| 发明名称 |
GAS TURBINE INLET |
| 摘要 |
An inlet for a gas turbine engine having an inlet lip and an inlet barrel, the inlet lip having a highlight defining a boundary between inner and outer surfaces of the inlet lip. The inlet barrel has a forwardly extending flange that is joined to the inlet lip by overlapping surfaces. The flange interface surface has a conus angle that is divergent from the highlight axis. |
| 申请公布号 |
US2015285144(A1) |
申请公布日期 |
2015.10.08 |
| 申请号 |
US201514674400 |
申请日期 |
2015.03.31 |
| 申请人 |
ROLLS-ROYCE DEUTSCHLAND LTD & CO KG |
发明人 |
TODOROVIC Predrag;KUBISCH Thomas |
| 分类号 |
F02C7/045;F02C7/04 |
主分类号 |
F02C7/045 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. An inlet for a gas turbine engine, the inlet having in flow series an inlet lip and an inlet barrel, the inlet lip having a highlight defining a boundary between inner and outer surfaces of the inlet lip, and on all longitudinal sections through the inlet that contain a longitudinal axis of the inlet (i) said inner and outer surfaces having their tangents coincident on the highlight, and (ii) said inner and outer surfaces have their maximum curvature at the highlight, the highlight having an axis that extends normal to the highlight; wherein the inlet barrel has a forwardly extending flange that is joined to the inlet lip. |
| 地址 |
Blankenfelde-Mahlow DE |
