| 发明名称 |
COMPOSITE SPLITTER LIP FOR AXIAL TURBOMACHINE COMPRESSOR |
| 摘要 |
The invention proposes a splitter lip for a low-pressure compressor of an axial turbomachine for an aeroplane. The splitter lip comprises an upstream annular wall made of metal with a circular leading edge, and a downstream annular partition made of an organic-matrix, short-fibre composite material. The splitter lip also supports an outer shroud for a stator upstream of the compressor. The upstream wall comprises an annular anchoring portion arranged in the thickness of the downstream partition so as to anchor the partition and the wall to one another. The anchoring portion has distributed hexagonal openings in order to increase anchoring. The invention also proposes a method for producing, by moulding, a bi-material splitter lip or a mixed lip. |
| 申请公布号 |
US2016327052(A1) |
申请公布日期 |
2016.11.10 |
| 申请号 |
US201615141926 |
申请日期 |
2016.04.29 |
| 申请人 |
Techspace Aero S.A. |
发明人 |
Bouillon David;Herbaut Ghislain |
| 分类号 |
F04D29/02;F02C3/04;F04D29/70;F02C7/047;F04D19/02;F04D29/52 |
主分类号 |
F04D29/02 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A splitter lip for a turbomachine, the splitter lip comprising:
an upstream annular wall with a circular leading edge; a downstream annular partition, wherein the upstream wall comprises an annular anchoring portion arranged in the thickness of the downstream partition so as to anchor the partition and the wall to one another. |
| 地址 |
Herstal (Milmort) BE |
