| 发明名称 | Aircraft nacelle comprising an improved air intake | ||
| 摘要 | An aircraft nacelle comprising an air intake configured to channel an air flow in the direction of an engine assembly which comprises a fan with an axis of rotation, said air intake comprising, according to a flow direction of the air flow, a lip with a leading edge and an internal conduit which extends said lip towards the fan, wherein the air intake comprises a plurality of protrusions distributed over the circumference of the air intake and following each protrusion, a concave form configured in order to achieve compression of the air flow. | ||
| 申请公布号 | US9623979(B2) | 申请公布日期 | 2017.04.18 |
| 申请号 | US201514728593 | 申请日期 | 2015.06.02 |
| 申请人 | Airbus Operations SAS | 发明人 | Rouyre Francois |
| 分类号 | B64D33/02;F02C7/045;B64D29/00;B64C7/02 | 主分类号 | B64D33/02 |
| 代理机构 | Greer, Burns & Crain, Ltd. | 代理人 | Greer, Burns & Crain, Ltd. |
| 主权项 | 1. An aircraft nacelle comprising: an air intake configured to channel an air flow in the direction of an engine assembly which comprises a fan with an axis of rotation, said air intake comprising, according to a flow direction of the air flow, a lip with a leading edge having a profile alternately comprising hollow forms and projecting forms, a projecting form being separated from the fan by a greater distance than the adjacent hollow formsan internal conduit which extends said lip towards the fan,a plurality of protrusions distributed over the circumference of the air intake, and,after each protrusion, a concave form configured in order to achieve compression of the air flow. | ||
| 地址 | Toulouse FR | ||