| 发明名称 |
INTEGRATED THERMAL SYSTEM FOR A GAS TURBINE ENGINE |
| 摘要 |
A thermal system for a gas turbine engine includes a bypass flow duct and a compressor flow duct which meets with the bypass flow duct at an intersection. A valve is located within the intersection and is movable between a first position and a second position. First position is operable to selectively communicate fan bypass flow from the bypass flow duct and block the compressor flow duct. The second position is operable to selectively block the bypass flow duct and communicate bleed flow through the compressor flow duct. |
| 申请公布号 |
US2015267617(A1) |
申请公布日期 |
2015.09.24 |
| 申请号 |
US201514729800 |
申请日期 |
2015.06.03 |
| 申请人 |
United Technologies Corporation |
发明人 |
Suciu Gabriel L.;Penda Allan R.;Merry Brian D.;Dye Christopher M.;Snape Nathan |
| 分类号 |
F02C7/18;F02C7/14;F02C7/08 |
主分类号 |
F02C7/18 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A thermal system for a gas turbine engine comprising:
a bypass flow duct; a compressor flow duct which meets with said bypass flow duct at an intersection; and a valve located within said intersection said valve movable between a first position and a second position, said first position operable to selectively communicate fan bypass flow from said bypass flow duct and block said compressor flow duct, said second position operable to selectively block said bypass flow duct and communicate bleed flow through said compressor flow duct. |
| 地址 |
Hartford CT US |
