| 发明名称 |
Compressor Airfoil |
| 摘要 |
A compressor airfoil has a leading edge, a trailing edge, and a radially outboard edge connecting the leading edge and the trailing edge. The leading edge is formed according to a leading edge tip profile and the trailing edge is formed according to a trailing edge tip profile. The leading edge tip profile and/or trailing edge tip profile has a chamfer and/or a radius. In this manner, contact stress experienced by the compressor airfoil such as upon contact with a surrounding abradable seal are ameliorated. The leading edge tip profile and/or trailing edge tip profile are coated with an abrasive coating such as to enhance fitting of the abradable seal to the path of the compressor airfoil upon such contact. |
| 申请公布号 |
US2016238021(A1) |
申请公布日期 |
2016.08.18 |
| 申请号 |
US201514623245 |
申请日期 |
2015.02.16 |
| 申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
Furrer David Ulrich;Strock Christopher W.;Hillebrand Joseph G.;Bintz Matthew E.;Kasprow Thomas D. |
| 分类号 |
F04D29/32;F04D29/02 |
主分类号 |
F04D29/32 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A compressor airfoil comprising:
a leading edge comprising a leading edge tip profile comprising one of a leading edge tip radius and a leading edge tip chamfer; a trailing edge comprising a trailing edge tip profile comprising one of a trailing edge tip radius and a trailing edge tip chamfer; and a radially outboard edge comprising a surface connecting the leading edge and the trailing edge. |
| 地址 |
Hartford CT US |
