| 发明名称 |
GAS TURBINE ENGINE BLADE OUTER AIR SEAL THERMAL CONTROL SYSTEM |
| 摘要 |
A clearance control system for a gas turbine engine is provided. The system includes an inner axial wall that extends between a forward wall and an aft wall. The system also includes an outer axial wall that extends parallel to the inner axial wall to pivotally receive a full hoop thermal control ring. |
| 申请公布号 |
US2016237842(A1) |
申请公布日期 |
2016.08.18 |
| 申请号 |
US201415025602 |
申请日期 |
2014.08.05 |
| 申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
Blaney Ken F.;Lutjen Paul M. |
| 分类号 |
F01D11/18;F16J15/44 |
主分类号 |
F01D11/18 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A carrier segment of a clearance control system for a gas turbine engine, the carrier segment comprising:
an inner axial wall that extends between a forward wall and an aft wall; and an outer axial wall that extends parallel to the inner axial wall, wherein the outer axial wall is axially shorter than the inner axial wall. |
| 地址 |
Farmington CT US |
