| 发明名称 |
AIRFOILS HAVING POROUS ABRADABLE ELEMENTS |
| 摘要 |
A gas turbine engine includes a plurality of airfoils that are circumferentially arranged to rotate about an engine central axis. Each of the airfoils includes a base and a free tip end. The tip end includes first and second porous abradable elements that are axially spaced apart. The first porous abradable elements of the airfoils circumferentially align with each other, and the second porous abradable elements of the airfoils circumferentially align with each other. |
| 申请公布号 |
US2016053625(A1) |
申请公布日期 |
2016.02.25 |
| 申请号 |
US201514853059 |
申请日期 |
2015.09.14 |
| 申请人 |
United Technologies Corporation |
发明人 |
Fisk Benjamin T.;Propheter-Hinckley Tracy A. |
| 分类号 |
F01D11/12;F01D9/04;F01D5/14 |
主分类号 |
F01D11/12 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A gas turbine engine comprising:
a plurality of airfoils circumferentially arranged to rotate about an engine central axis, each of the airfoils including a base and a free tip end, the tip end including first and second porous abradable elements that are axially spaced apart, wherein the first porous abradable elements of the airfoils circumferentially align with each other, and the second porous abradable elements of the airfoils circumferentially align with each other. |
| 地址 |
Hartford CT US |
