| 发明名称 |
AXIAL TURBOMACHINE COMPRESSOR BLADE WITH BRANCHES AT THE BASE AND AT THE HEAD OF THE BLADE |
| 摘要 |
The invention relates to a blade of an axial turbomachine comprising an airfoil which extends radially and a first set of branches or divisions, which radially extend a radial end of the airfoil, and a second set of branches which radially extend the other of the radial ends of the airfoil and which are offset over the circumference of the turbomachine. The branches extend axially along the entire length of the airfoil. The sets have different numbers of branches. The branches further occupy the channel of the turbomachine and further counteract debris in the event of intake. |
| 申请公布号 |
US2016024932(A1) |
申请公布日期 |
2016.01.28 |
| 申请号 |
US201514803818 |
申请日期 |
2015.07.20 |
| 申请人 |
Techspace Aero S.A. |
发明人 |
Hiernaux Stephane |
| 分类号 |
F01D5/14 |
主分类号 |
F01D5/14 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A blade of an axial turbomachine, said blade comprising:
an airfoil which extends radially and which has two radially opposing ends; a first set of branches which radially extend one of the ends of the airfoil; and a second set of branches which radially extend the other of the two radially opposing ends of the airfoil. |
| 地址 |
Herstal (Milmort) BE |
