| 发明名称 |
LAYERED ICE LINER |
| 摘要 |
A liner assembly for lining of a gas turbine engine includes a honeycomb core having at least two axially adjacent segments, including a forward segment and an aft segment. An impact resistant layer is disposed against and radially inward of the honeycomb forward segment. A radially interior layer, defining a relatively substantially uninterrupted flowpath over at least a portion of the impact resistant layer and the aft segment, extends against and radially interior of both the impact resistant layer and the honeycomb aft segment. |
| 申请公布号 |
US2016273550(A1) |
申请公布日期 |
2016.09.22 |
| 申请号 |
US201415037770 |
申请日期 |
2014.12.08 |
| 申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
Clarkson Steven;Bergethon Richard B. |
| 分类号 |
F04D29/52;F04D29/38;F02K3/06;F04D29/32 |
主分类号 |
F04D29/52 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A liner assembly for lining of a gas turbine engine, the liner assembly comprising:
a honeycomb core having at least two axially adjacent segments, including a forward segment and an aft segment; an impact resistant layer disposed against and radially inward of the honeycomb forward segment; and a radially interior layer, defining a relatively substantially uninterrupted flowpath over at least a portion of the impact resistant layer and the aft segment, the interior layer extending against and radially interior of both the impact resistant layer and the honeycomb aft segment. |
| 地址 |
Hartford CT US |
