling channel extending upstream a final stage of a compressor of the system, wherein the cooling channel is configured to receive cooled compressed air from the compressor and direct the cooled compressed air adjacent to the turbomachine rotor to reduce thermal expansion and/or axial displacement of the turbomachine rotor. |
| 地址 |
Schenectady NY US |
